Encyclopedia Astronautica
LR87-11


Aerojet N2O4/Aerozine-50 rocket engine. 1218.8 kN. Out of production. Isp=302s. Powered Titan 3 and 4 first stages. Replaced the -9 model, first flown 1968. First flight 1964.

Replacing the 9 model, this is the only engine - together with its stage 2 derivative - to be operated on storable propellants as well as LOX/kerosene and tested on LOX/LH2.. Manufacturer: AeroJet Propulsion Division. Applications: Titan 3 & 4 stage 1. First Flown: 1968 Titan 3, 1989 Titan 4. Dry Mass: 2281 kg (paired), 758 kg (single). Length: 3.84 m to top of thrust structure, 3.13 m to top of turbopump assembly. Maximum Diameter: 1.14 m. Mounting: fixed pair. Engine Cycle: gas generator. Oxidizer: nitrogen tetroxide at 540.7 kg/sec. Fuel: Aerozine-50 at 284 kg/sec. Mixture Ratio (O/F). 1.91:1. Thrust: 2437.5 kN vacuum paired. Isp: 301 sec vacuum. Expansion Ratio: 15:1. Combustion Chamber Pressure: 58.3 atm. Cooling Method: fuel regenerative & ablative skirt.Used in Titan 4-1; Titan 3B-1; Titan 3A-1.

Thrust (sl): 968.400 kN (217,705 lbf). Thrust (sl): 98,754 kgf. Engine: 758 kg (1,671 lb). Chamber Pressure: 59.10 bar. Area Ratio: 15. Thrust to Weight Ratio: 163.955030945495. Oxidizer to Fuel Ratio: 1.91. Coefficient of Thrust vacuum: 3.03319858090835. Coefficient of Thrust sea level: 2.77590870097696.

Status: Out of production.
Height: 3.84 m (12.59 ft).
Diameter: 1.14 m (3.74 ft).
Thrust: 1,218.80 kN (273,997 lbf).
Specific impulse: 302 s.
Specific impulse sea level: 250 s.
Burn time: 200 s.
Number: 534 .

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Associated Countries
See also
Associated Launch Vehicles
  • Titan 3BAS2 American orbital launch vehicle. Configuration of Titan 3B proposed by Martin in mid-1960's. Titan 3B for deep space missions with Centaur upper stage, Algol strapons for liftoff thrust augmentation. Never flown. More...
  • Titan 3A American orbital launch vehicle. Titan with Transtage third stage. Core for Titan 3C. More...
  • Titan 3C American orbital launch vehicle. Titan 3A with five segment solid motors. Man-rated design originally developed for Dynasoar spaceplane. More...
  • Titan 3M American orbital launch vehicle. Man-rated launch vehicle designed for MOL and other missions of the 1970's. Malfunction Detection System initiated abort procedures during launch. Also suited for launch of 'bulbous and lifting body payloads'. 7 segment UA1207 motors developed but not used until Titan 4 in 1990's. Cancelled with MOL program in 1969. More...
  • Titan 3C7 American orbital launch vehicle. Variant of Titan 3C with seven segment solid motors. Proposed by Martin for precise delivery of payloads beyond Titan 3C capacity into geosynch orbit. Never flown. More...
  • Titan 3B American orbital launch vehicle. Titan core with Agena upper stage. Found to be more cost effective and higher performance than using Transtage. More...
  • Titan 3D American orbital launch vehicle. Titan 3C without transtage. More...
  • Titan 3E American orbital launch vehicle. Titan 3D with Centaur D-1T upper stage. Used by NASA for deep space missions in 1970's. More...
  • Titan 34B American orbital launch vehicle. Stretched Titan core, originally developed for Titan 3M MOL, with Agena D upper stage. Guidance provided by the Agena upper stage. The Agena and its payload were completely enclosed in a 3.05 m diameter shroud. 'Ascent Agena' seperated after orbital insertion and did not remain attached to the payload. More...
  • Titan 34D American orbital launch vehicle. Stretched Titan core designed for use with 5 1/2 segment solid rocket motors. IUS (Interim/Inertial Upper Stage) solid upper stages, Transtage, or used without upper stages. More...
  • Titan 4 American orbital launch vehicle. Developed to handle military payloads designed for launch on Shuttle from Vandenberg before the USAF pulled out of the Shuttle program after the Challenger disaster. Further stretch of core from Titan 34, 7-segment solid rocket motors (developed for MOL but not used until 25 years later). Enlarged Centaur G used as upper stage (variant of stage designed for Shuttle but prohibited for flight safety reasons after Challenger). Completely revised electronics. All the changes resulted in major increase in cost of launch vehicle and launch operations. More...
  • Barbarian MM American heavy-lift orbital launch vehicle. The Zenith Star space-based chemical laser missile defence weapon required a launch vehicle capable of placing a 45,000 kg payload into low earth orbit. Martin and Aerojet turned to their work 20 years earlier on advanced Titans for the MOL program. These earlier studies were combined with new concepts for tank construction and materials. The Martin Barbarian was a 4.57 m diameter Titan vehicle (instead of the customary 3.05 m) with four LR-87 engines on the first stage, and a single LR-87 engine on the second stage. More...
  • Titan 4B American orbital launch vehicle. Titan 4 with Upgraded Solid Rocket Motors replacing UA1207. Developed to improve performance for certain missions, and reduce number of field joints in motor after Challenger and Titan 34D explosions involving segmented motors. More...

Associated Manufacturers and Agencies
  • Aerojet American manufacturer of rockets, spacecraft, and rocket engines. Aerojet, Sacramento, CA, USA. More...

Associated Propellants
  • N2O4/Aerozine-50 Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Aerozine was a 50-50 mixture of hydrazine and UDMH developed for use in the Titan 2 missile. Copied in one Russian missile but otherwise straight UDMH used more commonly. Higher boiling point than UDMH. More...

Associated Stages
  • Barbarian MM-1 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 400,000/25,000 kg. Thrust 6,080.00 kN. Vacuum specific impulse 302 seconds. All values roughly estimated based on number of engines and diameter given. More...
  • Barbarian MM-2 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 80,000/6,000 kg. Thrust 1,214.00 kN. Vacuum specific impulse 302 seconds. All values roughly estimated based on number of engines and diameter given. More...
  • Titan 3A-1 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 116,573/5,443 kg. Thrust 2,339.76 kN. Vacuum specific impulse 302 seconds. More...
  • Titan 3B-1 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 139,935/7,000 kg. Thrust 2,413.19 kN. Vacuum specific impulse 302 seconds. More...
  • Titan 4-1 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 163,000/8,000 kg. Thrust 2,428.31 kN. Vacuum specific impulse 302 seconds. More...

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