Editing Titan IIIC

{{Short description|Expendable launch system used by the US Air Force}}
{{infobox rocket
|image = DF-SC-84-05192 cropped.jpeg
|caption = Launch of a Titan IIIC
|name = Titan IIIC
|function = [[Medium-lift launch vehicle]]
|manufacturer = [[Glenn L. Martin Company|Martin]]
|country-origin = United States
|height = {{convert|137|ft|m|abbr=on}}
|diameter ={{convert|10|ft|m|abbr=on}}
|mass = {{convert|1,380,510|lb|kg|abbr=on}}
|stages = 2-3
|family = [[Titan (rocket family)|Titan]]
|status = Retired
|sites = [[Cape Canaveral Air Force Station Launch Complex 40|LC-40]] & [[Cape Canaveral Air Force Station Launch Complex 41|41]], [[Cape Canaveral Air Force Station|CCAFS]]<br>[[Vandenberg AFB Space Launch Complex 6|SLC-6]], [[Vandenberg AFB]]
|launches = 36
|success = 31
|fail = 5
|first=18 June 1965
|last=6 March 1982
|capacities = 
  {{Infobox rocket/payload
  |location =  [[Low Earth orbit|LEO]]
  |kilos    =  {{cvt|28900|lb}}
  }}
  {{Infobox rocket/payload
  |location =  [[Geostationary transfer orbit|GTO]]
  |kilos    =  {{cvt|6600|lb}}
  }}
  {{Infobox rocket/payload
  |location =  [[Mars]]
  |kilos    =  {{cvt|2650|lb}}
  }}
|stagedata    =  <!--insert one of the following templates for each stage:-->
  {{Infobox rocket/stage
  |type       =  booster
  |diff       =  Stage 0
  |stageno    =  <!--position of stage in rocket, spelled out (eg. First, Second, etc), required-->
  |name       =  [[UA1205]]
  |number     =  2
  |length     =  <!--length of a single booster/stage in metres, use {{convert}}, optional-->
  |diameter   =  <!--diameter of a single booster/stage in metres, use {{convert}}, optional-->
  |width      =  <!--width of a single booster/stage if not axisymmetric, use {{convert}}, optional-->
  |empty      =  <!--empty mass of a single booster/stage in kilograms, use {{convert}}, optional-->
  |gross      =  <!--gross (fuelled) mass of a single booster/stage, use {{convert}}, optional--> 
  |propmass   =  <!--propellant mass carried by a single booster/stage in kilograms, use {{convert}}, optional--> 
  |engines    =  
  |thrust     =  {{convert|1,315,000|lbf|kN|abbr=on}}
  |total      =  <!--total thrust for all boosters in kN, use {{convert}}, optional-->
  |SI         =  263 secs
  |burntime   =  115 seconds
  |fuel       =  [[solid rocket|Solid]]
  }}
  {{Infobox rocket/stage
  |type       =  stage
  |diff       =  <!--variant of rocket this is used on, optional-->
  |stageno    =  First
  |name       =  <!--name of the stage/booster, optional-->
  |number     =  <!--number of boosters, required if type = booster-->
  |length     =  <!--length of a single booster/stage in metres, use {{convert}}, optional-->
  |diameter   =  <!--diameter of a single booster/stage in metres, use {{convert}}, optional-->
  |width      =  <!--width of a single booster/stage if not axisymmetric, use {{convert}}, optional-->
  |empty      =  <!--empty mass of a single booster/stage in kilograms, use {{convert}}, optional-->
  |gross      =  <!--gross (fuelled) mass of a single booster/stage, use {{convert}}, optional--> 
  |propmass   =  <!--propellant mass carried by a single booster/stage in kilograms, use {{convert}}, optional--> 
  |engines    =  2 [[LR-87|LR87-AJ9]]
  |thrust     =  {{convert|1941.7|kN|lbf|abbr=on}}
  |total      =  <!--total thrust for all boosters in kN, use {{convert}}, optional-->
  |SI         =  <!--specific impulse of an individual booster/stage, in secs, optional-->
  |burntime   =  147 seconds
  |fuel       =  [[Dinitrogen tetroxide|N<sub>2</sub>O<sub>4</sub>]] / [[Aerozine 50]]
  }}
  {{Infobox rocket/stage
  |type       =  stage
  |diff       =  <!--variant of rocket this is used on, optional-->
  |stageno    =  Second
  |name       =  <!--name of the stage/booster, optional-->
  |number     =  <!--number of boosters, required if type = booster-->
  |length     =  <!--length of a single booster/stage in metres, use {{convert}}, optional-->
  |diameter   =  <!--diameter of a single booster/stage in metres, use {{convert}}, optional-->
  |width      =  <!--width of a single booster/stage if not axisymmetric, use {{convert}}, optional-->
  |empty      =  <!--empty mass of a single booster/stage in kilograms, use {{convert}}, optional-->
  |gross      =  <!--gross (fuelled) mass of a single booster/stage, use {{convert}}, optional--> 
  |propmass   =  <!--propellant mass carried by a single booster/stage in kilograms, use {{convert}}, optional--> 
  |engines    =  1 [[LR-91|LR91-AJ9]]
  |thrust     =  {{convert|453.1|kN|lbf|abbr=on}}
  |total      =  <!--total thrust for all boosters in kN, use {{convert}}, optional-->
  |SI         =  <!--specific impulse of an individual booster/stage, in secs, optional-->
  |burntime   =  205 seconds
  |fuel       =  [[Dinitrogen tetroxide|N<sub>2</sub>O<sub>4</sub>]] / [[Aerozine 50]]
  }}
  {{Infobox rocket/stage
  |type       =  stage
  |diff       =  <!--variant of rocket this is used on, optional-->
  |stageno    =  Upper
  |name       =  [[Transtage]]
  |number     =  <!--number of boosters, required if type = booster-->
  |length     =  <!--length of a single booster/stage in metres, use {{convert}}, optional-->
  |diameter   =  <!--diameter of a single booster/stage in metres, use {{convert}}, optional-->
  |width      =  <!--width of a single booster/stage if not axisymmetric, use {{convert}}, optional-->
  |empty      =  <!--empty mass of a single booster/stage in kilograms, use {{convert}}, optional-->
  |gross      =  <!--gross (fuelled) mass of a single booster/stage, use {{convert}}, optional--> 
  |propmass   =  <!--propellant mass carried by a single booster/stage in kilograms, use {{convert}}, optional--> 
  |engines    =  2 [[AJ-10|AJ-10-138]]
  |thrust     =  {{convert|16000|lbf|kN|abbr=on}}
  |total      =  <!--total thrust for all boosters in kN, use {{convert}}, optional-->
  |SI         =  <!--specific impulse of an individual booster/stage, in secs, optional-->
  |burntime   =  440 seconds
  |fuel       =  [[Dinitrogen tetroxide|N<sub>2</sub>O<sub>4</sub>]] / [[Aerozine 50]]
  }}
}}

