the uprated saturn i- it's growth potential and future role in space

8/3/2019 The Uprated Saturn I- It's Growth Potential and Future Role in Space

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Rem:irks by Vai:io 2. V c h k o , Di r chctor of Engin eering, Ch ry sl er Corp oration Space

k\.7 Thank you for inviting m e to be he re with you today. It is always a pleasure49 to app ear before a knowledgeable group such a s yours, and ;n this instance, renew> '.

- some old acquaintances. I would f ir st l ike to review for yo^ the s ta tus and cur rent.a ha ra ct er is t i cs of the Uprated Saturn I , and then describ e its growth potential an dfuture role s in our spa ce act ivi t ies .

Probably the very first thing I should do is c l e a r up ;he fairly rece nt nomen-cl at ur e change in the designation of the Sat urn I family of launch veh icle s. Th efirst Saturn, the Saturn I , which used the S-I f irst- stag e and the 90,000 pound thrustS-IV sec ond -sta ge, success fully compl.eted all of its ten missions, the las t one onJuly 3 0, 1965. The Saturn I was used for launch vehicle development, ApoPPoboiler-plate test ing, and orbiting of the thr ee P eg asu s Meteoroid Technology Satellites.

The Up rate d Saturn I, which use s the much lighte r aizhough almo st identicalS-IB first-stage and the 205,000 pound thrust S-IVB second-stage, is the vehicle thatis cu rre ntl y in production and will be used fo r the balance of i ts m iss ion s in theApollo Pr og ra m and many m i s s i o ~ s lanned for the Apollo Applications Program.The third Uprated Saturn I mis sion was flown on August 25, 1966 aiid was the 13thconsecutive succe ssful launch in the Saturn I family of flights. The f i rs t and thi rdflights of Wprated Saturn I tested the Apollo Command Module heat shield for there- en try neating i t will encounter on retur n f rom ear th or ts ikl missions. The secondflight wa s an orb ital te st of the S-IVB Stage and instrume nt nit arid carried out azero-gra vity l iquid hydrogen experiment.


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P r e s e n t rescheduling indicates that Uprated Saturn 94 (AS-2C4) w i l l launcnand orbit an unmanned lunar module. The suc ceed ing 1aunc;l is now p l a m e d as thefirst manned flight in the Apollo Pr ogr am . Th is mission will tes t the commandmodule and the ser vic e module in orbit.

The next mis sion may combine two launchings. A manned com ma nd/ se rvi cemodule payload will be launched on the first vehicle and an ,amannec? lucar modulewill be launched on the oth er vehicle about a day late r. They w i l l rendezvous anddock and conduct m a n e d test s of the lunar module in orbit.

Subsequent deli veri es under the ini tial Uprated Satu rn I order, vehic les208 - 2 1 2 , and the initi al follow-on o r de r s , may be utilized ;n the Apolio ApplicationsPr og ra m , assum ing no furt her need develops in the mains trea m Apollo prog ram .

The f lr st four m is si ons in the Apollo Applications PI-ogram a r e now schedul edto s t a r t in 1968.

A A P Launch No. I will be the launch of the comm and and se rv ic e modulewlth th re e men into orbit. AAP Launch No. 2 will be the la m ch of the S-IVB orbita lworkshop. They will rendezvous and dock to the multiple docking adaptor. Theastr onau ts will tran sfe r to the S-IVB through an a i r lock module aft er the sta ge hasbeen pr ep ar ed for en tr y and s et up the workshop. An or bit :,me of 2 8 days is plaixedfor the flr st phase of thi s mission. After this time they will ree nt er, leaving theworkshop In orbital storage. It is planned to r etu rn t o the workshop a fte r abouts ix months wlth two other launches to c ar ry out d ifferent ex ~ e r i m en t s nd operat ions.Lifetim e in orb it of th e workshop at 260 n aut ic al m il es a l t i t ~ l es about two yea rs .

AA? Launche s Nos. 3 and 4 a r e s imi la r to 1 and 2 iri :hat the maimed co mm an cand se rv ic e module will be or bite d initia lly followed by the lailnch of a seco nd payloaci,af te r rendezv ous and docking. The combined payload will in cr ea se altitud e for


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r.endezvuus and docking with the workshop which was left 1 orbl ta i s torage. In t h i sca se the second payload w i l l be the Apollo Telescope LMour~t, nd the crew will spend56 days in orbit . This is twice the miss ion tim e of the previous A A P manned oper -ation. Upon the comp letion of t his m iss io n, the workshop and the Apollo Tel esc opeMount will be left in orbit with the intention of revisiting this cluster the followingmission.

