Directory of U.S. Military Rockets and Missiles
Appendix 3: Space Vehicles
SLV-4/SLV-5/SB-4/SB-5/SB-6
SB-3
SSB-7
Copyright © 2003-2006 Jos Heyman
(HTML formatting by Andreas Parsch)

Lockheed Martin SLV-4/SLV-5/SB-4/SB-5/SB-6 Titan

The Titan launch vehicle was developed by the Martin Company (which in 1995 merged with Lockheed to become Lockheed Martin) as the SM-68 military intercontinental ballistic missile as a back-up to the SM-65 Atlas ICBM missile. Development was started in October 1955 when Martin was awarded a contract for the airframe design. As a missile it was designated as SM-68, HGM-25 and LGM-25. Towards the end of its military operational life, some of the missiles were refurbished as space launchers. This was in addition to some of the missiles that had been used earlier in a space launch function. Also, the missile formed the basis of a family of space launch vehicles.

In addition to the military missile designations, as described separately for HGM/LGM-25, the Titan launch vehicles also received military designations in the LV/SLV and SB series. These designations probably refer to the first stage only. The following table lists the known designations and the cross references to the launch vehicle types, however, there remain discrepancies in this list. It is probable that these designations were only used for flights carrying military satellites.

DesignationType
SLV-4Titan IIGLV
SLV-5Titan III
SLV-5ATitan IIIA
SLV-5BTitan IIIB
SLV-5CTitan IIIC
SLV-5DTitan IIID
SLV-5ETitan IIIE
SB-4ATitan IIG
SB-5ATitan IV
SB-5BTitan IVB
SB-6ATitan 34D

There is further confusion about the designations of the Titan launch vehicles themselves. Several reference sources use arabic numerals for the Titan I, Titan II, Titan III and Titan IV, rather than the roman numerals as used by military references as well as Lockheed Martin. But there are designations such as Titan 34D, which are 'legitimate' designations, as well as designations such as Titan 3(23)C, Titan 3(34)B Agena D etc, which indicate sub-versions in which the first digit indicates the stage stretch and the second digit the type of guidance system. Individual flights are identified by a letter/number combination in which the letter is a reference to the vehicle type. However, some individual flights are identified by two different numbers. In addition vehicles that have a military origin, have a military serial as well.

Titan I

In total 163 Titan I missiles were built of which 62 were built as research and development vehicles identified as:

In addition 101 operational missiles were built as part of the SM lot.

A total of 54 operational Titan Is were deployed at Lowry AFB (2 complexes), Mountain Home AFB, Beale AFB, Larson AFB and Ellsworth AFB. Each complex had 9 missiles in 3 structures with 3 missiles each. There was a test facility at Vandenberg whilst there were also test flights from Cape Canaveral.

The first flight of a Titan I missile took place on 6 February 1959 and 68 tests launches were conducted from Cape Canaveral as well as Vandenberg. Five of these launches have been identified as failures. The final launch was on 5 March 1965. Although it was at one stage proposed to mate the Titan I with a Vanguard rocket as upper stages for lunar orbital and surface landing mission, the Titan I was not used for space launches. The Titan I had a total length of 28.04 m.

Stage Length Diameter Engine Fuel Thrust
116.00 m3.05 m2 Aerojet LR87-AJ-3Lox/Kerosene 1,333,752 N
29.80 m2.30 m1 Aerojet LR91-AJ-3Lox/Kerosene 355,896 N

Specifications for Titan I

Titan II

Although the Titan II was originally developed as a missile, it also had two careers as a space launch vehicle. In total 141 of the missiles were built of which 33 were for research and development purposes (identified as Lot N) whilst 108 operational missiles were built. A total of 54 operational Titan IIs were deployed in silos at Davis Monthan AFB, McConnell AFB and Little Rock AFB. Each site has 18 silos. There were also three silos at Vandenberg, used for test firings. As a missile the first launch took place on 16 March 1962 and 81 flights were conducted until 27 June 1976. Of these flights seven were considered as a failure. The basic Titan II had a total length of 33.20 m.

Between 8 April 1964 and 11 November 1966, the Titan II was also used as the launch vehicle for twelve flights in the Gemini programme. As the launch vehicle in this programme the vehicle was known as Titan IIGLV and was capable of placing a 3810 kg payload into low-Earth orbit.

Photo: Lockheed Martin
Titan II (SB-4A)


On 5 September 1988 the first surplus and refurbished Titan II missile was used for a space launch and up to 31 December 2003 13 launches have been conducted, of which one failed. At total of 56 missiles were available for refurbishment although current plans concern only 14 missiles. Some of the launchers used parts of several missiles. These refurbished missiles are sometimes referred to as Titan 2, Titan 2G, Titan 23G or Titan 2(23)G whilst some of the launches carried an additional propulsion stage to place the satellite into a higher orbit. The refurbished launchers, which had a length of 31.40 m, were capable to place 2170 kg payloads into low-Earth orbit.

