Titan IV
![]() A Titan IV-B rocket carrying theCassini-Huygensspace research mission before takeoff fromLaunch Complex 40onCape Canaveral,12 October 1997 (NASA) | |
Function | Heavy-lift launch vehicle |
---|---|
Manufacturer | Lockheed Martin |
Country of origin | United States |
Cost per launch | $432 million (USD) |
Size | |
Height | 50-62 m (164-207 ft) |
Diameter | 3.05 m (10 ft) |
Mass | 943,050kg(2,079,060lb) |
Stages | 3-5 |
Capacity | |
Payload toLEO | |
Mass | 21,680 kg(47,790 lb) |
Payload toPolar LEO | |
Mass | 17,600 kg(38,800 lb) |
Payload toGSO | |
Mass | 5,760 kg(12,690 lb) |
Payload toHCO | |
Mass | 5,660 kg(12,470 lb) |
Associated rockets | |
Family | Titan |
Comparable | Atlas V,Delta IV Heavy,Falcon 9 |
Launch history | |
Status | Retired |
Launch sites | SLC-40/41,Cape Canaveral SLC-4E,Vandenberg AFB |
Total launches | 39[1] (IVA:22,IVB:17) |
Success(es) | 35 (IVA:20,IVB:15) |
Failure(s) | 4 (IVA:2,IVB:2) |
First flight | IV-A:14 June 1989 IV-B:23 February 1997 |
Last flight | IV-A:12 August 1998 IV-B:19 October 2005 |
Type of passengers/cargo | Lacrosse DSP Milstar Cassini-Huygens |
Boosters (IV-A) –UA1207 | |
No. boosters | 2 |
Powered by | United Technologies UA1207 |
Maximum thrust | 14.234MN(3,200,000lbf) |
Specific impulse | 272 seconds (2667 N·s/kg) |
Burn time | 120 seconds |
Propellant | PBAN |
Boosters (IV-B) – SRMU | |
No. boosters | 2 |
Powered by | HerculesUSRM[2] |
Maximum thrust | 15.12 MN (3,400,000 lbf) |
Specific impulse | 286 seconds (2805 N·s/kg) |
Burn time | 140 seconds |
Propellant | HTPB |
First stage | |
Powered by | 2LR87[3] |
Maximum thrust | 2,440 kN (548,000 lbf) |
Specific impulse | 302 seconds (2962 N·s/kg) |
Burn time | 164 seconds |
Propellant | N2O4/Aerozine 50 |
Second stage | |
Powered by | 1LR91 |
Maximum thrust | 467 kN (105,000 lbf) |
Specific impulse | 316 seconds (3100 N·s/kg) |
Burn time | 223 seconds |
Propellant | N2O4/Aerozine 50 |
Third stage (Optional) –Centaur-T | |
Powered by | 2RL10 |
Maximum thrust | 147 kN (33,100 lbf) |
Specific impulse | 444 seconds (4354 N·s/kg) |
Burn time | 625 seconds |
Propellant | LH2/LOX |
Titan IVwas a family ofheavy-lift space launch vehiclesdeveloped byMartin Mariettaand operated by theUnited States Air Forcefrom 1989 to 2005.[4]Launcheswere conducted fromCape Canaveral Air Force Station,Florida[5]andVandenberg Air Force Base,California.[6]
The Titan IV was the last of theTitan family of rockets,originally developed by theGlenn L. Martin Companyin 1958. It was retired in 2005 due to their high cost of operation and concerns over its toxichypergolic propellants,and replaced with theAtlas VandDelta IVlaunch vehicles under theEELVprogram. The final launch (B-30) from Cape Canaveral occurred on 29 April 2005, and the final launch from Vandenberg AFB occurred on 19 October 2005.[7]Lockheed Martin Space Systemsbuilt the Titan IVs near Denver, Colorado, under contract to theUS government.[1]
Two Titan IV vehicles are currently on display at theNational Museum of the United States Air ForceinDayton, Ohioand theEvergreen Aviation and Space MuseuminMcMinnville, Oregon.
Vehicle description[edit]
The Titan IV was developed to provide assured capability to launchSpace Shuttle–class payloads for the Air Force. The Titan IV could be launched with noupper stage,theInertial Upper Stage(IUS), or theCentaur upper stage.