Subsequent Apollo Applications Pr og ra m activity may include tne launchingof ea rt h re so ur ce s sat ell ite s, manned photographic telesco;2es, and use of a modliiedcommand module a s a logistics vehicle. The eart h resou rce s satell i t e will help u smanage our res ou rce s to improve man 's standard of living. The satell i te sens or swill be capable of such things a s detecting and surveying crop damage and dis ea se,and collection of ocea nogra phic and ma rin e biological data fo r bett er uti lization of thefood poten tial of the ocean. We will be able to su rve y ground wa ter , lake lev el s, andsnow cover for better flood control and optimum water dis'iribution for agriculture,industry, p ersonal, and recreatio nal uses. The design of th i s satell i te is s t i l levolving.

Th is slide shows one of the manned telesco pe conce2ts developed in theCh ry sl er C orporat ion Space Division Optical Technology Scdy. This is only one ofa va rie ty of con figurati ons and ope rati ng modes. One concept that we have foundat t ract ive is a partially manned operation. That i s , astroria uts will set u p the obser -

vatory, program remote operating equipment, and then lezve the observatory. Theobservatory w i l l then operate automatically for some pericd of t ime. The astron autswill then re tu rn to the obse rvat ory to re tr ie ve da.ta, conduc: maintenance, and ?re?%;-@the observa tory fo r another period of r emo te operation. TrAs co nc ep th as the advac-tage s of greatly reduced life support requirem ents sand r e ~ c t v a if dist urb anc es cau ecby man's presenc e during observations.


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Contracting for th.e Uprated Saturn I follow -on vehic:.its ha s alreaciy beeniniti ated by the government. We rec eiv ed $7. 2 Million in 1966 for long lead t im ei te ms for veh ic les 2 1 3 through 216. T h i s y e a r ' s KASA Budget submit tal propos es$78. 5 Mill ion for the se sa me four vehicles plus funding for io ns lead t im e i t em s forth ree o ther s - 217 through 219.

The c apabi li t ie s of the Uprated Saturn I have been steadily inc rea sin g withweight reduc tions of both st ag es and incr ea se d engine thrust. We a r e p resen t lycapable of boosting in exc es s of 40,000 p of ~ nd snto 100 nautical m ile orb it on a.ileas ter ly launch from KSC. Th is plac es the Uprated Saturn I; cont r ary to qu ite a bitor' popular opinion, in a cla ss by i tself . Th er e is no other exist ing launch vehiclein this payload cla ss, and proposed growth vers ions of the Uprated Saturn I s t r e t chthi s a l l the way to 110,000 pounds in low e ar th or bit and with correspondingly heavypayloads for othe r types of m issio ns.

This bas ic veh ic le is the ma insta y of the c ur re ni Apollo ear th orb ita l fl ightprogram and is planned for mis sio ns in the Apollo Applications Pr og ra m previouslymentioned. It ha s the power t o boost bulky payloads. Paylo au cos t effe ctive ness isgood. Th i s is in keeping with the gener al improveme nt in co st effect iveness a s theboost capabili ty of the launch vehicle increases. F o r the Uprzted Saturn I, t h i scos t ef fect iveness is about $500. 00 per pound of payload b ooste d Into orbi t. It isoperational, ha s manr ate d reliabili ty, all of the requi red facil, .:ies and supportingequipment a r e in ex is tence, the en t i re veh ic le is curren t ly iri production, and i t hasexcellent systems growth potential .

The bas i c Uprated Saturn I and f ive growth vers ions a r e ar rang ed in o rd er ofincreasing boost capabili ty. The vehicle designat ions a r e those used in the secondphase of a Saturn Improvement Study that was just compieted. 'LWLTT' s tands forModified Launch Vehicle .


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On the extr em e left is the vehicle as it exi sts today. The next configurationhas four Minuteman first-s tage solid rocket motor s trap- ons and a 10 f t . extension tothe S-IB first-stage. This is a boost assist vers ion in that al l eight engine s of th efirst-stage and.al1 four solid rocket motors a r e ignited on the launch pad.

Next is the baseline vehicle "with four 120-inch d iam ete r five-seg ment solidrocket motor s t rap-ons. This is a zero -stag e configuration in that only the four solidrocket moto rs a r e ignited on the launch pad. The eight engines of the S-IB a r e igniteda t altitude just before jettison of the solid stra p-on s.

The fourth configuration ha s two seven-seg ment s olid rock et motor str ap- on sand a 20 ft. extensio n to the S -1B. This is als o a boost as si st version with a ll eightS-IB eng ines and th e two solid ro ck et m oto rs ignited on tile launch pad.

The fifth configuration has four five-segment solid rocket motor strap-ons anda 20 ft. S-IB extension. Although at first glance the solid rocket m otor s ap pear tobe seven-segment ra th er than five segment, this is not the c ase. The upper portionsof these s t rap-o ns a r e dummy segments and a re required for s t ructural purposes.The dummy segments allow us to tie into the S-IB spi de r beam; ot herw ise, we wouldbe re quire d to provide additional s tru ctu re on the S-IB tanks at about the location ofthe dotted lines on the drawing. This is a modified boost as si st version. The foursolid rocket moto rs and the fo ur outboard engines of the S--IBa r e ignited on the launchpad. The four rema inin g S-IB engines a r e ignited at altitude just prior to stagingthe four solid rocket motors. The vehicle continues through the boost stag e on theeigh t S-IB eng ines unti l boost er cutoff and ignition of the S-IVB sta ge.

