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Transtage was developed in anticipation of a requirement to launch military payloads to geostationary orbit; a contract for development of the stage was issued on 20 August 1962. Transtage used a pressure-fed two-chamber configuration, using Aerozine 50 fuel and nitrogen tetroxide as oxidizer; the thrust chambers were gimbaled for steering and each produced 8,000 lbf (36 kN) of thrust. The design specification required up to three restarts during the first six hours of a mission.
Forty-seven Titan III launches are known to have used Transtage upper stages; of those, three are known to have suffered launch failures. The first launch, boosted by a Titan IIIA, occurred on 1 September 1964; the Transtage failed to pressurize, resulting in premature engine cutoff, and a failure to reach orbit. The second launch, on 10 December, was successful, and all ensuing launches used the Titan IIIC launch vehicle. The last launch of a Transtage was on 4 September 1989, boosted by a Titan 34D rocket.
Wade, Mark. "AJ10-138". Encyclopedia Astronautica. Archived from the original on December 28, 2016. Retrieved 2019-07-24.
Foradori, Paolo; Giampiero Giacomello; Alessandro Pascolini (2017). Arms Control and Disarmament: 50 Years of Experience in Nuclear Education. London: Palgrage Macmillan. pp. 56–57. ISBN978-3-319-62258-3.
Hunley, J.D. (2007). The Development of Propulsion Technology for U.S. Space-Launch Vehicles, 1926-1991. College Station, TX: Texas A&M University Press. p. 168. ISBN978-1-58544-588-2.
^ Heyman, Jos (17 March 2003). "Martin Marietta SSB-10 Transtage". Directory of U.S. Military Rockets and Missilesm Appendix 3: Space Vehicles. Designation-Systems. Retrieved 2017-12-17.
A Transtage
