Directory of U.S. Military Rockets and Missiles
Appendix 3: Space Vehicles
SLV-3/SB-1/SB-2
 
SB-3
Copyright © 2003-2008 Jos Heyman
(HTML formatting by Andreas Parsch)

Lockheed Martin (General Dynamics) SLV-3/SB-1/SB-2 Atlas

Although the development of the SM-65 Atlas intercontinental ballistic missile did not commence until 1951, the "thin skin" tank, which had to be pressurised at all times, had been developed in the late forties for the Convair MX-774 missile. The first studies were conducted as MX-1593, commencing in January 1951. Later that year the military designation XB-65 was assigned to the project. By 1953 the initial design studies had been completed and it was decided to develop a single engined test bed designated as X-11, followed by a three engines X-12, before embarking on the XB-65 missile prototype, with production starting in 1959.

As a military missile substantial numbers were built but due to their slow response time when under attack, they were gradually replaced by HGM/LGM-25 Titan and LGM-30 Minuteman missiles. The Atlas missiles which became available in this manner were used as launch vehicles, either by themselves or in combination with an upper stage. In addition development of the missile as a dedicated launch vehicle, continued. The initial prime contractor of the Atlas was Convair, which later became General Dynamics. In 1994 the rights to the Atlas launch vehicle were sold to Martin Marietta, which in 1995 merged with Lockheed to become Lockheed Martin.

In addition to the military missile designations, as described separately for CGM/HGM-16, the basic Atlas first stage received military designations in the LV/SLV and SB series. The following table lists these 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
LV-3AAtlas first stage for Agena upper stages
LV-3BAtlas D (for Mercury programme)
LV-3CAtlas first stage for Centaur upper stage
SLV-3Atlas first stage for Agena D upper stage
SLV-3AAtlas first stage for Agena D upper stage but with upgraded engines and longer tank
SLV-3BAtlas first stage for Agena D upper stage but with constant diameter tank
SLV-3CAtlas first stage for Centaur D upper stage but with constant diameter tank
SLV-3DAtlas first stage for Centaur D1AR upper stage but with constant diameter tank
SB-1AAtlas E
SB-2AAtlas II
SB-2BAtlas IIA, Atlas IIAS

Individual launch vehicles were identified by a number followed by the type letter of the basic Atlas vehicle. Military vehicles also had serial numbers. The Atlas Centaur combinations were identified by the letters AC followed by a sequential number.

Drawing: Mark Wade
Atlas Family
From left: MX-774 of 1946; MX-1593 of 1953; Atlas A, B, D; Atlas Agena D; Atlas Centaur; Atlas I, IIA, IIAS, IIIA, IIIB, V (3 versions)


Atlas A

The first launch of an Atlas A missile took place on 11 June 1957, as part of a series of eight test flights from Cape Canaveral, of which only four were successful. The first two flights, on 11 June 1957 and 25 September 1957, were not successful. The third, and first fully successful flight, took place on 17 September 1957 and the last flight was on 3 June 1958. The Atlas A was never used for the launching of satellites.

Stage Length Diameter Engine Fuel Thrust
123.20 m3.05 m2 Rocketdyne XLR89-NA-1Lox/kerosene 1,517,466 N

Specifications for Atlas A

Atlas B

The Atlas B was capable of placing a payload of 68 kg into orbit. Its first test launch took place on 9 July 1958 and in total ten launches were made until 4 February 1959 of which 4 failed. All launches were sub-orbital except for the eighth launch, which placed the 70 kg Score satellite in orbit on 18 December 1958. The Atlas B which was used for the Score satellite has also been referred to as Atlas-Score.

Stage Length Diameter Engine Fuel Thrust
125.90 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,517,466 N
+ 363,231 N

Specifications for Atlas B

Atlas C

The Atlas C was used for six flights between 23 December 1958 and 24 August 1959, none of which orbited a satellite but were for sub-orbital programmes to test the thin skinned fuel tanks and the radio command configuration. Two of the flights failed.

Photo: Author's collection
Atlas C


Stage Length Diameter Engine Fuel Thrust
125.90 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,517,466 N
+ 363,231 N

Specifications for Atlas C

Atlas D

The Atlas D version was the initial production version with a length of up to 25 m and was launched as a missile for the first time in July 1959. Known military serials indicate 121 Atlas D missiles were built. The missile test programme lasted until 23 January 1961 and involved 49 launches of which 6 failed, 8 were partially successful and 35 were successful. The last flight was on 7 November 1967.