Stage Length Diameter Engine Fuel Thrust
121.40 m3.05 m2 Aerojet LR87-AJ-7 N2O4/Aerozine1,912,365 N
27.90 m3.05 m1 Aerojet LR91-AJ-7 N2O4/Aerozine444,835 N

Specifications for Titan II

Titan IIIA

In 1962 the Titan IIIA (there was no Titan III as such) was selected by the US Air Force as its standard launch vehicle for military payloads. It differed from the Titan II by more powerful first and second stages as well as the addition of the Transtage (refer SSB-10) as a third stage. The vehicle had a length of up to 48.76 m, depending on the size of the payload carried, and was capable to place a payload of 2810 kg into a low-Earth orbit. It was used between 1 September 1964 and 6 May 1965 for four flights of which one failed.

Stage Length Diameter Engine Fuel Thrust
121.64 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,339,852 N
27.90 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine453,730 N
34.60 m3.05 m2 Aerojet AJ-10-138 N2O4/Aerozine71,199 N

Specifications for Titan IIIA

Titan IIIB

A further development was the Titan IIIB which used the Agena D upper stage instead of the Transtage. This combination is sometimes referred to as Titan III Agena D whilst in the early 1970s designations such as Titan 3(23), Titan 3(24), Titan 3(33), Titan 3(34) and Titan 34B were also used. The launch vehicle had a length of up to 48.76 m, depending on the size of the payload carried, and could place a payload of 3630 kg into a low-Earth orbit. The first flight was on 29 July 1966 and the 68th and last flight was on 12 February 1987. Of these four failed.

Photo: Author's collection
Titan IIIB


Stage Length Diameter Engine Fuel Thrust
122.22 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,339,852 N
27.50 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine453,730 N
36.31 m1.54 m1 Bell LR81-BA-9 N2O4/UDMH71,100 N

Specifications for Titan IIIB

Titan IIIBAS2

The Titan IIIBAS2 was a mid 1960 proposal for a Titan IIIB with two strap-ons, a Centaur D/E third stage and a Burner 2 fourth stage. It was to be used for deep space missions but development was not proceeded with.

Stage Length Diameter Engine Fuel Thrust
0------2 Algol 2solid 564,265 N
each
122.22 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,339,852 N
27.50 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine453,730 N
39.60 m3.05 m2 P&W RL-10A-3-1 or -3Lox/LH2 131,227 N
40.80 m0.70 m1Thiokol Star 37solid 43,553 N

Specifications for Titan IIIBAS2

Titan IIIC

The next version was the Titan IIIC which was basically similar to the Titan IIIA but with the addition of two United Technologies 1205 solid fuelled boosters to the first stage. These boosters had a length of 25.90 m and a diameter of 3.05 m whilst the launch vehicle's total length was 35.05 m, depending on the payload carried. Initially proposed to be used with the X-20 Dyna Soar, this configuration was capable to place a payload of 13,150 kg into low-Earth orbit. It was used between 18 June 1965 and 6 March 1982. Of the 36 flights 2 failed. During the 1970s the launch vehicle was also referred to as Titan 3(23)C. The vehicle had a length of up to 48.76 m, depending on the size of the payload carried.

Stage Length Diameter Engine Fuel Thrust
0------2 United Tech 1205solid 5,849,620 N
each
122.22 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,339,852 N
27.50 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine453,730 N
34.60 m3.05 m2 Aerojet AJ-10-138 N2O4/Aerozine71,199 N

Specifications for Titan IIIC

Titan IIIC7

The Titan IIIC7 was a 1965 proposal that would use a lengthened Transtage third stage with as well as upgraded solid boosters with a length of 34.10 m. The version was not further developed.

Stage Length Diameter Engine Fuel Thrust
0------2 United Tech 1207solid 7,117,725 N
each
122.22 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,339,852 N
27.50 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine453,730 N
35.30 m3.05 m2 Aerojet AJ-10-138 N2O4/Aerozine71,199 N

Specifications for Titan IIIC7

Titan IIID

The Titan IIID was similar to the Titan IIIC but with the deletion of the Transtage upper stage. It is, however, believed that some Titan IIID vehicles were used with an additional Agena D upper stage. In this configuration, the vehicle was capable to place 12,300 kg into a low-Earth orbit. It had a length of up to 48.76 m, depending on the size of the payload carried. The vehicle was used 24 times between 15 June 1971 and 28 August 1985. Of these one was a failure.

