interplanetarymissiondesign handbook, volume i, part 3
TRANSCRIPT
JPL PUBLICATION82-43 ":
InterplanetaryMissionDesignHandbook, Volume I, Part 3Earthto Jupiter Ballistic Mission Opportunities,1985-2005 _ '-
/
AndmyB. 8ergeyevsky .-GeraldC. Snyder ¢,
(N ASA-CP- 16S9 l ._) T NT__PPLA NF"a I_Y qI_S:UN Li83- 18775DESIGN HA}IDBCOK. VOLrlRg 1, P.a._T 3: .P.._RTItTO J£PITER P._LLI_TTC _.TSSICN CfFCF'ICNITII',S,1985-233q (Jet Propulsion lab.) __BU p Ox,clasIIC AI3/MF AOI C_CL 22A G3/12 02865
December1, 1982
NaUor_Aeronautk_andspace_n_nm_k)nJot_ La_CldWomknImlitumof Tech_PaMdenl, California
1983010504
• JPL PUBLICATION 82-43
Interplanetary MissionDesignHandbook, Volume I, Part 3Earth to Jupiter Ballistic Mission Opportunities,1985-2005
Andrey B. SergeyevskyG 3raid C. Snyder
December 1, 1982
NASANat!onalAeronauticsandSpace Administration
Jet Propulsion LaboratoryCalifornia Instituteof TechnologyPasadena, California
&
1983010504-002
1983010504-003
Abstract
]'hl._ doc.:'_e.I CL'qll_llil$ l_raphic:ll data .L'¢_'._._ll._ foI tile ptehi.lil:ll_ dL'.'ill_ll 0|" baUislic
IlltS._liSll._I_ .Ili|_lll'l. ('L_ll|t_tll,_ 0|" I_llll£h L'll¢[l_._ IL'LlllZlL'lllL'lll,_, _15Wt'i] ;I._ In:lll._ ollt¢'l
I.Itllldl ,lIlt| .IIIl_llt'l ;illlV_ll p31.11llt't¢'l$. ;Ill." I_lt'st'lllt'd I!l I;Itllldt dillt" 311lV:l] d31@ $|l-'le'L"
tL_l .l!l I,nlllCh t)i_plHllillltlt'5 |'lL_lll Iq')_._ thlOtl_h 2l)L)._. hl addl|lllll, :lIt t'XIl.'l|xl¥_ It'.Xl I$
lll_'itidt'dWitk']l¢%.pl:ltll,'_tlIIS$1tH|tl¢_Sl.l_llIlICtht_J._,.IlL,IlllilllllL'h_._lttdL_%1,JcYt']_plll¢'lllto
]Iip11elpie,be.rodL_ibltct,itiiv:llde._tl_,,iltill_IIll"the _t,II_llt¢:IId,il,IIlllhl._v_hlI,e iI$
wellil_IIIIIII¢.'I,_II:it'qllilll_It._I_'I,11111_,_JllOll_p.llillllt'l¢l.',.'l'hl._l._|he 111._I_I",Ip]iUlllt'd
_'_ies"f llll._._I_i_Je,_l,_lld_CIItlleltl._which will:Ippl_l_ .Illpl,I'let._,rod,_om¢ _lhel bodies
iii|lieiOLli._%1.I¢'III.
IIi
1983010504-004
Preface
This publication is one of a series of volumes devoted to interplanetary trajectories ofdifferent types. Volume 1, of which the present publication is Parl 3, describes ballistictrajectories. Parts 1.2, and 4, which will be published in 1983. will treat ballistic trajec-tories to Venus. Mars, and Saturn, respectively.
1983010504-005
Contents
I. Introduction ..................................................... 1
II. Computational Algorithms ...................................... 1
A. GeneralDescription............................................. 1
B. Two-BodyConicTransfer ........................................ 1
C. PseudosteteMethod ............................................ 3
III. Trajectory ChamcteriMics ..................................... 4
A. MissionSpace .................................................. 4
B. TransferTrajectory............................................... 5
C. Launch/injectionGeometry ....................................... 9
1. LaunchAzimuthProblem .................................... 9
2. DailyLaunchWindows ...................................... 10
3. RangeAngleArithmetic..................................... 15
4. ParkingOrbitRegression.................................... 16
5. DoglegAscent ............................................. 17
6. TrackingandOrientation .................................... 17
7. Post-LaunchSpacecraftState ............................... 18
8. OrbitalLaunchProblem ..................................... 18
D. PlanetaryArrivalSynthesis ....................................... 18
1. FlybyTrajectoryDesign ..................................... 18
2. CaptureOrbit Design ....................................... 24
3. EntryProbeandLanderTrajectoryDesign .................... 28
E. LaunchStrategyConstruction..................................... 31
IV. Description of Trajectory Characteristics Data ............... 32
A. General ........................................................ 32
B. Definitionof DepRrtureVariables .................................. 32
C. Definitionof ArrivalVariables ..................................... 32
V. Table of Constants ............................................. 33
A. Sun ........................................................... 33
B. Earth/MoonSystem ................................... 33
C. JupiterSystem, ..................................... 33
V
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1983010504-006
D. Sources ....................................................... 33
Acknowledgments .................................................... 34
Refe,ences ............................................................. 34
Figures
1. The Lambert problem geometry ................................... 2
2. Departure geometry and velocityvector diagram .................... 2
3. Pseudostate transfer geometry .................................... 3
4. Mission space in departure/arrival date coordinates,typical example ,. 5
5. Effect of transfer angle upon inclinationof trajectoryarc .............. 6
6. Nodal transfer geometry .......................................... 6
7. Mission space with nodal transfer ................................. 7
8. Broken-plane transfer geometry .................................. 8
9. Mission space with broken-plane transfer, effective energyrequirements ................................................... 8
10, Launch/injection trajectory plane geometry ......................... 9
11, Earth equator plane definitionof angles involvedin thelaunch problem .................................................. 10
12. Generalized relative lau'lch time tRLTVS launch azimuth _Land departure asymptotedeclination,_z ............................ 11
13. Permissible regionsof azimuth vs asymptote declinationlaunch
space for Cape Canaveral ....................................... 12
14. Typical launch geometry example in celestial (inertial) Mercatorcoordinates ................................................... 12
15. Central range angle () between launch site and outgoingasymptote direction vs its declination and launch azimuth ............ 13
16. Typical example of daily launch geometry (3-dimensional) as
viewed by an outside observer ahead of the spacecraft .............. 14
17. Basic geometry of the launch and ascent profile in the trajectoryplane .......................................................... 15
18. Angle from perigee to depaff.ure asymptote ....................... 16
19. Oefinition of cone and clock angle .............................. 17
20. Planetary flyby geometry ..................................... 19
21. Definition of target or arrival B-plane coordinates ................ 20
22. Two "_-axisdefinttic,-s in the arnval B-plane .................... 21
23. Defintbon of approach onentatK)nalcoordinatesZAPSand ETSP. ZAPE and ETEP .......... 22
vi
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1983010504-007
24. Phase angle geometry at arrival planet ..................... 22
25. Typical entry an(; flyby trajectory geometry ............... 23
26. Coap_-,daland cotangential captureorbztinsertiongeometries ..... 25
27. Coapsidal capture orbit ,nsertion maneuver .IV requ,rements
for Jupder ......................................... 26
28. Coapsidal and intersectingcapture orbit ,nsertion geometnes ......... 27
29. Charactenstcs of intersectingcapture orb,t ,nsertmnand
constructionof optimal burn envelope at Jupiter .................. 29
30 Minimum ._V requ,red for ,nserhoninto Jupiter captureorbit of
given apsidal orientation ................................. 30
31. General satellite orbit parameters and precessK)nalmot,ondue
to oblateness coefficient"/2 .............................. 31
32. Voyager (MJS77) trajectory space and launch strategy ............ 31
Mission Design Data Contour Plots,Earth to Jupiter Ballistic Mission Opportunities,1985-2005 .............................................. 35
1985 Opportunity ...................... 37
1986 Opportunity ......... 49
1987 Opportunity ............... 61
1988 Opportunity ....... 73
1989 Opportunity ..... s5
1990 Opportunity 97
1991 Opportunity to9
199213Opportunity 121
199314Opportunity f33
199415Opportunity t45
1998 Opportunity 157
1997 Opportunity 16,.3
1983010504-008
1998 Op.r_rtunity ,e:
19S3 Opportunity 1_.;
2000 Opportunity _._
2001 Opportunity 217
2002 Opportunity 229
2003/4 Opportunity ."41
200415 Opportunity 2._
2005/6 Opportunity ._5
1983010504-009
I. Introduction but certainl_ nut unrealistic nsing future urbital assemhlyl*'t'tl niqlle'_.
The purpose of tl,ts series of Mission i)esign Iiandh.oks isto provide trajectory designers and mission planners with A separate series of vohnnes (Rel, 3l is being published
graphical trajectory inlornlation, sufficient for preliminar_ concurrently to provide purely geometrical {i.e.. trajectory-
interplanetar_ mission design and evaluation, in ernst respects independent) data ol planetary positions and vi_,'in',_ortenta-
the series is a continuation ,if tile previous three _,ohltnes of tion angles, expeuenced by a spacecraft in tile vicinity of these
tile Mission Design Data. TM 33-736 {Ref. I I and its predeces- planetary bodies. Tile data cover tile time span thr, utgh 2020sots [e.g.. Ref. 2}; it extends their coverage to departures A.D.. ill order to allow sufficient nlission duration time tot all
through tile year 2005 A.D. I-arth departures, up to 2005 A.I).
The entire series is planned as a sequence ofvohlmes, each Tile geonletrit" data are presented in graphical form anddescribing a distinct mission mode as follows: consist of 20 quantities, combined ,, ",, eight plots fi_r each
caler.dar 3,'earand each target planet. Tilt .,raphs display equa-Vohmle 1" Ballistic (i.e.. unpowered) transfers be-
torial declination and right ascension uf i'arlh and Sun (plan-tween Earth and a planet, consisting of
etocentricl, as well as th,_ of tile target planet (ge-cemricl;one leg trajectory arcs. For Venu_ :(nil
heliocentric (cclipticl longitude of tile planet, its h21iocentricMars missions tile planet-tt,-Earth return
and geocentric dist;lnce: cone angles of l-arth and ('anopus.trajectory data are also provided, clock angle of l-arth (when Sun,'Canopus-,ric:_tedl. l-arth-Sun-
Volunle i1: Gravity-Assist IG'AI trajectory transfers, planet, as well as Sun-Earth-planet angles and fin:ally, rise and
comprising from two to four ballistic set times for six deep-space tracking stations assuming a t_-deg
interplanetary legs. connected by SilO- horizon tnask. Tilts information is similar to that ill the secondcessive planetary swingb_ s. part of each of tile vohlnles previously published (Ref. 1).
Vohlmelli: Dt,lta-V-EGA (AVI'.GAI transfer trajec-
tories utiliting an impulsive deep-space II. Computational Algorithmsphasing and shaping bum. fi_llowed b._ a
return to l'arth f,,r a G,'A swingb.v nl:lnell- A. General Descriptionvet taking tilt' spacecraft (S ('t t,_ the
eventual target planet. rhc plots for tilt' entire series _,ere computer-generated. Alninintunl of editorial and gr:lphic suppoit was postulated frt,,n
Each volume consists of several parts, de.,,cltbllig tralecto L the outset in an effort to reduce cost.opportunities fur Illt_Mon._,toward ,,pecfflC talget el ,,wingb%
l_tdtes. A number of computer progra:ns were created and/or tnodi-
This Voh(nle l. Pall 3 of the' series is dew_ted to baUistic fled to suit tile needs of the llandhook productio,i.
transt_'rs between I-arth and Jupl.ter. It ,.,,..scribes tlaiectoric.,,lhe computing effort involsed tile generation el arrays eltaking from I to 5 yeats of flight time tt,r tile 20 successive
n,issiol) opportunities, dep:lrting l-alth ill tile folhtwing ye:lr.,,: transter traieclor._ arcs conuecting departllre :rod arri_,al10I'IS. IriSh, I()H"_. ItlSg, It),_tl. itlttt}. It)el. IOO2,:3 lilt)3 4. planets on a large nunlber o! ._uitable d:ltes at each body.
• • _ , AIgorlthnls tconlputational int_delsl to ,_t_lv.."tills problem CallJell4'. ¢,. ]t)t)O, ] t)Q7. Iqt)8. l tlt)tl. 2|)00. 2Ill)l, .00_. _IX)., 4.2004 S. and 2ties t, V:lry grcatl_ as to their coml_lexity, c.st t_l data generated, and
resulting data accuracy. In light of these ctm:'idelations, tilechoice of lllelhods used In this elloft has been "lSSCs.,a.,d.
Individual valiahles presented herein are described in det:lil
in subsequent sections and sunlmarited again in Section IV.B. Two-Body Conic Tr,,nsfer
Silt'rice it to say here that :ill tilt, data ate presee:e,I In ,_ets:d
I I contour plots each. dlspla._ ed till the ]allnt.ll date arrival !- :oh departure attltal dale COlltblnalt.tn ;CplC.Setlt',. a (Itlltl(le
•late space 1"Oleach oppt,rtltllit_. Required depilltllte eneig_ flair, let tlalectt_l_ bel_,eell two ,p, .ttwd bodle,,, it the Ill(.'lbel
('.t, departure a._._nll_tOt, dechl_:ltlOn anti light il_,cen,Mt_ll, el Iclohlthtll,, tit the _pa_:e_latt .ibt,tll tile pllltlal_, le._z, the
arrival I:. and its equahut;tl dlrCCtlOll'_, ,Is _ell .', Still and SIllll I, ,,pe_ !led l;-te I .tlnbelt lheol¢lll ptO_,lde', a ,,ultableI-alth dlreCtltql angle,, _tth respect to the tlelt4rtute atllt,ll Ilattle_olk |.tl tilt' , 'lllptll,ltltHI t_l ,,ut.h tlale_bttle',, btil
as._nli'ttote,.i, ate ple.lentetl, t_[l]_ It l t.',,,tllcted t_,tt hods, _..ttlll_,. lllOthtll prec,.ill, ,..
It should be '" led that pall .... l lilt" l.lltlh l, ,pa,¢ ,'t,_, ..,i Ige,,trtctt.'d two-bod_, lutttlon ItUlqlC,, th.lt tile d_nanlt_:al
In,l_,. tell(lit,: I,iLlHdlet enelgh", not ple,,entl_, I "d.%3) a_,atl,ible. ",A_lelll CItII._,I_.I,.,tit Olll_, t_&t_blare,,, one el _ltt,lt. th,- pllmat_,.
i
1983010504-010
ORIGINALPAGE moFPOOR
iss,,..,oh ntore,.assiv.tha.th. other,that:ill ,,t the'_yste,.'s ! 1
gravitational allraclioll may he . _stlnletl as c, mcentrated at :n [_ ........... 2a- - -point tile center ol It:at primary body. Ihe sect.adary hod)
lerian(coniclorbitsabout tileprimary(e.g..theSunl insuch
a wa_ that the center of the primary is located at one of the
foci of the conic (an ellipse, palahola, or hyperhola). _"s
tati,,lal parameter _ (al_ known as GM) for the central hod', EARTH ....
the time of Ilight between two arhitrar], points in space. __ _('- _"_"= = ;J_ _"._L.V"R I and R,. Is a function of onl), three independent variables: _ _PLANET
the sllnl of the distances of the two points fronl the fi)cus, _ /IRnl + IR21, the distance between the two points C = IR: - R I1. /
and the semimajor axis. a. of the conic orbital flight path T=/(R 1 +R 2 .C,a) /between them (Fig. I.J
l)etailed algorithm descriptions of the Latnbert method, in. Fig. 1. The Lambert problem geometryeluding necessal._ branching and singularity precautions, are
presented in numerou_ publications, e.g., Refs. 2 and 4. The
computatk)ns resuh m a set of conic classical elemel_ts (a. t'. i. the hyperbolic excess velocity, '"I,:infinity'" or simply "'speed"
[2. to. vI ) and the transle_ angle. A%:, ol Iwt_ equivalent (e.g.. Ref. 4). TheY.. represents the velocity of the spacecraft
,,pacecratt heliocentric velocl() vectors. Vh,v¢.¢ one at depar- at a great distance t'rom the planet (where its gravitationa _lure. the othei at the alrwal plaaet Suhtlactlon of Ih," '_pl, o. attraction is practically negligiblel. It is attained when the
priate planetar_ heliocentric velocity vector. Vhpz..4.x._.r. at spacecraft has climbed away from the departure planet, fol-the t_,o corresponding times t'rom each of these two space- lowing injection at velocity VI:
craft ;-locity vectors results in a pair of planetocentric velocity
7,states "'ai iilliillt} ""with re._i,ect h_ each planet I ir:ig. 2)
I.. i '_ 2Pl= -"r--"7 . km • (2 I
V.. ""Vh3;:¢..it , - Vhpl.,4.'¢l"l t ( ilor before it starts its fall into the arrival planet's gravity well,
where I = I and 2 refer to positions at departure and arrival, where it eventuall> reaches a closest approach (periapse, C/.4 I
resl,ectivel,_. Th:' scalar of tins I" vector is also referred to as velocity I'p.
Vllt I1_111
11[l | (etll_l'a
.. - " A_iy _ilp h I l I Viii
k ,_Sl I_ [ "" VIII IKII{ . Jr-i- ,.,.,,,,,,, .I..//I / _ _'" ,,..,, ill
....
X _ '.._ .% ,' ' i[llli I I |
v
Fig. 2. Departure geometry and veloc0Wvector diagram
1983010504-011
ORIGINAL PAGE g
OF POOR qOALrI_
-- 2/_+ Pseudostate theory ts based on the assumptlun that for|p = 2_ + --" . km/_ (3) modest gravitational perturbations the spacecraft conic mot,t,.:
I"- 2 rp about the primary and the pseudo<oat displacement due to athird body may be superimposed, if certain rules are |olh)wed.
1 he variables r I and rp refer to the departure injection anda,rivai periapse planetocentric radii, respectively. Values for The method, as applied to transfer trajectory gener'ttion.
the gravitational paranlet_r p (or GM ) .'iregiven m _ubsequenl does not provide a flight path og,ly its end states. It s-Ires theSection V oil constants, original Lambert problem, however, not between the true
planetary positkms themselves, but instead, between two _om-The V. vectors, computed b_ the Lambert tnethod, repre- puted "'pseudostates.'" These are ohtamed b_, tte_at,or, on tw.
sent a body center to body center transter. They can, however, displacement vectors oft" the planetary ephemeris positiorls on
be translated parallel to themselves at either billy without the dates ,,f departure and arrival. By a ,+uttable superpositttmexcessive error due to the offset, and a great variety t:f r*; .istic with a planetocentrtc rectilinear mlpact hypelb-la and a
departure and arrival trajectories ma) thus be constructed constant-velocity. "'zero gravity." sweepback at each end of
throu_, their use. to he discussed later, fhe magnitude and the L.ambertnan conic (see Fig. 3). a _atlsfactol3' mat,:h i_directk11, of I:. as we'J as the angles that this vector f,)rms obtained.with the Sun and Earth direction vector._ at each terminus, are
required for these n:ission design exercises. Of the five ar_ it,v,ivcd in the iteration, the la_t three
(h,watd._ and at Jupiter) act over tile lull II,ght lime. ,.X712.Nh_d :;_ • tl,e relatively small terrestrial planets are suited and repreyJnt:
to I. • analy,,ed hy tile Lambert metht,d, as the problem can he
adequately represented by the restricted tw,-hody formula- (IJ Conic heliocentric motion between the two pseudo-
tion. resulting in flight time enors of less than I day an states R; and R; (capital R is used here for -'-'11hell,accuracy that cann-t even be read from tile contt)ur plots centric positionsl.presented in this d-cument.
