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J ' ,p O DRAWER B
NUISTSVILLE ALABAMA _5_'_
TR-82-MSFC-34431-048
FINAL REPORT
ASCENT TRAJECTORY DISPERSION ANALYSIS
CONTRACT NO. NA88-34481
(NASA-CR-17CT_I) A_C_ " "BISPERSICN _NALYS[S Final F_;c[t {[yE_etic_,
Inc., Huntsville, Ala.l 2_£ _ FC _I]/_F A_ICSCT 72_
11117
gnclas
C]ECI
DECEMBER 1982
GEORGE C. MARSHALL SPACE FLIGHT CENTER
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
MARSHALL SPACE FLIGHT CENTER, ALABAMA
d
TR-82-MSFC-34431-048
ASCENT TRAJECTORY DISPERSION ANALYSIS
CONTRACT NO. NA88-34431
DECEMBER 1982
PREPAFIEO FOR:
GEOFI_IE C. MAR_4ALI. SPAC! FLIGHT CENTER
_ATIONAL AERONAUTIC_ ANID SPACE ADMINISTRATION
MARSHALL SPACE f=LIGHT CENTER, ALABAMA
TABLE OF CONTENTS
I. INTRODUCTION ................................................
2, MISSION I AND MISSION 3A NOMINAL TRAJECTORY REQUIREMENTS .....
3. DISPERSION PARAMETERS ........................................
4. COMPgSITE AND WIND RELATED TRAJECTORIES ......................
APPENDIX A
APPENDIX B
APPENDIX C
APPENDIX D
APPENDIX E
APPENDIX F
APPENDIX G
APPENDIX H
APPENDIX I
DISTRIBUTION
- MISSION I CRITERIA INPUT REQUIREMENTS ...........
- MISSION 3A CRITERIA INPUT REQUIREMENTS ..........
- DERIVATION OF ERRORS AND UNCERTAINTIES ..........
- COMPUTER PROGRAM FOR DISPERSION ANALYSIS ........
- COMPUTER FILE INPUT/OUTPUT REQUIREMENTS .........
- MISSION I DISPERSION ANALYSIS TABULAR DATA ......
- MISSION 3A DISPERSION ANALYSIS TABULAR DATA .....
- MISSION I COMPOSITE AND WINDDISPERSED TRAJECTORIES ..........................
- MISSION DA COMPOSITE AND WINGDISPERSED TRAJECTORIES ..........................
LIST ............................................
P_
i-I
2-I
3-I
4-1
A-1
B-I
C-1
D-I
E-I
F-I
G-I
H-I
I-i
D-i
,,qECED!NG PAGE BLANK NOT FILMED
iii
LIST OF ILLUSTRATIONS
A-I
B-]
Title Page
Winter Mean Wind ..................................... A-2
WTR Mean Wind B-2''4"'0°''''_''''_,,,,.., ..... .° ..... _,,.
Tab]e
3-I
3-2
3-3
3-4
4-i
A-I
A-2
A-3
B-I
B-2
B-3
B-4
D-!
LIST OF TABLES
Title
Propulsion Perturbations ............................. 3-2
Aero/Environment Perturbations ....................... 3-3
Mass Property Perturbations .......................... 3-4
GN&C Perturbations ................................... 3-5
Composite Parameters ................................. 4-2
MSFC 86-80 Motor Data - ETR Version (60oF) ........... A-7
Variation of OMS/RCS Performance for Pre-MECO
Abort (Single Engine Values) ......................... A-9
Mission Update Nominal Trajectory .................... A-IO
Flight Control i0 .................................... B-3
MSFC 86-80 Motor Data - WTR Version (52_F) ........... B-8
OMS and RCS Burn-Damp Sequencing for AOA (Pre-MECD) .. B-IG
Variation of OMS/RCS Performance for Pre-MECO
Abort (Single Engine Valuesl ......................... B-If
Interpretation of [VAR Variables ..................... E-3
IV
AHIAOAETETRFPLGN&CIMUMECOMPLMPSMRMSFCNASAOMSRCS
RPLRSS
RTSL5-OOFSOFI
SRB
SRM
SSMEWTR
LIST OF ABBREVIATIONS
aerodynamic heating indicatorabort-once-aroundexternal tank
Eastern Test Rangefull power level
guidance, navigation, and controlinertial measurement unitmain engine cutoffminimum power level
main propulsion systemmixture ratio
MarshalI Space Flight Center
National Aeronautics and Space Administrationorbit maneuver systemReaction Control Systemrated power level
root-sum squarereturn-to-launch-sitesix-degree-of-freedomspray-on fo_m insulationsolid rocket qoostersolid rocket motor
Space Shuttle main engineWestern Test Range
Units of Measure
dogo F
fpsftft/s
g'sinin 2
kftIbs
Ibs/ftIbs/sminms
nm
_/spsfpsiS
degreesdegrees Farenheitfeet per secondfeet
feet per second
acceleration per sea level gravityinches
inches squaredkilofeet
poundspounds per feetpounds per secondminutes
milliseconds
nautical miles
percent per second
pounds per square feet
pounds per square inchsecands
(Reverse Blank)V
1. INTRODUCTION
This final report documents the results of a Space
Transportation System ascent trajectory dispersion analysis performed by
Dynetics. Inc. under contract to the Marshall Space Flight Center
(MSFC) of the National Aeronautics and Space Administration (NASA). The
purpose of this dispersion analysis is to provide critical trajectory
parameter values useful for the definition of "lightweight" external
tank insulation requirements. The "lightweight" external tank is a
developmental subsystem of the Space Shuttle.