Photo: Author's collection
Titan IIID


Stage Length Diameter Engine Fuel Thrust
0------2 United Tech 1205solid 5,849,620 N
each
122.22 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,339,852 N
27.50 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine453,730 N

Specifications for Titan IIID

Titan IIIE

The Titan IIIE was built specifically for NASA as a launch vehicle for its deep space missions. The first two stages were identical to the Titan IIIC. On top of this was a third stage consisting of a Centaur D1T upper stage. This stage developed a thrust of 133,375 N. For the two Helios missions in 1974 and 1976, a further stage was added which was propelled by a Thiokol TE-M-364-4 solid fuelled motor. The length of the four stage launch vehicle was up to 48.76 m, depending on the payload it carried and it had a capability to place payload of up to 15,400 kg into orbit. Seven flights were conducted between 11 February 1974 and 5 September 1977, of which one failed.

Photo: Author's collection
Titan IIIE


Stage Length Diameter Engine Fuel Thrust
0------2 United Tech 1205solid 5,849,620 N
each
122.22 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,339,852 N
27.50 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine453,730 N
39.60 m3.05 m2 P&W RL-10A-3-3Lox/LH2 131,227 N

Specifications for Titan IIIE

Titan IIIL

The Titan IIIL was a mid-1960s proposal for a launcher to place heavy payloads into low-Earth orbit. Its principal feature was a larger diameter first stage to accommodate four engines rather than two. A version with four strap-ons was also considered. Neither version proceeded beyond the early design stage as there were no perceived payloads that required these launch vehicles.

Stage Length Diameter Engine Fuel Thrust
0------2 United Tech 1207solid 7,117,725 N
each
129.90 m4.88 m4 Aerojet LR87-AJ-7 N2O4/Aerozine4,334,618 N
213.40 m4.88 m1 Aerojet LR91-AJ-7 N2O4/Aerozine444,835 N
39.60 m3.05 m2 P&W RL-10A-3-1 or -3Lox/LH2 131,227 N

Specifications for Titan IIIL

Titan IIIM

A Titan IIIM vehicle, which was to have larger solid fuelled boosters, was intended to be used in conjunction with the Manned Orbital Laboratory (MOL) programme. It was cancelled in 1969, by which time only the first and second stages had undergone static tests. The launch vehicle was to have a length of app. 39 m and a capability to place a 9100 kg payload into low-Earth orbit.

Stage Length Diameter Engine Fuel Thrust
0------2 United Tech 1207solid 7,117,725 N
each
124.00 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,339,852 N
28.60 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine453,730 N

Specifications for Titan IIIM

Titan 34D

A further development of the Titan III family of launchers was the Titan 34D, which used 27.60 m long strap-ons and the first and second stages of the Titan IIIC launch vehicle and combined this with the Boeing developed Inertial Upper Stage (IUS) (refer SSB-7A), which was propelled by a United Technologies solid fuelled motor or a Martin Marietta Transfer Orbit Stage (TOS). This was topped with an IUS-2 as the fourth stage. Some flights also included the Transtage of the Titan IIIC. The length of this combination was 48.76 m, depending on the size of the payload carried. Being capable of placing payloads of 14,515 kg into low-Earth orbit, the first flight was on 30 October 1982. The thirteenth and last flight was on 4 September 1989. One of these was a failure.

Photo: Author's collection
Titan 34D (SB-6A)


Stage Length Diameter Engine Fuel Thrust
0------2 United Tech 1206solid 6,227,219 N
each
123.77 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,339,852 N
28.60 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine453,730 N
3various
42.10 m1.60 m1 United Tech Orbus 6solid 78,416 N

Specifications for Titan 34D


Stage Length Diameter Engine Fuel Thrust Used
IUS3.50 m2.30 m 1 United Tech Orbus-21 +
1 United Tech Orbus 6E
solid173,500 N
+ 74,730 N
1
TOS4.60 m2.30 m1 SRMsolid185,107 N 12

Titan 34D Upper Stages

Commercial Titan 3

In the early 1990s Martin Marietta identified four launch vehicles as Commercial Titan 3. The flights were between 1 January 1990 and 25 September 1992. It was an upgraded version of the Titan 34D intended to be fitted with a Transtage, IUS (refer SSB-7A), PAM-D2 (refer SSB-9A) or the Martin Marietta Transfer Orbit Stage (TOS) upper stage. The length of this combination was 48.76 m, depending on the size of the payload carried. It was capable of placing 14,500 kg into a low-Earth orbit.