12) The transformation of R_ to a plane|Been|rio position.it *
r2 [lower case r is used for planetocentric positions).C. Puudostate Method performed in the usual manner is followed by a
"'constant-velocity'" sweepback in _ime to a point
Actual precision interplaneta_ transfer tralectories, espe- r_ "--r_ - V. 2 X .XTt2. correcting the planetocen'.iccially tho._ inv, dving the giant outer planets, do noticeably position r 2 to what ii would have heen at T I, had
violate the assumptitms inherent in the Lambert The,tent. th,':e bee,i ,,o solar attract,oil dur,ng ,.XTlz. andThe restricted two-httdy pr,blem, on which that theorem is |,nail).
based, is supp,sed to de._ribe tile tunic liB|ion of a nl._ssles_,
•,t.,ondarx li.e., tile spacecraftl about the point mass of a pri. 13) The planetocentric rectil+.near incoming h_perbola.mary attractive bode, (i.e.. the SunL both objects beat| placed charactel,zed h) m_t_mmg |'-nntmtt) V.,. ,t ,adtal
in an otherwise crept) Universe. In reahty, the gravitational _.---
a:'ractlon ol either departme or target |,od_ ma+_,significazltly -" _" "" "" "" "_.
ah..r tile etltlte tgansl'er trajectt+r.x.l
/ NO-GRAVITY X
Nm.eflcal _-h.d._ tr;,Icct-l_ integration could hc called I SUN SWEEPBACK • _,
upon t, represent the" true physical mt,Je! h,r the laws of /R1 "" -Voo",X _T.,,., !,,,t,tit)P.. hut _.-uld be too _..+tl._. _.t)i1_Id¢,,i,t_the numhel ol EARTH.'JI_-- .c Iz | I
,-,,,plete t,-,le,t-,le, ,¢qt,,¢d t,, lul,+_ ,ca, ell-.1,d des,,tbc., _R_ _ Ira. \ ra RECTI'LINEAR
+t,,e,I ,n,,,,,m ,,l,p-,tm,it.'+ _ • -.m_..,_ _.+j_ HYPERBOLA.
The p,_z.d.,,tate the.r._, tu,,t intr.duccd h.+,S. 9, _,li_m r; - R; - R_ - '"_+_1 _
I Ret. -_| and modtlicd t, _dvc Ihe thlee-bod_, Lambert p,t)h- " _ -1 JUPITERlent h_ D. V B,,mes IRet. 1,1. rel'reu:nts an extretnd,, usetul jf
inlpgovenlent o_,el the st-',ndald [.anlhclt udUtlOn l:o, the LAMBERT CONIC /r_giant p+anet mis.tt,ns, it Call correc about q5 pezcent ot tile AT12 / R_- R 2
three-hod) ellOl+ int_ufled, e+_.. U|+ to 30 d.l) _. 11, t]tght little tln
a Juptt¢,-hound i,,'ul,e) Fit 3. P_ottew teen|fee geometry
I
1983010504-012
OR;GINAL PAGE ISOF POOR QL,_ALITY
*aW" ,-a.... * ;'"P""* .,.a a *-;p *;"," A7_a ';..'-' r_ ...... I.. ;. thus ,I,._..,hl..- ..,. a"y da_,.... .I.;., ;, ....... .... ,h..to perijove, which can be _llslied b_, tteratic:n -n the capability (rf a given launch/injection vehicle must equal or
r_-magnitude and ,hus al._ on R_. exceed the departure energy requirement for a specifiedpayl.ad weight.
This last aspect provides for a great simplifiL,flion of the
formulation as the R_ end-point locus now moves only along In the coprsc of time the_ minimum departure energy"
the V. z II r; vector directkm. The resulting reduction in com- opportnnities do recttr regt,larly, at "synodic periou " mtervals.puting or,st is significant, and the equivalence to the Lambert reflecting a repetiti.n of the rcmtive angular geometry of the
point-to-point crmic transfer model is attractive, two planets. If _l and to 2 are the orbital angular rates .f theinner and outer of the two planets, respectively, m-ving about 'Ill
The first two segnlcqts of the transfer associatetl with the the Sun in circular orbits, then the mutual configulation of
departure planet may be treated in a like manner. If the planet the two bodies changes at the following rate:is [:arth. the pseudostate correction n,a_v he disregarded It :'.
R; = R n ). or else the duration (,I Earth's perturbatwe etfect COl2 = coI - co: . radis (41may be reduced t, a l'ractton of ATI_. It can als, he set Its
equal a fixed quantity, e.g../aT = 29 days. The latter value If a period of revolution. P. is defined aswas in fact used at the Earth's side of the ttansfe, ,n the
data generation process for this dt)cunlent 2nP = -- . s 151
Tbe rectilinear pseudostate method thi._s inwdves an itera
tive procedure, utili/ing the standard l.ambert algorithn: t- then,btain a starting set of values fi,: |'. at each end .f the trans-
ter arc This first guess is then improved by allowing the I I I
planetocentric pseudostate ptrsititrit vector r_ to he scaled t,p 17s = Pn-- I"-_ (b)and dt)'ia,n. using a suitable partial at either bod_, ,,uch that
ATRe..(I. the :tree required t'_ fall along the rectil,neat hypel- where Ps. the svinodic, period, is tl.e peri,d of plan,'tar_.
bola through t_ (the sum of the sweepback distance |'., geometr_ recurrent-', while I' I and P2 are the orbital "'siderealx. AT and the planetocentric dtstanh.e ir: I1. equ:nl the gra_,lta- ii.e., inertial) peri,ds'" ,rt" the inner (faster) and the outer
ti.nal perturbation dural,on. AT B,th r: and V . al,utg (slower) planet considered, respectiveb,._,luch the rectilinear fall -cculs. are contmuousl,, reset ,itih/-
" ._ the latest _alues of magnutude and dirtctl, n ,f V at each Since planetary t,rbits :ire neith,'r exactly circular nor co-
end. i. ot file new Lambert transte, .tic. as the Iteratl_qi plo. planar, launch opportt,r:,ies do ntrt repeat exactl'.,, sonic
gre.,,ses. "tile procedule com, erges ral':dl_ as th,: h._l_.'rboluc trip )'ears being better than -thers in energy requJrenlents or in
time discrepant). AAI" : A7_/. V - AI_. tall,, below a preset other parameters. A c-mpl,:te repeat of trajectory character-
small t-lerance IStlCSoccurs ,nly when exac'i_, the same orbital geonnetrv ofdeparture and arrival hod.,, recurs. For negligibly perturbed
Once the V. _,ectors at each planet are converged upon. planets approximately identical inertial positions in space attire desired output variables can be generated arid contour departure and arrival imply near.recltrre,.¢e ,rt" transfer tra-
plotted h_, existing standard alg,,rntluns, ject.l_, characteristics. Such events c-n rigorot,sb be ,.¢sessed
only for nearl_ res.nant nonprecessing planet;,-_ orbits. I.e..
t'-r those whose periods can be related m terms of Integer
III. Tre.lectory Characteristics fiactions. For instance, ff five revolutions of one hod._ cor-
A. Milmion Space resp.nd to three rewdutt:,,ts of the _ ther. that ttme intervalwould constitute the "'period of repeated characteristics."
All realistic laun_.h and mlection vehicles are ener_:.,,-Imlued Near-integer ratios provide nearl._ petitlve configurationsand imptw_ vet) stringent constraut',_ on the mterplar,.ta,._ Xtlth lespect to the hnes t,t apsldes and rtodes. 1"lie i-arth.
mission selection prt_ess. Onl.,, tht,w transfer opp, • . ". relative synt_llc period ot Jupiter ns 3tlS F,N4 days. I.e.. about_hlch occur near the tnl*eS o|" a nlullniunl I-arth , .. 13 nlonths, i'ach c_cle ol I I ctrnsecutive Jovian mission
erlelg) reqt:denteflt ale thus of plactlcal interest. I 1, . -'h,-" ttpllortUllitleS 41nodnts It+4.1N"T7 d.'._ $and ts neatl) IepetltlVe.side or' such an optunal date. departme enetg.*, lib're. ,% lizst del,,,.n b._ Jt,pltet's sidereal perl-d ot I I St,2t) )ears ,r 4332.bslov.ly, to,breed b_ a rapid inc_e.,_', th,ls lequirmg "'¢,,:,¢_ a da_,s It h oh_,l, ttl', that Iol an Id¢llth.al mutual Jllflll,ll Scott1
greatel ]auncll eap,thlllt_,., ol altetnatlVell,, d h_v.et .dl, twable et_. Jupltc_ _otlld be h,tlnd he_,olld.. Its lit, trial po.dtl',n lit the
payload i|la.¢_. A "'launch period." measured tit da._s ,u esen pl_.-t,httls _._,,.[¢I_, ¢_KI dd_s Ihttl|ll t*| Ilhtllttlll4 ¢_N,!¢¢1 whtl,"
4
d
1983010504-013
ORIGINALPAGE mOF PoOR QUALITY
Faith wo,ld hart. ¢_mq_lelt'd43_L7.7/.thS.25 =- I_.(ll 3 levLdu i:n "- i'21/2. Arrival date c_weragewas set at 1600 days to dis-
Illql.%bcllUg.',headL_Ililt" ,rid innalkhy lilt" ._lne anllAlllalaltiOtnill play lUiSsitll:s|'11)u11I- h_ ._-yt"arsflight lime,
aS J tipItt't
The m:drix _st"t|t.parfllre :lrac| :lrriva| dates to he presented
A variety of _.o.sidt'uations fore," fine realistv la.ncln period comprises fine"'nli.ssionspace" l'*_reaclndeparture opportunity.
!not tea tlCClll at line nlilliin,lln energyCol.lti,, ,lion o1" depar-
ture and arrival datt's. I,auncln vehiclt, readinL..,,sstatus, procc- B. TramslerTralocto_d,nre slippage, wea;;ter anomalies, multiple launch strategies.arrival characteristics all causefine lanmclnor. nmre generally.
the departure period to hr. extended ,wet a mnmher td'days or As previously stated, each pair of departure/arrival dates
weeks and not unecc_arily centered on the mimuumm e,erg: specifies a unique Lransfer trajectory, l-aeh s, ch point in theJale. missio, sp:tce ha._ a._sociated with it ;in array of descriptive
raft:dales. Depart,re enetg)', clnaracteri/tJ by Cj, is by far tlne
For this docunnetnt, a 1 20-day departure date coverage span inlOStsignificant among tlne_, parameters. It incre:nses It)wards
was selected, primarily m t_rder to encou=npass launcln t'ner&v tlne ,'dges t)f the miss|tin space, hut it :tist_experiences a dr-"--
requirements ¢_t"up tt_ a {'3 = 200 kltz21 b2 t.'ontour, where n:.ttlC rise ahmg a "'nidge," pa._sing diag, mally from lower leftL'.t = |":1' i.e., twits, the injection en|er&v per unlit inlay, tt_ upper riglnt acros_ tlne n|issnou space (Fig 4). This distur-
t_AinTtt JLJPITEtul198b. ('.]1. . I f l
HAL I. IST I¢ r RANSF nH TFIAJt C'i t][l_
,caO/Ol/_.q . 48100 5
90104119 48000.5
qo;01109. ' 47900.b
a9'10,'01 47800.5
89:06;23 4 i lO0.b
89:03' I b 4760U,5
HE I._,Ob 415 _" ,,5
41400.bq l_ILnll,;' J',
I
8H'tll,'19 ' 47300 b
er 8tl'(n_,L_t.l 41200.b _.
H1_11111! 41no0 5
.ql,Ol:24 47000 b
81 tMI I b 46900 h
81/01 _tnh .46800 5
86:t19_2/ 46700 b
86 'nHi'19 ' ,4C,_Ll13',
H6 0.1 1I ,4tL%00 b
I AnlNt'!l liar1
4111! !_ !1 4n11bb _,, 461qb !'= 4623b b
I ALINt:tt j|l :40t_)01l tl
Fig. 4. Mission space in departure/arrival date coordinates, typical example
1983010504-014
r "" ORIGINAL PAGE ISOF POOR QUALITY
bance is a_uciated with all diametric, i.e., near-!gO-deg, out of the eclivtic and forces a polar 180-degtransfer, inordertransfer trajectories (Fig. 5). to pick up the target's vertical out-of-plane displacement.
In 3-dimensional space the fact that all planetary orbits are The obvious sole exception to this rule is the nodal transfernot strictly coplanar causes such diametric transfer arcs to raison, where depiuture occurs at one node of the targetrequire high ecliptic inclinations, culminating in a polar flight planet orbit plane wRh the ecliptic, whereas arrival occurs at
; path for an exact 180-deg ecliptic longitude increment be- the opposite such node. In these special cases, which recurtween departure and arrival points. The reason for this every halfofthe repeatability cycle, discussed in the precedingbehavior is, as shown in Fig. 5, that the Sun a,_d both trajec- paragraph, the transfer trajectory plane is indetenzinate andtory end points must lie in a single plane, while they are also may as well lie in the departure planet's orbit plane, thusfining up along th_ /gin.=.di_,'peter across the ecliptic. The requiring a I:sser departure energy (Fig. 6). The opposite mat-WsSghtesttarget planet orbital inclination causes a deviation egy (i.e.. a transfer in the arrival planet's orbit plane) may be
preferredif arrival energy, V. 2. is to be minimized (Fig. 7).
= TRUE TRANSFERANGLE It shouldbe noted that nodaltransfers,beingassociate,
_' _1 = TRANSFERANGLE with a specificJupiterarrivaldate,may showup in the dataonPOLAR IN ECLIPTICPLANE severalconsecutiveJovian missionopportunity graphs(e.g.,TRANSFER 1991-1994/5), at points correspondingto theparticularnodal
PLANET arrival date. Their mission space position moves, from oppor-/__ / ORBIT tunity to opportunity, alongthe lR0-degtransfer ridge, by
// _/_ / / 1_ _ TARGET departure dateg Only one of these opportunities would occur/ _ / | \ PLANET at or near the minimum departure energy or the minimum
/ /- _[ / ]/// _ \ POSITIONS arrival V date. which require a near-perihelion to near-
Y __1 180_ _ f(q/l) aphelion transfer trajectory. These pseudo-Hohmann nodalSUN = transfer opportunities provide significant energy advantages.
ECLIPTIC but represent singularities, i.e.. single-lime-point missions.
with extremely high error sensitivities. Present-day missionplanning does not allow single fixed-time departure strategies:however, future operations modes, e.g.. space station "'on-
EARTH t_i time" launch, or alternately Earth gravity assist (repeated)encounter at a specific time, may allow the advantages of anodal transfer to be utilized in full.
Fig.5. Effectof transferangleuponinclinationof
trajectory are The 180.deg transfer ridge subdivides the mission spaceinto two basic regions: the Type I trajectory space below the
PLANETORBIT ridge, exhibiting less th:,n 180-deg transfer arcs, and thePLANETRANSFER Type I! spacewhose transfersare longer than 180 deg. in
V_2 MIN.) generalthe first type alsoprovidesshortertrip times.PLANET ATNODE _ -"_% Trajectoriesof both types are further subdividedin twoAT ARRIVAL _.________--_ _ "_ parts-Classes 1 and 2. These are separated, generally hori-if -)'_ INTERMEDIATE zontaHy, by a boundary representingthe locus of lowest
_" ..__,, _TRANSFER C3 ener_' f°r each departuredate"Classesseparatei°ngerduration missions from shorter ones within each type. Type l,
_.. Class I missions could thus be preferred because of their_UN _ / / I ECLIPTIC shortertrip times.
"_ \ /// / TRANSFER
_ (MIN. C3L) Transfer energiesbecomeextremely high for very shorttrip times, infinite if launchdate equalsarrival date, andofEARTH AT NODE course,meaninglessfor negativetrip times.AT DEPARTURE
The reasonthat high-inclinationtransfers,as found alongFig.6. Nodaltransfergeometry the ridge, also require such high energy expenditures at depar-
J
.M
1983010504-015
OR!GlflAL P_G_ IS...... , q; Lrw
EARTH- JUPITER1987,('31,,TFLBALLISTICTRANSFERTRAJECTORY
92/10/0S ,, i I I//.''/:/I//IV lOO , 48900.592/06127 '. , J j /_ ;,'/ I :110 ' 4_B00.§
92/03119 _ ! : :,'/ : ," .... " 48700.5
_ /, ., / i! z,J_V ,"' I/,_ll_ ._ ,so 488oo.s
" 91/12/10 ; i i _ --" --" / _"' ;'_/ " _'_l/_ _. 14o.." 140.
,,,o,,,,.,,,,o,,,,o,,,:,,,,/ "j";" ,,. '" ia .ij- /, "l/ A ._,OO ;i /i" I
,_ 90107/28 /'/ IJ P"" _ v II Jv_"' " v " "f / X/ " !/ I// I) l,t'/ J// ,_",.:i._oo,' t ,_/yl 4BlOO.B
. . .J
>- _47I/'i' vz,. ,__e_/,.,,,vvJ,,,,,o4,,,// ,, , e/,'. ,_J,_ii/,,,,_/I,, .,,,,o,_
_ //,_ _ ;h_ NODALTRAN,,E[RX_/,).m, iv.
"L_s. i i,//i, iV-iT, 47_.B
"/01/_ _ 'r / " I : [.''87 _._ I_tlO." _'J ' IT " _/J[/
89110101 / '1 [ [ _;,I0 ,,_i'_ /::_ ,r l /y/_ .['" 47800.5"-4 - ,47700.5
_/owz_7, . .. ,o.."_ _T::'t _, _",/_i_r'! \_i'-._ / I �I/IV I /89/03/15 B _7_i5- " "--'_ / / j//I ", ..,., ....
I88/08/27 " %' '_ _ A /: : • 4?400.5
88/05119I I I =1""1",_,_1 "_ I I r c_ • 47300.5
LAUNCHDATE
469_).5 4C_.5 47000.5 47040.5LAUNCHJD--2400000,0
Fig. 7, Mission spacewith nodal transfer
lure is that the spacecraft velocity vector due to the Earth's
ecliptic in addition to the need to acquire the required transfer C31VOI_AL = V_: _ ap - 1 _ 77 km2/s _trajectory energy. The value of C 3 on the ridge is large but (8)finite: its saddle poinl minimum value occurs for a pseudo-
Hohmann (i.e.. perihelion to aphelion) polar transfer, requiring This is the lowest value of C3 required to fly from Earth toJupiter, assuming circular planetary orbils,
( 201' + I) _ 2400km2/s 2 17}C3 = I'_. _,I+% Arrival l-infinity. V.¢, is at its lowest when the transfertrajectory is near-coplanar and tangential to the target planel
where l"F = 2*).7hb kin/s, the Earth's heliocentric orbital orhit al arrival.
veltlcily, and % = 5.2 AU. Jupiler's (the arrival planet's) semi.maJou axis B) a smlilal est]male, il can he ,q_(iwn Ihal l'_ra Both C3 and V®a near the ridge can be significantly Iow-IIUe n_ldal pseudo-tlohmanrt llansfel, the ram:mum enetg._ ered if deep-space deterministic maneuvers are introduced into
_e,.. , "d would reduce to the mission. The "'broken.plane'" maneuvers are a category of
7
i
II
1983010504-016
ORIGINALPAGEISOF pOORQL:AL-rTY
such ridge-counteracting measures, which can nearly eliminate POLARall vestiges ot the near-180-degtransferdifficulties. TRANSFER
The basic principle employed in broken-plane transfersis toavoid high ecliptic inclinations of the trajectory by performinga nlane change maneuver in the general vicinity of the halfwaypoint, such that it would correct the spacecraft's aim towardthe targetplanet's out-of-ecliptic position (Fig. 8).
