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Centaur for the 1980'S The Space Congress® Proceedings 1981 (18th) The Year of the Shuttle Apr 1st, 8:00 AM Centaur for the 1980's John E. Niesley Advanced Systems Project Engineer, Advanced Centaur Programs, General Dynamics Convair Division Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Niesley, John E., "Centaur for the 1980's" (1981). The Space Congress® Proceedings. 4. https://commons.erau.edu/space-congress-proceedings/proceedings-1981-18th/session-6/4 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. CENTAUR FOR THE 1980s JOHN E. NIESLEY Advanced Systems Project Engineer Advanced Centaur Programs General Dynamics Convair Division San Diego, California ABSTRACT Currently, Centaur is undergoing additional per­ Centaur is currently the world's only operational high- formance improvements for Intelsat, which will energy upper stage, and is the United States primary enhance its capabilities for the 1980s. NASA has also upper stage for launching solar system probes, large recently decided to integrate Centaur with the Space geosynchronous communication satellites, and obser­ Shuttle for solar exploration missions, large future vatories to study the farthest limits of space. Centaur is geosynchronous commercial satellites, and potential currently launched on Atlas, but has also flown with Department of Defense (DoD) missions. These appli­ the larger Titan booster. NASA recently decided to in­ cations will ensure continued use of Centaur through tegrate Centaur with the Space Shuttle for future solar the remainder of the 1980s. system exploration missions. CENTAUR RECORD Current status of the Centaur program is discuss­ A little over ed including: vehicle characteristics, planned perfor­ two decades ago, Centaur was conceived as the mance improvements, and launch schedules. Modifica­ upper stage for United States' solar system ex­ ploration and geosynchronous tions required to integrate Centaur with Shuttle and communications sat­ the resulting capabilities are discussed. ellites. Today that dream has truly been fulfilled by the accomplishments of this vehicle. Centaur has launched INTRODUCTION 22 solar system exploration missions including Centaur development began in 1958 when General Voyager, Viking, Helios, Mariner, Surveyor and Dynamics/Convair was awarded a contract to develop Pioneer. Its selection by NASA for launching the the first space vehicle to use liquid hydrogen fuel. Galileo and International Solar Polar missions from Because NASA's Lewis Research Center (LeRC) did Space Shuttle means continuation of this enviable much of the pioneering work in liquid hydrogen tech­ record. In addition, 24 geosynchronous communica­ nology, LeRC was later assigned technical manage­ tion satellites have been launched as well as 6 space ment of Centaur and contributed to the first successful observatories (Figure 1). Centaur has flown 55 times launch in 1963. This successful working relationship with Atlas and 7 times on Titan for a total of 62 flights continues today. After completing the development and is now ready for integration with the Space phase in 1966, the resulting operational vehicle, called Shuttle. Centaur D, was launched 21 times on Atlas. During the past fifteen years of operational In the early 1970s, Centaur electronics and guid­ flights, Centaur has established itself as a reliable up­ ance systems were completely modernized. A new per stage. 96% of all operational flights were suc­ high-speed digital computer was added that permits ex­ cessful, with 100% or 36 consecutive successes since tensive use of software to perform functions previously 1971. The Pratt and Whitney RL-10 engines have a requiring hardware, thus simplifying new mission perfect flight success record and the current Centaur adaptation. Computer controlled launch set (CCLS) D-l guidance and navigation system has also perform­ was added to provide rapid automatic checkout of the ed 100% successfully on all countdowns and launches Centaur and diagnostic capabilities for anomalies. as indicated in Figure 2. This new version of Centaur, designated D-l, was in­ tegrated with both the Atlas vehicle and the more ATLAS CHARACTERISTICS powerful Titan booster, and has flown 32 operational The Atlas vehicle that boosts Centaur is a stage-and-a- missions. half configuration in which all engines are ignited on 6-39 Missions • Solar system exploration (22) - Voyager, Viking, Helios - Mariner, Pioneer, Surveyor • Communications(25) - Intelsat, Fltsatcom, Comstar • Astronomy (6) - HEAO, OAO Launch platforms • Atlas • Titan Figure 1. Centaur enabled the United States to achieve many dramatic firsts in space