This analysis has been conducted using two of the critical
missions specified for the Space Transportation System. The first
mission, referred to as Mission i, is a 28.5 ° inclination trajectory
launched from the Eastern Test Range (ETR). For purposes of selecting a
critical heating mission, a winter launch has been assumed. The second
mission, Mission 3A, is a Western Test Range (WTR) trajectory launched
into a I04° orbital inclination. A winter launch has also been selected
for severity of the heating environment and for comparison with the
Mission 1 trajectory. Using these two; missions, separate analyses have
been performed which have consisted of the following steps:
I. Nominal trajectories have been simulated under the
conditions as specified by baseline reference missionguidelines.
Dispersion trajectories were simulated using predetermined
parametric variations which spanned the +3_ dispersionlimits. Dispersion parameters were selected to represent
error sources stemming from propulsion uncertainties,aerodynamic/environmental errors, mass property
inaccuracies, and guidance, navigation and control (GN&C)errors.
t Since the dispersion parameters a_e assumed to beindependent variations, the requirements for a +3c"
aerodynamic heating trajectory have been determined by theroot-sum square (_SS) of the positive deviations of the
aerodynamic heating indicator time histories between the
dispersion trajectories and the nomina] trajectory. A +3_
trajectory has been used to represent the worst heatingcase.
gY
l-1
4. Usingthe aerodynamicheating indicator parametersas aguide, compesitetrajectories were simulated usingcombinationsof dispersion parameters which representedprimary contributors.
5. Eight directional wind histories were then applied
separately to the composite trajectories resulting inunique trajectories for each wind case.
Trajectory parameters associated with the eight wind cases, the
composite trajectories, and the RSS ana]ysis were delivered as computer
files to the Government. Files associated with Missions i and 3A are
resident on the MSFC Univac computer system.
The following report provides a summary of the analysis and is
subdivided in the same manner as the analysis steps. Section 2
describes the nominal trajectory requirements for Missions I and 3A.
These requirements are primarily based on inputs provided by Rockwell
International and MSFC. Section 3 summarizes the oarameters used in the
dispersion analysis and discusses the RSS analysis. Section 4 discusses
the formulation of the composite trajectories and wind related
trajectories. Several appendices are provided which present tabulated
results from the various analyses, a description of the RSS analysis
computer model, and a discussion of interpretations applicable to thecomputer output files mentioned above.
I-2
2. MISSION I AND MISSION )A NOMINAL TRAJECTORYR__RE__U_IREMENTS
Presented in Appendices A and B are the input requirements for
the baseline nominal trajectory simulation of Mission i and Mission 3A,
respectively. This input was used in the MSFC resident six-degree-of-
freedom (6-DOF) STAR 5D computer simulation. In order to simulate the
maximum heating trajectory, the abort-once-around (AOA) mode of
operation was chosen. This mode requires that an enqine out be
simulated at the AOA/return-to-launch-site (RTLS)_node boundary and
retargeted to the AOA terminal main engine cutoff (MECO) condition.
Because of the need to establish maximum heating requirements, the
trajectory to nominal MECO condition_ was not simulated.
Verification of the baseline trajectories was performed by
detailed comparison of trajectory parameters to similar trajectories
developed by Rockwell International.
3. DISPERSION PARAMETERS
Tables 3-] through 3-4 provide a summary of the parameters that
were used in the dispersion analysis. The primary assumption of the
dispersion analysis represented these dispersions as independent
variations and dispersion simulations were determined by the individual
biasing of these parameters. Approximately 60 individual trajectories
were simulated for each mission and data from these simulations were
stored on comouter files.
Appendices F and G provide summary information regarding the
aerodynamic heating indicator (AHI), angle of attack (_), and sideslip
angle (B) for all dispersion cases. The data in these appendices are
presented as increments between the value obtained and the nominal value
(shown as the second column of these tables). The notation at the right
uboer corner of each table gives the name of the parameter and the sign
of the dispersion value increment used in generation of the trajectory.
For example, a "BETA N[G" would indicate the parameter is sideslip angle
and the negative sign (-3_) was used in generation of the dispersions.
The table identification numbers shown in Tables 3-i through 3-4
correspond to the table headings of the tables in Appendices F and G.
3-I
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3-5
4. C@4POSITE AND WIND RELATED TRAJECTORIES
The establishment of a +3_ composite aerodynamic heating
trajectory was based on the combination of the nominal trajectory and
the RSS assessment of the dispersion trajectories. The goal of the
composite trajectory was to emulate an AHI time history which consisted
of the summation of the nominal AHI history and the positive RSS AH[
history. This combination reflected the worst case system dependent
heating trajectory. The composite trajectory was simulated by combining
mixtures of the dispersion parameters in such a manner to match the
summed AHI history. This mixture of parameters reflected the dependent
nature of the individual parameters. Table 4-i identifies the
combinations of parameters that were used to define the composite
trajectories For the Mission i and Mission 3A cases. In this analysis,
the matching scheme minimized the deviation of the AHI parameters along
the entire trajectory (prime interest, however, was devoted to matching
the trajectory through the AOA/RTLS mode boundary). Appendices H and [
present, under the appropriate column, the deviation of AHI, angle of
attack, and sideslip angle for the composite trajectories for Missions 1
and 3A, respectively. Also shown in these appendices are eight
additional cases which correspond to trajectories comprised of the
composite parameters plus eight different directional wind profiles (45 °
increments). These wind histories assume a 95% design wind profile
based upon data supplied by Space Sciences Laboratory of MSFC. The
combinations of the composites and the varying wind profiles provide a
worst-on-worst Case aerodynamic heating trajectory. Parameters shown in
these eight cases again reflect the deviation between the wind
trajectory parameters amd the nominal values.
Trajectory parameters of the composite as well as the eight
wind trajectories are also stored on the computer file in the same
manner as the dispersion trajectories.
4-i
Table 4-I.