Graphical data can be presented for this type of mission,but it requires an optimization of the sum of critical AVexpenditures. The decision on which AVs should be included
must be based on some knowledge of overall stagingand arrivalintentions, e.g., departure injection and arrivalorbit insertion ECLIPTII
vehicle capabilities and geometric constraints or objectives OPTIMALcontemplated. As an illustration, a sketch of resulting contours EARTH BROKEN-PLANEof C3 is shown in Fig. 9 for a typical broken-plane oppor- TRANSFERtunity represented as a narrow strip covering the ridge area
(Class2 of Type I and Class1 of Type 11)on anominal 1985 Fig.8. Broken-planetransfergeometry
EARTH - JUPITER 1988, C3].. TFLBALLISTIC TRANSFER TRAJECTORY
90/07128. _ 8 _ _R g o "48100.5
90/04119 , ' 480(X).5
90/01/09 , ' 47900.5
89110/01 ' 47800.5
89106/23 ' 47700.5
89/03115 476Q0.5
88112/05 47500.5 o.
r__ 88/08127 47400.5
88105119, 47300.5
88102/09' 47200.5< E
87/11/01' 47100.5 _
87/07124. 47Q00.8
-,8710411S' 4(6_.5
87/01105' 46800.5
86/09/27. 46700.8
88108119, 46600.5
86/03111 48500.5
iii!iiii,liLAUNCH DATE
46115.5 46155.5 46195.5 48235.5LAUNCH JD 2400000.0
Fig. 9. Mission space with broken-plane transfer, effective energy re(i drements
Jk |
1983010504-017
Ih-.ll
oF POORQ,,u.JTY
launch/arrivaldate C3 contourplot. Thedeep-spacemaneuver magnitudeC3 = IV,,.I2, called out as C3L in the plots andAgap is transformedinto a C3 equivalentby convertingthe representingtwice the kineticenergy(perkilogramof injectednew broken.planeC3ap to an injectionvelocity at parking mass)which must be matchedby launchvehiclecapabilities,orbitaltitude,addingAFap, andconvertingthesumto anew andthe V-infinitydirectionwith respectto the inertialEarthandslightlylargerC3 valueat eachpointon thestrip. MeanEquatorand equinox of 1950.0 (EMESO)coordinate
' system: the declination(i.e., latitude)of the outgoingasymp-C. Launch/Injection Geometry tote 6= (calledDLA),andits rightascension(i.e., equatorial
east longitudefromvernalequinox, T) o, (or RLA).TheseThe primaryproblemin departuretrajectorydesignis tothreequantitiesarecontour-plottedin the handbookdatapre-matchthe mission-requiredoutgoingV-infinityvector.V=, to
the specifiedlaunchsite locationon the rotatingEarth.The sentedin this volume.
site is defined by its geocentriclatitude,¢!."andgeographic !. launch _zimuff=problem.The first requirementto beeastlongitude,XL (Figs. 10and 11). met by the trajectoryanalystis to establishthe orientationof
the ascenttrajectoryplane(Ref. 7). In its simplestformthisRange safety considerationsprohibitoverflightof popu-latedor coastalareasby theascendinglaunchvehicle.Foreach plane must contain the outgoing V-infinity (DLA, RLA)launchsite (e.g.. KennedySpaceCenter,WesternTest Range. vector, the center of Earth, and the launch site at lift-offor GuianaSpaceCenter),a sectorof allowedazimuthfiring (Fig.10).Astile launchsitepartakesinthesiderealrotationof
directions ZI is defined (measured in the site's local horizontal the Earth, tile continuously changing ascent plane manifestsplane, clockwise from north). For each launch vehicle, the itself in a monotonic increase of the launch azimuth, Y'L. withallowed sector may be further constrained by other safety lift-off time, tt, (or its angular counterpart,a. - _/, measured
in the equator plane):considerations, such as spent stage impact locations down the
range and/or down-range significant event tracking capabilities.
cos91.X tan6 - sin0L X cos(% - %)TheoutgoingV-infinityvectorisa slowlyvaryingfunction cotan_. = (%- aL)
of departureandarrivaldateandmay be consideredconstantfor a givenday of launch. It is usuallyspecifiedby itsenergy (9)
ASYMPTOTE
N MERIDIAN
LAUNCH FLIGHTMERIDIAN PATH
LI V=.DEPARTURE
ASYMPTOTE
INJECTION
::- LAUNt
a=0
VERNALEQUINOX EQUATOR
TRAJECTORYPLANE
Fig. 10. Launch/injection trajectory plana geometry
=:
1983010504-018
ORIGII_L pAGCISOF pOORQuAt.rI'V
I'he d;,d._ lime h1.,4¢_=._of :=/imuth ca,=be _lbt;iltt@df, onl I{q. GREENWICH
(L)) for a given ¢_. b.. departur@asytnpte_tedhr'cliotl by CUlt. MERIDIANS,=
lull._ l_,llt,_ltll_ quad,a,it lilies @\plaIned h@h,w;t,td II.,,Ingthe Oh GUT A GREENVVICH HOUR ANGLEI'ollo_lng auxdlaiy expte.'_SlOlt.,,Ise@Fit I II EAST LONGITUDE OF'_ (GHA)
V L
__ _-I!.'_/__ ¢_ _ / EQUINOX';H"',,-I,'! --- |0007"_'_42"('l 47"_4"tlX'/._uLAUNCHSITE_ ;'/'7 u_-ul;41' Jol
, _',,0|sx 10'-' \ a_,, _||_ / "-..J_t. J DEPARTURE
ANGLE TRAVERSED '_ ASYMPTOTEwhet@ BY LAUNCH SITE _ MERIDIAN
SINCE Oh GMT \¢11 = light a_'@nsionof launch sit@tq i , XI ) at I ! OF LAUNCH DATE LAUNCH SITE
(d@gl AT LAUNCH. tl. (GMT)
(;ll"ll, trt" = (;te@tlwich hour angl@;it Gl' I.;MT of the
laullch Jate. the @;tstw:ud angk" belw@en Fig. 11. Earth equator plane definition of anglesinvolvedV@fl1:ll t.'Lilltll¢'J.X -'/lid th@ (;Ie=..'llwit,'h nlet ldtilll in the launch problem
I,Jegl
,l_lI "= l:lUtlIh dal@ Ill letlllS _'d Jill@get _.|;I._ ,_IllIe live) ;in_.l .lO0.t'_deg ill the l'outlh _.IU-'=dt:llll(w|letl ¢Olall _-"0 h ]Jll. I. l_I_O (dJ_.,4 i._llegalP,'@'l.
'"/ .iI,'/', Sl,.l@lealrotation l;lll." Ill" I:alth ( 15.tlSItll_t_LIA gene_ah/e-I ph+t el r@lativ@laullch tillle lRi I" X'_l:;ullchd¢._h Iol Ihe Iq,_'k-_tlll _' tall pcth_dl
:l/inluth _I Call be CLtll$11ll,,.'ICdba.,_'d¢',n l"qs. lit);llld (12l,
I I hll olI Imle lh. (;'_I I I If ;I fi_,ed launch ill@ l,tlilUJe IS :iJopled (@.g.._'*'I : "S.3 degl_tl K@ntl@J._,',;pac_."l:h_ht ('ent@i ,,I l,';ipe Canavet;=l.l:h,itd:=l.
:'L lelali_,'¢ l;Ulllch liul@, Ii, I I" m@;i._litedv,'ilh _espe¢l to :in _tlih ,t IdOt is l'qe.,¢enl@dIii Fig. 12 v,ilh depaltut@ ,4_)llll'qL_lelll¢lllJl leh.'l¢ll,:e |lhe dip,lilt:re ,is_llli'_l_tle lll¢lldt,lll',, tlglil de¢lillahon _., ;is lhe IL'qllC*lll |'_,.llillllelel. rhe plot i.,,;ll'_Ph¢:d_le
,is_..t.ll_l_.._ll_.t J, ¢-'III|'_@d@l'illedill to ;II|._' l@ah_li¢ depallUle coildllhtu, l[lJepeudeIll of _i....d;lle.
_l lille I.muih time zz (Rel SI.
_ko. tl I
zrl _ "4 0- . h t 121 ..• llaih', launch window:: IilSl'_¢'clp,_n,,H l:ll'. 12 llldt¢-'iles_'L_llh'lll lh,ll ge,letall._ two ¢i_IIIL_III$I."_I_I I'_I ca¢h de<hl_,lllL_ll v,lhle
{e.g.. _.,. : -I0 degl, _'qle_._c,.'Illllll!; Jl I/i.I I" duilni', lh@,i tit.[hls little tel_teseltt.,, J ._@net;lh,'eJSld@t@,IIlittle l_l" l,rtl,ch |louis. tile ¢_thet in tlte p.tll. ItOtlt_ ,,_I" the aS._lIlphqe Ieliltt,'e
,.'l,Ip,,eJ.,,ale lhe l::I,n¢h ,th: I,i.,,Ip.'i.,,._eJlhe d@patlule ;l.,kvnIp- "'d,I._.'"lole ittel Idl,lll. _A,
Sln,.'e hll-oll lllti¢.., .it@bImtid@d h_ pte._eie¢l@dl,luiIih .,,it@
l'he ,litllal t;leCll_,tiih ._le,lti little IIi.MI'I _t launch, _I" d@pcttdent htlttltllg _,alue.',el launch ,i/Illtuth _'I to'g, "tl _,lel_tli.l_, l,e _d'q.Uth,'dllttll111_I r i'*t' ,Iddlttg .I dale, ,,II¢. ,llh.l ,Is',hll'_- .llld I I._ [email protected],k'h of lh@ lwo _,|e¢lltt;lll_,_ll_OlIIliiIi_ lhu.,i¢Olt-
tole.depettdetll .hllIt,,Inleltl l,tttI.,, ,i .,_'I:.HI_'IlldUllllg whI¢h l,,lllllIh l.,,il_'ttltis._tble "',I lauIlch
v,,'lll_.lo_," rh¢ i_o ,,L,glllt'lll,i _,tll lhe idol do dt,lill@ lh@ 15_,t
_ l,ll.l_, if., ,_ II 151"I ,it.ttl,ible d,ltl_ l-'um¢l, wtnd_,',_.,.
_¢_1 I&'lll %S t',itt lit." ',,_,'etI lib, sill | Ig I. '_. h_t ,_ (|, the t_¢_ d,uh,
the e,g_t¢._,,,,tnl,,t _z II 'I ,It ttttlSt I'_," It.',ed v, tth iL_tttl'_ll|,l [,lUl1¢h _'=l'_l'_OttlllIlll@_ Jte .,,@pat.lied b_ eS,l¢ll._ I_ hltut_, _,l=ll|l
lh_tl.II te._'.,tt,l hq _llladt,lUl.,,.._llt_ll|,It I'_,_llll._, ,llld •Iglt ¢_,_II',elI- ,III lll¢le,l.,ilng ,_ I lh@_ ¢lo._e lit _,ql each olhet, II11111 ,=I I_ I
Item,, II the l.mn,'h I, kn,,;_n to b¢ dtte¢l Ire, _',,.,,tv,.itdl. ,01 . tlte_ metg@lille .I .•tngl@d,ul._ Ol'_l'*Ollllnll_ l:Ol I,_,.,I
thell •_I, _,_Iteli _,'_'=t,'.lI _I t_ tte,_,itt',e. 1,111_.II'_¢O,_lle,:led !_ _,*_I. ,l "'._phl".el thal Sltlgle launch _t, tth.|Ltt,_ _._,'*.'lll%.dt.',al|o_._,
•-I •-: _I ,. * I_1111 | _'=l lelt_'_t.lde, lt_e,,,t_,_,.ltd| LltlU¢lh,'.'.,. Itt_, ,III @vetIIIIIC,I._IIII_ tleIh,'_t_I ,I/IitlUlh t-,ht@.,,l'hL,,._eittst ISI,',ill t) ,le._'mtt,,t I,,' added in the Ihttd I_,_,llettcol,ill _ Is |ttt,,i _. tlltlleltl¢ J|'=OlllP,l._l.lth] IIs Iltltlt_ ,,',inI'll, ' t.let_'ttlttne_.lIttttll
10
k
1983010504-019
11
1983010504-020
: . tmBmNAL PAGE
OF POORI_'JALITY
180 sin (a - a_) X cos 6
sino --...... =.zL 08)160
"_-e extent of range angle 0 can be anywhere between
m 140 0 deg end 360 deg, so both cos # and sin 0 may be desiredinO
its determination. The range angle e is related to the equa-
r_ 120 torial plane angle, _ = a. - eL, discussedbefore. Even:z: though the two angles are measured in different planes, they
_" 100 both represent the angulardistance between launch and depar-3ture asymptote, and hence they traverse the same number of
N 80 quadrants.<.1-uz 80 Figure 15 represents a generally applicable plot of central
3 range angle 0 vs the departure asymptote declination and<-J 40 launch azimuth, computed using Eqs. (17) and (18) and a
launch site latitude @z. = 28.3 (Cape Canaveral). The twin20 daily launch opportunities are again evident, showing the
significant difference in available range angle when following a0 vertical, constant 6.. line.-90-70 -50-30-10 10 30 50 70 90
ASYMPTOTE DECLINATION 620, deg It is sometimes convenient to reverse the computational
Fill. 13. Permissible regiom of azir,_uth vs asymptote procedure and determine launch azimuth from known rangedeclination launch spacefor Cape Canaveral angle O and tRLT, i.e., ACe: a - =Z,,as follows:
: ASYMPTOTE RELATIVE LAUNCH TIME tRL T, h., BY DEFINITION
2, , =0"=24hATo 3 6 9 12 15 15 21 '.RLTI_ I I
-40 lY-£o I AZIMuTHLAU_JCHmmmmaml I = V=0- MERIDIAN
-30 _ - _'Lc / OF LAUNCH SITE
i / AT _L = 28"30
• -20-1STWINDOW/ / -_OPENS AT / / _ 2ND WINDOW
= 70° / 1ST WINDOW "_ OPENS AT
-10 / CLOSESAT i ( _'LO = 700
/EASTERLY T"Lc= 110° I.3 0 LAUNCH I I :g2.
1"11 _r = 900 _ SUN '< ,ASSUMED V=0,10 (ASSUMED) ASYMPTOTE
OI-- 68o= - 15° o LOCATION:< 620= _15°:3 2(w _ = 315°
3O
40 a=0 - aL 1 = 285°
-45 0 45 90 135 180 225 270 315
RIGHT ASCENSION a. deg(EARTH EQUATORIAL CELESrlAL LONGITUDE)
Fig. 14. Typioal launch geometry example in celeqtial (inertial) Mercator coordinates
I;!
1983010504-021
OF POOil Q'..'_LITY
400
360
=o "
.0 (/ ,=oie J,'-P'-.i___i\ _L-,oOI',,,._ (]/p, "- ,.,.,oolI,,oJ,.,,.,o,,°,,z,,o,,,oo '_ I I i I ,.,.=,,u_/_o,,o,.,-,v,_,_-o,
Ie0 .r tl \?',_"_%'_,_i / h "6°° I
z ,o _'-_L",k"F,..]'-_"-4_ _
4o ,0 Ti.illil iillJlli, IlllJllll IIIIJilli ItliJlttt liliJliil iillJllil IIlllllll illlJllll IIIIhltl Ililhitl IliiJllil IlilJllil-70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 80
DEPARTUREASYMPTOTE DECLINATION 6., deg
Fig.15. Centralrangeangle0 betweenlaunchsiteandoutgoingasymptotedirectionvsitsdeclinationandlaunchazimuth.Pairof typicalexamplelaunchwindowsfor 5_ = - 10deg areshownby boldlinesegments
(reproducedfromRef. 7}.
cos6. X sin(a.. - _L) with the lightingconditionsat lift-off andconsequentlyallowssinYL = sinO (19) alighting profile analysisalongthe entire ascentarc.
The anAleZALS, displayedhi Fig. 16, is defined astheanglebetween the departure V vector and the Sun-to-Earth
sin 6 - cos 0 X sin tn. direction vector It allows some jud_ent on available ascentcosEL = sinOX costz. (20) lighting.
Figure16 displaysa 3-dimensionalspatialviewof the same The length of die rangeanglerequiredexhibitsa complextypical launchgeometry exampleshown previouslyin map behavior-the first launchwindowof the examplein Fip. 14format in Fig. 14. The difference in available range ingles as and 16 offers a longer ranse angle than the second, but thewell as orientation of the trajectory planes for the two daily second launch window opens up with a rangeangle so shortlaunch opportunities clearly stands out. In addition, the f'q_urc that direct ascent into orbit is barely possible. Furtherlaunchillustrates the relationship between the "tint" and "second delay shortens the range even further, forcing the acceptancedaily" launch windows, defined in asymptote-relative time, of a very Ions coast (one full additional revolution in parking
I_n.r, as contrasted with "'nlorning'"or "'night" l:.unches, orbit) before transplanctary departure injection. A detaileddefined in launch-site-local solar time. The latter is associated analysis of requiredarc lengths for the various sub-arcsof the
1$
li
1983010504-022
ORIGINALPAGE ;SOF POOR QUALITY
RI IN
CLOsEsWINDOW_I_" ! I0L) _ (ASSUMED)INJECTIONCIRCLE
FIRST "DAILY" (tR! T)SECOND "'DAI OPENS , LAUNCH WINDOW "-
(NOON LAUNCHI(_.j,) LAUNCH
DOW(EVENINGLAUNCH) WINDOW
_-"1. lO°
EARTH LAUNCH SITE
LOCUS, 01. CONST.
SECONDDEPARTURE
ZALS '_ ,"SUN TO EARTHVECTOR
FIRSTDEPARTURE OUTGOING
ASYMPTOTE
V,.,
DEPARTUREFRAJECTORYENVELOPE
F,g. 16 Typical examph. ¢1fda,ly launch gt'_llte'tl¥ (3 dlmt,n_,t)nal) ,ISvlt'wt,d by a,I tlutsi¢|t,L)tsst,fvt,f ah=,ad¢1tthe,spacecraft
t4
I
1983010504-023
OF POOR qUALII"V
_11 titll'lNINU .XFIt" Ot tl_O._l 1 tl % I ttl_'t I ._ IN I_1 t'.XIIK.INU Ollt;i I
/1 • IILIIININ_ -_tii" _,'*t t IN-_i $1 "_,_t I tll(tl._|
{I Ii'_,N_.,I .M_IUli tit I_,%IIN L.XLIhI_'ii._II! .XI_ILILIII'.XIiIUIII ii.%L_I'XI .X._MI'IOII
I:.. "_NUL! tit I_,%l11%1t'1 )(It_l I -XNi_ L_II"_tIIL:Fil tl*_ltl._l ._._Ii'!OIt
l', lilLIt -_IN_'*._I-XI_ Or IIN.II_.'Ih,_N
t I_1 I I I_lsl¢ _llltliltf_ Ill thlt liuli_'h likl isl,'lllll pltsflhp lit the tlil_'llll_ ldane liilel H_f Ill
,I,'l..i :.1;," "!.11,', :,,_.% "_, |l',:l_ .| ::.11,', _,';% , ,'" ._' ,'It,": ,". |'.1:.1 '. i','tl,l|",¢ :.l,llll*,. I%i'l,.llh _,"{, ; _,:'" !,," .1 k,,tl.,".tl.l:I_.!,l,lll _. I'.?ll',':',,Itt, ," II ti_ | '_ tt11_,',ll_':i *.I,'*.: _. .I I, %% k_.: _. _ II_ll _ I1:_._,_ ) _'.l;_|tl._ ,"!'t|
• ", i.t#. _.t.l%tl.lth,t_..l! i,.i..U_.tt't, "_, ,,_, I .Ill!' I ,'l,'l I,' th,"
I RJIIIII¢ ,llllll¢ .lielhlis_'ll¢ | ,,' .t _t.lt,l," .l,,,'_'t "i.ll,',l,,t% I J_,'[_,",'| L ,'ll'_l.ll,l_.%,', tl,'ll _k )
_!_",t._.tl t.tl,," :.11'¢.," .ttlt:t_" -I '.'l,l',t Itt',! ,'._ .i t. .I,,,*ltltll,t*.l.it,," q't_"
|%l. ttl I_tltt_..t;,'_ ::t .it1,.! "l, ._.'i';.",_'tt|tttt .l%_l|l t'tU _ _'.liktt'_ lit,- t_lo|_l't 4_l_lltl_lt _l th¢,_¢ ItJ5",|,,l'* ".it|, .l:,', 41_,,,t tl%ittl|l,'_.