The '''Titan IIIC''' was an [[expendable launch system]] used by the [[United States Air Force]] from 1965 until 1982. It was the first [[Titan (rocket family)|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 ([[ATS-6]]) 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]] (later [[Martin Marietta]] and now [[Lockheed Martin]]) a contract to build an intercontinental ballistic missile (SM-68). 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 [[RP-1|kerosene]] (RP-1) and liquid oxygen (LOX) as propellants. A subsequent version of the Titan family, the [[LGM-25C Titan II|Titan II]], was similar to the [[Titan I]], but was much more powerful. Designated as LGM-25C, the Titan II was the largest [[United States Air Force|USAF]] missile at the time and burned [[Aerozine 50]] and [[nitrogen tetroxide]] (NTO) 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 SRM-equipped Titans (IIIC, IIID, [[Titan IIIE|IIIE]], [[Titan 34D|34D]], and [[Titan IV|IV]]) launched with only the SRMs firing at liftoff, the core stage not activating until T+105 seconds, shortly before SRM jettison. The [[Titan IIIA]] (an early test variant flown in 1964–65) and [[Titan IIIB|IIIB]] (flown from 1966 to 1987 with an [[RM-81 Agena|Agena D]] upper stage in both standard and extended tank variants) had no SRMs.<ref>{{cite web |url=http://www.astronautix.com/lvs/titan3b.htm |title=Titan 3B |access-date=2013-02-15 |url-status=dead |archive-url=https://web.archive.org/web/20121025055447/http://www.astronautix.com/lvs/titan3b.htm |archive-date=2012-10-25 }}</ref> 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 (ISDS) that would activate and destroy the first stage if there was a premature second stage separation. Titans that carried Solid Rocket Boosters (SRBs) (Titan IIIC, IIID, 34D, and IV) 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 GLV|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 {{chem|N|2|O|4}} 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. 

=== Launch history ===
{{Main|List of Titan launches}}
[[File:Titan 3C with Transtage 4 (Jun. 18 1965) - ascending.png|thumb|First Titan IIIC rocket with technological stage Transtage 4, June 18 1965.]]
The first Titan IIIC (3C-7) flew on June 18, 1965,<ref name=":1" /> and was the most powerful launcher used by the Air Force until it was replaced by the [[Titan 34D]] in 1982. 