Mission I
+3aPitch Accelerator
+3aPitch RateGyro
-1.5_ SRBWAT
Hot Atmosphere
CompositeParameters
Mission 3A
+3aPitch Accelerator
+3q Pitch Rate Gyro
-2_ SRB WAI
_-2
L
Mission
APPENDIX A--MISSION ] CRITERIA INPUT REQUIREMENTS
C.
a. 65,000-Ib payload
b. 28.5 ° orbit inclination
T_
a. General
b.
i. Psuedo-MECO altitude shaping
2. Last RTLS time equals earliest AOA time
Launch
i. Launch Pad
Latitude = 28.6084 ° North
Longitude = 279.39 o EastAltitude = 95 ft
Altitude corresponds to booster station 1942 (11.36 in. belowthe base of the booster skirt).
2. Orbiter tail-south orientation.
3. Staggered start on main engines. 120-ms delay between starts;each Space Shuttle Main Engine (SSME) reaches 90% thrust at3.7 s after its start signal.
4. Solid rocket booster {SRB} ignition command defines to and isissued 2.716 s after last SSME reaches 90% thrust. Solid rocket
motor (SRM) thrust rise starts 0.011 s after ignition command
5. Vertical rise until vehicle has gained 365 ft of altitude
6. Single-axis-rotation (pitch, yaw, roll) maneuver after verticalrise
First stage
i. 1963 Patrick reference atmosphere
2. ETR February mean wind (winter) {see Fi ure A-I2__ )
A-]
OF POOR QUALCf'Y _f
I[TR _ _[ND
I,--
LIJ
NI--,.J
Z
31
• IEI I _ t _
I
14°f
_a
J. j
: I I T
In lao
WINE} VELOCITY FPS
p-Lt_ tO0
LtJ
.J
.<
dZ
0 I
\\,
C\
.i
I
/S
WINO AZIMUTN OE_
Figure A-I. Winter _1_an Wind
A 2
,
4.
5,
Flight control 10
0;1'I_i'_'L '_,IL;L"
Maximum dynemic pressure 675 psf (winter) (maximum dispersion =819 psf)
Main propulsion system (MPS) throttle schedule (for al! threeengines), single-step throttle
I-Load Entries Reference Values
Command ActualVrel Throttle Time Throttle(fps) (_) (S) (3)
0 100 0 ]0052.625 109 3.5 I00
4.4 1091160 84 50.241 109
62.741 841367.4 109 59.27 84
61,77 109
6. SSME throttle change rate _i0%/s
7. Elevon Schedule 6A
Relative Inboard Outboard
Velocity Elevon Elevon MachWinter Deflection Deflection No.
(fps) (deg) (deg) CRef)
0 10 9 01147.6 10 9 1,051328.2 I0 2 1.251581.9 i0 -5 1.551779,9 I0 -5 1.802304.9 3,333 -5 2.402506.3 i 111 0 2.602612.9 0 0 2,70
A-3
L - L
8.
OF POOR ' '"'
194 Ib of spray-on foam insulation (SOF[)_eight loss duringfirst stage
Time SOF[Flow Rate
(s], (lbls)
0 2.425.0 2.450.0 1.4675 0 ]. 12
100.0 O. 97122.375 1.48015122.38 0150 0
d, Staging
i. SRB separation 6.0 s after Pc : 50 psi
2. Command SRB nozzle actuators to null 4.3 s after Pc : 50 psi
3. Attitude hold from SRB separation to 4.0 s after separation
4. Maximum dynamic pressure at separation shall not exceed 75 psf(with dispersions)
5. Begin SSME trim command after Pc = 380 psi (6-s ramp). Constant
SRB trim command beyond Vre I corresponding to nominal Pc =380 psi
e. Second stage
1. General
(a) Maximum acceleration = 3 g's by MPS throttling
(b) Alpha Limiter : 5° cone around 2°m prior to 150 s or200,000 ft
,
4°
[
2. Pseude-_ECO trajectory
(a) Three MPS endines at throttle setting = 109% full Dowerlevel (FPL)
(b) SSME throttle to reach 65% minimum power level (MPL) 6 sbefore MECO at -10%/s rate
(c) Pseudo-MECO target conditions
h (equatorial) 74.5 nm
Y (inertial) 0.65 °
v (inertial) 25676 fpsInclination 28.5 °
*Ascending Node 189.9939 °
*Referenced to Greenwich at t : 0 s
Normal trajectory
(a) MPS throttle setting = 109% (FPL)
(b) Instantaneous pitch/yaw maneuver at abort mode boundary
(c) SSME throttle to reach 65% (MPL) 6 s before MECO at -10%/s
(d) _ECO target conditinns
h (equatorial)
gamma (inertial)v (inertial)Inclination
Ascending Node
AOA trajectory
(a)
(b)
(c)
(d)
(e)
57 nm
0.65 °
25,680 fps28.5 °189.61857 °
MPS throttle setting = 109% (FPL)
Engine failure occurs on No. 3 SSME
Paralle] SSME from engine failure time to t(MECOI - 60 s
Aft Reaction Control System (RCS) burned pre-MECO to 65; level
Orbit maneuver system (OMS) and RCS used to burn off excessOMS and RCS propellants with 4,5 s allowed For auto connectand disconnect of OMS propellant supply to RCS engines
9Y
A-5
(f)
(g)
ORIGII_A_.. F _,-, "
OF POOR Q"J;_Lil _'
5SME is cutoff from existing power level (765%7
MECO target conditions
h (equatorial 57 nmgamma (inertial 0.65 °v (inertial) 25,676 fpsInclination 28.5 °
Propulsion
a. Nominal thrust and specific impulse
1. SRM
(at
2. SSME
(a
(b
(c
(d
(e
(f)
3. OMS
(a)
(b)
(c)
{d)
MSFC 86-80 data with ETR burn rate; 60°F grain temDeratureFor February; lightweight cases (see Table A-l)
Tva c : 470,000 Ib [100% level rated power level (RPL)]
Aexit = 6464.36 in 2 (LT = 95,000 Ib; Pref : 2116.22 psf)
!s_vac = 455.15 s for : 100%, mixture ratio (MR) atinjector = 6.014:1
Isbva c = 455.25 s for = 109%
Pitch null = -16 ° (No. i engine) and -i0 ° (No. 2 and No.engines)
Yaw null : 0_ (all engines); No. 2 and No. 3 are
electronically biased to 0 from their mechanical nulls of3.5 ° outboard
Tvac
Ispvac
: function OMS/RCS usage (see Tables A-2 and A-3)
Pitch null : -15 ° 49'
Yaw null : 6° 30' outboard (AOA pre-MECO burn executed at
null attitude; post-MECO burns electronically biased to O)
A-6
Table _-I.