,,;|ll_, .ltt,[ ;:,l".','..'t.itt_'t.ll% ttti_',tt,'t" !'Li'' _, tilt,' Ill,' ,I,'_.lttUt," .l_]ltl,,',"h'lt| I.,'t th,S_|t,'tt ,'l't.il tlll,',;t,'lt li," I,'t ;|re l|l_ht
.. .1:'_,' ,,'t't.ll; t . }'Jilt .In.l-'l¢ • It ) ,'_i,,',t.ilh %tl'tttlt,.lltll ,'l _, ,!it,',| .1'I_,'111
.i't%"11_%"," ,1','¢, ;._'I! II Ii: I%1• . .1_.11.%,.._ .I I_ .i_ _'-_.lh;li",l ll,'t.c.hl :.lit,,, iI;i,',ll,'_ll _.11_.'_,'*, |_'," i • ,_.... l,
i'hdi¢,l ,i', !,ql,,_a •
I ' - I _.'1_
i,,i,,,,l," %%h,"',,"
1983010504-024
• ORIC41NAL PAG._ ;:;OF pOOR QUALITY
140 NOTE:2 ' I
C3" V_ODEP ISTWICLk-uu _ THETOTALENERGY
PERUNITMASS130 1
U_ _
_ 120 ,ERIGEE-- A TIT O185km (100 nmi)
uu 110_" 370 km (200
IO0 I I I I i I I I -25 50 75 lOo 125 150 175 200 225
C3 , km3/s2
Fig.18. Anglefromperigeeto departureasymptote
vt = is the true anomaly of the injection point, usually leant role in the ascent orbit .selection. A limit on maximumis near 0 deg, and can be coraputed by iteration coast ducation allowed (fuel m,il-off, battery life, guidanceusing: gyro drift, etc.I may also influence the long/short parkin_orbit
decision. In principle, any numt)erof additional parking ort_,teli sin v! rewdutions is permissible. Shuttle launches of interplanetary
tan _s - ! +eH c.s vI (23) missions (e.g., Galileo) are in fact required to use such addi-tional orbits for cargo bay door opening and payload deploy-
"/I = injection flight path angle _.bove local borizontrd, ment sequences, in such cases, however, the precessionaldeg effects of Earth's oblateness upon the parkingorbit, primarily
the regressionof the orhital plane, must be considered.eH = eccentricity of the departurehyperbola:
4. Parking orbit regression. The average regression of theC'_Xr
P nodes (i.e., the points of spacecraft passagethroug.hthet_i = i+_ (24)P_.. equator plane) of a typical direct (prograde) circular parking
orbit of 28.3-deg inclination with the Farth's equator, due toTo make Eq. (22) balance, the parking orbit coast arc, Earth's oblateness, am.unts to about 0.46 deg of westward
#¢O.aSr, must pick tip any slack remaining, as shown in nodal motion per revolution and can be approximately corn-Fig, 17. A negative Oco.4sT implies that the vL-SOlution was puled fromtoo short-ranged. A direct ascent with positive injection true
anomaly eI (s.e.. upward el,robingll,ght path angle, 1'1. at 540" X r2 X J, X cosiinjection) with attendant sizable gravity losses, may be accept- S'l = deg/revolutLon (25)able, or even desirable (within limitsl for such missions, r,2,
Alternately, the other solution for _t., exhibiting the longer whererange angle O. and thu_ a longer parking olblt _oa_t. Oc.o.tsT,
should be mlpletnented An extra ,ew,lutnon m parking orbit • = l-arth equatorial surface radms,b378 kmma._ he -, viable alternatwe. Other ¢onsndcratk,,s, suclt as s
desire l'.r a lightsnde launch and/on uqectn.n, tracking sl:lp r° = circular orbrt radius, t.vph.ally 6748 km f-r ank_:ation and booster impact constraints, may all play a _lgmt- orbital altitude of .170 km( 200 nmt)
Iii
-1
1983010504-025
"/2 - 0.00108263 fin Eardl 6. Tracking and orientation. As .t.......... c,from the Earth along the asymptote, it is seen at a nearly
_ i = parking orbit inclinatioh, dc t _ "cor, zputed for zonstant declination that (,f the depart,_tc asymptote. &.
, a given launch geometry ft. ,., (DLA in the plotted data). The vah'e of Di A greatly affectstracking coverage by stations lu,:ated at various latitudes,
" _::": ' " " , """ 'L (26) highest daily spacecraftelevations, and thus best reception, areenjoyed by stations whose lahtude is closes_ to DLA. Orbit
determination, using radio doppler data. is adversely affected]'his .:u:rectl,'_.,1.:r,,t_tiph,..' , .,_" orbital stay time of N
rew)luth:ns, mu:'.tb,: c,,n.4d. ,, .' _,_de;ermining a biased launch by DLA's near zero degrees.
time and. hence, the rtg_,, a_'en.qon of the launch site at The spacecraft orientation in :he first few weeks is often
lift-off: determined by a compromise between communication 1antenna
lx)inting) and solar healing constraints. The Sun-spacecraft-
QL_.FI." t,L + _"L× ,V deg (27) Earth (SPE) angle, defined as the angle between the outgoingY-infinity vector mid the Sun-to-Earth direction, is veryuseful and is presented in the plots under the acronym ZALS.
5. Dogleg ascent. Planar ascent has been considered exclu- It was defined in the discussion of Fig. 16. This quantity hassively, thus far. Reasons for perfi)rming a gradual powered many uses:plane change maneuver during ascent may be many. Inability
to launch in a required azimuth direction because of launch (I) If the spacecraft is Sun-oriented, ZALS equals tl,eEarth cone angle (CA), depicted in Fig. IO (the conesite constraints is the prime reason for desiring a dogleg ascent
profile. Other reasons may have to do with burn strategies
or intercept of an existing orbiter by the ascending spacecraft,
especially it its inclination is less than the latitude of the
launcl', site. Doglegs are usually accomphshed by a sequence of PLANET
out-of-plane yaw tums during first- and second-stage burn, (SUNI
,.)ptimiz.ed to minindze performance loss and continent" rg as
soon as possible after the earl), low-altitude, high aerodynanuc
pre_ure phase of flight ts completed, or alter the necessarylateral range angle :)ffset has been achieved.
r .-.
B) contrast, powered nlane change maneuv--ts _)ut of
parking orbit or during 'ransplanetary injection are much le_s
efficient, a_ a much higher velocity vector mu_t now be rotatedthrough the same angle, but they may on occasion be opera- CONEtitmally preferable. ANGLE
As already discussed, a ,,peclal geometric _ttuation developswhenever the departure as_tnptote dechnattt)n magnitude
exceeds the latitude of the launch site. causing a "'split azi-muth'" dady launch window Figure 13 _.ws the effects of
as)mptote dechnatlon and range salet], constraints upon the
launch problem As the ab_dute value o! dechnati.n increases.
it eventually reaches the safety constraint on a/mtuth, prevent-mg an_ further planar launches The _ttu,,,tm _,ccurs mostl_ CLOCK
earl) and or late m the mission's departure launch period, arid TO ANGLE
is trequentl) associated with dual launches, when m-nth.long OBJECTdeparture periods are desired
STAR
The Shuttle-era Space Transportatmn System (STS), mclud- {CANOPUS)
ing contemplated upper stages, ts capable tit"executing dogleg
,,peratlons as _ell. Tiiew _,,uld. h,,_ever, ellectivel._ reduce
the launch vehicle's pa._l_,ad lot ('.tl capablht_, as the._ did-nexpendable la,mch velucl¢__l the pa_t. Fig. 19. Definition of cone and clock angle
I?
1983010504-026
ORI¢,IN PAliEISOFPOORQUALITY
'm,,h,.. 0+1 0,,......,d,p.,.I _,. ! '.p'a,.',?0:"!lt-I!x:'d ,:,','!:!!!!.'!:'. Annti,-'_,i,,,l_,,.......... |.-.,." Iq.%tl,..... , et,,,t_........................([/,,.,!. Ill _',,i,,t_ t ............ t"
J. augk" I+¢t_Celt tile _t'l,ld¢'`. hmgmldnlal--Z.lXl_..lld tile techniques available, sucll as F'lssive wait for .a!ural
tile" _,bJccl dnlcgtntm), aliglllncnt of Lh¢ ct+ntinuotlsly regre,;si,+,,.,pace station orbit
(2) The St,n-pla._ angle. 4,_ (pba._ an_le is the Sun-object- plane (dmen hy I'arth's oblaten,:_s} with the required, " :'-infinit.,, vector. ,_r tile utnlizalton of 2- anti 3- impulse man-
spacecraft atlglel describes tile state ,*f the ,bject'seuvers, seeking to perlorm spacecraft plane changes near the
disk lighting: a fully lit disk is at ,'ere phase, l:or the .tp.gee .,f .t ph.lsl!lg t,rbli wh.:re vdt,.,ly is Iowe.,,t and thus
l-arth land Moon}. several days ;,l'ter launch, the su,i- Itlml_;.tt the ,,rb_t .`. e.lsle`.t. llleSe t_,, :lppr,,:lcbe`. Call I)epha._ angle is: c_mlbl.ed _.+,itlleach other. :.s well ;ix _,l'h other .,.t.lt;ibl¢
lllallellver`.. `.lldl :l`..
,I, s Ill) - /AI S I'Sl
(11 Ih.'ep ,,p-'lce plopnl.,,Ive burul._ t}at orb:t xhapll|g ;ilia
(3) rhe etvlltour labeled ZALS = '+)0" separates two tale- ph.l`.mg..,'orles of tldll`.ler tlale_2toilex tlm`.c call) dcpaltll!¢,,
{"1 (Ira%'ll.} ,Iv, lst !1_ b). inchldlf|g l-arth ret:lxxl AVI'GA,tllat Itr`.t cut tllslde ]".,.ll,b'`. Olblt. thu., slatting out all
Ilegall%e Ilelmcentfic true atmtnalle, t_t /.ALS _-_l'.) 131 :x.etod.,.ut,,.'_lc IUllI',. at gl,l/lllg perugees el at inter-
atld tht.'.',e late, lille, thdt "_ldl t at psj`.ltlve It Be allt, llila- llledl;Ite pLlltetary `.- Itlgb)._. ;Itld
h¢.s. ]leadlll_ I,Ill l:l_,.lld j Rpllel .llld lle',g'l e_,p¢l ielh. Illg
file IIl¢led.ned :,elan _leallllg al dl',l,llh.es _,I l¢-,n lhall |4| .Mtllllple re_,t,lulion IIIle_.:ltlll burn.% fe_.llllllllg .s¢%'eriil
: AI f.[ ZAI_S "..'it}' I,,_. gl.s+,nngp.l._Scs,c,.nblned v+lib apogee pla.¢ cba.geI|l,iilell% ...'r`.. etc.
7. Post-laun_.'b ,_paet%.'rJft st:lIe. Alter the spa_'e_.la|t h,ls
dep'lrled |'loll! I[1¢ Illlllledl.ll¢ %1_1111t) el I'.lllh II.e.. ]elt lilt" All -I these dextt-¢s can be opllllll/ed Io pemul ..ialtsf,,ctory
I ,llth'_. ,phe!e ,,I IIl!!,lenc¢ ,_t .Ib,,ul 1-2 I!nlh,,! kIll|. It I!hl%e..,, ,,rlnt,d lallllebe`.. ,is well ,is t,, ,Ichleve the lIb,st desirable cold!-
oil a hch,+_.'ei+tric Ct,tlk' whose Illttl.li ,.'tmdlt_oits ,ll.l% I'}e lioins at the lilial alttval i'_od_, ill general, space |atlltcll advan-
apptt_%llt:.lted ,is t,lge's. `.llch a`. llll-tlll_lt .l`.sellll'_l% alld che_.kotlt nil" payh_adsarid
clil`.,ered Illlllllt_le |'_tl,pllIMIIII "_|.lges. t)f olbl|al coII.MILIcII'+III ll|
Ib'.%l" VI IRIII t V.. I-'_11 bulk_ .lInd l'.n:,lh.' `.ub,,_.,delns (',,,Lll l'Lllid`.. ,,all.,,. d.lliellnd.,s.
ladt.tlol,,. I,i,l,ll!s. '+,c.i _a,tll. it Is Imped. gle;i;I._ _,llt_,_etgh the
I_,'l RI tl,'lll 4, Ii,'. t • .._' | ll..|l M_lllll_,illt d_.''+'p-_|,,ice Itll',,,l_ll p,,',,,lltle,, IIIClll(ed tlt.'c,ill._ ,)|tile" ',p,lO,." M,III_Hi"_ Iltitel¢llt iqbitJI o11_.'ltt-ltlon IIiCOlltpatlbl]lt._
_A,itll d'+'p,lt lute l'+'qll,leltlellt.xah+,.'l¢ R Jlld _' o| l dlth all,,,.'e_.alu.tted It!ill' all t.'lIIIL'lllelt, Jl
III11¢ Ol lllle,glloll dlld ..._,P l¢l'It.%¢llls 11111¢ etap,,:d MII_.¢ tllt'll I III
i ,_.',,.'tilldslIhe V+ +e,t,,, l,, I Mi 50 ,.itt'+',.tdll ,,,,,l,hi!,_l,," ,..illO. Planetary Arrival $ynthasis
be _..m,dtucted lIstIng %'(";_" i" I)1 .% - '_, .*n,l RI .% ;,.Ill tilt'Or ,.+,,l"t',,llt..'llt',,.Is hillt;_.', I_i¢ plall;.'tal.X dlll1..ll t[ale,,.'t _lX deslglt ph,blem ln+,,,l+,es
,,;allSt.x ilt_ the pt_.qo,.;t"+, ellgllle+.'llllg -:nd SClen{e ,,bleetlV¢.'., at
%. q I - • co,, ,, • ,,,s ,S . I " ,m., .... ,'_ tit,' target b,,d+x b+ _dJaptllg tile attl,,al ttaI¢+tOl.', lit ..s ,!:liable
lltJIIllel. As these ,+t,le,;Is_,es ma.,, I,e ,lUit¢ dt,,ers..', t,,li.x h,':t
lllnistt.ltl_,,," s,.¢liaXlm sh.tU h,. dn-,.'u.,scd i,l till,, se,,.'ll_,tl l'k+ +,.I" • ,in.'_ ) t31)
" _llbllel alltl,,,,lqlell,. !+lob_'.._lld h, a ,,l;Idll e%t¢l,! ,ahd¢l
_. Orbil -',Ilausieh prublem (.)[.l'Ital lault,:h lh,m tlt,: Shutth.'. UlX',,,I,,,,',lloltl ethel ¢l¢lltetlts el the 51.% -,l tlottl all% tei!lI,<_!aix ,,i
pet!!!ale!It ,.nbttal spa,.'e +tath,n ,.'o!!tlqeXes. mttodlnces c,tt.elx I !-'!._b._ trajeclu+ des|g,|, ht tins tm,,sl,,n n!od,.', he alll%al
Ile_ ¢o11.,'|+1`. utlo lilt' l.axlh-dcpaxtul¢ I,l,,bl¢:n St,me ,,,I tlaJ,'clot.x Is Itl,l luodit]ed lit +nil'+ d,:lell;tl;lislb." g J% at line
the lleV. +..+tlStla!lltS..nhead_, lllentl_+n,.'d, httllt ,,tl! al'll-,t+, pl.,n,.'t the ,,,l.,.t'lil.ll .lllll p,,lltt .lltd alti+,Ji !lille .It++' ,.h,,sell Lt,
to la'lndl a gli¢li liilell', ,tict.llX ll_is`.l,.,ni I I'e ,_i,,mlx ICgleS'sll!g s.ltislx t:l¢ I.IL_¢sl nunxnbct t'.l r_,tcntl.ll Obledil¢_,. IOlil_ belol¢-
`.pa{e ,!.ill_,ii Olbil I+,,.'¢ 1.I 25i 7eliei-,|l) d,_¢'+ li,,l ,:Oill.iili li.ind
lli¢ I-llllinll.X le,.h,I i_.'qUliCd .it dcrailUle Oibll hl¢lil!i¢
Ol t,lhel ++Ollsid¢lali,,ll`. iiia.'l dl,.I.lt¢ .l ,p.l_.¢ slJliOli',, ,,IbllJI Ihi`. ph,,¢,,,, ilit,+k¢`. !ti¢ ,:h,,i_.¢ ,.I alli+,.ll dJk Io eli,+uie
41111uric Ihal niJx bt" I,,o hlgli lol ,ill ¢lliclelll ilil¢,.li_,li In.ill de_iIJI,k" _hal.l,l_':i`.ll,`.. sti,,'i .l,, ii% • _,aliiL'_ ,,I Ilie %allables
IlinOlalil¢ depdilUi¢ silaleg:e`. .lle b¢¢il!lilil¢ h, eili¢il:+... %,liP. !1%1' /.-%l'h. _'i.. plCsCtiicd ill I,l,,ued h,illi iii Ih+.' datadllelnlllllilZ It. alle%la'¢ tlie`.e plobk'lu_ a I¢,¢1it %,k'll, c _',ll,,li,,l lhl,,I,_hlllle
?ll
l
d
1983010504-027
ORIGINALPAGt ISOF POORQUALITY
I)A|'. tilt" pi_lll,'t C,lti.lt.10Ld l,h'clul,dhln, h.... _lt tile IIIC_IIIIIII_ I I
,I_SIIIptl,stt'. I.L'., td lilt' I Ill|liill, ", Vel,'tOt. p'LIVldt"_ till," ;llt'aMIIl." L'LtSt! -- _I._i'" |:tnl the Illll_llliUlll I_L,sslblt• I.,'htt.lll_,, ,it Ih b_ It._ IIt'l._,;ItlVt" IS i ! "" I'
,,llSn k;ILIWII 4_ till,' I:ltltlll,h' Ot '_¢tth';ll Itllp,l_ I (| Ib'l). _llI,
The Ilhlgltlllll,ll," ol | Illllllll'_. VIII' i,I,'... , .i l,'llab|t's _qlr hi VIii' al,_n _',l:ll_h's lilt' l,k',_l_z..'l. IL_ el,':lhlalL' pl:mdLwenhl¢
¢l,_ltllttl lilt' 11._b._ tlllil .I,_',lt" .._ bt'l_,_'l,'l,'tl till," IIh'Olllllll. _,'llll,I VL'IIIt:II._'. i'. :It -'lily dl_l;lll_.'('. I. ,_tl till" |l.vlt._ hYl_rlbtd_l
Olltl.°s_Ull', V.. _'l,'l,'hll.'_I'_ .I ._Ult.ll_k" _'llLIh:_"_1 _'!(_('xl .ll_pl_S;l_'il
((' "| _111,llil_,.! I I_l,'t"I:l._: 'Ill / _;- I " _' I i : km ._ LI4i :,/
' II1 till," ,'.bert' t'tltl;lll_lt_, ill, (l,ll (;,|11,), I.',tilt" ,_I;IYI;.III¢III:II |!;11;1111- .
w11¢1¢)_. tilt' .I._._IIIpttsl¢ II;111.little. I'_tOlllld Imtlt t'tt'l l,_l"til_" .lltlV:ll b,,,h,
t
V! IIII(:AIIMPAL'I illl|N ANL;I I
PLIIN I
SUN _ I'
\
I AHlll \ HI AI',_I
" " IAS(:| NITIN(; NL)I)I
ASYMI'INItL'I,N,)I,, l i i v'' 'V-la i, I I
Fig 20 PIIIIIIIIIII¥ flyby WeOllll|Iy
!1
M
1983010504-028
ORIGINALPAGEISOF POORQUALITY
Another Fair of significantvariableson which to base TARGET B-PLANE,' T" IN""MING _'arrivaldate selectionare ZAPS andZAPE--theanglesbetween • u _u
•l:;"n";*,'....,..jand the planet-to-Sun........nrl .Earth vec'fnr_ re;pec- - ........ PARALLELTOA_TMrZUI,- _ INCOMINGtively.Thesetwo anglesrepresentthe coneangle(CA) of the _ _",_ ASYMPTOTE
orientedspacecraft,in that order. ZAPS alsodeterminesthephaseangle,_s, of the planet'ssol= illumination,asseenbythe spacecraft on its far-encounter approach leg to the planet: o
(I)s -- 180 - ZAPS (35) I
defined and discussed in the Earthdeparturesection above.