The Titan IV was made up of two largesolid-fuel rocket boostersand a two-stage liquid-fueled core. The two storable liquid fuel core stages usedAerozine 50fuel andnitrogen tetroxideoxidizer. These propellants arehypergolic,igniting on contact, and are liquids at room temperature, so no tank insulation is needed. This allowed the launcher to be stored in a ready state for extended periods, but both propellants are extremely toxic.
The Titan IV could be launched from either coast:SLC-40or41at Cape Canaveral Air Force Station near Cocoa Beach, Florida and atSLC-4E,atVandenberg Air Force Base launch sites55 miles northwest ofSanta BarbaraCalifornia. Launches topolar orbitsoccurred from Vandenberg, with most other launches taking place at Cape Canaveral.
Titan IV-A[edit]
Titan IV-A flew with steel-cased solidUA1207rocket motors (SRMs) produced by Chemical Systems Division.[8][9][10]
Titan IV-B[edit]
The Titan IV-B evolved from the Titan III family and was similar to the Titan 34D.
While the launcher family had an extremely good reliability record in its first two decades, this changed in the 1980s with the loss of a Titan 34D in 1985 followed by the disastrous explosion of another in 1986 due to aSRMfailure. Due to this, the Titan IV-B vehicle was intended to use the new composite-casing Upgraded Solid Rocket Motors.[11]Due to development problems the first few Titan IV-B launches flew with the old-style UA1207 SRMs.
-
Titan IV-A
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Titan-4(01)A Centaur
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Titan IV-B Centaur
-
LR91-AJ-11rocket engine thrust chamber and injector
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Bottom of first stage of Titan IV-B rocket
General characteristics[edit]
- Builder: Lockheed-Martin Astronautics
- Power Plant:
- Stage 0 consisted of two solid-rocket motors.
- Stage 1 used an LR87-AJ-11 liquid-propellant rocket engine.
- Stage 2 used the LR91-AJ-11 liquid-propellant engine.
- Optional upper stages included theCentaurandInertial Upper Stage.
- Guidance System: Aring laser gyroguidance system manufactured byHoneywell.
- Thrust:
- Stage 0: Solid rocket motors provided 1.7 million pounds force (7.56 MN) per motor at liftoff.
- Stage 1: LR87-AJ-11 provided an average of 548,000 pounds force (2.44 MN)
- Stage 2: LR91-AJ-11 provided an average of 105,000 pounds force (467 kN).
- Optional Centaur (RL10A-3-3A) upper stage provided 33,100 pounds force (147 kN) and the Inertial Upper Stage provided up to 41,500 pounds force (185 kN).
- Length: Up to 204 feet (62 m)
- Lift Capability:
- Could carry up to 47,800 pounds (21,700 kg) into low Earth orbit
- up to 12,700 pounds (5,800 kg) into ageosynchronous orbitwhen launched from Cape Canaveral AFS, Fla.;
- and up to 38,800 pounds (17,600 kg) into alow Earthpolar orbitwhen launched from Vandenberg AFB.
- into geosynchronous orbit:
- with Centaur upper stage 12,700 pounds (5,800 kg)
- with Inertial Upper Stage 5,250 pounds (2,380 kg)
- Payload fairing:[12]
- Manufacturer: McDonnell Douglas Space Systems Co
- Diameter: 16.7 feet (5.1 m)
- Length: 56, 66, 76, or 86 ft
- Mass: 11,000, 12,000, 13,000, or 14,000 lb
- Design: 3 sections, isogrid structure, Aluminum
- Maximum Takeoff Weight: Approximately 2.2 million pounds (1,000,000 kg)
- Cost: Approximately $250–350 million, depending on launch configuration.
- Date deployed: June 1989
- Launch sites: Cape Canaveral AFS, Fla., and Vandenberg AFB, Calif.
