Aerojet LR91-AJ-5
Exact Aerojet LR91-AJ-5 liquid rocket engine variant used as the Titan II second-stage engine. Official NASA and USAF references identify the variant with Aerozine 50/nitrogen tetroxide propellants and approximately 440 kN (100,000 lbf) vacuum thrust.
Identity
- Aliases
- LR91-AJ-5Aerojet-General LR91-AJ-5
- Domains
- spaceflight
- Identity Level
- variant
- Kind
- liquid-rocket-engine
- Name
- Aerojet LR91-AJ-5
- Status
- historical
Details
- Description
- Exact Aerojet LR91-AJ-5 liquid rocket engine variant used as the Titan II second-stage engine. Official NASA and USAF references identify the variant with Aerozine 50/nitrogen tetroxide propellants and approximately 440 kN (100,000 lbf) vacuum thrust.
- Propellants
- Aerozine 50nitrogen tetroxide
- Rocket Specs
- Vacuum Thrust Kn
- 440
Links
Assets & Meta
- Creation Time
- August 7, 2026 at 04:55:13 UTC
- Updated Time
- August 20, 2026 at 12:09:25 UTC
Other
- Sources
- Accessed Date
- 2026-08-06
- Note
- Official USAF museum fact sheet identifies the Titan II second-stage engine as Aerojet LR91-AJ-5 rated at 100,000 lb thrust and using Aerozine 50/nitrogen tetroxide propellants.
- Publisher
- National Museum of the United States Air Force
- Title
- Martin Marietta SM-68B/LGM-25C Titan II
- Accessed Date
- 2026-08-06
- Note
- NASA launch-vehicle table independently lists Titan II second-stage LR-91-AJ-5 and its N2O4/A-50 propellant combination.
- Publisher
- NASA
- Title
- Aeronautics and Space Report of the President 1999
- Accessed Date
- 2026-08-20
- Note
- NASA U.S. Space Launch Vehicles table lists LR-91-AJ-5 as Titan II stage 2 with 440.0 kN thrust; the upper-stage context supports storing this value as vacuum thrust rather than sea-level thrust.
- Publisher
- NASA
- Title
- NASA Technical Memorandum 110743