RBOLIC
The flyby itself is specified by the aim point chosen upon _ _ _ [ PATH OF
the ar-;.val planet target plane. This plane, often referred to _ '_ // "_,_ SPACECRAFTasthe B,plane,is a highlyusefulaim point designtool. It isa
" V. the relativespacecraft incoming velocity vectm at infinity. /• The incomingasymptote, i.e., the straight-line,zero-gravity _ INCOMINGASYMPTOTE
extensionof the V.-vector, penetratesthe B-planeat the aim J" V== 'TRAJECTORY PLANEpoint.Thispoint, dc..... ,1by the targetvectorB in the B-plane,is often describedby its two componentsB • T andB - R,wherethe axesT andR form an orthogonalsetwith V=. The B MISSPARAMETER, B_T-axisis chosento be parallelto a fundamentalplane,usually (TARGET VECTOR)the ecliptic(Fig. 2i) or alternatively,the planet'sequator.The 0 AIM POINT ORIENTATIONmagnitudeof B equalsthe semi-minoraxisof theflyb) I.yper- S PARALLEL TO INCOMING ASYMPTOTE,V==bob. b, and can be related to the closestapproachdistance. T PARALLELTO ECLIPTICPLANEalsoreferredto asthe periapseradius,r, by AND 1TO
R =SXT
)(( ,,,IBI - -__- ! + _ - I , km 136) Fig.21. Definitionof targetor arrivalB-planecoordinatesPp /
or The two system.s of B.plan_ T-axis definitior,can be recon-
lip (/lip _2 /t/2 oiled by a planar rotation.-AO, between the _cliptic 'T-andr = + +IBI 2/ ,kin (37) R-axes and the _'- and _:axis orientations of the equator.. based system
The d;,rection angle 0 of the B-vector, B, measured in the sin (a - c_:p)farget plane clockwise from the T-axis to tileB-vector position tan A0 =
cos fi X tan 8_.p- sip 6 X cos (am - (XEp)can easily be related to tile inclination, i, of the flyby trajec-
tory, provided that both//,, (DAPI and the T-axis, from which 13¢9)0 is measured clockwise, are defined with respect "o the samelhndamental plane to whidr 'he inclination is desired. For a wheresystem based o=1the planet equatcr (Fig. 22):
%.e and _.p are right ascension and declination of the
cos ipF0 = cos OpF(_X cos _ (38) ecliptic pole in planet equatorial coordinates. For Jupiter,PP._ t,sing constants in Section V:
which a_¢umes that Op_..¢is compttted with the T-axis parallel al..-p = 290.598 6Ep = 87.780, degto the planet equatoT (i.e., Tp/.-(,)= V X POLEp_.(ll,not theechptt¢, as is trequenth assumed 11'_.(,i = V ×'POLE/..,,! ). a, and ,_. are RAP and DAP. the ditection_ of incoming('are must be taken to ttse the 0-a,gle as defined a,;d intended. V. also in planet eqttatorial coordinates.
2O
1983010504-029
ORIGINALPPGE '";,J
OF POOR QUALITY
ECLIPTIC POLE (EP)
PI.'('I.PEQ POLE / ,I"PEQ DECLINATION
lil,i." OF EP, _EP
PEO RIGHTASCENSIONOF EP. aEp
.90 °
:PLANE(ECL)
PLANET EOUATOR(PEO)
a,..- 180
.-PLANE.TOV.It -- \ P:C'I.
TI,I.,CI: V_ \ Ptv..CiAa : 90- [(aEp- 90)- (ooo- 18011-.ooo-aEp
At/- ARCTAN [SIN A¢_,"(COSboox TAN ¢5/:..p.. SIN _,_, x COb Act)]
Fig. 22, Two :r-axisdefinitions in the arrival H-plane
The ¢oriection All i,_applied to att ;lllgle ¢onll_Ull'd ill the i_eliapsc, ,ll the I'liti) poinl of a plobc, ol gcn¢ially .'it :ill)
l'¢lipli¢ ._.l,'sll,lll ,is hllloivs IFig. 2}i: pOSllilln r Isull,_,-iil_i ,%"= SIIII, could hi" il, placed by !"_ I::lrlh,; if dc._i_edL t_'e Fig.."41:
Oi,l.U .'. tilL. I �.%0(4tl)cos ,1' -- -cos _l. \ cot/AP_ - sin i#, \ sin/AI_
I'hl" ¢¢11pli¢T, lt_-l,! -ixcs, lllll_t,l'l'l, h-',ve Io be llll,ill, d b.%
-A0 tdockllis¢ dllCt:llOll IS llOsllli¢ Iii Ih¢/I-pl.'lll¢I hi otll:llll \ cos {1"11_1'- li,_.i.I 1411p!,uil, I t'qllahlllll i. I_FI, I ¢lloldui:il¢ a.xcs lhl,/I-nl,iglUllidl,ol Jll 11111ilOlnl in ¢llhl, i ,_.%,_I¢11li,_Ihe ._;lllli" wh¢le
I'h¢ plOl¢¢llOns of lhl' SIiil-lO-i_l,lnel _llld I:alih.lo-pl;iil¢l Ii -- Ih¢ ,illn pOlnl -'ingll" I:l Ih¢/t lllan¢, lllii,_l he wilew¢_,ois illlO tire II pI;ille Tcpr¢,_lll ainl poinl lociofdi;llli¢llk" iespecl IO the ._iilll- :r, ,i,_I-i',_PSIIli "-illd I:,iilh L_,'¢ull,illOns, lespe¢llvl'l%_,,i,_d¢llnl'd in I:i I, 2.1,I'h¢ it phin¢ t#-,ingl¢,_ll_ illi iesp¢¢l Io Tt,%,! ,1%1._1of Ili¢,_¢v-'lil- tJ,. -- Ih¢ ;illw:il lang¢ _nl'.l¢ lioll _.illliilll) I;i posilloll I,ii;iblcs ,lie pi¢,_lllCd :illd I'.ll_ded l'i,_l' ;llttl Frl-P,icspccti_,el_, oul oil Ih¢ Ili<Onilnl_ ,is)inllh_ll'l hi Ih¢ I_llllil ol
Illl¢ll'fl r ll:lg 2,_1in Ih_" plollcd iilllSion dal-'i. In ,iddilion Io h¢lpul I dl'Slgll Ol
l,lsl' ,IVOld dl,lnl¢lll_" _.'ciIIl-'illOns, Ihl'l" qll;illlllll,,_ alh,_ rhe ¢Ollll_Ul;lllOli of lhl" ;lliil'-'ll i.'Ulge -illgll', ii,,, io die
¢ollipulalloll ol ph,i._i',illl_lcs,_l_, of llll" pI,in¢l al Ih¢ spa¢¢¢l;ll'! po,qlioll ol the dcslicd ¢_,l,lll dcpcnd,_oil I!$ Ii l_l', ,11l\_llo_'s
21
i
1983010504-030
ORIG_ALPAGE1OF POORQUALITY
SUN (OR EARTH) TO I. At flyby periapse. (i_,, ->-L_Odeg):ARRIVALPLANET VECTORB PLANE
-icos/_. = cos(-v) = (42)
{.2 rp
SHADOW PPNDER
(SUN OREARTH) (Tp is periaps_ radius).
2. At given radius r. anywhere on the flyby trajectory•_ .(see Fig. __ ).
/]= = -_ + _ (43)
u® should be computed front periapse equation.
: Eq. (42) _r at r can be obtained from t-v= _g v r _g +
v,,. v r has negative values on the incoming branch):
T r r, _ 2+ P-----_-_ -1
r ppcosv =_' (44_
I rp1":1t!+
Pp !
TO SUN 3. At !11e entry point h wing a specified flight pall= azlgle
(OR EARTH) R "_1."IFig. 25"w.
Fig. 23. Definition of approach orientational coordinatesZAPS and ETSP. ZAPE and ETEP _. : -=- + I'F (45)
INCOMING TERMINAIOR
ASYMPTOTE d_s 90:
180 ZAPS "
r. RADIUS TOA POINT ON
TO SUN TRAJECTORY
TRAJECTORY ARC _;,, Rl.(.i. PHASE ANGLE. '[_ PROJECTEDuNITSPHEREONTO
.._ "ETSP- 180°-0
Fig. 24. Phase angle geometry at arrival planet
22
i
1983010504-031
ORIGINALPAGEIOF POORQUALITY
ARBITRARY TRAJECTORY OUTGOINGPOINT AT RADIUS r ASYMPTOTE
AND TRUE ANOMALY UrX I
FICTITIOUS
ENTRY PERIAPSE
RADIUS. rp /,/h
FLYBY PERIAPSE
PLANETARY RADIUS. rpFENTRY ENTRY
INTERFACE _oo= Uoo
TURN ANGLE
= 180-2p
IMPACT
POINTAT RADIUS
rE = rSURF + hL.AND FLIGHT PATH
ANGLE 3'p"FLYBY
INCOMING _oo= -v=,A,qYMFTOTE
ENTRY
FLYBYTRAJECTORY
IBI-I-"FFLYBY MISSPARAMETER
Fig. 25. Typical entry and flyby trajectory geometry
23
1983010504-032
ORIGINALpAGE Wof POORquM.rrt
where PE is the true anomaly at entry, should always control of arrival time. The number of satellites passed at
be -lep,ative, and can be computed if entry radius and various distances also depends on the time of planet ('/,4.
altitude, rp..= rsuRi,. + h_: and Vp..,the entry angle, are These fine adjustments do, however, demand arrival time
known: accuracies substantially in excess of those provided by the
ra V _ computational algorithm used in this effort, which generatedrp 2 + _2 -I the subject data (accuracies of I-5 rain for events or I-2 hr_. /Jp ] for encounters would be reo, ired vs uncertainties of up to
cos u_: = V 2 (46)• 1.5 days actually obtained with the rectilinear impact pseudo-
(l+ p " ) state theorem). Numerically searched-in i,ttegrated trajec-/l tories, based on the information presented as a first guess
in.put, are mandatory for such precision trajectory work.
, whereas the fictitious periapse radius rp for the entry.
to satisfy _/_:at r_:, is equal to Preliminary design considerations for penetrating, grazing.
_ 'I'_"_ _ I" /I (_-,_)/1"2 I V2 )1 °r av°iding a h_)st _)f planet'centered fields and particle strut"
/zp / . lures, such as magnetic fields, radiation belts, plasma tori. lingrp = I + + rF cos27_: 2 *"u rE and debris structures, occultations by Sun, Earth, stars, or
• /Jpsatellites, etc.. can all be presented on speciahted plots, e.g,,
the B-plane. and do affect the choice of suitable aim point
(47) and arrival time, All of these studies require the propagationof a nmnber of flyby trajectories. Adequate initial conditions
The B value corresponding to this entry point can be com- for such efforts can be found in the handbook as: VHP (V t
puted from Eq. (36), while _J,e 0 .. "le in the B-plane would and DAP (6) already defined, as well as RAP (_), thedepend on the desired ent,. tatitt_.te inclination, Eq. (38), or planet eqt atori_! right ascension of the incoming asymptote
phase angle, ,.q. (41). (i.e.. its east ',ongitude from the ascending node of the planet'smean orbital plane on its mean equator, both of dateJ, The
The general flyby problem poses the least stringent con- designer's choice of the aim point vector, either as B and O, orstraints on a planetary encounter mission, thus allowing as cartesian B • T and B • R. complete the input set. Suitable
optimization choices from a I:rge it< ,.f secondary parameters, programs generally exist to process this information.such as satellite viewing and occultation, planetary fie!ds andparticle in situ measurements, special phase-angle effects, etc.
2. Capture orbit design. The capture problem usually
A review of the plotted handbook variables, required in tile involves the task of detemfining what kind of spacecraft orbit
phase-angle equation (Eq. 41 ), shows that the greatest magni- is most desired and the interconnected problem of how and attude variations are experienced by the ZAPS angle, whicb is what cost su':h an orbit may be achieved. A scale of varying
strongly flight-time dependent: the longer the trip, the smaller complexity may he assnciated with the effort envisioned anZAPS. For low equatorial inclination, direct flyby orbits, this elliptical hmg period orbit with no specific orientation at the
implies a stead_ move of the periapse tuwards the lit side and. trivial end of the ,_ale. through orbits of controlled or opti-
eventually, to nearly subsolar periapses t_,r long missions. This mized line_ of apsides (i.e., periapse location), nodes, inclina-
also unpiles that on such flights the approach legs of the tra- tion. or a safe perturbed orbital altitude. Satellite G/A-aidedjectory are facing the morning terminator or even the dark capture, followed by a satellite tour. involving multiple satel-
side. as trip time becomes hmger, exhibiting large phase angles lite G/A encounters on a numher of rewdutions, each designed(recall that phase is the supplement of the ZAPS angle on tn achieve specific goals, probably rates as the most complexthe approach legl. This important variation is caused by a grad- capture orbit class Some orbits are energetically very difficult
ual shift of the incoming approach direction, as flight time in- to achie le, such as close circular orbits, but all require signifi-
creases, from the subsolar part of the Jovian leadmg henusphe, e cant expenditures of fitel. As maneuvers filrm the backgroundIm tile sense of tts mbital mottonl It, tts antisolar part. It) this subject a number of useful orbit design concepts shall
be pre_nted to enable even an unprepared user to experiment
The arrival time choice on a ver_ fine scale may greatly with the data presented.
depend on tile desire to observe specific atmospheric,:surface
t'ealm _',_(e,g.. tbe (;real Red Spot) or to achieve close encoun. Tile simplest and most efficient mode of orbit inlection is
ters with specific satellites of the arrival planet. Passages a ¢oplanar burn at a ctznnnon periap._ of the arrival hyperbola
Ihrough special _tellile event /ones. e.g.. Ilux hlbes, wakes, and the resulting capture olbit (Fig. 26). The maneuver AI"get_.'entrlc and ou heli_.'entric occultations, require close required is:
24
t
I
1983010504-033
ORtcISIALPAGEISOF POORQUALITY
I " /, ........ A idol of orbil in._'ilton .._1' lequzzed ;1_:i I'ullcllon el #i, .Ind- p,, #r_i- p;, \ v l I' . ...%1'": " ¢ .... , kill .,, 14,'4) lusnlg I', !. 50| is Plrsellled Ill I:lg. "" l'he ,Ipo,ll_sei:lthu.,, of
• rt, lr-I4"(,i su_'h :IllOlbll ol_lYell llVliOd would Ill,
The oibilal petted I'ot mlrh .in orbit, tequuing kn,lwledge /'- Pr \ t':ofperlal,_,:llldapO.llt_"ladit,r/.:llld/'4•IS rl "-" .i/............el, .kill (_I)
%. _-"
,/L: i<jFr I �r1"1/' " An e_:dualiontit"l'q.1501(,tndl'lg._")silov.stheirlo_,esl
!' 2= ,/ Pt' . .', (4'}) titbit Ili,k'lIlOIt _1 IS obt:uued Ioi tilt"Io_t'st vahle t,f r/,. lilt"iOllg¢.,I pet led !'. alld tile lowest I _..of alliV:ll.
It till tile ethel il:llld, a klloWll Olblt pelted l' (ill seconds}
is de_lletl, tile e.%ple.,_:41Oll(tit & I'is Of some Illl,.'leSl IS hlleetlon illlo ClleUlal ¢apttli¢ Olblt_. a
special C:l_, of tile ¢oapsld:d ill.,ierliOll piobient. It call be
3: ..... '"""'""'""'=""'"'"'""'""""'""'""'""",,. , -_"_,.I- ",. :L".,.'"/ <,,,,,,,,<",,,,,,,.,,,,<,,,,.,,.,,,,,.<<,.,,,,,<,,>.,,,<,,,<,,,,.,..-,,.,.,...rl, rp _/_ l" l (Sill l'llCUlal till,it.i, Ilu,'h v.ould lequile a sl,eclll,: I-'ldlU._.
COAPSIDAL COTANGENTIALCAPTURE CAPTUREORBIT ORBIT
t. I
/ \APPROACH (., .7
\ \ "#t "HYPERBOLA _ ,_ COTANGENTIAL• ./ IURN POINT
ORltl T PERIAPSE / II-" \ COAPSIDAL BURNAND PERIAPSE OF
HYPERBOLIC PERIAPSE _ ITS CAPTURE ORBIT
Fig, 26. Colipsldlll and cotingentlll capture orbit insertion geometries
ill
l
1983010504-034
Oflllt_ PAGEMoF poor q,JAUTY
Atop. one can solve for the hyperbolic periapse rCA apd tileCAPTURE burn radius • using selected values of true anomaly at hyper-ORBIT
7 I I " he|it bur.-, point I,, =rid it_ eaptilre orbit equivalentNOTE: COMMONPERIAPSE [ PEfllUU: ....
301 I .... RJ
! INSERTION MANEUVER j'-j--'3_ - -,v6 - t.J : 71398k. _x_° I p _ : v'! (551
5 rp = 5RJ utilizing the folowing three equations (where E ai,d it stand/ 200 ) for elliptic and hyperbolic, respectively):
P=, I ,.:
= , .j v (r"+:).,r.-;>3 s / ) PERIAPSE sill I'/. -
'RADIUS / rCA |'2 ' (56)
O 2 D_rp=IRJ 2r.lr P _)1+**
'- ...."I
o ill|lilt, ,i,,l,lil ../ - - +2
ARRIVAL V-INFINITY V.., km/s rca _ /_p /• = (57*
Fig. 27. Coapsidalcapture orbit insertion maneuver AV [ r(._. 1"_
requirements for Jupiter (usingEq, 50) t ] + _ / cos Vii + ]/Jp /
2 lu,- (52) 2 ra
re'° I'2 = 158)
while the corresponding optimal value for A V would be rp
• - t_ II The procedure of obtalninl_ a soluqon to these equations is.11('o _ _, ""
iterative. For a set of given values for r I. rt,. and all assumedFrequently die orbital r.'ldius obtained by use of Eq, {521 is .3to. a tgl of I"H and i_. the hyperbolic and dhptt_:al bullinconlpalible with practical injection aspect., or with arrival point true anomalies which would satisfy Eqs. (55-58) canplanet ._'ience and engineeling objectives, be found. This in turn leads to r, the maneuver point radial
distance, and hence. ,.%i"(Eq, 54). A plot of _l'cost for a set
A nlore general el,planar mode tit"capture orbit insertion, tit consecutive .31_r choices will provide the lowest .3 l" s aluerequirivlg Ollly tangenliality of the two trajectories at an I'ot this nlaneu,'er ntode.
arbltlai.% in-qlt tlv¢l pOllll of radius r common to both oibli.,,.
