Titan IIIC
The Titan IIIC was an expendable launch system used by the United States Air Force from 1965 until 1982. It was the first Titan booster to feature large solid rocket motors and was planned to be used as a launcher for the Dyna-Soar, though the spaceplane was cancelled before it could fly. The majority of the launcher's payloads were DoD satellites, for military communications and early warning, though one flight was performed by NASA. The Titan IIIC was launched exclusively from Cape Canaveral while its sibling, the Titan IIID, was launched only from Vandenberg AFB.
History
The Titan rocket family was established in October 1955 when the Air Force awarded the Glenn L. Martin Company a contract to build an intercontinental ballistic missile. It became known as the Titan I, the nation's first two-stage ICBM, and replaced the Atlas ICBM as the second underground, vertically stored, silo-based ICBM. Both stages of the Titan I used kerosene and liquid oxygen as propellants. A subsequent version of the Titan family, the Titan II, was similar to the Titan I, but was much more powerful. Designated as LGM-25C, the Titan II was the largest USAF missile at the time and burned Aerozine 50 and nitrogen tetroxide rather than RP-1 and LOX.The Titan III family consisted of an enhanced Titan II core with or without solid rocket strap-on boosters and an assortment of upper stages. All Solid Rocket Motor -equipped Titans launched with only the SRMs firing at liftoff, the core stage not activating until T+105 seconds, shortly before SRM jettison. The Titan IIIA and IIIB had no SRMs. The Titan III launchers provided assured capability and flexibility for launch of large-class payloads.
All Titan II/III/IV vehicles contained a special range safety system known as the Inadvertent Separation Destruction System that would activate and destroy the first stage if there was a premature second stage separation. Titans that carried Solid Rocket Boosters had a second ISDS that consisted of several lanyards attached to the SRBs that would trigger and automatically destroy them if they prematurely separated from the core, said "destruction" consisting mainly of splitting the casings open to release the pressure inside and terminate thrust. The ISDS would end up being used a few times over the Titan's career.
Another slight modification to SRB-equipped Titans was the first stage engines being covered instead of the open truss structure on the Titan II/IIIA/IIIB. This was to protect the engines from the heat of the SRB exhaust.
Titan III/IV SRBs were fixed nozzle and for roll control, a small tank of nitrogen tetroxide was mounted to each motor. The would be injected into the SRB exhaust to deflect it in the desired direction.
As the IIIC consisted of mostly proven hardware, launch problems were generally only caused by the upper stages and/or payload. The second launch in October 1965 failed when the Transtage suffered an oxidizer leak and was unable to put its payload into the correct orbit. The third launch in December experienced a similar failure.
The fifth Titan IIIC failed shortly after launch when pieces of the payload fairing started breaking off. Around 80 seconds, the remainder of the shroud disintegrated, causing loss of launch vehicle control as well as the payload. The ISDS activated automatically when one of the SRBs broke away from the stack and destroyed the entire launch vehicle. The exact reason for the shroud failure was not determined, but the fiberglass payload shrouds used on the Titan III up to this point were replaced with a metal shroud afterwards.
A Titan IIIC in November 1970 failed to place its missile early warning satellite in the correct orbit due to a Transtage failure and a 1975 launch of a DSCS military comsat left in LEO by another Transtage failure.
On March 25, 1978, a launch of a DSCS satellite ended up in the Atlantic Ocean when the Titan second stage hydraulic pump failed, resulting in engine shutdown approximately 470 seconds after launch. The Range Safety destruct command was sent, but it was unclear if the stage received it or if it had already broken up by that point.
The first Titan IIIC flew on June 18, 1965 and was the most powerful launcher used by the Air Force until it was replaced by the Titan 34D in 1982. The last IIIC was launched in March 1982.
Design
The Titan IIIC weighed about 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 in diameter, long, and weighed nearly. They produced a combined thrust at sea level and burned for approximately 115 seconds. Solid motor jettison occurred at approximately 116 seconds.
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 that burned about of Aerozine 50 and nitrogen tetroxide and produced thrust over 147 seconds. 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 of propellant and was powered by a single Aerojet LR-91-AJ9, which produced for 145 seconds.
The upper stage, the Titan Transtage, also burned Aerozine 50 and NTO. Its two Aerojet AJ-10-138 engines were restartable, 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. Transtage contained about of propellant and its engines delivered.
General characteristics
- Primary Function: Space booster
- Builder: Martin Marietta
- Power Plant:
- *Stage 0 consists of two solid rocket motors.
- *Stage 1 uses two LR87 liquid propellant engines.
- *Stage 2 uses one LR91 liquid propellant engine.
- *Stage 3 uses two Aerojet AJ-10-138 liquid propellant engines.
- Length: 42 m
- *Stage 0: 25.91 m
- *Stage 1: 22.28 m
- *Stage 2: 7.9 m
- *Stage 3: 4.57 m
- Diameter:
- *Stage 0: 3.05 m
- *Stage 1: 3.05 m
- *Stage 2: 3.05 m
- *Stage 3: 3.05 m
- Mass:
- *Stage 0: Empty 33,798 kg/ea; Full 226,233 kg/ea
- *Stage 1: Empty 5,443 kg; Full 116,573 kg
- *Stage 2: Empty 2,653 kg; Full 29,188 kg
- *Stage 3: Empty 1,950 kg; Full 12,247 kg
- Lift capability:
- *Up to 28,900 lb into a low Earth orbit with 28 degrees inclination.
- *Up to 6,600 lb into a geosynchronous transfer orbit when launched from Cape Canaveral Air Force Station, FL.