CIT'!,_Ii ,, L:
MSFC 86 80 Motor Data - ETR Version 4160°F)
|
DIO.TA PLOT. Q,O0
Table A-I.OF POOr, r_:JAi :',
MSFC 86-80 Motor Data - ETR 'Jersion (50UF) (Concluded)
fable A-2. Variation of OMS/RESPerformancefor Pre-MECOAbort (Single EngineValues)
Data for RCSJets Fueledfrom RCSTank
Numberof RCSJets OperatingAcceleration
Level Four _ X l_elve*
(g'sl Thrust FlowRate Isp T,Irust Flow%te(Ibs) (Ibs/s) (s) llbs) (Ibs/s)
0 870 3.1071 280 838 2,9928
3 950 3,3928 280 920 3.2857
"Includes 4 ÷ X thrusting RCS,remaining numberare null RCS(used inpairs) with zero net + X thrust
Data for OMSand RCSFueledfrom OMSTank
Numberof Thrust (Ibs) FlowRates (Ibs/s)RCSThrustersFiring With Per OMS Per RCS Per OMS Per RCS TotalOneOMS Engine Thruster Engine Thruster OnePod
OMS+ 0 6070 19,37 19.37
OMS+ 2 5960 870 19.03 3_I00 25.23
OMS+ 6 5690 8)_ 18,21 2.892 35,56
OMS÷ 9 5471 775 17.53 2.749 _2.27
OMS + 12 52a5 738 _6 84 2.610 48,16
A-g
:>_
C)
E0
Z
M
Z
_11111!
_o_ • _ _.
i!:iiiiiii:iiiiillb
Y
A-IO
4, RCS
CII_I_!,_' _ L _...
OF po,c R Q, t4L;.iY
la) Tva C I = function OMS/RCS usage Csee Tables A-2 and A-3)(b) Ispva c
(c) Pitch = -I0.0 °
+ X jets(d) Yaw = 0°
_cs.
July 1979 Aerodata Book, Rev. 2K-I
Mass Properties
_. Mass properties of elements
b. Element weighcs
Orbiter planning weight
External tank (ET) planning weightSSME planning weight
c. MP_ propellant weights
ET propellant weigh_ at to . 5 min = 1,592,124 IbOrbiter MPS at to - 5 min 5,039 Ib
Total MPS at to - _ mim = 1,597,163 Ib
d. SRS weights
e,
= 140,821 Ib70,990 Ib20,484 Ib
5RB gross weight = 2,579,976 IbSRB inert weight = 365,72; Ib
FPR ana fuel bias
OMS : 19,700RCS = 7,508
(3_) (2_) (2::)Normal AO.__AA RTLS
FPR (Ib) 5551 3786 3186
LH2 Bias (Ib) 1047 1100 II00
{Reverse 31ank)
A-11
APPENDIX B--MISSION 3A CRITERIA INPUT R_EQUIRFMENTS
O*
Mi_ssion
a. 32,000 lb payload
b. I04° orbit inclination (normal mission)
a. General
b°
i. Variable Iy shaping
2. Last RTLS time equals earliest AOA time
Launch
I. Launch pad
Latitude : 34.58139: Northlongitude = 239.374720 EastAltitude = 430 ft
Altitude COrresponds to booster station 19_2 (11.36 in belowthe base of the booster skirt)
2, Orbiter tail-west orientation
3. Staggered start on main engines. 120-ms delay between starts;
each SSME reaches 90% thrust at 3.7 s after its Start signal
4. SRB ignition command defines to and is issued 2.716 s after lastSSME reaches 90% thrust. SRM thrust rise starts 0.011 s afterignition conTnand
5. Vertical rise until vehicle has gained 365 ft of altitude
First Staqe
I, 1971Vandenberg reference atmosphere
2. Vandenberg December mean wind (see F_u._[reB-I)
3. Flight control I0 (see Table B-I)
4. Maximum dynamic pressure 650 psf, nominal (maximum dispersion819 Psf) =
8-I
Figure B 1. WTR Mean WindORIGI,N_.t';
p_OF pc..s: _
I--I.I.
WQ
{--
I--..J
lb_ I I I * I _ T i i 1 i i
//
-° //
100 /
B_
/I I I I f I P ]
W[NO VELOCITY FPS
I i I ! I
200 JO0
DECE_.rl: WIR nC_T__IN2
]&O
LL
B-2
Table B-!. r]ight Contro] i0
0!_, ..... ,'
rL !GkT ¢C4TR._I 10
_LOC;TY IT_ITJ_
qtJ _0 0 C_O * 567 401_
I_: SJ E _: ;_i :',3
_'_ :3 S ::2 " _E_ . ;.!_
_;_ _ 0 CSS ?20 _:_i
B
Y
B-3
,
ORIGINA t Pk
OF. POOR Q,..;:,L.
MPS throttle schedule (for all three enqines , single-stepthrottle
I-Load Entires Reference Values
Vrel Command Throttle Time Actual Throttle
(fps) (_) (s) (_)
0 I00 0 I003.5 i00
52.625 109 4 a 10934.7 109
818.665 65 39.1 6559.29 65
1326.567 109 53.69 109
6. SSME throttle change rate LlO%/s
7. Elevon schedule 6A
Relative Inboard Elevon Outboard Elevon _achVelocity Deflection Deflection No.