Fig 2b. vequue,, a propulsive effolt of For an optimal insertion into an tobit of an atbittal._ Illa.lt)laxis tlrlentatlon one mUSt tUln to tile mole genelal.._Illl ¢o-
I,l'+ ",, .I-'"':' +,,.-,l pial,ar,b,,,.,ersecting(ie..°,,,a,,gent,albu,,lp,,,,,,,,,,=,.31"=, 7 -- (54) euvel (see Fig. 2x). It provides sufficient flexibilii_ to allow
%, _/ r(r_ + r) numerical optimization of .31" with respect to apsidal rotation,
.3%it Call be cleari._ seen that b) pert\tuning the burn at periap._e
the substitution r : rp brings us back to Eq. 1481. A inole apploptiale wa) to define ap,..idal olientation is tonleasule tile ptlst-nlaneuvei rapture orbit periapse posillOll
The Colang¢llllal maneuver mode prowdes nolll.)plinlal con- angle with lespect to a fixed direction, e.g.. a far eucounler
lrol ovel the OlletlldtIOII tie the inaiol axis tie tile capture orbit, point till tile UlCtlnllng a.,,ymptot¢. -V,. thu.i defining a cap-It it i,, desiled to rotate this line tie apsides ¢lockwl._ by lure oibit perlap._ iange angle
111
l
1983010504-035
OR_Gr,_ALPAGEBor POOR
INTERSECTINGCOAPSIDAL CAPTURECAPTURE ORBITORBIT
'A
VE 2ND BURNPOINT
r2 OPTION
v=ASYMPTOTE
II II I I
%
== / \APPROACH I NOTE:HYPERBOLA / E = ELLIPTIC
H = HYPERBOLIC
CAPTUREORBIT / _ PERIAI_E, rcA.CAN
PERIAPSE,rp I VARY: rA ;_ rCA ;_O.
I PROVIDED rs IS AVOIDED.
I OPTIMAL BURN AV1STBURNPOINT REQUIRES tCA ;_zpOPTION
Fig,28. Coapsidalandintersectingcaptureorbit inurtion geometries
where
0 = I /,_ xr_,x-- I-"_, _,_._I v ,_.., I"_=I +1" r I
I+ "=_ ,_ -'p_,lr-_,Al+ i'_ ir2-rz_.._ilir-rl, i(r.., -,i I#p
IbOiTaken from lef. 8, d,e expression for the inlersectinl bum
.._I"is'
, ! .'
_1": = I'" + 2 #/, rt �-7 _¢/ rl + r × L) r I alld rl, = apoapscandperlapscradiiol caplllrc +')lip._
t'/
1983010504-036
ORIGINALpAGEBoFeooeQuALrrY
re,4 = closest approach radius of flyby hyperbola
n = /_ .mean orbital motion, rad/s (63)t -- flag: _ = 4-1 if injectinn occurs on same lee(inbound or outbound) of both hyperbola
and capture ellipse, 6 = -i if not. r l + re
a - 2 , semi-major axis of ellipitical orbit, km (64)it should be pointed out that Eq. (57) and (58) still apply
in the intersecting insertion case, while Eq. (56) does not 2 rA rp(as it assumes orbit tangency at bt.rn point), p - , semi-latus rectum of elliptical orbit, kin(65)
rA +" P
The evaluation of intersecting orbit insertion is more
straightforward than it was for the cotangential case. By assure- R s = Jupiter's equatorial surface radius, km
ing V andorUit size(e.g., V =0km/s,r_ =4RJ, P= 20017
days. similar to a Galileo capture orbit) and stepping through a "/2 = Jupiter's ublateness coefficient (for values see
set of values for vE. the capture orbit burn point true anomaly, Section V on constants).one obtains, using Eqs. (57-60), a family of curves, one for
each value of Rt,.A , the hyperbolic closest approach distance. For the example orbit (4 X 272.4 RJ) used in Figs. 28As shown in Fig. 2t), the envelope of these curves provides the and 29, if near equatorial, the regression cf the node and
optimal insertion burn AV for any value of apsidal rotation advance of periapse, computed using Eqs. (61-65), would
A_o desired. The plot also shows clearly that cotangent...,I and amount to a negligible -0.23 and +0.46 tier/year, respectively.apsidal insertion burns are energetically inferior to burns on For contrast, for a grazing (a = 71,398 kin) Iow-inchnation,the envelope locus. For the same assumed capture orbit, a near-circular orbit, the regression of the node would race along
family of optimal insertion envelopes, for a range of values at -64.5 deg/day, while periapse would advance at 129 d:g/
of arrival V, is presented in Fig. 30. The mlallest value, day, i.e., it would take less than 3 days for the line of apside_
V = 4.458 kin/s, represents the remaining pre-insertion to dua complete turn.energy after an lo encounter, typical of Galileo mission
It should be noted that _'Z= 0 occurs for i = 90 deg, whilestrategy. CO= 0 is found for / = 63.435 deg. Sun-synchronism of the
The location t_f periapse with respect tu the subsolar point node is achieved by retrograde polar orbits, e.g., a 5 P-J cir-
is of extreme importance to many mission objectives. It can be cular orbit should be inclined ! 11.08 deg.
controlled by choice of departure and arrival dates, by AV 3. Entry probe and lander trajectory desiBn. Entry tra-expenditure at capture orbit insertion, by an aerodynamic jectory design is on one hand concerned with maintenance of
maneuver during aerobraking, by depending on the planet's acceptable probe entry angles and low relative velocity withmotion around the Sun to move the suhsolar point in a manner
optimizing orbital science, or by using natural perturbations respect to the rotating atmosphere. On the other hand, the
and making a judicious choice of orbit size, equatorial inclina- geometric relationship of entry point, subsolar point and
tion, i, and initial argument of p,,riapsis, wo, such as to cause Earth (or rela) _pacecraft) is of paramount importance.
regression of the node. _'_, an_ the advance of periapsis, CO. Lighting during entry and descent is el'tel; considered the
both due to oblateness to mo/e the orbit in a desired manner primary problem to hc resolved. As detailed in the flyby and
or at a specific rate. Maintenance of Sun-synchronism could orbital sections abo_e, the choice of trip time affects the valueprovide constant lighting phase angle at periapse, etc.. by some of the ZAPS angle which m turn moves the entry point Ior
or all of these techniques, l:or an elliptical capture orbit longer missions closer tt) the subsolar point and even beyond,
(Fig. 31 ). towards the morning terminator.
2 nj 2 180
_'! := --_X"3 Rs_.._p2 ct_siX _,n deg/s (01) Landers t_r balloons, regardless of deceleration mode,prefer the morning terminator entry point which provides a
better chance l't_rvapor-humidity experiments, and allows a
Co ='T3 X _R_ n J, 12 = I- :,) sin: i)×S_" 180, deg]s longer daylight interval for operations f, Uowing arrival.. p: v
The radio-hnk problem, allowing data llow directly to
iO2) I'arth. el via another spacecraft in a relay role. is very complex.It could reqmre studle_ tzf the F,arth phase ungle at the entry
where It_:ations or alternately, it could require detailed parametric
I
1983010504-037
ORIGINAL PAGE |_;
OF POOR QUALITY
-I
1983010504-038
3O
1983010504-039
1983010504-040
ORIGiNAl- pAGE I11OF pOOR QUALITY
IV. Description of Trajectory Characteristics vector obtained by vecto,ial subtractionof theData hehocentricplanetary orbital velt;city from the
spa,'ecraft arrival heliocentricvelocity. It repre-A. Gel'Im'al sentsplanet-relativevelocitya' ,reatdistancefrom
The data representtrajectory performance informatio;_ targetplanet,at beginningo, far encounter.(.:anplotted in the departuredatevs arrivaldatespace,thusdefin- be used to compute spacecraftvelocity at anyingall possibledirectballistictransfertrajectoriesbetweenthe point r of flyby, including ('/A (periapse)dis-two bodieswithin the time spanconsideredfor eachoppor- tancerp:tunity. Twe]veindividualparametersare contour-plotted.The
first, C31., is plotted buId (m a Time of Flight (TFL) hack- I" = /[:2 + 2_p km/sground;the remainingten variablesareplottedwithbold con- _/ r
I
touring on a faint C_L background. Elevenplots arepresentedfi)r each of twenty ntission opportunities between Iq_5 and where2005.
The individual plots are labeled in the upper outer corner PPfJt'Prrl..'l¢= gravitational parameter GMby bold Iogos displaying an acronym of the variable plotted, svsre:._lJ of the arrival planet system-the mission'sdepartureyear. and a symbol of the targetplanet. Jupiter plus all satell;tes. (ForThese peru)it a quick and fail-safelocation of desired informa- values, refer to Section V onlion. constants.)
B. Doflnition of Oeparture Vmr,_abl,_ I)AP _a, planetocentricdeclination(vs meanplane'equator of date) of arrival |', vector. Defines
C._I.: Earth departure e,ergy Ikm-./s2); _me as the lowest possible flyby/orbiter equatorial inclinationsquare of de, ,s,lure hy'perl,olic excess velocity (dee).[.2_,= (.3L = |.2 _ 2 pe./Rl, where
RAP o.._. planetocentric right ascension (vs meani_ =-..onic injection velocity (kin/s). planet equator and equinox of date, i.e., RAP is
measured m :he planet equa*.orplane from ascend-R! = R_ + h! , injection radius (kml, sum of in.',node of the planet's mean orbit plane on the
surface radius RspL,t.x./.r and injection planeta_" equator, both of date) Can be usedaltitude hI, where Rs_._krH refers to together with VIIP and DAP to compute anEarth's surface radius. (For value, see initial tlyby trajectory state, bu: reqt'tresB-planeSection V on constants.) aim point informal;on, e.g., B and 0 (dee).
PF = gravitational constant times mass of ,he ZAPS Angle between arrival [', vector and the arrivallaunch body (for values, referto Section V planet-to-Sun vector. Equivalent to planet.probe.on constants) Sun angle at tar encounter: for subsolar impact
C3L must be equal to or exceeded by the launch would be equal t, I,_O dee. ('an be used withvehicle capabilities. ETSP, VIII), DAP, and 0 to determine solar phase
I)LA: fi-n "geocentric declination Ivs mean l'artlnequattJr angle at pertapse,entry, etc. (deg)
of iqSO.O) of the departure V vector. May ira- ZAPF Angle between arrival t', vector and the planet-to- 'pose launch cons, taints (dee). Earth vector. Equiv',dent to planet-probe.Earth
RLA: a./., geocentric right ascension Iv,, mean l'.'arth angie at far encounterldeg).
equator and equinox of lt|50.O) of the departure ETSP Angle in arrival B.plane, measured from T.axis',I-" vector. Can be used with C31. and DLA to cha:kwise tO projection of Sun-to-planet vector.compute a heli_:entri¢ mittal state t'.r tralectory l:quivalent to s_daroccultation regton centerlineattalysts I deg) dtfectton m B-plane Ideg).
ZALS: Angle between depature I'. vector and Sun-Earth ETEP Angle m arrival B-plane. measured t'r,m T-axis .vector, l-qutvalent to Earth-probe.Sun attgleseveral ch_:kwtse, t,) projection of i-arth-to-pl_et vector.daysout (deg). l.qutvalent to l-at,It t_cultatloq legion centerline
C. OMInition of Arrival Vlrlalalu direction in La-plane(deg).
_,lip i ,._. plarletocetttrh; ,,ritual h_ pc, bolt,, ex,.e_x "EISi',.-.dETI-.Pplut__re b,tsedon r a,t,.deemed, bckqttptralleltoveloc:t) or l'-mfinit) Ikm s). the magmtude of the ecliptic plane(g- text tot ¢_,pLtn.trtohl
• .,am*jP-.-_ •
1983010504-041
f.
OWIQINALPA(3EmOF POOR QUALITY
V. Table of Constants ....... _-;_.,_.............._|11 |;,L'(" thhlI
('Ol,.,|-'llll', tl._t'd |O I_,t'Vl_'l,lt(" the Ilt|,Hlll.llltlll I_lt',_Clll¢'d ;It{' (;M. R;Idn|l._. Radius. t') Petb)d.
SIIIlllll:lll/¢'d In lhls _'l'llOII, .1'.!_,I"|'''_ hill L::; _.i,_.,,
A. Sun Jllpltrl I?bt'lHb467 :1.1'_,_II 11,41i._._11(*el, Rnnl_s
t;.tl I ;" .'l : .I.;'J '}.;_ kin "1s"_,, ._;4 I_4:(1 421571 I 'hL}I .IX2
/(',_I"/,'I It "I (_*}(_t'lOl) kltl I nlop.1 .;lql, I._._l b7Llq81l, I 5_1 1141_)I;ant n11rde I)148_ ._(,1124 1070.1.114 7 15455.10
e. Ellrlh/Moon Syslem L-.llll,lU ....................Vl ": 244_ iHl_?S7_}. 1668qlllt4o
(;'IIA- 1,4.17'If .It|.| %(| | _% I kill ] $'_ lel L'ontpllled fvom perked and lupllr! (;.If. io,ndcJ• ' I*'Pl | el ._)'_|(Dlll III .Ill|lilt41 Iot;lllOll 1.1|¢
(;'Ill 81,"rH ._}._hO0..l.l._II." 1 kill -s .,;:I)irecli_m of the Joyi,'llt pl,lltel;lr.v equatorial norlh pole
.I, LI.IXIILI,_;(,.; (in I:arlh Mean l_q_,latOl_d"l_)._l).O¢oordin'lt_._):
/_',_r'l_ a,"; I,.|'._ I.lll kin'_v -- (_4"S(%10_)"deg
C. Jupiter System D. Sources
c;,If,_.l,_r_._ I:(: "1 : (A_; '.;4 knl_ ._:The constants repte_nl tile I)!:.-I 18 planetar.v ephemeris
.I, _ O.OI.I_,;,_I_IN (!_1) and tile Vo.v_er-2 Jupiter encollnter trajectury"._ "t'n't _," tecottslrucliOll da!a (1_7_)).
1983010504-042
Acknowledgments
|'lie contributions, review,,, and _uggcqiun,, b_ n.cmut, J_ u_ u,..l.,.iuo,,,,,, A,,,,,,v,,Committee, especially those of K. T. Nook. P. A. Penzo, W. I. McLaughlin. W. A. Bull-
man. R. A. Wallace. D. F. Bender, D. V. Bymes. U A. D'Amario, T. H. Sweetset, and
: R.E. DieM. as well as the computational and ph)tting _gorithm d_velopment effort byR.S. Schlaifer are acknowledged and greatly appreciated. The authors would like tothank Mary Fran Buehier and Paulette Cali for their editorial contribution.
References
I. Sergeyevsky, A.B., "'Mission Design Data lbr Venus. Mars. and Jupiter Through19qO,'" Technical Menlora:_dut_.r 33-736. Vols. I, II. III. Jet Prupuision Laboratoo,.'.
Pasadena. Calif., ,Sept. I. !q75.
2. Clarke. V. C., Jr.. Bolhnan. W. E.. Feitis. P, tl.. Rotb, It. Y., "'Design Pat:-'meters for
Ballistic Interplanetary Trajectories. Part 11: One-way Transfers to Mercury andJupiter." Tedmicai Ret_ort 32-77. Jet Propulsion Laboratory. Pasadena. Calif.. Jan.IO60.
3. Snyder. G.C.. Paulson. B.L., "'Planetary Geometry |landbta_ t .'" JPL Pubht'atio.i
,¢2-4-', (in p:eparatiot)L
4. Ross, S.. Planetary Flieht ltandbook, .V..IS4 SP-35. Voi. III. Parts I. 5. ae.C 7. Aug.i t)63 - Jan. It,%t).
5. Wilsol'. S. W.. "'A Pseudostat¢ Theory for the .gpproxilnation t_l"three-Body Trajec-
tories," AIAA Paper 70-I0(_1. preseuted at the AIAA Astrt,:ly:,amtcs Conference.
,_illl-'l Barbara. Calif.. Aug. I t}70.
h. Bymes. D. V.. "'Applicatitm of the P._udostate theory to the "l'hr_e-Body Lambert
Problem." AAS Paper 7_)-It_3. presemed at the AAS'AIAA Astrodynanucs Confer-elite. Provincetown. Mass.. June Iq7q.
7. Clarke. V. C,. Jr., "'Desig'l of Lunar attd Interplanetary Ascent Trajectories," Tech-
nical Repctrt 32-30. Jet Propulsit)n Laboratory. Pasadena. Calif.. March 15. l t)(12.
8. Kohlhase, ('. i-.. Bolhnan. W. |-., "'Trajech_ry Selection Considerations for VoyagerMiss|oils to Mats Dttrillg the It)71-1o77 Tmle Period." JPL hlternal Docunletlt
I.IPD=2sl. Jet P opulsion Laboratory. Pasadena. Calif., _'pt. IO05.
q. Anotlytnttus, "'Assesstnent of I)la,etat._ Mis.,,iotl Performance as Launched _[otll a
: Space Opeuitions ('eilttr.'" Presented by Science Applications, I,e. to NASA Ilead-
quarters. Feb. I. ION2.
It).Beerer. J. G.. "'Orbnt ('hange Requinemeuts attd Evaluatnou,'" JPL Internal Document725-74. Jet Ihopulsttm Labor:ltoty. P:lsadena. Calif.. Match tl IO82.
34
21
1983010504-043
Mission Design DataContour Plots
Earth to Jupiter BallisticMission Opportunities 1985- 2005
3b
1983010504-044
Earth to Jupiter
1985
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 84.288 I 85/04/17 87/03/23
C3L 83.500 II 85/05/15 89/02/10
VHP 6.0059 I 85/05/03 87/10/09
VHP 6.0550 II 85/03/31 87/10/16
31
a J
1983010504-045
1
C3L om._ PAQ,-",
1985EARTH - ,.]UPITER 1985 , C3L , TFL
* BALLIS "r[C TRANSFERTRAJECTORY
!_ !/r / f] .