Upgrades[edit]
Solid Rocket Motor Upgrade test stand[edit]
In 1988–89, TheRalph M. Parsons Companydesigned and built a full-scale steel tower and deflector facility, which was used to test the Titan IV Solid Rocket Motor Upgrade (SRMU).[13]The launch and the effect of the SRMU thrust force on the Titan IV vehicle were modeled. To evaluate the magnitude of the thrust force, the SRMU was connected to the steel tower through load measurement systems and launched in-place. It was the first full-scale test conducted to simulate the effects of the SRMU on the Titan IV vehicle.[14]
Proposed aluminum-lithium tanks[edit]
In the early 1980s,General Dynamicsdeveloped a plan to assemble a lunar landing spacecraft in-orbit under the nameEarly Lunar Access.A Space Shuttle would lift a lunar lander into orbit and then a Titan IV rocket would launch with a modifiedCentaur G-Primestage to rendezvous and dock. The plan required upgrading the Space Shuttle and Titan IV to use lighteraluminium-lithium alloypropellant tanks.[15]The plan never came to fruition, but in the 1990s the Shuttle'sExternal Tankwas converted to aluminum-lithium tanks to rendezvous with the highly inclined orbit of the RussianMirSpace Station.[16]
Type identification[edit]
The IV-A (40nA) used boosters with steel casings, the IV-B (40nB) used boosters with composite casings (the SRMU).
Type 401 used a Centaur 3rd stage, type 402 used an IUS 3rd stage. The other 3 types (without 3rd stages) were 403, 404, and 405:
- Type 403 featured no upper stage, for lower-mass payloads to higher orbits from Vandenberg.[17]
- Type 404 featured no upper stage, for heavier payloads to low orbits, from Vandenberg.[17]
- Type 405 featured no upper stage, for lower-mass payloads to higher-orbit from Cape Canaveral.[17]
History[edit]
![Interactive 3D model of the Titan IV](https://upload.wikimedia.org/wikipedia/commons/thumb/d/dc/Titan-IV.stl/274px-Titan-IV.stl.png)
TheTitan rocket familywas established in October 1955 when the Air Force awarded theGlenn L. Martin Company(laterMartin-Marietta,now part ofLockheed Martin) a contract to build anintercontinental ballistic missile(SM-68). The resultingTitan Iwas the nation's first two-stage ICBM and complemented theAtlas ICBMas the second underground, vertically stored, silo-based ICBM. Both stages of the Titan I usedliquid oxygenandRP-1as propellants.
A subsequent version of the Titan family, theTitan II,was a two-stage evolution of the Titan I, but was much more powerful and used different propellants. Designated as LGM-25C, the Titan II was the largest missile developed for the USAF at that time. The Titan II had newly developed engines which used Aerozine 50 and nitrogen tetroxide as fuel and oxidizer in a self-igniting,hypergolic propellantcombination, allowing the Titan II to be stored underground ready to launch. Titan II was the first Titan vehicle to be used as a space launcher.
Development of the space launch onlyTitan IIIbegan in 1964, resulting in the Titan IIIA, eventually followed by the Titan IV-A and IV-B.
CELV[edit]
By the mid-1980s the United States government worried that the Space Shuttle, designed to launch all American payloads and replace all unmanned rockets, would not be reliable enough for military and classified missions. In 1984Under Secretary of the Air ForceandDirector of the National Reconnaissance Office(NRO)Pete Aldridgedecided to purchaseComplementary Expendable Launch Vehicles(CELV) for ten NRO payloads; the name came from the government's expectation that the rockets would "complement" the shuttle. Later renamed Titan IV,[18]the rocket would only carry three military payloads[19]paired with Centaur stages and fly exclusively from LC-41 at Cape Canaveral. However, theChallenger accidentin 1986 caused a renewed dependence onexpendable launch systems,with the Titan IV program significantly expanded. At the time of its introduction, the Titan IV was the largest and most capableexpendable launch vehicleused by the USAF.[20]
The post-Challenger program added Titan IV versions with theInertial Upper Stage(IUS) or no upper stages, increased the number of flights, and converted LC-40 at the Cape for Titan IV launches. As of 1991, almost forty total Titan IV launches were scheduled and a new, improved SRM (solid rocket motor) casing using lightweight composite materials was introduced.
Program cost[edit]
In 1990, the Titan IV Selected Acquisition Report estimated the total cost for the acquisition of 65 Titan IV vehicles over a period of 16 years to US$18.3 billion (inflation-adjusted US$ 42.7 billion in 2024).[21]
Cassini–Huygens launch[edit]
In October 1997, a Titan IV-B rocket launchedCassini–Huygens,a pair of probes sent toSaturn.It was the only use of a Titan IV for a non-Department of Defense launch.Huygenslanded onTitanon January 14, 2005.Cassiniremained in orbit around Saturn. The Cassini Mission ended on September 15, 2017, when the spacecraft was sent into Saturn's atmosphere to burn up.