The extreme right configuration has four seven-segment 120-inch diametersolid rock et mo tor s and a 20 ft. extension to the S-IB. Thi s 1s also a modified b o ~ s tass i s t vers ion. The four so lid rocket mot ors and the four ouxboard S-I% engines are


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ignited on the launch pad. The boost phase proceeds in a manner si mi la r to that ofthe previo us vehicle except, of cou rse , the solid rock et motor burning tim e is extended

All of the growth versio ns we re developed with these common prog ram con-side ratio ns: Payload and miss ion flexibility, maintenance of rhianrated reliabili ty,minimum faci lities modification s, low development ris k, low investme nt cos t,excellent co st effectivenes s, and early availabili ty. These considerations highlightou r co nse rvati ve approa ch and emphas is on reliability that has paid off s o well in thepast .

This is the de gre e t o which the alre ad y substantia! capab ility of t h e UpratedSaturn I can be increa sed for l ikely manned ear th orbit missions. It is noteworthythat the vehicle today ha s a payload margin over that cu rrently req uired fo r the A i rFo rc e Manned Orbiting Lab orat ory and the ea rly Apollo Applications miss ions .

Fo r t he NASA Manned Orbiting Resea rch L abo rato ry and the Manned OrbitingTelescope, existing conc epts lie well within the capability cf growth versions of theSaturn I and s om e of thes e c oncepts a r e within the capability of the existing vehicle.All launche s a r e out of KSC and, in the cas e of polar o rbi ts, an allowance is includedfor the re qu ire d dog-leg maneuver.

With a chemical third stage and a fourth o r kick stage, payloads can be launchedon high energy miss ions . The mission deta ils might requ ire a little explanation sinc eon all of the mis sio ns the energy requ ired will va ry with the traje cto ry that is flown.

In the c as e of the Saturn fly-by, flight time ha s been selecte d a s the thi rd variab le -on a two ye ar miss ion about 2,000 pounds could be boosted with the che mical t hir dstag e and about 4,00 0 pounds could be boosted with the chemic al thi rd s ta ge plus akick-stage. Fo r a so lar probe orbit ing the sun at about the sa me distance from thesun as the ea rth but inclined to the ear th' s plane of orbit , the third parame ter is this


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angle of in clination to the eclipti c. Fo r the th i rd p l u ~ ick-stage version, about1,000 pounds could be boosted at a 35-degree inchnatio n anc about 3,000 pounds couldbe boosted at the 30-degree inclination.

Nuclea r propulsion applications, which se em to be the most likely next stepin rock et propulsion, open up the perf orm ance potential shown on thi s slide. Nuclearchara cter i s t ics are : Engine thrus t - 10,000 pounds, engine weight 3,5 00 pounds,engine ISP - 800 seconds , and stag e dry weight - 0. 2 of the weight of the prop ell an ts.The nuclear upper stage is , of course, a hypothetical one but is still a very conser-vative projection of our cu rr en t technology. It is evident that very substantial payloadscan be boosted f o r just about any type of m iss ion you might sele ct.

The Uprated Saturn I has a growth potential that approaches one-half thecapabil ity of th e giant of the Sat urn family, the Satu rn V, and has potential applicationsfo r a11 typ es of s pa ce mi ssi on s. All of t he potentia ls th at have been pr es en te d todaya r e well within ou r capability for accomplishment. In fact , th ese concepts have beenthe subje ct of a s e r ie s of Saturn Improvement Studies conducted by Ch ry sl er Co rpo r-ation Space Division f o r NASA of which the final pre-h ardw are phase is now undercontract.

In today's Uprated Saturn I we have a launch vehicle sy ste m that can boost ove r40,000 pounds into low earth orbit; it is manrated; it has already flown successfuliythree t imes; the Saturn program has a reco rd of 13 su cc es se s out of 13 flights.Ove rall, going back eleven ye a rs t o the launching of o ur f ir st Redstone on July 19, 1956,80 boo ster sta ges built by Ch ry sl er have been launched with no failure s.

We have the hardw are sy st em s today fo r boosting very heavy and bulky pa yh ad sinto orbit and these vehicles have a one-hundred p er cent suc ces s reliabil i ty r ecor d.We plan on incre ased applications fo r the Uprated Saturn I-vehic le and i t s growthvers ions , and a continuation of ou r reliability r ec or d in the nation's spa ce pro gra m.

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the uprated saturn i- it's growth potential and future role in space

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