(fps) (dog) (deg) (Ref)
0 I0 9 01092.406 10 9 1.05
1249.897 i0 2 1.251496.753 IO -5 1.55i718.813 i0 -.5 180
2305.636 3.333 -5 2.402520.737 I.I11 0 2.60
262_.795 0 0 2.70
8 I 194 Ib of SOFI weight lOSS during first stage
B-4
gY
d,
Time SOF_(s) Flow Rate
(Ibs/s)
O. 2.425, 2.450. 1.4675. 1.12
100. 0,97
122.375 1.48015122,38 0.150. O.
Staging
I. SRB separation 6.0 s after Pc = 50 psi
2. Command SRB nozzle actuators to nulf 4.3 s after Pc = 50 psi
3. Attitude hold from SRB separation to 4.0 s after separation
4. Maximum dynamic pressure at separation shall not exceed 75 psf(with dispersions)
5. Begin SSME trim command after Pc = 380 psi (6 s ramp). ConstantSRB trim command beyond Vre l-corresponding to nominalPc = 380 psi
e. Second stage
1. General
(a) Maximum acceleration : 3 g's by MPS throttling
(b) m limiter = 5° cone around 2° _ prior to 150 s or200,000 ft
2. Pseudo-MECO Trajectory
(a) Three MPS engines at throttle sett,,ig : 109% (FPL)
(b) SSME is throttled to reach 65% (MPL) 6 s before MECO at-lO%/s
B-5
3,
4,
(c)
h (equatorial)(inertial)
v (inertial)Inclination
Ascending Node
Normal trajectory
Ca)
<b)
(c)
Pseudo-MECO target conditions
70 nm (r = 21,351,050 ft)0.65 °
25,374 fps96.907 °55.87913 °*
MPS throttle setting : 109% (FPL)
Instantaneous pitch/yaw maneuver at abort mode boundary
SSME is throttled to reach 65% (MPL) 5 s before MECO at-I0%/s
(d) MECO target conditions
h (equatorial)(inertial)
v (inertial)Imclination
Ascending Node
AOA Trajectory
(a)
(b)
(c)
(d)
(e)
(f)
(g)
57 nm0.65 _
25,374 fps104 °51.83485 °*
MPS throttle setting = 109% (FPL)
Engine failure occurs on No. 3 SSME
Parallel SSME from engine failure time to t(MECO) - 60 s
Aft RCS burned pre-MECO to 65% level
OMS and RCS used to burn off excess OMS and RCS propellants(Enclosure 2) with interconnect
SSME is cutoff from existing Power level (>65%)
MECO target conditions
h (equatorial) 57 nm(inertial) 0.65 °
v (inertial) 25,346 fDs
B-6
_)'U_ _ i_ -
Propulsion (Nominal Thrust and Specific Impulse)
a. SRM
1. MSFC 86-80 data with WTR burn rate for 52°F grain temperaturefor December (see Table B-2)
b. SSME
C,
d°
i. Tvac : 470,000 Ib (100% power leveF RPL)
2. Aexit : 6464.36 in2 (_T = 95,000 Ib; Pref : 2116.22 psf)
3. Ispvac = 455.15 s for T = 100% MR at injector = 6.014:1
4. Ispvac - 455.25 s for T = 109%
5. Pitch null = -160 (No. I engine) and -10° (No. 2 and No.engines)
Q
OMS
Yaw null = O° (all engines); No. 2 and No. 3 are electronicallybiased to 0 from their mechanical nulls of 3.5 ° outboard
i. Tvac
2. Ispva c
3.
I : function OMS/RCS usage (see Tables B-3 and B-4)
Pitch null = -15 ° 49'
4Q
RCS
Yaw null = 6° 30' outboard (AOA pre-MECO burn executed at null
attitude; post-MECO burns electronically biased to O)
I, Tva C
2. _sDvacI : function OMS/RCS usage (see Tables B-3 and B-4)
3. Pitch : -i0.0 _ # + X jets4. Yaw = DO )
Aerodynamics
July 1979 Aerodata Book, Rev. 2K-I
B-7
Table B-2.
ORIC_If_AL _J....
OF POOR QUALIT"t
MSFC 86-80 Motor Data - WTR Version (52°F)
OELI& RM_T= 13._C
B-8
Table B-2.
r_F :,,,- - •
MSFC 86-80 Motor Data - WTR Version (52°F) (Concludeo)
gY
B-9
Table B-3.
ORIt'5;IN/_L t-, _ :
OF POOR QUALITY
OMS and RCS Burn-Dump Sequencing for AOA (Pre-MECO)
OMS & _CS Burn-Dump Sequencing for AOA (Pre-ME£O)
OMS (2 Engines)
RCS (4 +
Time tram Liftoff ,is)
Time Intervals
OiMS (2 Engines)
qnlh,. _,> ,-.. ............... _.
"-_l:_:_:_!:!_!;!;!':'i;i!'_!;i;iTi_iTiiTi:i_.ON_?RQ,PELLAINT ii!i iii I.i ......
x) : :i::i F%]: :llllllllllll
2 I " _ i60 $9 264 99 281.23 285.73 363.04
(S) 102,55
"_--4.5 _ "_-'16.24-_-_---4.5 _._--77.31-_.
T 12,140. 11,920. I 12,140. 12,140.v_ 38.74 38.86 I 38.74 38.74
£Wp 17a.33 518.07 J 174.33 2,994.9
RCS (4 + X) T 0.0 3,480. 3.0 3,640.