The second launch (3C-4) in October 1965 failed,<ref name=":1" /> when the Transtage suffered an oxidizer leak and was unable to put its payload (several small satellites) into the correct orbit. The third launch (3C-8) in December experienced a similar failure.
[[File:Titan IIIC-11 launch.jpg|thumb|Titan IIIC-11 launch 16 June 1966 carrying first seven Initial Defense Communications Satellite Program satellites and GGTS]]
The [https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1965-108Bthe fourth IIIC launch] (3C-11 on June 16, 1966)<ref name=":1" /> was used to send the LES 4 (Lincoln Experimental Satellite 4) into orbit. It was a US Air Force experimental communications satellite launched along with OV2-3, LES 3, and Oscar 4 from Cape Canaveral aboard a single Titan 3C rocket. It transmitted in X-band.

The fifth Titan IIIC (3C-12 on August 26, 1966)<ref name=":1" /> 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 (a group of IDCSP satellites intended to provide radio communication for the US Army in Vietnam). 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 (3C-19) failed to place its missile [[early warning satellite]] (DSP 1) in the correct orbit due to a Transtage failure and a 1975 launch (3C-25) of two DSCS II (DSCS-2 5 and DSCS-2 6) military communication satellites left in LEO by another Transtage failure.<ref name=":2">{{Cite web |title=Titan-3(23)C |url=https://space.skyrocket.de/doc_lau_det/titan-323c.htm |access-date=2025-03-14 |website=Gunter's Space Page |language=en}}</ref>

On March 25, 1978, a launch of two DSCS II satellites (3C-35 with DSCS-2 9 and DSCS-2 10) ended up in the Atlantic Ocean when the Titan second stage hydraulic pump failed, resulting in engine shutdown approximately 470 seconds after launch.<ref name=":2" /> 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 last IIIC (3C-38 with DSP 10) was launched in March 1982.<ref name=":2" />

==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}}.

==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 rocket propellants|liquid propellant]] engines.
**Stage 2 uses one LR91 [[Liquid rocket propellants|liquid propellant]] engine.
**Stage 3 uses two Aerojet [[AJ-10| AJ-10-138]] [[Liquid rocket propellants|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&nbsp;kg/ea; Full 226,233&nbsp;kg/ea
**Stage 1: Empty 5,443&nbsp;kg; Full 116,573&nbsp;kg
**Stage 2: Empty 2,653&nbsp;kg; Full 29,188&nbsp;kg
**Stage 3: Empty 1,950&nbsp;kg; Full 12,247&nbsp;kg
*Lift capability:
**Up to 28,900&nbsp;lb (13,100&nbsp;kg) into a low Earth orbit with 28 degrees inclination.
**Up to 6,600&nbsp;lb (3,000&nbsp;kg) into a geosynchronous transfer orbit when launched from [[Cape Canaveral Air Force Station]], FL.
*Maximum takeoff weight:  626,190&nbsp;kg
*Cost:
*Date deployed: June 1965.
*Launch sites: [[Cape Canaveral Air Force Station]], FL., and [[Vandenberg Air Force Base]], CA.

