Aerojet AJ10-138 rocket engine
Aerojet historical AJ10-138 model in the AJ10 family: a pressure-fed, restartable storable-propellant engine used in Titan Transtage propulsion and adapted for Voyager work. NASA's Titan III analysis reports 35,584 N (35.584 kN) upper-stage thrust per engine, 310 s specific impulse, approximately 110 kg dry mass, and 2.07 m length; two engines work in tandem on Transtage for 71,168 N combined thrust. This record keeps per-engine values separate from the tandem installation.
Identity
- Aliases
- AJ10-138AJ 10-138AJ10-138 Transtage engine
- Domains
- spaceflight
- Identity Level
- model
- Kind
- liquid-rocket-engine
- Name
- Aerojet AJ10-138 rocket engine
- Status
- historical
Details
- Description
- Aerojet historical AJ10-138 model in the AJ10 family: a pressure-fed, restartable storable-propellant engine used in Titan Transtage propulsion and adapted for Voyager work. NASA's Titan III analysis reports 35,584 N (35.584 kN) upper-stage thrust per engine, 310 s specific impulse, approximately 110 kg dry mass, and 2.07 m length; two engines work in tandem on Transtage for 71,168 N combined thrust. This record keeps per-engine values separate from the tandem installation.
- Dry Mass
- …
- Family
- Length
- …
- Propellants
- nitrogen tetroxideAerozine-50
- Rocket Specs
- Cycle
- pressure-fed
- Restartable
- Yes
- Vacuum Specific Impulse
- …
- Vacuum Thrust
- …
Links
Assets & Meta
- Creation Time
- August 15, 2026 at 05:34:44 UTC
- Updated Time
- August 22, 2026 at 06:51:02 UTC
Other
- Sources
- Accessed Date
- 2026-08-14
- Note
- NASA's Voyager Transtage study identifies two unmodified pressure-fed fixed-thrust AJ10-138 engines, their common-frame installation, combined 16,000 lbf vacuum thrust, and multiple zero-gravity restarts.
- Publisher
- NASA Technical Reports Server
- Title
- Voyager Spacecraft System Final Report
- Accessed Date
- 2026-08-14
- Note
- NASA's Titan III propulsion analysis identifies the Transtage as two AJ10-138 engines working in tandem, reports 35,584 N maximum thrust and 310 s specific impulse per engine, and gives approximately 110 kg dry mass and 2.07 m length; the tandem output is 71,168 N.
- Publisher
- NASA Technical Reports Server
- Title
- Titan III Propulsion Systems