"_ 0.0 I 12.4 '3.0 13.3
,lWp 0.0 201.37 0.0 1,005.0
Total OMS + RCS T 12,140. 15,400. 12,1,_0. 15,780.38.74 50.46 38.74 51.74
£Wp 174.33 819.44 174.33 3,999.90
T=Thrust (Ibs); 1:1=Flow Rate (Ibs/s); £Wp =Propellant increment (]bs)
B-IO
Table B-8.
OF POoRQ'-JALFT',_
'Variation of OMS/RCS PerFormance for Pre-MECOAbort (Single Engine Values)
Data for RCS Jets Fueled from RCS Tank
AccelerationLe,Jel
(g's)
Number of RCS Jets Operating
Four + X Twelve*
Thurst Flow Rate is _ Thrust(bs) (Ibs/s) _s,, (Ibs)
0 870 3.1071 280 838
3 950 3.3928 280 920
_Includes 4 + × thrusting RCS, remaining number are nullpairs) with zero net + X thrust
Flow Rate(1_s/s)
2.9928
32857
RCS (used in
Data for OMS and RCS Faeled from OMS Tank
Number of Thrust (Ib) Flow Rates (lbs/s)qCS Thrusters
Firing with Per OMS Per RCS Per OMS Per RCS TotalOne OMS Engine Thruster Engine Thruster One Pod
OMS + 0 6070 19.37 - 19.37
OMS + 2 5960 870 19.03 3.100 25.23
OMS + 6 5690 812 18,21 2.892 35._6
OMS + 9 5471 775 17.53 2.749 42.27
OMS + 12 5245 738 ]6.84 2 610 48.16
B-]I
_ass Properties
a. Mass properties of elements
b. Element weights
c. MPS
OR_,_!;; _ i. _-. . . •
Orbiter planning weight : 140,821 IbET planning weight : 70,990 IbSSME planning weight 20,484 Ib
prepellant weights
ET 9ropeIlant weight at t o -5 min : 1,592,124 IbOrbiter MPS 5,039 IbTOT MPS at t e -5 min = 1,597,163 Ib
d. SRB weights
SRB gross weight = 2,579,976 IbSRB inert weight : 365,722 !b
e. FPR and Fuel Bias
[3J) (2;) (2_)Normal AOA RTLS
FPR {lb) 5767 3632 3107
LH2 Bias (Ib) 1047 1100 1100
$
B-12
L
APPENDIX C-DERIVATIDN OF ERRORS AND UNCERTAINTIES
Y
C-I
L
ORIGINAL PA:._L: ',.:.'
OF PO:JP, QL,,,,LrF_r y
SRB Terminal Mismatch Data*
Time
(PreviousData)
112.2
l13.a
]14.6
_i_.8
117.0
118.2
i19.4
120.ff
121.8
123.0
12a_2
[.eftMotor
(Low)
],577,500
],353,500
1,I05,580
72!,700
431,750
331,640
246,470
191,453
164,470
131,750
87,590
RightMotor
(High)
1,845,500
1,923,600
1,775,580
i_431,700
1,011,760
801,640
616,470
a81,450
384,470
291,750
187,590
1,881,840.4
1,951,478
i,810,544
1,459,892
i,03],683
817,425
628,509
490,930
392.041
297,495
191,284
I!3.i0484
lli.28243
112.46002
113.63761
11481521
115.9928
117.17039
118.34798
i[9.52557
120.70317
121,88076
*Re#: EL.O] (I]2-80),
1,208,563.1
;,380,254
1,127 350
735 911
440 262
338 170
251 323
195 220
167 709
134 344
89 315
29 May !980
([-R (_ 60 P)_]ow _a_e
(7bs/s)
6472,9
6285.Z
5672.7
4104,5
2791.1
2143.6
1779.7
1430.6
1!45.9
843.9
509.7
(WTR _ 52 F _
6596.1
6ao4.8
5780.6
4182.6
2844.2
2184.4
1813.6
1457.8
1167.7
86o.o
519.5
c-2
ORIGIN#_[ p;. ....
Oeriva[ion of %he SRB Thrust
Vector Angular Misa]ignm_nt Error
]) Cone I/2 angle
2) SRB/ET cente_l_ne mis_lignment
3} Electronics/actuator errors
= 1.0 deg
= 0.12 deg
= 0.3 deg
RCS !,0509
Average RSS oI 2 SRBs = _'_/2 = x 0.70?
Resultant misa]ignment error = 0.7431
Component of the actuatormisalignment in the pitch
or yaw plane {cosine aT 45 _)
= x 0.707
0.$254 deg.
0.5254 left, right (tilt, rock) per motor
I_ 0.5254 ACTUATORTiLT ROCK _
z M[SAL IGNMENT/
.,- ERRO'<
9.7431 RESULT&NT
MISA! IG_IMFNT"N lozz e Pivot. Center Shift" is included Jr, the above. ERROR
C--3
Derivation of SSME Thrust VectorAngular Misalignments (Pitch, Yaw],
C'RIGII_AL P;_.C;;. _,
OF POOR QUALllY
Engine =I
P Y
Engine _2 Engine :3
P Y P Y
Actuator System (+) .534 .441 .537 .606 .537 .455
151 of Nominal Thurst (+],Structure Deformation - .098 .060 .376 .015 .249 .071
3) Combination of:
a) L0.25 _ installation tolerance!
+0.546 ° dynamic thrust vectorb) _includes +0.6 in. ecoentricity)_: +-0"607= (P, Y)
Ic +0.09 ° ET _ misalignment
4) Nominal thrust structuredeformation (deterministic) +'654 -.399 +.510 +.og8 _1.663 -.476
5) RSS (I), (2), and (3); add (4) per engine; then RSS 3 engines anodivide by 3
5) Results P y
_i.066 +.353
-0.115 -.618
7) Dse largest of pitch, yaw values for simulation; P = +1.066, Y = +.618I
NOTE: (I), (2), and (3) are dependen_ on gimbal angle deflections(flight averaged).