Retirement[edit]
While an improvement over the shuttle, the Titan IV was expensive and unreliable.[18]By the 1990s, there were also growing safety concerns over its toxic propellants. TheEvolved Expendable Launch Vehicle(EELV) program resulted in the development of theAtlas V,Delta IV,andDelta IV Heavylaunch vehicles, which replaced Titan IV and a number of other legacy launch systems. The new EELVs eliminated the use of hypergolic propellants, reduced costs, and were much more versatile than the legacy vehicles.
Surviving examples[edit]
In 2014, theNational Museum of the United States Air ForceinDayton, Ohio,began a project to restore a Titan IV-B rocket. This effort was successful, with the display opening June 8, 2016.[22]The only other surviving Titan IV components are at theWings Over the Rockies Air and Space Museumin Denver, Colorado which has two Titan Stage 1 engines, one Titan Stage 2 engine, and the interstage ‘skirt’ on outdoor display;[23]and at theEvergreen Aviation and Space Museumin McMinnville, Oregon, including the core stages and parts of the solid rocket motor assembly.[24]
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Titan IV-B in theNational Museum of the United States Air Force
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Titan IV-B in the National Museum of the United States Air Force
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Titan IV-B in the restoration hangar at the National Museum of the United States Air Force. This is Stage One aft with two Aerojet LR87-AJ-11 engines.
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Titan IV-B stage one and SRMU's at the National Museum of the United States Air Force
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Titan IV-B at theEvergreen Aviation and Space Museum
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Titan IV-B at the Evergreen Aviation and Space Museum
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Titan IV-B at the Evergreen Aviation and Space Museum
Launch history[edit]
Date / Time (UTC) |
Launch Site | S/N | Type | Payload | Outcome | Remarks |
---|---|---|---|---|---|---|
14 June 1989 13:18 |
CCAFSLC-41 | K-1 | 402A /IUS | USA-39 (DSP-14) | Success | An engine bell burn-through left only a narrow margin for success. |
8 June 1990 05:21 |
CCAFS LC-41 | K-4 | 405A | USA-60 (NOSS) USA-61 (NOSS) USA-62 (NOSS) USA-59 Satellite Launch Dispenser Communications (SLDCOM) |
Success | |
13 November 1990 00:37 |
CCAFS LC-41 | K-6 | 402A /IUS | USA-65 (DSP-15) | Success | |
8 March 1991 12:03 |
VAFBLC-4E | K-5 | 403A | USA-69 (Lacrosse) | Success | |
8 November 1991 07:07 |
VAFB LC-4E | K-8 | 403A | USA-74 (NOSS) USA-76 (NOSS) USA-77 (NOSS) USA-72 SLDCOM |
Success | |
28 November 1992 21:34 |
VAFB LC-4E | K-3 | 404A | USA-86 (KH-11) | Success | |
2 August 1993 19:59 |
VAFB LC-4E | K-11 | 403A | NOSSx3 SLDCOM |
Failure | SRM exploded at T+101s due to damage caused during maintenance on ground. |
7 February 1994 21:47 |
CCAFSLC-40 | K-10 | 401A /Centaur | USA-99 (Milstar-1) | Success | |
3 May 1994 15:55 |
CCAFS LC-41 | K-7 | 401A /Centaur | USA-103 (Trumpet) | Success | |
27 August 1994 08:58 |