and provided a valuable capability for geosynchronous missions. •••^•••••••••••••••••^^^^•^^••••••••••••[^•••i^BaBBBMMBHBBaBBHMI Vehicle operational successes • 96% overall • 100% since 1971 (36 consecutive successes) P&W RL-10 engine • 100% successful flight record (66,000 sec in space) Guidance & Navigation — D-1 (Honeywell IRU & Teledyne DCU) • 100% flight & countdown success (33 missions with 450 operational hours) Figure 2. Centaur's success record proves its reliabilty as a high-energy upper stage. the ground and share common propellant tanks. The control is accomplished by gimbaling the Atlas engines booster engines are jettisoned at approximately 140 during flight under direction of the Centaur guidance seconds into the flight when vehicle acceleration and navigation system. reaches 5.5 g. The sustainer engine continues to burn •until propellant depletion occurs about 110 seconds CENTAUR CHARACTERISTICS later. Two -small vernier engines burn throughout the Centaur is a high energy upper stage powered by two booster phase and provide all roll control during the Pratt & Whitney RL-10 engines developing 33,000 Ib sustainer phase* All engines use liquid oxygen (L(>2) total vacuum thrust at a rated Isp of 446 seconds (see and RP-1 fuel,, which is similar to kerosene. Vehicle Figure 4). The stage burns 30,000 Ib of liquid hydrogen characteristics are shown in Figure 3. (LH2) and liquid oxygen (LC>2) propellants. Tanks are The Atlas vehicle is 10 ft in diameter and approx­ made of thin-walled type 301 stainless steel welded imately 70 ft in length, not including the interstage construction that is pressure stabilized. They are adapter. Tanks are made of thin-walled stainless steel separated by a double-wall vacuum-insulated inter­ bands which are welded together and pressure stabi­ mediate common bulkhead and pressurized with gas­ lized for structural strength, A helium pressurization eous helium. Until now, tank-mounted boost pumps , system maintains tank pressure for structural integrity have been used to provide the required engine inlet and turbopump pressure head during flight. Vehicle pressures. The boost pumps are driven by turbines 640 Liquid oxygen tank Intermediate bulkhead Oxidizer boiloff valve RP-1 tank ^S&&3s^^ Length: 70 ft Vernier ^^vvj^ engine (2) x Diameter: 10 ft Jett wt: Sustainer •Avionics Booster 7,916 Ib engine equipment Sustainer 8,035 Ib Propellants: 286,000 Ib Propulsion;Rocketdyne MA-5 Booster k Booster section Rated thrust (SL); Booster 370,000 ib engine (2f Sustainer 60,000 Ib 01100698-8 Vernier 2,000 Ib Figure 3. The Atlas booster vehicle is a state-and-a-half configuration with a sustainer engine that continues to burn 90 seconds after the initial booster engines are jettisoned. Avionics equipment module Stub Radiation adapter shield or Length: 30 ft insulation Diameter: 10 ft panels - LH2 tank Dry weight: 3,850 Ib Guidance: Inertia! Propulsion: P&W RL-1OA-3-3 Intermediate Rated Thrust: 16,500 Ib per engine bulkhead Rated Isp (vac): 446 sec Propellants: LO.2/LH2; 30,750 Ib LO2 Aft bulkhead Thrust barrel RL-1 0 engines 02030698-9A Figure 4. Centaur characteristics. powered by hydrogen peroxide, the same monopropel- engine bleed for LH2 tank pressurization during iant used in the reaction control system. Beginning engine operation, and hydrazine monopropellant for with vehicle AC-62, minor tank and engine changes the reaction control system., have allowed the elimination of boost pumps. Reduced The Centaur integrated, astrionics system is - illus­ cost and improved reliability and performance will trated in Figure 5. The heart of this system is the Tele- result. Associated changes are gaseous hydrogen dyne Digital Computer Unit (DCU) which has 16,000 6-41 C-BAND AND RANGE SAFETY ABBREVIATIONS Digital Computer Unit PAYLOAD/VEHICLE" Inertial Reference Unit SEQUENCING System Electronics Unit Sequence Control Unit Servo Inverter Unit Remote Multiplex Units Propellant Utilization Computer Controlled Launch Set Control Unit Pyrotechnic ATLAS Computer Controlled Vent and Pressurization System INTERFACES AFT SIGNAL CONDITIONER INSTRUMENTATION SIGNALS 25031215-3 Figure 5. Centaur astrionics system. words of memory, fast execution speed, and extensive apogee kick motor changes. These included an engine input-output capabilities allowing it to perform many thrust increase (1,500 Ib/eng), a zero-gravity parking functions that previously required separate hardware. orbit coast, earlier nose fairing jettison, and weight im­ A Honeywell Inertial Reference Unit (IRU) con­ provements. Additional changes are being incor­ taining four-gimbals, three reference gyros, and three
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