C-_
I'
_2,0-
_ 1,5-
1,0-
00
0,5--
CG 3o UNCERTAINTIES
P;st.STAG_
I I I I
2 3 4 5
TOTAL WEIGHT x ]0 6 ITbsl,
r C_TORIGINAL pA.O-._ .,:-_OF POOR QuAL','W
CS 3,,• UNCERTAINTIES
io- I
-. ] _2nd STAGE5
¥0 'I I I I I i
5 7 9 Ii 13 15TOTAL WEIGHT x 106 (Ibs)
C-6
OF ; . • "JE
Derivation of Accelerometer Errors
1) ACCURACY
a) AA null offset
(includes vibration)
b) AA noise
c) MDM noise
d) MDM bias
e) AA scale factor
P (0.028x0.20 g),Y (0.032 x 0.004 g)
RSS
f) MDM quantization(add i/2 value)
Z
Apply mid-select (x 0,67)
2) ALIGNMENT
a) Accel. to AA axes #
b) AA axes to body axes
c)
Normal __
0.021
0.020
0.024
3.025
0,006
_0,046
0,004
+0,050
+0.034
Normal de_
+0.43
Bulkhead flexure (deterministic) 0
Lateral
0,014
0.020
0.006
C.006
n.o0o
+0.025
0.001
*0.027
+0.018
Lateral (deg)
+0.43
+0.23
Apply mid-select (x 0.57)
+0.43 o
+0288 °
+0.66 _
+0.442 °
[,-7
ORIGINAL PAC,: _:a
OF POOR QUAL._F:
Derivation of Rate Gyro Assembly Errors(Pitch, Yaw)
ACCURACY:
NOTE;
a) DC zero offset -
b) Threshold
C) Hysteresis
d) Linear acceleration
sensitivity (O.05°/S/g)
e) Linearity
f) Scale factor
g)
n)
Noise
Angu]ar acceleration
sensitivity (0,003 deg/s 2)
Zero offset due totemperature variations
MDM -
StaticVibrational
Noisebias
PIY
RSSMDM quantization × I/2
5u, {:Apply mid-select factor (0,67)
Average qSS of 2 SRBs (×_72
RGA misalignment (+_0.7a4 degl neglected
DEG/S
: 0.i0- 0.15
- 0.02
= 0.02
: 0.05
- 0.05
= 0.05
= 0,051= 0.051
: 0.05
= Negligible
= 0,002
= 0.12= 0.12
= 0.273
= 0.271
- 0.059
= 0,332= 0.330
= 0,222
= 0.157
x 0.15 ". 0.008x 0.002 = 0.0
x 0.5 _ 0.026
x 0.I - 0.005
x 40 - 0.08
C-8
3q MECOTargeting Errors (1__)
NORMAL NAV G&C
AVi (fps) 9.27 7.95
&Ti (deg) 0.041 0.06
_r (ft) 2016_0 ]155.0
&i [deg) 0,103 --
RSS
12,21
0.073
2323.0
O.iO3
AOA
AV 10.21 12,94SAME
#_ 0.04 0,072AS
±r 3148,0 3353.0ABOVE
±i 0.084 0.084
RTLS
&V 10.04 SAME 12.88
LIY 0.038 AS 0.071
'_r 2310.0 ABOIIE 2583_0
NOTES:
i) The variables are treated independently.
2) Noda_ error5 neglected,
(Reverse Blank)
C-9
APPENDIX D--COMPUTER PROGRAM FOR DISPERSION ANALYSIS
The following ASCII Fortran Computer program has been written
to facilitate the RSS analysis performed on the dispersed set of
trajectories. AIso provided via this program is a tabular listing of
the time ordered dispersion as a function of the dispersion type.
Output of this program has been compiled in Appendice_ F, G, H, and I.
D-I
ORIGINAL PAGE _3
OF POOR QUALII"Y
OF F)O0_ _"....
= = °4o : =
: .... : •
=:_ ...... ;
i_' ..... z r
: ... :;_" ....... • ......... o .ooo ._,_..
..:_ _'
~-._ ..........
-._... :. - :=
0.,= ,
D-?
ORIGINAL PAGE |_l
OF POOR QUALITY
Z
• a*,****_****° ° *
2_ ...... J .................................
_ _ _ _ r* _ _. m _ _ _ _ _ _ _ _ _ i_ _-_p _ _ = w = _ _ _ =
ORIGINAL PAGE I9"OF POOR QUALITY
]E
0b-
o
.Q
k,
i
ql
u
¢.
v
3
w¢c x
Z
¢¢_ 0¢ ¢¢ ¢n
(Reverse B]anklD-5
ORI,?!,'I°•OF _0'.3-,L- _.:l. Y
APPENDIX E-COMPUTER FILE [NPUTIOUTPUT REQUIREMENTS
Two resident files associated with Mission I and Mission 3A are
provided on the MSFC Univac computer system. These files are direct
access files which contain time ordered data associated with all
trajectories which have been simulated in this study. This apDendi× has
been written to aid the future use of these files by defining their
input/output requirements.
The structure of each file is the same fur both missions and
therefore the input/output requirements can be treated in a generic
fashion. A file is made up of 16,000 records and each record consists
of 13 words, In a Fortran program, the programmer must have _F,e
Following statement before any executable statements:
'DEFINE FILE N(16000,13,U,IP)'
The letter N is given a numerical value depending on the
proqremmer's choice of file numbers. This file will be identified by
proper control cards to assign the chosen numerica| value to the stored
file. The ]5000 and L3 refer to the number of elements and words per
element, respectively, The Univac programmer's manual Should be
consulted For the additional parameters on this statement.