CCAFS LC-41 | K-9 | 401A /Centaur | USA-105 (Mercury) | Success | |
22 December 1994 22:19 |
CCAFS LC-40 | K-14 | 402A /IUS | USA-107 (DSP-17) | Success | |
14 May 1995 13:45 |
CCAFS LC-40 | K-23 | 401A /Centaur | USA-110 (Orion) | Success | |
10 July 1995 12:38 |
CCAFS LC-41 | K-19 | 401A /Centaur | USA-112 (Trumpet) | Success | |
6 November 1995 05:15 |
CCAFS LC-40 | K-21 | 401A /Centaur | USA-115 (Milstar-2) | Success | |
5 December 1995 21:18 |
VAFB LC-4E | K-15 | 404A | USA-116 (KH-11) | Success | |
24 April 1996 23:37 |
CCAFS LC-41 | K-16 | 401A /Centaur | USA-118 (Mercury) | Success | |
12 May 1996 21:32 |
VAFB LC-4E | K-22 | 403A | USA-120 (NOSS) USA-121 (NOSS) USA-122 (NOSS) USA-119 (SLDCOM) USA-123 Tethers in Space Physics Satellite (TiPS) USA-124 (TiPS) |
Success | |
3 July 1996 00:30 |
CCAFS LC-40 | K-2 | 405A | USA-125 (SDS) | Success | |
20 December 1996 18:04 |
VAFB LC-4E | K-13 | 404A | USA-129 (KH-11) | Success | NROL-2 |
23 February 1997 20:20 |
CCAFS LC-40 | B-24 | 402B /IUS | USA-130 (DSP-18) | Success | |
15 October 1997 08:43 |
CCAFS LC-40 | B-33 | 401B /Centaur | Cassini Huygens |
Success | |
24 October 1997 02:32 |
VAFB LC-4E | A-18 | 403A | USA-133 (Lacrosse) | Success | NROL-3 |
8 November 1997 02:05 |
CCAFS LC-41 | A-17 | 401A /Centaur | USA-136 (Trumpet) | Success | NROL-4 |
9 May 1998 01:38 |
CCAFS LC-40 | B-25 | 401B /Centaur | USA-139 (Orion) | Success | NROL-6 |
12 August 1998 11:30 |
CCAFS LC-41 | A-20 | 401A /Centaur | NROL-7(Mercury) | Failure | Guidance system short-circuited at T+40s due to frayed wire, vehicle lost control and destroyed by range safety. |
9 April 1999 17:01 |
CCAFS LC-41 | B-27 | 402B /IUS | USA-142 (DSP-19) | Failure | Spacecraft failed to separate from IUS stage. |
30 April 1999 16:30 |
CCAFS LC-40 | B-32 | 401B /Centaur | USA-143 (Milstar-3) | Failure | Centaur software database error caused loss ofattitude control,insertion burns done incorrectly. Satellite deployed into useless orbit. |
22 May 1999 09:36 |
VAFB LC-4E | B-12 | 404B | USA-144 (Misty) | Success | NROL-8 |
8 May 2000 16:01 |
CCAFS LC-40 | B-29 | 402B /IUS | USA-149 (DSP-20) | Success | |
17 August 2000 23:45 |
VAFB LC-4E | B-28 | 403B | USA-152 (Lacrosse) | Success | NROL-11 |
27 February 2001 21:20 |
CCAFS LC-40 | B-41 | 401B /Centaur | USA-157 (Milstar-4) | Success | |
6 August 2001 07:28 |
CCAFS LC-40 | B-31 | 402B /IUS | USA-159 (DSP-21) | Success | |
5 October 2001 21:21 |
VAFB LC-4E | B-34 | 404B | USA-161 (KH-11) | Success | NROL-14 |
16 January 2002 00:30 |
CCAFS LC-40 | B-38 | 401B /Centaur | USA-164 (Milstar-5) | Success | |
8 April 2003 13:43 |
CCAFS LC-40 | B-35 | 401B /Centaur | USA-169 (Milstar-6) | Success | |
9 September 2003 04:29 |
CCAFS LC-40 | B-36 | 401B /Centaur | USA-171 (Orion) | Success | NROL-19 |
14 February 2004 18:50 |
CCAFS LC-40 | B-39 | 402B /IUS | USA-176 (DSP-22) | Success | |
30 April 2005 00:50 |
CCAFS LC-40 | B-30 | 405B | USA-182 (Lacrosse) | Success | NROL-16 |
19 October 2005 18:05 |
VAFB LC-4E | B-26 | 404B | USA-186 (KH-11) | Success | NROL-20 |
Launch failures[edit]
The Titan IV experienced four catastrophic launch failures.
