Ascent propulsion system

Ascent propulsion system (APS)

Apollo LM ascent engine
Country of origin	United States
Date	1964–72
Manufacturer	Bell Aircraft / Rocketdyne
Application	Lunar Ascent Stage/Spacecraft propulsion
Predecessor	Bell 8247
Successor	RS-18
Status	Retired
Liquid-fuel engine
Propellant	N 2O 4 / Aerozine 50
Mixture ratio	1.6
Cycle	Pressure-fed
Pumps	None
Configuration
Chamber	1
Nozzle ratio	46
Performance
Thrust, vacuum	3,500 pounds-force (16 kN)
Thrust-to-weight ratio	16.7 (weight on Earth)
Chamber pressure	120 psia
Specific impulse, vacuum	311 seconds (3.05 km/s)
Burn time	465 seconds
Restarts	Designed for 2 restarts
Dimensions
Length	51 inches (130 cm)
Diameter	31 inches (79 cm)
Dry mass	210 pounds (95 kg)
Used in
Lunar module as ascent engine
References
References	[1]

The ascent propulsion system (APS) or lunar module ascent engine (LMAE) is a fixed-thrust hypergolic rocket engine developed by Bell Aerosystems for use in the Apollo Lunar Module ascent stage. It used Aerozine 50 fuel, and N
₂O
₄ oxidizer. Rocketdyne provided the injector system, at the request of NASA, when Bell could not solve combustion instability problems.^[2]

The LMAE traces its origin to the earlier Bell Aerosystems engines (8096, 8247) used in the RM-81 Agena, the rocket upper stage and satellite support bus developed by Lockheed initially for the canceled WS-117L reconnaissance satellite program.^[3] The Agena served as an upper stage for several defense, intelligence, and exploration programs: SAMOS-E, SAMOS-F (ELINT Ferret) and MIDAS (Missile Defense Alarm System) military early-warning satellites, Corona photo intelligence program, and the Ranger and Lunar Orbiter lunar probes.

The Lockheed Agena target vehicle using the Bell 8247 engine was qualified for 15 restarts for NASA's Project Gemini.^[4]

A total of 365 Agena rockets were launched by NASA and the U.S. Air Force between February 28, 1959, and the last Agena D launched on 12 February 1987, configured as the upper stage of a Titan 34B.^[5][6]

During the spring of 1963, Grumman hired Bell to develop the lunar module ascent engine, on the assumption that Bell's experience in development of the Air Force Agena engine would be transferable to the lunar module requirements. Grumman placed heavy emphasis upon high reliability through simplicity of design, and the ascent engine emerged as the least complicated of the three main engines in the Apollo space vehicle, including the LM descent and CSM service propulsion system engines.

Embodying a pressure-fed fuel system using hypergolic (self-igniting) propellants, the ascent engine was fixed-thrust and nongimbaled, capable of lifting the ascent stage off the Moon or aborting a landing if necessary.^[7]

The engine developed about 3,500 pounds-force (16 kN) of thrust, which produced a velocity of 2,000 meters per second from lunar launch, to LOR, and CM docking.^[7][2] It weighed 180 pounds (82 kg), with a length of 47 inches (120 cm) and diameter of 34 inches (86 cm).^{[8][unreliable source?]}

Rocketdyne brought the lunar module ascent engine out of its 36-year retirement in 2008 for NASA's Exploration Systems Architecture Study (ESAS) engine testing, re-designated it as RS-18, and reconfigured the non-throttleable hypergolic engine to use LOX/methane.^[9]

 This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.

• NASA Technical Note: Apollo Experience Report – Descent Propulsion System. March 1973 31 pages, much detail on both designs, and the testing.
• Apollo Lunar Module Propulsion Systems Overview, NASA