•11 •4"/900.5
i 1,_',_-
M
2,
1983010504-046
m
1983010504-047
87/0t/05 46800.5
86 / 09 / E7 46"/00.5
410
1983010504-048
41
42
i
1983010504-050
1983010504-051
44
1983010504-052
1
1983010504-053
41
1983010504-054
47
1983010504-055
411
1983010504-056
Earth to Jupiter
1986
Opportunity
ENERGYMINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 84.154 I 86/05/26 88/06,'ft7
C3L 80.658 II 86/06/11 89109126
IVHP I 5.8436 I 86/06/07 88/11/19
|
VHP I 5.9105 II 86/05/12 88/11/30I
411
1983010504-057
So
C3L =oFeooR_Jw
1986F-FIRTH - JUPT TFR 1986 , C3L , TFL
N BALL IST !C TRANSFER TRAJECTORY
"""'0' H - ",'- "'="'"_'" H --. -TT'7 V.;_7 -_ '0" .,8,oo._o,,o_,,_ i "- il 1"/ ,/,_,/,// / ,o.
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i IVI/l/7 i l i / i
! ,,"/1 XA,,A//" AI_
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{'%1_o_,_,2_ /,I I, ,/I, i ,_ ."lP'._ I I i ,, -" 180. - 47700.5 I
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.,,,,,o_ / I //i/III I 4i_._"/I _ i/V A/ '/ ,_/ ,'_._l/ t//! l_'_._i".,,_. I A _ A/Y/_ /,/=,o,,,_ i / _/ / ......_.,=_l_x'_'l/LL/I//// .,,,oo._
8BIO_Ii9 I t l ,- "_.- //-/ L,,," I /I ]r 7-/-r_ _- -47_.5__..=_iil _'_dliiElY__/i 1 / ! 11 # l .4 l
-,-,- /_._- I, ".'/I/!
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1983010504-058
61
p-' -......... ...................... , ,- i - _ .... _ ' _lllhlakUl=mll._m_ ......... .....-,, ........................ t
1983010504-059
ti2
k
/ o
1983010504-060
; ORIGINALrAGEI= 4.oFpoorou4_ ZALS
1986EARTH - JUPITER 1986 , C3k , ZALS* BALL IST IC TF_AN.SFEI_ TI_AJEC.TODY
91109101 •48=J00.5
87/11/0l 47100.5
13
"_'_ ..................... I I ............... i imlllll- - i • ......
1983010504-061
5, ORi_ztG_l..IrAUE i_lVHP o_-PooRQua.
1986EARTH - JUPITER 1986 , C6L , VHP
• BALI i T i - T_.'AN:.FEF--, TI.;AJEC. T,'31;Y
66 66666 6
. 48500 5
, . i ] ; . , I I i, I / i I.'., / ,/, //'J,'/" /
k--- e-- _--- _ -'---_..... _-- ' " I / 90., I T-T 1 , . /1 , ', ' 4 _-_--- tl LI. _.-[, , -" _ _ _ ,8_o._
--_-._T-T,,_--r--r--r- _ i "i." / _/t/, "" / /9011|I05 ....4---+--}---_---_......_ i i " -, #'7 " I -48_0._
_ ' ' I 1 i ' -/_/ //' "" /" " " J--,-_-+-JP-I ! _ , I ,..,:-.-,,.-,/,, / I/ '' ' i I l , i I I 1_ "/ ,'.. X/ / / / " /_ -48100.5
q0o07o28 --_.--_-. I _............ :- ,: ,. , - / r " / l #,,.,, T-T--FT.>_..,t., _,:./, -¢ IL-_i I •• , !- ,T-T-q-Vr l J. [.....I,J ,t" , .__hl//_ _ .,,_ooo.
_,,o,,,,_T T-_[LT_-I-Fi_!,"I,._,:K,I..'HI; ,./_.,._/,_.,"___Lr ,,o.,o,o,,__ ,-T x iI T I_ 1,_.,,x ,f X.,k: _, _1/.//;/, ,,o. 8
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...._ _.__--1l_,1/_L,.._T_..Z!__J_.,_Ff__._._I__I_L.L/(/(/,,o. ,woo.,..,5>- -___i_-__/fb%.;__A _ __,.._!,.;_Dmmi_,+!,__oo.=_ o _ -- .... V ,_oo_
0,,,,,,o,....T-T-]-/Tv'IAM,"tl.fJZ!k"_'-'</ai_../C_P'i_V..._../Y/,:.J.., =
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8"n_,oi --_----1 ,6Z.lkkl\,,1,,.,.T.q_q-q /i ,.I/V/ _ _ ll.
• _ l + .............. , _ 47000 587_ov_24 , t . , _ -I" _"._m_,----':l___ ;/- -" !' ' / 9=--'I_ I I I _ . j t- -_ + -,1- --i - "1"" _,,_lll__,_liml_'_ 7
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- _ _ - .0 0 0 0 0 0 0 0 0
LAUNCH DATE
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LAUNCH _D-2400000,0
N
.... i ,i ...... iii llill - . . i II I , ,d,.' /ml .......... "m ,_lii.U" ........................ ..................... --......
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1983010504-062
U
r,
1983010504-063
M
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............ • ,.,r ., .. . , ....
1983010504-064
ORIGINALPAGE _ 8.OF POOR QUALITY ZAPS
1986EARIH - 3UPITER 1986 , C3L , ZAPS• _,ALL[J'i: Tr-Pr,:rEr- ..';_AjE,]TO_-<
6_ d66c1 6 6
9ll_lOl .... __..-, .... .--- _; 48500.5, ' I , I I I
......--:--, ; i _-_-¢--V-4-.-r-r .- -:- !/:.-. / l.- t--_, ' i ! l i _/ I I i I ; j i ,".¢' b'///., X l ,
,,,o_,, , _[1 i t , i! i./l,'H.,/, /! _,o.--- è�p�-..---_---- ' i _ t 'f t t _ - , 7 / / " 1 _ 48400.5
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9,,o2,1s ' i ; 1, ! i i ! I l l.l _,,f Y/I/Y/..4 .-d,sJ/i ....... ' , -- t I I 1 I ; lr • /! - 48300.5
. , l 1 , _ ..... _--L _ _ _ LL_i I L_[_IvF !/./,s,'_'/I/ I_--_ .... --_'_"- ......... "1 " . :- -, /- - : ;-" :, A "48200.5: i I I I I I I . /, ."b'.4." L/ L/ .fi l /I M- t , I i 1 ! " /I "//" , / "
9010"/128 --I'---'_ _ "t t t , , , .- .... -..... .A" V _ I ._o,_ i,t "48100.5i I I I --I ylf wx/y./_., ,1 ,/- .LJ.LL_I; " i , ' , - . .- ..../', i. - < 'ii, i, Ill! L.'Vl.,;k/1.J,I"I/'I/×'-II/ZI._ll .,oooo.s
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LRUNCH DRTE
L_UNCH JD-2_O0000.O
1983010504-065
SO
ii
1983010504-066
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1983010504-067
I10
............. _ •, "ll
._ .. _r,mmm_..=.l-..
1983010504-068
c_=_ _'PJ-I _
Earth to Jupiter
1987
Opportunity
ENERGY MINIMA
OEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
I
C3L I /'9.191 I 87/07/05 90/01/22
C3L 79.818 II 87/07/G3 90/02/22
VHP 5.6228 I 87/07/03 90/01/19
VHP 5.6319 II 87/06/30 90/02/01
|1
1983010504-069
9210612"1 48800.5
F41L
D
1983010504-070
• .......... ,_ ...... . I II ........ , r , .............
Ilmm_ ........ .........i
1983010504-071
_4
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1983010504-072
m
ORIGINAL PI:t;'j_. "".• ZALSOF POORqu_,._
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1987EARTH - JUP ; TER 1987 . L'3L , Z,qL.<3., _,,_,,z.t1_,,,',,,_,,_, _,_!_.,,_,',.....
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1983010504-073
II
1983010504-074
17
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1983010504-075
7. ORIGn_-PAO!IIRAP o,:_ _rn'.
1987EARTH - JUPITER 1987 , C3L , RAP* BALL IST IC TI_ANSFE_ TI_AJECTOI_Y
..... ddd oo_go0 _ _
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! i ! I I ' /r/ ,r/;/., /r/.i i i I J L // ill/l/ /_,i I' L I ! =,, .',r ///,/,/ /,,;__
91112110 • i . , i "_ " ' " / ....... -4_00.5n ' , _ i , , ,,// 4,A/J/yI / i /,_'o ,_o._.4__._._x___l__,l , ,,, . ,,. ,, _ ., I<.';,'"o. -
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= ! i A./P :/(?..__l!#4.111-_l;ZJ/V_!/.' IV/ .'/ .,_ooo._
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1983010504-076
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1983010504-080
ORIGINALPAGE ISOF POOR QUALrI_.
Earth to Jupiter
1988 i
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 83.916 I 88/08/05 90/09/2_
C3L 90.018 II 88/08/17 92/02/21
VHP 5.5288 I 88/08/22 91/03/23
VHP 5._363 II 88/07/28 91/04/03
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1983010504-081
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1983010504-091
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1983010504-092
ORIQINAL PAGE
OFPoor QUALr_
Earth to Jupiter
1989
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 89.199 I 89/09/09 91/09/29
C3L 88.569 II 89/10/19 94/07/30
VHP 5.4544 I 89/09/28 92/06/03i
VHP ::).4197 II 89/08/28 I 92/06/15...| i
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1983010504-093
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.... l, Jr-.l-4 ........ :.+:1,-.-..-,.-, '?-_-]"={_F t......... r,r.r ,9310810t) I I _ /" l ' , : " • :,_---_-_......_ _--1.-.4-1T_-_4:.._-_-..:.._,,:
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,., • . , , ;. ,/_.L_..,a,-.-__;.,". , _, i,,ooo.5o" _l | -_ .... _ "t" _',.... . 1......1 _ , : .
_e2, lo,o_ ', ! i .,-1-,:J - ...L_.] .d __..LL_L.__i.. t_!I_ I A ....... W._'--._> .-._.Z-_. _'L .l-_hl.,,,-.t,,,,., ," • ' I/ ' t'i
<< --_ 7!::i-F-id-i.-_-Kt-VX,+'_':,l_.i.-7,;o_,o.,,_o-r_-tI_iL.X,-;illl---l-_;_'..;_F-i-,_-,__It_iI.".;'4_ I'_'oo._:._i_..:_-7_-7-..l__._J..=d,,;_L.._l-r_i lr zi7i'/1;--i., ;'- I. _ ,, /• I ' .'. I0. ,
,,,,_,,o.,_'++_I_--.TT-C:_'.zJ_-t--;..4,<-tt-F-4!-4.-._--;,_--t_---,, [,,,,,oo.__l_.l_ , III <-'f.Al_l I , _ _'iJ I 1 IS. u ..#... ; ) .j_. ," t ill(1.:
•__-:.Vl,rtI_._'_.-.r_r;-r.t)_,>[,'..... . _/,x._/F_II./LT...I..L,.. ...i ; [,_oo._o,,oo.o,_,:r___.-.r-..l-.f:l/h,,.,, .__,,,o__,__. . #,tX..7--FrL..T.:.._:'. [,,,,oo.,,,,o,,,,...,..-."_'-_'-.:_'i._:,_,_,_-,.__._._"L__'"._b:_!-,i-"i-r-.'v-_.t_"_"__.!,_.,,_:__-_,,.' .' [,,,oo.,, . , ', _ ._ -.-_.. ,. ]- : , , .qlOI | 1105 48200._
qO/0"/#28 _ ' _ _ •48100 ._
O 0 _ O
I I_ IO
LAUNCH DATEi •
47720.5 477b0.5 47860.5 47840.5LAUNCH JD-2400000.0
N
1983010504-101
i
: ZAPE _ e_E,.__1: (_ plxll Qul_nrY
1989 EARTH - <JUPITER 1989 , C3L , ZRPE• i_,_lt_i-.lI,- I_HN:FEP T_'AjE,TT,._;'Y
-- e _I_ aD e --
9d112114 " T- T F 110. 49?00.5i ' (
;iilll I , ,'A/,",'//.4_1_. .,_oo_9410910_ .............. .-d .... " ,;, / .... .
- t_4, li '" "_' , ' I ! , ' / J //< ""1"/ '1 /,'_ ,"'1>,
94m_#28 ,_........ : -,, --+j...... ) ....._ . ., I i j- /- ;i /_ ;/ ./i_/_ , -49500.5
_ ]_ / /!/ / / / // Ii /]/ # I -: ., ' ," "11/1 i:,' , . ,_o.9410t11' i ...................... " / .... -",! 15o. .49400.5
"'" " "-"" °" ,4<L,i_ .4_._•,,0,,o,_ ,,.........., ...... ... ._i 11 I IVi[! ! // ._, _.,i.,;_'.#. ,I/ /
- _ il _ i ;,._-. -- aoo. o, y.A_,,i i / . .._._._ ..",",_ ! .,_,oo._'.' -_1, i !/ ,.,#" ./ I I/ F oF93#01# 13 . ,49000.5 o
I _-. ,._,-_.;_) tll / o
i]/_..,,I,/_'_,,'_i'iili)._I..'_7.J,'_ !! /!_U_ / '"__"___/}/_W_J/!II4AJ1...._I,_'t>'r l ! Jl,'l_-.7:_'_. .,,_oo._l9_1031 t9
-_-T-717"i b'.aL_.!.{..L'-'__.'.'"-_ _ l /IM/ ! I Il/I/_ I l_r-_--_l; ',,_"L__L_IiL_411/ Y c
I9llI2#lO __...i.-_'--;-r m n i r. _/z "_--'---_.,;.#.._1 [ Ill I F ill i i_ | '48600.5
u II I III II I /..7t l l_:_y/ I/-il i I I ([ ! I ,I I J I
1.2 I i . . .. , I i _)0. : 48500.5o,,.,o, ......91105124 _ _ ' 18-0 " / f ,_....l_l "._. --i-
.._.___.._.I._I___--__-_'_-+-__'-:. v, . ."-ii_l-__z_ ___- L].,"• ____:,. .,_._eo,_i,o_ _ -! : -T -l::'P-_:_,-J_ _r._L_i_L ....
_ __.._..__l___..k___.i___..--m-"_:_---_-_-_i_,--_r ._7.L_ ......... i !: ) ) ! I I I _ '_"-F"___,":" i , "90107128 , l , ! , l / I l _ l l I I I i '48|00.5
- _ o - _ o _ _ = _ _ -..... _ _ ...._o _ _ _, o_ _o o o... _.. o... --
LRUNCH D_TE
47720.5 47760.5 478 O, 5 47840.5LI:IUNCHJD-2400000.0
N
. °
1983010504-102
J
lie
=.
1983010504-103
N
|
1983010504-104
ORIGIPtALr,_---,+
OF POOR gUAL;-,_;
Earth to Jupiter
1990
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 91.572 I 90/10/12 92/11/03
C3L 84.731 II 90/11/11 95/04/16• i ,i
VHP 5.4517 I 90/10/30 93/07/30
VHP 5.4325 II 90/09/28 93/08/11
In
I
1983010504-105
92103119 " 40700 ._
9to 12otO 14_"
i
I
9t 10910| [ 48fJO0. _
LI_WJNCHORTE
,._NCHJO-_,O0000.O
lie
i A
1983010504-106
_l
1983010504-107
1oo
l_F_R_ln._n__ln_
101
1983010504-109
Q
onllu¢ P/IoF Quuw DAP
1990ERRTH - JUPT TER _990 C3L , oiqP'_ f.",_t I. [ :..T[, Ti-.*4.4:.FF"_ T_;_,jt , T,'IPY
...... ._ _ ¢'_ ,r' _ -0 0 OOO0 C .......... 0
...... T', " r . 1. • 1 ,t". . _ ,_ . ,96101118 ' , : I , , ] t - -T .......... --r-, .... -..... 71 '50100.5
" --. ."" " I/ // / I_,0.
95103124 , ' . + + ,........•---t--_7_-_.,r--7'_/lyF,ll,.#rli,#/#FI._JR'.)_I.'.-_ _'ii,,.o.-49800.5, i I i , •-t f. t !--- ��D�h�1..... ¢Jf _'t._-t" -/Iy/ I; /1 ,_1/;_.'7_/_V /_/"r_ __/'_/_'_ il _ _ f!11,7"_'71'/711Zl: .,]
, , : , i._" _ _---------'",'"'.__'_I/__'_LI.,'_,/"" " " --,._/11"
94112114 ,, , ' .' .... It4". _ 49_00 B _
• , %. '...,,, ,4 - . ,-q:/I-_Z_71--/F ,_TD_fl l/rJ_,
,,,,o,,,o_ Tit _T/I ___--_..:.¢]7"/_'/_,i/I "°'' .,_,6oo.5..... -- _ __V-_'_ l.:.'_lN/l/h l/Vq' ' .,,_oo_o
" " V-F,.Z,,:'/XY/]z ' _ -..... ) i ,,_e'_.__e
iit].4.I
92_10_05 48900.5
'; ';" ___t'/'' it'''
o_,,_,_o _-_"! i-_,,_ ' _ . : • • .8600.5........ __.-t : __,.. ;. i,...• ' _"', ' I
9ti09/01 : : ' ! : ; : ; : ; : ; -" ; : ; : ; : ; : ; : _ " 48_00. -%
r'- P ,O ,o ,O ,O ,O ,0 ,p _n _ ,n
0 0 O 0 O _ _ _ _ _ _ _
LAUNCH DATEr t t
4812,0.5 48160.5 48200.5 48240.5L_UNCH JD-2400000.0
1@3
1983010504-111
1
RAP om=._PAGEIllOERX)RqNJJcrl_
1990EARTH - JUPITER 1990 , C3L , RAP
BALLISTIC T_ANSFEI_ TI_AJECI0_Y
,0 ir'i M il_(_'_D I-- I-- _:ii%li'i 0ell -- O'ooi' io _i iIO'o'
96'°"'8] I I I I i I 1 1 I ,t//I"A/,._,{/I/,_,'/[/ /////l'/ 501oo.5_L ,_,%'VXi i2,,"/ "/'_/?_' 500oo.5
95110110 i /IiI f" /Vll FI lh#I/Ixl "_ II 140.
,_,o'-o2 t ' 1 I "L "F/1/ _ K/ '// // _ / // /_;/'/_r '/ "° 49900.5_,, / v/v/_///A///'/ 1//j,_/d" _'/"/, 1_o.
* - _ / / ///_,/ i-_ ._//_..___./ 49800.5l I i . ,"1 I,'rv//,,.,,,,, ;, ,: _!_'-"_..r .1oo.9,,,2,,_! 1 1 I/i,,/_//1/, _;, / ,_o..49700.5
9.,o_,o_ I _L_/I/L,'?b;_,__@iT/li_.N _', Z. .49_00.5I_' " " ...... "_ _L.1 1 1 "_'_/._1///// i , v,'/v/I/]///A_m.::_ .7- ?_-e_ o
_9,,o_,,-,11 _L_/ i II1%,'/ /_lli _-_7_""_ I1' I/ .4_400.50o | J ) ,! ! Iv ll, ll I I _1( "_..:!,",_.. III _1,/1 ,,
' '/ /1/,,/Y I/I/I(_._ZNX .I.;#,x..X '_'/////I .4_oo.5,_93_li_mt I/ " ' plm--', " ' _..... ,41 :> I.,_llllll_.l..__u_,it,lillili,.. vi '-'- LL v_'lltti!llti'.'.'19_,o_,o_ .ill. _/'/ /I7_. _ s 49_oo.5"
9_,o,,_L_Z../-dl"M/ { _,_t. i__-__'_ii//// ' .-• ' 49100.5 ii
_t _;' I _"'{_k_'_'-'/!_!/I-o_. _ t 49000.5921 I0/0_
_ 489001_
--_'-.i _._-, ,,_.x,,-._.' ii/DL/_ .48800.5_. • T"-.---.r" | l :.' l/A,,., ,_II, tt_,,_i _ ) ]
" I i I--:_--] ! "_\'_ -"" "/,'/Y ,: ll:::'°"'= _._--p-- .48700.5
°+'°""-i_"--_+,,,+,,o--:-t_:..._!."T-,_+_i-.___r-___, =__/----"-___.___(1! I 'i91109101 : i I : l " -48500 5
0 0 0 0 0 _ --* -_ _ _ _ ,_ ,,-i
LAUNCH DATEI--'-- i • _
48120.5 48160.5 48200.5 48240.5LAUNCH ,.1'D-2400000.0
1983010504-112
,__.= 8.__ ZAPS
1990EARTH - JUPITER 1900 , C3L , ZAPS
BALLISTIC T_ANSFER TRAJECTORY
6 6 6666 6 ._..._. _. ._.6
"'°"" i !i I 1 1 I "t×;_//'//,'<""i 1.4///,"/ _o_oo.,, .,_ IX, ," / _
I l [ ! I I /,I,'/,'//I'//A'5" ,?_Y/Z.'-" 5000o.5
.: I 1 1 ' ////9///_,:'_'///' /,_:_ ,,,o.