1993 booster explosion[edit]
![](https://upload.wikimedia.org/wikipedia/commons/thumb/c/ca/Titan_IVA_K-11_failure_%28August_1993%29.jpg/170px-Titan_IVA_K-11_failure_%28August_1993%29.jpg)
On August 2, 1993, Titan IV K-11 lifted from SLC-4E carrying a NOSS SIGNIT satellite. Unusually for DoD launches, the Air Force invited civilian press to cover the launch, which became more of a story than intended when the booster exploded 101 seconds after liftoff. Investigation found that one of the two SRMs had burned through, resulting in the destruction of the vehicle in a similar manner as the earlier 34D-9 failure. An investigation found that an improper repair job was the cause of the accident.[25]
After Titan 34D-9, extensive measures had been put in place to ensure proper SRM operating condition, including X-raying the motor segments during prelaunch checks. The SRMs that went onto K-11 had originally been shipped to Cape Canaveral, where X-rays revealed anomalies in the solid propellant mixture in one segment. The defective area was removed by a pie-shaped cut in the propellant block. However, most of CSD's qualified personnel had left the program by this point and so the repair crew in question did not know the proper procedure. After replacement, they neglected to seal the area where the cut in the propellant block had been made. Post repair X-rays were enough for CC personnel to disqualify the SRMs from flight, but the SRMs were then shipped to Vandenberg and approved anyway. The result was a near-repeat of 34D-9; a gap was left between the propellant and SRM casing and another burn-through occurred during launch.
1998 IV-A electrical failure[edit]
1998 saw the failure of Titan K-17 with a NavyELINTMercury (satellite)from Cape Canaveral around 40 seconds into the flight. K-17 was several years old and the last Titan IV-A to be launched. The post-accident investigation showed that the booster had dozens of damaged or chafed wires and should never have been launched in that operating condition, but the Air Force had put extreme pressure on launch crews to meet program deadlines. The Titan's fuselage was filled with numerous sharp metal protrusions that made it nearly impossible to install, adjust, or remove wiring without it getting damaged. Quality control at Lockheed's Denver plant, where Titan vehicles were assembled, was described as "awful".
The proximal cause of the failure was an electrical short that caused a momentary power dropout to the guidance computer at T+39 seconds. After power was restored, the computer sent a spurious pitch down and yaw to the right command. At T+40 seconds, the Titan was traveling at near supersonic speed and could not handle this action without suffering a structural failure. The sudden pitch downward and resulting aerodynamic stress caused one of the SRMs to separate. The ISDS (Inadvertent Separation Destruct System) automatically triggered, rupturing the SRM and taking the rest of the launch vehicle with it. At T+45 seconds, the Range Safety Officer sent the destruct command to ensure any remaining large pieces of the booster were broken up.[26]
An extensive recovery effort was launched, both to diagnose the cause of the accident and recover debris from the classified satellite. All of the debris from the Titan had impacted offshore, between three and five miles downrange, and at least 30% of the booster was recovered from the sea floor. Debris continued to wash ashore for days afterward, and the salvage operation continued until October 15.
The Air Force had pushed for a "launch on demand" program for DOD payloads, something that was almost impossible to pull off especially given the lengthy preparation and processing time needed for a Titan IV launch (at least 60 days). Shortly before retiring in 1994, GeneralChuck Hornerreferred to the Titan program as "a nightmare". The 1998-99 schedule had called for four launches in less than 12 months. The first of these was Titan K-25 which successfully orbited an Orion SIGNIT satellite on May 9, 1998. The second was the K-17 failure, and the third was the K-32 failure.
Stage failure to separate[edit]
After a delay caused by the investigation of the previous failure, the 9 April 1999 launch of K-32 carried a DSPearly warning satellite.The IUS second stage failed to separate, leaving the payload in a useless orbit. Investigation into this failure found that wiring harnesses in the IUS had been wrapped too tightly with electrical tape so that a plug failed to disconnect properly and prevented the two IUS stages from separating.
Programming error[edit]
The fourth launch was K-26 on April 30, 1999, carrying aMilstarcommunications satellite. During the Centaur coast phase flight, theroll controlthrusters fired open-loop until the RCS fuel was depleted, causing the upper stage and payload to rotate rapidly. On restart, the Centaur cartwheeled out of control and left its payload in a useless orbit. This failure was found to be the result of an incorrectly programmed equation in the guidance computer. The error caused the roll rate gyro data to be ignored by the flight computer.[27]
See also[edit]
- Comparison of heavy lift launch systems
- List of Titan launches,Titan I, II, III & IV
References[edit]
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{{cite web}}
:CS1 maint: multiple names: authors list (link)
External links[edit]
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