Stage Length Diameter Engine Fuel Thrust
0------2 United Tech 1206solid 6,227,219 N
each
123.77 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,339,852 N
28.60 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine453,730 N
3various

Specifications for Commercial Titan 3


Stage Length Diameter Engine Fuel Thrust Used
Transtage4.60 m3.05 m2 Aerojet AJ-10-138A N2O4/Aerozine71,110N0
IUS3.50 m2.30 m 1 United Tech Orbus-21 +
1 United Tech Orbus 6E
solid 173,500 N
+ 74,730 N
2
PAM-D21.80 m1.60 m1 Thiokol Star 63Fsolid 107,200 N1
TOS4.60 m2.30 m1 SRMsolid 185,107 N1

Commercial Titan 3 Upper Stages

Titan IV

An improved version, designated as Titan IV but also Titan 4, has been procured by the US Air Force and comes in various versions. The 'A' version was fitted with 2 United Technology 1207 strap-on boosters which had a length of 34.10 m, a diameter of 3.05 m and produced a thrust of 7,117,725 N each. The 'B' version was fitted with 2 Hercules SRMU strap-ons with a length of 33.50 m and a diameter of 3.20 m, producing a thrust of 7,562,000 N each. The length of the Titan IV was up to 62.80 m, depending on the configuration and the payload carried. The payload fairings varied from 17.10 m to 26.20 m in length and were up to 4.27 m in diameter. The last flight was on 19 October 2005.

Photo: Author's collection
Titan IV (SB-5A)


The Titan 401 version combined the first two stages of the Titan vehicle with boosters with a Centaur T upper stage. Payloads up to 21,830 kg could be placed into low-Earth orbit. The Titan 401A flew for the first time on 7 February 1994 and nine flights were conducted of which one failed. The last flight was on 12 August 1998. The Titan 401B was used for the first time on 15 October 1997. Seven flight were conducted, the last one on 9 September 2003.

Stage Length Diameter Engine Fuel Thrust
0------2 various  
126.40 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,428,400 N
29.90 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine459,526 N
39.00 m4.30 m2 P&W RL-10A-3ALox/LH 146,810 N

Specifications for Titan 401


Photo: Lockheed Martin
Titan IVB (SB-5B)


The Titan 402 version used the Boeing IUS as the upper stage and was launched from Cape Canaveral to place 17,700 kg into a low-Earth orbit. The first Titan 402A flight was on 14 June 1989 and three were made, with the last one on 22 December 1994. The first Titan 402B was launched on 24 February 1997 and five had been launched with the last one on 14 February 2004.

Stage Length Diameter Engine Fuel Thrust
0------2 various  
126.40 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,428,400 N
29.90 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine459,526 N
33.50 m2.30 m 1 United Tech Orbus-21 +
1 United Tech Orbus 6E
solid173,500 N
+ 74,730 N

Specifications for Titan 402


The Titan 403 did not carry an upper stage but had Hercules strap-on boosters instead. Titan 403 was a Titan 4 with no upper stage (NUS) launched from Vandenberg AFB. It had a 20.10 m payload fairing and was able to put a 14,685 kg into a low-Earth orbit from Vandenberg. Five Titan 403A flights were made between 8 March 1991 and 24 October 1997 of which one failed. The only two Titan 403B flights were on 17 August 2000 and 30 April 2005.

Stage Length Diameter Engine Fuel Thrust
0------2 various  
126.40 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,428,400 N
29.90 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine459,526 N

Specifications for Titan 403


The Titan 404 was a configuration with no upper stage to be launched from Vandenberg. The payload fairing size and orbital parameters are secret. Payload capacity is 13,600 kg into low-Earth orbit. Three Titan 404As were launched between 28 November 1992 and 20 December 1996. The first of three Titan 404B flights was on 22 May 1992, with the last one on 19 October 2005.

Stage Length Diameter Engine Fuel Thrust
0------2 various  
126.40 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,428,400 N
29.90 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine459,526 N

Specifications for Titan 404


The Titan 405 was similar to the Titan 403 but was launched from Canaveral. Two Titan 405A flights were conducted on 8 June 1990 and 3 July 1996. The Titan 405B version was never flown.

Stage Length Diameter Engine Fuel Thrust
0------2 various  
126.40 m3.05 m2 Aerojet LR87-AJ-11 N2O4/Aerozine2,428,400 N
29.90 m3.05 m1 Aerojet LR91-AJ-11 N2O4/Aerozine459,526 N

Specifications for Titan 405

Titan 5

The Titan 5 was a proposal for a development with an improved first stage with a Pratt & Whitney engine with a thrust of 445,728 N. No other details are known as the development was not proceeded with.


Back to Directory of U.S. Military Rockets and Missiles, Appendix 3





Last Updated: 21 January 2006