95110110
" ,_///// /9 /"_" ,,o. 49_o.__,o-,,o_ l ' _ '//1 /A '_;9,,o3,a, i //'/I "//;/_" ,,o.
i _ ,," _ T." 160.
941ta_t,I --i-,,'---i---4---h-- x _ // " _eo. 49"#00.5, i i_ ,._; &'/, /I_i//il ,/.X_ I #i_ ii/ i" . . _ v_,,__#___ +_'97;,7_i,_oo.,,,,o_,_-_-t- ,--_]-_,_/_ ,/ _:..;_. - ,=9600.- :-;-4-,--_ _ _/ v _'/ / / / I /,Y/ _'. 11/A1/
__L___ ,I h//,"///_1 .._?_ _ I h V v o94#05/28 i , ' ! .,'I/]/A:, ;. 49500.5
_- 94102/1"/ .' , ... " " t' /I 49400.5 O0
- - 49300. ,5 I_>_d:"_' " '°<' _ 7A/ , _ -_ i ">_,_,o,,o,i _--/ _ I _"" ,',. , l i ,o. ,,_oo.__. _ I IV t_./. .#' I 1, I, ><,,o,,_._LIALAd-tl--FII _'.-'._;_.'_ I iiil i -c® "_..... 49100.5 n-
_r. _ /1 li l t .. _B. •"":"" ! !, I/ ! I ,_,o,_,o,,,_ _'+-,__e.., _.________. ._."'_iI 1 l!ll I ..... 1 - _9ooo.__U_.' _4L-t-tI .S,., " .._ ¢..' " 111,1_11i i ; / - __l. I
_]L,! _.Lk_!,>_.:=.'h'/ .ll'il¢y /il'/I_,,,.I !!i_,o_,_ "--3--._=T__.-i_'"_;_"<_--"..___-_:_+___._.,_.'., i" ti,ii,I it i...l ! i _eeoo._
._ .....,_.'.tif_%i'.3_-k----- j,...i,'iV ,I _ I '_._ [
.............-"_- >_-;__-_,--'-!.....,oooo._', 91112110 ....
I ------il l-T'! : ' ':91#09#01 "48500.5
r- e- ,o ,o ,o ,o ,o ,o ,o _o ,o to r,
O O O O O _ _ _ -, ,". .'-. -.-.
LAUNCH DATE
481 0.5 48160.5 48200.5 48240.5El:lUNCH ,JD-2400000.0
i
I
1983010504-113
95/03124 • 49800.5
941121 |4 "49"700.5
94 I09105 •49600.5
094/05/28 -49500.5 -
00
uJ 0
94/02/17 49400.5 000 _t
I93/t 1/09 , 49300.5 Oq.> i i-_
93/08/0t 49200.5 _J
93104/23 49100.5 _
i
93/01 / 13 49000.5ii
---,I
921 i0105 L--_ 48900.5
f,o- wii I
92/06/27 - 4 .... ' 48800.5I
/
+ -.1.--J....... . - -,II
92103119 48"/00.5
lOIS
|
1983010504-114
107
1983010504-115
91 e l_.e tO '48600.5
911_101 48500.5
:_8 i 8-_._.__- _LAUNCH DATE
48120.5 48z60.5 _8a00.5 48_40.5L_UNCH JD-_400OO0,O
' 1983010504-116
OIII_AL P_ SC)[:pOOR QUAUTY
Earth to Jupiter
1991
Opportunity
SNERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 89.738 I 91/11/12 93/12/30
C3L 80.682 II 91/11/30 95/10/16
VHP 5.5057 I 91/11/28 94/09/06
VHP 5.5068 II 91/10/30 94/09/16
1N
l
1983010504-117
I. amajeLPJ IoC3L oF_ Qu_
1991 EARTH- dUP[TER 1991 , C3L , TC-L, BALLISTIC TRANSFER TRAJECTORY
......... _ In0
9"7/02/2! "50500.5
96111113 • 50400.5
96108705 • _0300.5
96101! 18 50100.5
951101I0 -- 50000.5
09510"1102 49900.5 0
0L_ 0
95103124 49800.5 0O
I,_.J94/12114 49'/00.5 Q
_ 941o9105 49600.5 (£-I8.==e
fy94105/28 ' 49500.5 n,
(Z
941021 I"/ - 49400.5
93111109 - 49300.5
93108101 ,49200.5
93104123 "49100.5
93101113 .49000.5
92_10105 •48900.5
o o - = R R =
LAUNCH DATEI / -- - - • " v
48515.5 48555.5 48595.5 48635.5LAUNCH JO-2400000.O
110
l
1983010504-118
111
m
1983010504-119
113
1983010504-120
11_1
4
1983010504-121
Illl
1983010504-122
116
" 1983010504-123
7. oiiIG,IHAL PAGE liRAP oepooeOuA,.v
o,
1991 EnRTH- JUPITER 1991 , C3L , nnP
o <; ,,..,;,_ o - -". ': • •
vT#r_,2t 1 ' ; ' " T -- -r - r- r [, ._ , '50500.5
.,,,i__LL_t.L..} _f....i..)._L,,'VIII,4 ],.%]"°-) *- '*-- , f- -t" '," "" # : -- = "1 ....... • i ,r. .4' ,_, I f.,.' I, d'. )i'll[.:/Y//l), 0;,o.96104/L_7 _, , �-i $ .,L ...L_ ._._-.,+.,,-")e---4-. ,_...-_----*.-1.-----_---_--_--',._e i'" '*" 50200._
I I t ' ' I /I I' _ i I',O.
96101118 ..... ;_-' }' .;-f :--L'L-7-._'__.'7+t_--Trr---i'--_, __--l'.'l-SllLtllt'"' 50100,5• ," " v ,- , - . -" ,7,_.l.,.li " ' ' _=
.,,,o,,o......." " ' '_ _,._;_'.-..._._...v._,,.,+,:.+_,_1,____++_'-/-/:_.77"_',1',:"'°_'"_.;;:_+.a,.>._;..___.____.__.,.....__,.r.L_,___+'_,'X_', ,<_oo._°-_- i... _ . *' _ , 0
" ':,, 6l,: LA- k(4L<yJ,_it. °°,-_,o_._, . . + .X... IZ_ {;'_+._ _!-"@i._.... ,_)ooo._o
o ] -x +A/I_ i "- • " @ i ¢_
" T_.L___ _ ,_P,/£i/.__?__-i >1- " l _. _ " "" _ I. .7. --
_t_ ; -,1_.__._ L; ,B.!!_• Ii_[ !_ J. ,'!t_ l 'I. 7'.' _-i-7_/t_ 'l; # ,'_.0,,,,,_, , _ ,+ .: ".. ,,_._
b-:,t,,. .1 • . •
. i:_03_O0oOt ' " * ' " _ 1 .... _- _- tl *, ) • . . 49200.
o,,o,,,,..... _< ,e_.r " , • • • "=.'• "" -_ . • , • 49000._
93o01013 .... [ .
9gOtOoO_ , : ; : ; _ ; : _ -" i : . _ ; -" _ I _ 48go0._
_ ....... -@ o, @ o, a, o, _, @ @ @ @ @ @
LAUNCH DnTE
_ i_._ _o_._ _. _ _,,]_.LRUNCHJD-24_0000.0
11I
i
1983010504-124
117
1 |
1983010504-125
.... f................................ itl,. --.............J- •• i
_.r., -
9. ORiGiNALt'A¢_;ISZAPE o__oo.__
1991 EARTH- JUPITER 1991 , C3L , ZnPE
_.', ,.-, ,'., _."=..',,,.-', O , ", _ " -- _ _ =: "" "
.............. u_" dk,
_"°_'_' ....... i i " L' i";'-' "; _i: _,; '-' _o_oo._i , . 4 ,.= '
96111113 ......... . t.l_r_r.r I .,.4.,., .,..+,, i _o,oo_........ , : 4,-+.4-.*- _ i' 4" '_,_¢_+"; '96_08#05 • • , * _ ' _" ,e 50300.5
, . : . .
r _4' : , • ' " �-t "_"- - _. ,',aO.' + i_ -. - 50200. ,596/04/27 : " " : " t t t "t ° _ �=' . " _ ;':-"-""
96/01 / 18 -" : -50100.5• t." .... :.., . .-V ,,-1: _ ,"_o.
' ' : L f ! " -''' 4 '''2" ' " " " ''_' ":"- 50000.5_113110 .... 71_ .... "i " '-" ",'"_" , . _,'_'i_._^ ",/., .. _,"_ _ ' " t ,.,'¢,' ,'l,/ _s. _' X'i'-'. ' _'°<'..... +1 + *+ T . $ _ -- r+" if "1:4_1_ . _ ' = + 4 " _ : I --_ . " ' ' ' I . ' ,_ " "+ " " 4
; "mr i ¢ _ * I .',_ -'.#/_,_'-'l_"___.P °u" ll_._/-7 1/Q]_.L - ' O95,o7,oa , • , * ,_ +,-- - r. - --,,--, ,-,, • _'_# ' .49900.5, . _ , • . :r_. I_ ,17"-_:_'APF-, " -1:_ • , _ z / /,z n. .
95/03/24 _ .... -..-.i--,¢-#_#--.#f-.-+#Ef'l-#,4,Z--_='-';.:.._#4_---._'}-r-f_J-t-'J_"_"#-i .l.-. •49800.5 0a _ ., ;. __!_",'V l..,'(Ol_. 12#L'. il )//II/L_,'z +I o
' 1 -_- -- . " " '_-TI-_Z__'I ill]l/_ /iil i " "_#0,.I
......i i_94109105 y ! /I _ ![/ /Vl >
_, -'-,,-FT:,,'rTT-/"I t_ _;r I _ll_...-l'_l1 ! III 41,4! 7_Ito. ' -_,
• I_l;i'[ ,a ;:li\ , .'1i- / L_'I'-I-A/ i_/',liilll /1/' _49400._
..-__ :l li._k___._I./_ i..111;. L,]II _ /! /is sisal I/-D--!;_-_."__'-__',7#;.'Y Ig 7 i! i ]I Vl!l Ill ,I I, _._'_"
9J, tt,o9 _ _'_. ,il;7q/fl _P,,-ii7 1/' /(IFII / /! .... ' ' 19300.5- v V l. "L_.¢- " " . ,, I
.,,o.,o. ,;[
• -,---1 .le 9l
• • , 49100.5931041=?.3 * * ' *
: } 49000
93101113 , , , *"-- .5
92# 10#05 t. 48900.5
<, ,o _ ,o ,_ _o ,o _ ¢, e, _ .,, ,,,IM -- i'%l 0 _ 0 "" 0
0 0 -- _ _ _ "" "" _ _ _ 0 0
LAUNCH D_TE
485 15.5 4855_.5 485 5._ 48635.5LAUNCH JD-2400000.0
111
i 4'
1983010504-126
119
|
i
1983010504-127
I10
|
1983010504-128
ORIGINALPAGEIIOF POORQUALITY
Earth to Jupiter
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 83.478 I 92/12112 95104113
C3L 76,865 II 92112119 96/03/20
VHP 5.6007 I 92/12/21 95109/25r
VHP 5.6132 II 92/12103 95/10/04
121
1983010504-129
122
I
1983010504-130
,+
Ill3
1983010504-131
114
1983010504-132
1211
.... A
1983010504-133
5. o_L PAE IIVHP OFpoor_,_rn'.
1992/3ERRTH - JUPITER 1992/3 C3L , VHP* f_AL_i:.Ti: TF,'C_N-_PE_Ti.,':::IjE,[T0i_'Y
6 6 6 6 "].
,)a_o30aa. "- T T- ! -t- r r--t- I I T ....T--I--T_T-_F'-T.-T717-T ' _oo .50900.S
' ' ' ' ' t ' ! ' - 32 1 ' '" ':b- _'--,-t--4" .... *-- --+ .... f ....... .: p_,,,_,,8.,- i '.T.;....._.... -__.__..... L-..._I,_. ,_o.---.--t ---t - if- f---i---t ........ t -- .... ,'-/p:-l/_/J/_/A_
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ORIGINALPAGE i$OF POOR QUALITY
Earth to Jupiter
1993/4
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALV_,;.UE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 75.558 I 94/01108 96/06/09
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1983010504-151
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1983010504-152
ORIG'I/V.',,L_.:,W r,i
Earth to Jupiter-- ii
1994/5
OpportunFty
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 78.594 I 95/02/09 97/03/17
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1983010504-157
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Earth to Jupiter
1996
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
I
C3L 82.080 I .('_103/16 98/02/29
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1983010504-165
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ORIGINALPAGE II 2.OF POOR QUALITY DLA
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9. ORIGINALPAGEISZAPE OF POORQUALITY
1996EARTH Jbr I Tr_r_ 1996
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ORIGINALPAGE iSOF POOR QUALITY
Earth to Jupiter
1997
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 84.420 I 97/04/22 99/03/29i i
C3L 83.161 II 97/05/19 2001/01/27
VHP 5.9837 I 97/05/08 99/10/12
VHP 6.0500 II 97/04/06 99/10/28
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1983010504-177
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Earth to Jupiter
1998
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 33.832 I 98/06/01 2000/06/25
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1999
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ENERGY MINIMA
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C3L 79.534 I 99/07/08 2001/12/10
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LAUNCH DATE
, . , . .... , . . .-_51310,5 513_0.5 51390.5 5 4 0,5LAUNCH JO-2400000.0
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1983010504-209
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ZAPE,,. _.e_,_ _sQUALITY/'_ OFPOOR
1999EARTH - JUPITER 1999 , C3L , ZFIPE* BALLISTIC TRANSFE_ TRAJECTOI_Y
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1983010504-210
00/06105 51700.5
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1983010504-211
11.ETEP o__ P_-__
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1999EARTH - JUPITER 1999 , C3L , ETEP* BALLISTIC TI_ANSFEI_ TI_AJECTOI_Y
04110122 I0o. "53300.5
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0410'//14 I_: - 53200.5
04104105 53100.5
01/0'7/tO ' 52100.5
Ii
1983010504-212
ORIGINALPAGEiSOF POORQUALITY
Earth to Jupiter
2000
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) YEAR/MONTH/DAY)
C3L 84.783 I 2000/08/10 2002/09/22
C3L 90.349 II 2000/08/26 2004/05/12
VHP 5.5036 I 2000/08/27 2003/04/04
VHP 5.4694 II 2000/08/01 2003/04/15
m
1983010504-213
lm
C3L o._=._-eA_ts_( OFpOORquAI.n'v
2OO0EARTH - JUPITER 2000 , C3L , TFL
, BALLISTIC TRANSFER TRAJECTORY
05/11/26 •53?00.5
o5/08/t8 53000.5
2N
k
1983010504-214
A
1983010504-215
11
RLA o.,_.ALpAot_( OFpOOROU_r_
2000ERRTH - JUPITER 2000 , C3L , RLF:I
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1983010504-216
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1983010504-218
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1983010504-219
III
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1983010504-220
8.
Oml_LI,,li iS ZAF$OF POORQUii.'TV
2000EARTH - JUP!TER 2000 , C3L , ZAPS* 7.-,, [TI TPAh-FEP I"F-.F_jE,'_T,_Y
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1983010504-221
214
1983010504-222
216
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1983010504-223
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1983010504-224
ORIGINALPAGE13OF POORQUALITY
Earth to Jupiter
2001
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 89.741 I 2001/09/14 2003/10/03
C3L 88.063 II 2001/10/23 2006/07/29
VHP 5.4502 I 2001110/03 2004/06/12
VHP 5.4169 II 2001/09/01 2004/06/24
217
,a
1983010504-225
tli
1.
C3L oRl=._PA_-__( oF pOOR_Cl_l.IT'f
2001E_RTH - JUPITER 2001 , C3L . TFL
_: BALL [ST IC TRANSFER TRAJECTORY ,n
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1983010504-226
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1983010504-227
1983010504-228
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1983010504-229
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1983010504-230
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1983010504-231
T_4
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1983010504-232
1
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2001EARTH - JUPITER 2001 , C3L , ZNPS* P.,-4L,.i_TI TP_t_:FET-, T_;4jE,:T,._r_''
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1983010504-235
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' 1983010504-236
OnmHALPA_ JSOF pOORQU_nY
Earth to Jupiter
2002
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 91.575 I 2002/10/16 2004/11/09
C3L 84.166 II 2002/11/13 2007/03/24
VHP 5.4559 I 2002/11/04 2005/08/06m
VHP 5.4395 II 2002/10/02 2005/08/17
2;m
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1983010504-237
I
C3L ow.Au.F,,,_:_..'OF POOR QUAUTY
2002E""-'"-' ' "' "-'" "'-'-" • C3L TFL_K,n - ou_l ,L_ 2002 ,
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1983010504-248
ORIGINALPAGE ISOF POOR QUALIfy
Earth to Jupiter
2003/4
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 89.129 I 2003/11/16 2006/01/10
C3L 80.127 II 2003/12/03 2007/09/19, IL
VHP 5.516R I 2003/12/01 2006/09/10b, ii i l l e
VHP 5.5202 II 2(J03111104 2006109/:_0
141
1983010504-249
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1983010504-250
04/10/22 53300.5
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1983010504-259
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1983010504-260
ORIGINAL PAGE IS, OF POOR QUALITY
Earth to Jupiter
2004/5
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 82.238 I 2004/12/17 2007/05/101
C3L 76.407 II 2004/12/21 2008/02/15
VHP 5.6158 I 2004/12/24 2007/09/27
VHP 5.6263 II 2004/12/08 2007/10/04
1
1983010504-261
1983010504-262
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1983010504-263
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1983010504-270
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1983010504-271
' 1983010504-272
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ORIGir,iAL P_'_ l_rOF POOR QUALITY
Earth to Jupiter
200516
Opportunity
ENERGY MINIMA
DEPARTURE ARRIVALVALUE TYPE (YEAR/MONTH/DAY) (YEAR/MONTH/DAY)
C3L 75.683 I 2006/01/12 2006/05/19
C3L 79.222 II 2006/01/12 2008/11/12t
VHP 5.8037 I 2006101125 2008109116
VHP 5.7668 II 2006/01/09 2008/09/25
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1983010504-273
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1983010504-281
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LAUNCH DATE
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1983010504-282
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LI:IUNCH DI:ITI:"
L_UNC_ao-a4oo0oo.o
NA.T_-JPt-Con_ L A IF.,IM
1983010504-284