== List of launches ==
{| class="wikitable" border="1"
|-
! Date/Time (GMT)
! Launch Site
! S/N
! Payload
! Outcome
! Remarks
|-
| 18 June 1965<br />14:00
| [[Cape Canaveral Air Force Station|CCAFS]] [[Cape Canaveral Air Force Station Space Launch Complex 40|LC-40]]
| 3C-7
| N/A
| {{Success}}
| Transtage test flight
|-
| 14 October 1965<br />17:24
| CCAFS LC-40
| 3C-4
| [[Lincoln Calibration Sphere|LCS-2]]<br />OV2-1
| {{Failure}}
| Transtage failed in low Earth orbit due to oxidizer tank leak
|-
| 21 December 1965<br />14:00
| CCAFS [[Cape Canaveral Air Force Station Space Launch Complex 41|LC-41]]
| 3C-8
| [[Lincoln Experimental Satellite|LES-3]]<br />[[Lincoln Experimental Satellite|LES-4]]<br />OV2-3<br />[[OSCAR 4]]
| {{Partial failure}}
| Transtage failed during 3rd burn due to stuck oxidizer valve; left payloads in [[geosynchronous transfer orbit|GTO]]
|-
| 16 June 1966<br />14:00
| CCAFS LC-41
| 3C-11
| OPS-9311 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9312 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9313 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9314 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9315 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9316 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9317 ([[Defense Satellite Communications System|IDCSP]])<br />[[Gravity Gradient Test Satellite|GGTS]]-1
| {{Success}}
|
|-
| 26 August 1966<br />14:00
| CCAFS LC-41
| 3C-12
| 7X [[Defense Satellite Communications System|IDCSP]]<br />[[Gravity Gradient Test Satellite|GGTS]]-2
| {{Failure}}
| Payload fairing broke up at T+78 seconds. RSO T+83 seconds.
|-
| 3 November 1966<br />13:50
| CCAFS LC-40
| 3C-9
| [[Gemini B]]<br />OV1-6<br />OV4-1R/T<br />OV4-3
| {{Success}}
| [[Gemini B]] was launched on a sub-orbital trajectory
|-
| 18 January 1967<br />14:19
| CCAFS LC-41
| 3C-13
| OPS-9321 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9322 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9323 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9324 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9325 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9326 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9327 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9328 ([[Defense Satellite Communications System|IDCSP]])
| {{Success}}
|
|-
| 28 April 1967<br />10:01
| CCAFS LC-41
| 3C-10
| OPS-6638 ([[Vela (satellite)|Vela]])<br />OPS-6679 ([[Vela (satellite)|Vela]])<br />[[Environmental Research Satellites|ORS-4]]<br />OV5-1<br />OV5-3
| {{Success}}
|
|-
| 1 July 1967<br />13:15
| CCAFS LC-41
| 3C-14
| OPS-9331 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9332 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9333 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9334 ([[Defense Satellite Communications System|IDCSP]])<br />[[Lincoln Experimental Satellite|LES-5]]<br />[[Department of Defense Gravity Experiment|DODGE]]
| {{Success}}
|
|-
| 13 June 1968<br />14:03
| CCAFS LC-41
| 3C-16
| OPS-9341 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9342 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9343 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9344 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9345 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9346 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9347 ([[Defense Satellite Communications System|IDCSP]])<br />OPS-9348 ([[Defense Satellite Communications System|IDCSP]])
| {{Success}}
|
|-
| 26 September 1968<br />07:37
| CCAFS LC-41
| 3C-5
| [[Lincoln Experimental Satellite|LES-6]]<br />OV2-5<br />OV5-2<br />OV5-4
| {{Success}}
|
|-
| 9 February 1969<br />21:09
| CCAFS LC-41
| 3C-17
| [[TACSAT 1]] (OPS-0757)
| {{Success}}
|
|-
| 23 May 1969<br />07:57
| CCAFS LC-41
| 3C-15
| OPS-6909 ([[Vela (satellite)|Vela]])<br />OPS-6911 ([[Vela (satellite)|Vela]])<br />OV5-5<br />OV5-6<br />OV5-9
| {{Success}}
|
|-
| 8 April 1970<br />10:50
| CCAFS LC-40
| 3C-18
| OPS-7033 ([[Vela (satellite)|Vela]])<br />OPS-7044 ([[Vela (satellite)|Vela]])
| {{Success}}
|
|-
| 6 November 1970<br />10:36
| CCAFS LC-40
| 3C-19
| [[Defense Support Program|DSP]]-1 (OPS-5960)
| {{Partial failure}}
| Transtage 3rd burn failure left satellite in unusable lower than planned orbit
