Editing Titan IIIC (section)

==Design==
[[Image:Titan-3C MOL-Gemini-B-Test 3.jpg|left|220px|thumb|[[Manned Orbiting Laboratory|MOL]] mockup launch by a Titan IIIC on Nov. 3, 1966 from [[Cape Canaveral Air Force Station Launch Complex 41|LC-41]] Cape Canaveral]]

The Titan IIIC weighed about {{convert|626000|kg|abbr=on|order=flip}} at liftoff and consisted of a two-stage Titan core and upper stage called the Titan [[Transtage]], both burning [[hypergolic]] liquid fuel, and two large [[UA1205]] solid rocket motors.

The solid motors were ignited on the ground and were designated "stage 0". Each motor composed of five segments and was {{convert|10|ft|abbr=on}} in diameter, {{convert|85|ft|abbr=on}} long, and weighed nearly {{convert|500000|lb|abbr=on}}. They produced a combined {{convert|2380000|lbf|kN|abbr=on}} thrust at sea level and burned for approximately 115 seconds.<ref name=anxt3>{{cite web|title=Titan 3C|url=http://www.astronautix.com/lvs/titan3c.htm|website=Astronautix|access-date=February 2, 2015|url-status=dead|archive-url=https://web.archive.org/web/20141225140441/http://www.astronautix.com/lvs/titan3c.htm|archive-date=December 25, 2014}}</ref> Solid motor jettison occurred at approximately 116 seconds.<ref name=BTs>{{cite web|title=Titan|url=http://www.braeunig.us/space/specs/titan.htm|website=braeunig.us|access-date=February 2, 2015}}</ref>

The first core stage ignited about 5 seconds before SRM jettison. Designated the Titan 3A-1, this stage was powered by a twin nozzle [[Aerojet]] LR-87-AJ9 engine <ref name=":0">{{cite web|last1=Norbert|first1=Bruge|title=Titan III/IV Propulsion|url=http://www.b14643.de/Spacerockets_2/United_States_6/Titan_III/Description/Frame.htm|website=B14643.de|publisher=Norbert Bruge|access-date=20 June 2017}}</ref> that burned about {{convert|110000|kg|abbr=on|order=flip}} of  [[Aerozine 50]] and [[Dinitrogen tetroxide|nitrogen tetroxide]] (NTO) and produced {{convert|1941.7|kN|lbf|abbr=on}} thrust over 147 seconds.<ref name=":1">{{Cite web |title=Titan-3C (Titan-IIIC) |url=https://space.skyrocket.de/doc_lau_det/titan-3c.htm |access-date=2025-03-14 |website=Gunter's Space Page |language=en}}</ref> The Aerozine 50 and NTO were stored in structurally independent tanks to minimize the hazard of the two mixing if a leak should have developed in either tank.

The second core stage, the Titan 3A-2, contained about {{convert|25000|kg|abbr=on|order=flip}} of propellant and was powered by a single [[Aerojet]] LR-91-AJ9,<ref name=":1" /> which produced {{convert|453.7|kN|lbf|abbr=on}} for 145 seconds.<ref name=":0" />

The upper stage, the Titan [[Transtage]], also burned Aerozine 50 and NTO. Its two Aerojet [[AJ-10| AJ-10-138]] engines were restartable,<ref name=":1" /> allowing flexible orbital operations including orbital trimming, geostationary transfer and insertion, and delivery of multiple payloads to different orbits. This required complex guidance and instrumentation.<ref name=BTs/> Transtage contained about {{convert|10000|kg|abbr=on|order=flip}} of propellant and its engines delivered {{convert|16000|lbf|kN|abbr=on}}.