The Fortran read statement for this File is the followinq:
where
'READ(N'NR }VAR, IVAR'
N - file number
NR - number oF requested ,-ecerd (I to 16000)
VAR - a storage arra_ consisting _f 12 parameters;
(I) - time from liftoff (s)
(2) - angic of attack (m) (deg)
(3) - sideslip angle (B) (deq)
(4) .. aerodynamic heat;rig indicator (BTUI
(5) - dynamic pressure (lb/ft 2)
E-I
(6) - altitude (ft)(7) - earth relative velocity (ft/s)(8) - airspeed (ft/s)(9) - radius from the earth's center (ft)
(i0) - inertial velocity (ft/s)(II) - inertial flight path angle (_) (deg)(12) -Mach number
IVAR- multipurpose variable flag used to specify the contentsof the records. Table E-I identifies the waythevariable is used.
All trajectory casesare stored within a maximumof 2OGrecordsand therefore the start of each trajectory will begin at somemultipleof 200plus I. Thenormalmodeof reading this data is to interrogatethe starting record which indicates by the ,,alue of IVARthe type oftrajectory and continuing reading sequential records until the value of
IVAR is equal to 9999 (which specifies the end of the trajectory data).
The only data on the file that do not correspond to the above
definition of the VAR array are associated with IVAR = 5100. In this
case, the VAR array is defined iq the following manner:
VAR(1) - time from liftoff (s)
(2) - positive RSS dispersion for aerodynamic heatinaindicator
(3) .- megative RSS dispersion for aerodynamic heatingIr_dicator (value is positive in sign)
[4) - positive RSS dispersion for angle of attack
(5) - negative RSS dispersion for angle of attack
(6) - positive RSS dispersion for sideslip angle
(7) - negative RSS dispersion for sideslip angle
(8) to (12) - [not used)
Table E/]. Interpretation of IVAR Cariables g
O000
9999
---0
._-1
0010
---
101_
102_
i03.
104_
105.
106.
107_
108.
109_
ii0_
iii.
201.
202.
203_
204
VAR contaims data
Terminal point nas been reached for this trajectory
Positive dispersion (the parameter is perturbed in apositive sense)
Negative dispersion (the parameter is perturbed in anegative sense)
The following data are the nominal trajectory
lhe following data are related to propulsiondispersion parameters
SRB with action time
SRM terminal thrust mismatch
SRM specific impulse
SRM steady state thrust mismatch
SRM steady state _-,.:ific impulse mismatch
SRM thrust misaligh,_ent (pitch)
SRM thrust misalignment (yaw)
SSMR vacuum thrust
SSME vacuum specific impulse
SSME thrust misalignment (pitch)
SSME thrust misalignment (yaw)
The gollowing data are related to aero/environmentdispersion parameters
Axial force coefficient
Normal force coefficient
Pitch moment coefficient
Side force coefficient.
E-3
Table E-1.
OR1GIN,_L P Af_E I_
OF POOl_ Q'jAL,'TY
Interpretation of IVAR Variables (Continued)
3
3___
_=_
205_
205.
207.
208_
301_
302.
303.
304_
305_
306_
307_
308_
309.
401_
402.
403.
404.
405.
406_
407_
408_
Yaw moment coefficient
Roll moment coefficient
Base force
Atmosphere (hot 2080, cold 208i)
The following data are related to mass propertiesdispersion parameters
External tank propellant weight
SRB propellant weight
SRB inert weight
Second stage inert weight
First stage longitudinal center of gravity
First stage ]ateral center of gravity
First stage normal center of gravity
Second stage longitudina] center of gravity
Second stage normal center of gravity
The following data are related to GN&C dispersionparameters
Accelerator error (pitch)
Accelerator error (yaw)
Rate gryo (pitch)
Rate gyro (yaw)
Inertial measurement unit (IMU) platformerror (pitch)
IMU platform error (yaw)
IMU platform error (rot1)
MECO targeting
E-4
Table E-I.
ORIC_INAL r,.. , ,.:
OF pr/ . '- ._! :,'¢
Interpretation o _ IVAR variables (Concluded)
501.
502.
503_
504.
505.
506_
507.
508_
509.
5100
The following data are related to the composite andwind related trajectories
Composite
Composite plus head wind
Composite plus right quartering head wind
Composite plus right cros_ win_
Compnsite plus right quartering tail wind
Composite plus tail wind
Composite plus left quartering tail wind
Composite plus left crnss wind
Composite plus left quartering head wind
The following data are time ordered RSSvalues for positive and negative dispersionsof aerodynamic nearing indicator, angle ofattack, and sideslip angle
(Reverse Blank)
F-5
APPENDIX F--MISSION I DISPERSION ANALYSIS TABULAR DAIA
iF-I
_J
• o * o • * * * ° * , ° • • o , • • * • ..... * • * * * , * * * * • • • • * ,_,
........... _ .=.. :,_ = -- . .........................
F-2
_n
I
i
z
rQ
:-:_o °oo° ooooooooooo_.............................o
' , • . . * . . . . . , • ..... • , . , • ..... • , • • , , . ._ _'_'^ _" _ _ _¸¸7 • _t
Z
• _t ___mr._a____t_._ _
.,==
l--i
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e
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° _F PC).'_F(Q' !_',LI'i'YII
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• • _ • ii= _ * • • i _ • • • .14 • • _ . • •
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ilill
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e _e
e
6,
-o:• .I}
e 4,
e •
...................... ---_ .--- . . --_ _i* _ i_ * ,
::::::::::::::::::::::::::: .... ============.............................. __
m • _m
i
• o . • • , , i , ° _ • , • ° , .... , , . , , . o . , ° , ° , • ° _ . , ,
e e _,
. . • ......................... z_ _--_ .......
F-4
I
I
I
I
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fo
t_ o
4
tt
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ol
* OI:BGINAL pAC_C _
o OF POOR QuAL|I'_,
............ ???_? .............i
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,Ip I
i
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OF po:_p, _Y'_,_LI-ry
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t t
D
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OF POOR QUALITY
JQ
I,m
...... . ............ _ _._®_ .... _ ....... _,_
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