The AJ10-137 engine (20,500 lbf (91 kN) of thrust) was used in the Apollo service module's service propulsion system from first flight in 1966. Trans-Earth injection, from lunar orbit, was the most critical usage of this engine during the Apollo program.

2009年11月1日 · Aerojet - AJ10-137 Apollo Service Module Engine The general configuration of the SPS engine was 20,000 pounds of thrust, with a chamber pressure of 100 psi and specific impulse (Isp) of 314.5. The very large nozzle had an area ratio of 62.5:1 (exit area to throat area).

在Apollo计划中，AJ10的燃料组合发生了变化，应用在Apollo CSM (Command and Service Module，也就是我们熟知的Apollo飞船)，代号为AJ10-137。 氧化剂进化为N2O4，燃料则改为Aerozine 50 (aero-空气的;航空的，zine为hydrazine后半部分)，也就是偏二甲肼和肼按50:50混合。 喷管直径扩大为2.501m，长3.882m，最终推力达到91kN，为Apollo计划出入环月轨道发挥了重 …

Investigation of the Apollo SPS Engine (AJ10-137) Reignitior Characteristics at Pressure A1 titudes Abon0,000 Fe-0, Inc. ; KDC-TR-69-13 (M arch 1969). 7. A 0110 Service Pro ulsion S stem Injector Cold FJow Test, A:O, Inc.; b2* 8. The Reignition Characteristics of the Apollo Service Proplilsion System Engine at Pressure Altitudes AT- -.

2025年2月26日 · The SPS engine was an AJ10-137, built by Aerojet General Corporation of Azusa, California. It burned a hypergolic fuel combination of Aerozine 50 and nitrogen tetraoxide, producing 20,500 pounds of thrust (91.19 kilonewtons).

At the heart of the Apollo SPS was the engine itself, the AJ10-137. Built by Aerojet General Corporation, this liquid-fueled engine delivered a vacuum thrust of 20,500 pounds. It featured a gimbaled nozzle that allowed for thrust vectoring, enabling precise control of the spacecraft’s attitude and trajectory.

Clay Boyce, Aerojet - AJ10-137 Apollo Service Module Engine Remembering the Giants 63 The general configuration of the SPS engine was 20,000 pounds of thrust, with a chamber pressure of 100 psi and specific impulse (Isp) of 314.5. The very large nozzle had an area ratio of 62.5:1 (exit area to throat area).

Engine for Vanguard was AJ10-37; for later Able models AJ10-41 and AJ10-42. Total of 21 stages built and delivered by Aerojet.

Used as Apollo SM engine. Status: Out of Production. Thrust: 97.50 kN (21,919 lbf). Specific impulse: 312 s. Burn time: 585 s. Chamber Pressure: 6.90 bar. Oxidizer to Fuel Ratio: 1.6. Family: Storable liquid. Country: USA. Spacecraft: Apollo CSM, Apollo CSM Block I, Apollo RM. Propellants: N2O4/Aerozine-50. Agency: Aerojet.

It was a throat-gimbaled engine, and it was the first engine to fly with columbium (also known as niobium, used as an alloying element in steels and superalloys) in the nozzle. The general configuration of the SPS engine was 20,000 pounds of thrust, with a chamber pressure of 100 psi and specific impulse (Isp) of 314.5. The very large...