Rocketdyne XRS-2200 explained

XRS-2200
Country Of Origin:	United States
Designer:	Rocketdyne
Manufacturer:	Rocketdyne
Date:	1999
Purpose:	X-33
Predecessor:	J-2S
Status:	Experimental
Cycle:	Gas Generator
Type:	liquid
Fuel:	LH2
Oxidiser:	LOX
Nozzle Ratio:	58:1
Thrust(Sl):	909kN
Thrust(Vac):	1184kN
Chamber Pressure:	58bar
Length:	2.01m (06.59feet)

The Rocketdyne XRS-2200 was an experimental linear aerospike engine developed in the mid-1990s for the Lockheed Martin X-33 program.^{[1] [2] [3]} The design was based on the J-2S, the upgraded version of the Apollo era J-2 engine developed in the 1960s. The XRS-2200 used the J-2's combustion cycle and propellant choice.^[4]

Rocketdyne intended to develop the subscale XRS-2200 into the RS-2200 for use on the VentureStar. While the X-33 program was cancelled, two XRS-2200 engines were produced and tested.^[5]

Notes and References

1. Web site: Boeing Rocketdyne XRS-2200 Linear Aerospike. engineering.purdue.edu. 2019-08-26.
2. Web site: XRS-2200 Link . www.hq.nasa.gov . . Washington D.C., U.S. . 2019-09-29 . 2016-03-22 . https://web.archive.org/web/20160322075222/http://www.hq.nasa.gov/office/pao/History/x-33/xrs2200.htm . dead .
3. Book: Rowbotham, Maureen . https://arc.aiaa.org/doi/abs/10.2514/6.1999-2334 . XRS-2200 linear aerospike engine - Use of Pro/ENGINEER for determining mass properties . 35th Joint Propulsion Conference and Exhibit . 1999 . . U.S. . 10.2514/6.1999-2334 . 2019-09-29.
4. Web site: XRS-2200. https://web.archive.org/web/20161228054952/http://astronautix.com/x/xrs-2200.html. dead. December 28, 2016. www.astronautix.com. 2019-08-26. Encyclopedia Astronautica.
5. Web site: X-33 XRS-2200 Linear Aerospike Engine Sea Level Plume Radiation. D'Agostino. M.G.. January 2001. NASA Technical Reports Server.