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J2 - CP4-12_1315- 1

Development of the J-2 Rocket Engine. Paul Coffman July 13, 2004. Rocketdyne Propulsion & Power. J2 - CP4-12_1315- 1 .ppt. The J-2 Engine. Launch Escape Tower. Requirements Man rated High thrust / performance Multiple space starts Gimbal for TVC Application to both SIVB & S-II stages

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J2 - CP4-12_1315- 1

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  1. Development ofthe J-2 Rocket Engine Paul Coffman July 13, 2004 RocketdynePropulsion & Power J2 - CP4-12_1315-1.ppt

  2. The J-2 Engine Launch Escape Tower • Requirements • Man rated • High thrust / performance • Multiple space starts • Gimbal for TVC • Application to both SIVB & S-II stages • Usage on Apollo, Skylab & ASTP • SIB/SIVB – 9 flights • SV/SII – 13 flights • SV/SIVB – 12 flights Command Module Launch Escape Tower Service Module Command Module Lunar Module Adapter S-IVB Stage Instrument Unit Service Module LH2 Tank Lunar Module Adapter LOX Tank J-2 Engines (1) Instrument Unit S-II Stage LH2 Tank S-IVB Stage LH2 Tank LOX Tank LOX Tank LOX Tank J-2 Engines (5) J-2 Engines (1) LOX Tank S-IC Stage RP-1 Tank Outer LOX Tank S-IB Stage RP-1 Tank H-1 Engines (8) F-1 Engines (5) Center LOX Tank Saturn IB Vehicle Saturn V Vehicle

  3. J-2 Basic Engine Features Performance & Weight Nominal vacuum thrust (lb) 230,000 Nominal vacuum specific impulse 425 Chamber pressure (psia) 717(nozzle stagnation) Engine mixture ratio 5.5:1calibration (O/F) Basic engine dry weight (lb) 2,754 Engine dry weight (lb) 3,492(including accessories) Description Pump-fed, liquid-propellant rocket engine Propellants: liquid oxygen & liquid hydrogen Nozzle area ratio: 27.5:1 Tubular-wall thrust chamber, regeneratively cooled Separate oxidizer & fuel turbopumps Bearing lubrication: liquid oxygen & liquid hydrogen Turbine drive: gas generator burning main propellants 34 Flights, 86 Engines, 98% Reliability

  4. J-2 Engine Development • Development engines - 38 • Engine tests – 1730 through qualification • Engine (and stage) test facilities • Rocketdyne/ Santa Susana Field Lab • Including one (1) simulated altitude facility • NASA / MSFC • NASA / MTF (now SSC) • USAF / AEDC simulated altitude facility

  5. J-2 Engine J2072 Qualification Program

  6. J-2 Engine Development Summary • Began in 1960 as part of the national goal • Schedule driven • Low technology readiness in many areas • Accelerated development accomplished • First long duration engine test (250 sec) in two years • Initial formal test demonstration in four years • Formal development (QUAL II) completed in six years • “Flight support” testing continued • J-2S & Linear engine development through 1973 • Over eighty different unplanned engine cutoff modes experienced • Prompt resolution enabled Apollo mission successes • J-2 engine experience enabled subsequent programs • SSME • RS-68 • XRS-2200 (X-33)

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