- Maximum takeoff weight: 626,190 kg
- Cost:
- Date deployed: June 1965.
- Launch sites: Cape Canaveral Air Force Station, FL., and Vandenberg Air Force Base, CA.
Launch history
| Date/Time | Launch Site | S/N | Payload | Outcome | Remarks |
| 18 June 1965 14:00 | CCAFS LC-40 | 3C-7 | N/A | Transtage test flight | |
| 14 October 1965 17:24 | CCAFS LC-40 | 3C-4 | LCS-2 OV2-1 | Transtage failed in low Earth orbit due to oxidizer tank leak | |
| 21 December 1965 14:00 | CCAFS LC-41 | 3C-8 | LES-3 LES-4 OV2-3 OSCAR 4 | Transtage failed during 3rd burn due to stuck oxidizer valve; left payloads in GTO | |
| 16 June 1966 14:00 | CCAFS LC-41 | 3C-11 | OPS-9311 OPS-9312 OPS-9313 OPS-9314 OPS-9315 OPS-9316 OPS-9317 GGTS-1 | ||
| 26 August 1966 14:00 | CCAFS LC-41 | 3C-12 | 7X IDCSP GGTS-2 | Payload fairing broke up at T+78 seconds. RSO T+83 seconds. | |
| 3 November 1966 13:50 | CCAFS LC-40 | 3C-9 | Gemini B OV1-6 OV4-1R/T OV4-3 | Gemini B was launched on a sub-orbital trajectory | |
| 18 January 1967 14:19 | CCAFS LC-41 | 3C-13 | OPS-9321 OPS-9322 OPS-9323 OPS-9324 OPS-9325 OPS-9326 OPS-9327 OPS-9328 | ||
| 28 April 1967 10:01 | CCAFS LC-41 | 3C-10 | OPS-6638 OPS-6679 ORS-4 OV5-1 OV5-3 | ||
| 1 July 1967 13:15 | CCAFS LC-41 | 3C-14 | OPS-9331 OPS-9332 OPS-9333 OPS-9334 LES-5 DODGE | ||
| 13 June 1968 14:03 | CCAFS LC-41 | 3C-16 | OPS-9341 OPS-9342 OPS-9343 OPS-9344 OPS-9345 OPS-9346 OPS-9347 OPS-9348 | ||
| 26 September 1968 07:37 | CCAFS LC-41 | 3C-5 | LES-6 OV2-5 OV5-2 OV5-4 | ||
| 9 February 1969 21:09 | CCAFS LC-41 | 3C-17 | TACSAT 1 | ||
| 23 May 1969 07:57 | CCAFS LC-41 | 3C-15 | OPS-6909 OPS-6911 OV5-5 OV5-6 OV5-9 | ||
| 8 April 1970 10:50 | CCAFS LC-40 | 3C-18 | OPS-7033 OPS-7044 | ||
| 6 November 1970 10:36 | CCAFS LC-40 | 3C-19 | DSP-1 | Transtage 3rd burn failure left satellite in unusable lower than planned orbit | |
| 5 May 1971 07:43 | CCAFS LC-40 | 3C-20 | DSP-2 | ||
| 3 November 1971 03:09 | CCAFS LC-40 | 3C-21 | DSCS-II-1 DSCS-II-2 | ||
| 1 March 1972 09:39 | CCAFS LC-40 | 3C-22 | DSP-3 | ||
| 12 June 1973 07:14 | CCAFS LC-40 | 3C-24 | DSP-4 | ||
| 13 December 1973 23:57 | CCAFS LC-40 | 3C-26 | DSCS-II-3 DSCS-II-4 | ||
| 30 May 1974 13:00 | CCAFS LC-40 | 3C-27 | ATS-6 | ||
| 20 May 1975 14:03 | CCAFS LC-40 | 3C-25 | DSCS-II-5 DSCS-II-6 | Transtage inertial measurement unit failure caused it to be stranded in low Earth orbit. | |
| 14 December 1975 05:15 | CCAFS LC-40 | 3C-29 | DSP-5 | ||
| 15 March 1976 01:25 | CCAFS LC-40 | 3C-30 | LES-8 LES-9 Solrad-11A Solrad-11B | ||
| 26 June 1976 03:00 | CCAFS LC-40 | 3C-28 | DSP-6 | ||
| 6 February 1977 06:00 | CCAFS LC-40 | 3C-23 | DSP-7 | ||
| 12 May 1977 14:27 | CCAFS LC-40 | 3C-32 | DSCS-II-7 DSCS-II-8 | ||
| 25 March 1978 18:09 | CCAFS LC-40 | 3C-35 | DSCS-II-9 DSCS-II-10 | Second stage hydraulics pump failure. RSO T+480 seconds. | |
| 10 June 1978 19:08 | CCAFS LC-40 | 3C-33 | OPS-9454 | ||
| 14 December 1978 00:40 | CCAFS LC-40 | 3C-36 | DSCS-II-11 DSCS-II-12 | ||
| 10 June 1979 13:30 | CCAFS LC-40 | 3C-31 | DSP-8 | ||
| 1 October 1979 11:22 | CCAFS LC-40 | 3C-34 | OPS-1948 | ||
| 21 November 1979 02:09 | CCAFS LC-40 | 3C-37 | DSCS-II-13 DSCS-II-14 | ||
| 16 March 1981 13:30 | CCAFS LC-40 | 3C-40 | DSP-9 | ||
| 31 October 1981 09:22 | CCAFS LC-40 | 3C-39 | OPS-4029 | ||
| 6 March 1982 19:25 | CCAFS LC-40 | 3C-38 | DSP-10 |