|-
| 5 May 1971<br />07:43
| CCAFS LC-40
| 3C-20
| [[Defense Support Program|DSP]]-2 (OPS-3811)
| {{Success}}
|
|-
| 3 November 1971<br />03:09
| CCAFS LC-40
| 3C-21
| [[Defense Satellite Communications System|DSCS-II]]-1 (OPS-9431)<br />[[Defense Satellite Communications System|DSCS-II]]-2 (OPS-9432)
| {{Success}}
|
|-
| 1 March 1972<br />09:39
| CCAFS LC-40
| 3C-22
| [[Defense Support Program|DSP]]-3 (OPS-1570)
| {{Success}}
|
|-
| 12 June 1973<br />07:14
| CCAFS LC-40
| 3C-24
| [[Defense Support Program|DSP]]-4 (OPS-6157)
| {{Success}}
|
|-
| 13 December 1973<br />23:57
| CCAFS LC-40
| 3C-26
| [[Defense Satellite Communications System|DSCS-II]]-3 (OPS-9433)<br />[[Defense Satellite Communications System|DSCS-II]]-4 (OPS-9434)
| {{Success}}
|
|-
| 30 May 1974<br />13:00
| CCAFS LC-40
| 3C-27
| [[ATS-6]]
| {{Success}}
|
|-
| 20 May 1975<br />14:03
| CCAFS LC-40
| 3C-25
| [[Defense Satellite Communications System|DSCS-II]]-5 (OPS-9435)<br />[[Defense Satellite Communications System|DSCS-II]]-6 (OPS-9436)
| {{Failure}}
| Transtage inertial measurement unit failure caused it to be stranded in low Earth orbit.
|-
| 14 December 1975<br />05:15
| CCAFS LC-40
| 3C-29
| [[Defense Support Program|DSP]]-5 (OPS-3165)
| {{Success}}
|
|-
| 15 March 1976<br />01:25
| CCAFS LC-40
| 3C-30
| [[Lincoln Experimental Satellite|LES-8]]<br />[[Lincoln Experimental Satellite|LES-9]]<br />[[Solrad]]-11A<br />[[Solrad]]-11B
| {{Success}}
|
|-
| 26 June 1976<br />03:00
| CCAFS LC-40
| 3C-28
| [[Defense Support Program|DSP]]-6 (OPS-2112)
| {{Success}}
|
|-
| 6 February 1977<br />06:00
| CCAFS LC-40
| 3C-23
| [[Defense Support Program|DSP]]-7 (OPS-3151)
| {{Success}}
|
|-
| 12 May 1977<br />14:27
| CCAFS LC-40
| 3C-32
| [[Defense Satellite Communications System|DSCS-II]]-7 (OPS-9437)<br />[[Defense Satellite Communications System|DSCS-II]]-8 (OPS-9438)
| {{Success}}
|
|-
| 25 March 1978<br />18:09
| CCAFS LC-40
| 3C-35
| [[Defense Satellite Communications System|DSCS-II]]-9 (OPS-9439)<br />[[Defense Satellite Communications System|DSCS-II]]-10 (OPS-9440)
| {{Failure}}
| Second stage hydraulics pump failure. RSO T+480 seconds.
|-
| 10 June 1978<br />19:08
| CCAFS LC-40
| 3C-33
| OPS-9454 ([[Vortex (satellite)|Vortex]])
| {{Success}}
|
|-
| 14 December 1978<br />00:40
| CCAFS LC-40
| 3C-36
| [[Defense Satellite Communications System|DSCS-II]]-11 (OPS-9441)<br />[[Defense Satellite Communications System|DSCS-II]]-12 (OPS-9442)
| {{Success}}
|
|-
| 10 June 1979<br />13:30
| CCAFS LC-40
| 3C-31
| [[Defense Support Program|DSP]]-8 (OPS-7484)
| {{Success}}
|
|-
| 1 October 1979<br />11:22
| CCAFS LC-40
| 3C-34
| OPS-1948 ([[Vortex (satellite)|Vortex]])
| {{Success}}
|
|-
| 21 November 1979<br />02:09
| CCAFS LC-40
| 3C-37
| [[Defense Satellite Communications System|DSCS-II]]-13 (OPS-9443)<br />[[Defense Satellite Communications System|DSCS-II]]-14 (OPS-9444)
| {{Success}}
|
|-
| 16 March 1981<br />13:30
| CCAFS LC-40
| 3C-40
| [[Defense Support Program|DSP]]-9 (OPS-7350)
| {{Success}}
|
|-
| 31 October 1981<br />09:22
| CCAFS LC-40
| 3C-39
| OPS-4029 ([[Vortex (satellite)|Vortex]])
| {{Success}}
|
|-
| 6 March 1982<br />19:25
| CCAFS LC-40
| 3C-38
| [[Defense Support Program|DSP]]-10 (OPS-8701)
| {{Success}}
|
|}

==References==
{{reflist}}

==External links==
{{Commons category|Titan IIIC}}
* [https://www.youtube.com/watch?v=Oh-dMH1m-sg Titan III: Research and Development for Today And Tomorrow ]
*[https://web.archive.org/web/20141225140441/http://www.astronautix.com/lvs/titan3c.htm Titan3C]
*[http://www.fas.org/spp/military/program/launch/titan.htm Titan III & variations]
*[http://www.airpower.maxwell.af.mil/airchronicles/aureview/1969/jan-feb/bleymaier.html Future Space Booster Requirements] {{Webarchive|url=https://web.archive.org/web/20080320003845/http://www.airpower.maxwell.af.mil/airchronicles/aureview/1969/jan-feb/bleymaier.html |date=2008-03-20 }} - January–February 1969 ''Air University Review''

{{Expendable launch systems}}
{{US launch systems}}
{{Titan rockets}}

[[Category:1971 in spaceflight]]
[[Category:1973 in spaceflight]]
[[Category:1974 in spaceflight]]
[[Category:Lockheed Martin]]
[[Category:Titan (rocket family)]]
[[Category:Military equipment introduced in the 1960s]]