The use as a space launcher started on 9 September 1959 and of the 19 launches, three failed and three were sub-orbital. The last launch was on 27 July 1967. These basic missiles were fitted with an additional upper stage and have also been referred to as Atlas Satar. Those Atlas D launch vehicles used in the Mercury programme were also referred to as Atlas-Mercury and could place payloads of 1360 kg into a low-Earth orbit. The remainder of the Atlas D missiles were used as first stages in the Atlas configurations with the Agena, Able and Centaur upper stages although the actual disposition is not known.

Photo: Author's collection
Atlas D


Stage Length Diameter Engine Fuel Thrust
121.20 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,517,466 N
+ 363,231 N
22.23 m0.76 m1 Thiokol TE-M-364Solid 43,552 N

Specifications for Atlas D

Atlas E

The Atlas E was launched successfully for the first time on 24 February 1961. Known serials indicate that 203 missiles were built. The 18th and final Atlas E missile was launched on 13 February 1962 in a test programme which had 9 successful launches, 7 partial successful launches and 2 failures.

In the eighties surplus Atlas E missiles, which had a length of 28.10 m, were used as space launch vehicles after having been fitted with an additional upper stage, allowing them to place a 820 kg payload into a low-Earth orbit. Between 18 December 1981 and 24 March 1995 a total of 25 flights were made of which two failed. The remainder of the Atlas E missiles were used as first stages in the Atlas configurations the Agena, Able and Centaur upper stages although the actual disposition is not known.

Stage Length Diameter Engine Fuel Thrust
120.10 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,645,026 N
+ 386,395 N
22.23 m0.76 m1 Thiokol TE-M-364Solid 43,552 N

Specifications for Atlas E

Atlas F

The Atlas F differed from the Atlas E by having a modified fuel system. The version was launched successfully for the first time on 8 August 1961. Known serials indicate 122 missiles were built. Surplus military missiles were fitted with an additional upper stage and were used as space launch vehicles from 6 April 1968 to 23 June 1981. They had a payload capacity of 820 kg into a low-Earth orbit. A total of 20 flights were made of which one was a failure. The remainder of the Atlas F missiles were used as first stages for the Agena, Able, Burner and Centaur upper stages.

Stage Length Diameter Engine Fuel Thrust
120.10 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,645,026 N
+ 386,395 N
22.23 m0.76 m1 Thiokol TE-M-364Solid 43,552 N

Specifications for Atlas F

Atlas G

The Atlas G versions had further improved engines. It was specifically developed as a first stage for the Atlas Centaur combination and was not flown as a launch vehicle without the upper stage.

Stage Length Diameter Engine Fuel Thrust
127.00 m3.05 m 2 Rocketdyne LR89-NA-7 +
1 Rocketdyne LR105-NA-7
Lox/kerosene1,896,085 N
+ 386,395 N

Specifications for Atlas G

Atlas H

The Atlas H version had further improved engines. Between 5 February 1984 and 15 May 1987 three were used as space launch vehicles for payload of up to 3630 kg into a low-Earth orbit.

Stage Length Diameter Engine Fuel Thrust
127.00 m3.05 m 2 Rocketdyne LR89-NA-7 +
1 Rocketdyne LR105-NA-7
Lox/kerosene1,896,085 N
+ 386,395 N

Specifications for Atlas H

Atlas Able IV and V

To increase the launch capability the Atlas D basic stage was combined with the Able IV and V upper stages developed by Aerojet and Allegheny Ballistic Laboratories for the Vanguard launch vehicle. After three failed flights between 26 November 1959 and 15 December 1960 it became evident that the Atlas Able combination was not successful and further development was abandoned. The length of the vehicle was up to 35 m and it would have been capable to launch a payload of 170 kg into a low-Earth orbit.

Stage Length Diameter Engine Fuel Thrust
120.60 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,517,466 N
+ 363,231 N
26.60 m0.80 m1 Aerojet AJ-10-42 N2O4/UDMH33,345 N
30.50 m0.50 m1 ABL X-248 AltairSolid 13,340 N

Specifications for Atlas Able


The Atlas Vega was a proposed development of the Atlas Able but was cancelled when the Atlas Agena B vehicle was developed. The second stage was to have been propelled by a General Electric liquid fuelled engine, whilst a third stage was to be propelled by an engine to be developed by the Jet Propulsion Laboratory. An orbiting capability of 2270 kg into a low-Earth orbit was envisaged.

Atlas Agena

The Atlas D first stage was also mated with the Lockheed Agena upper stage which had been developed in associations with the US military reconnaissance satellite programmes as described for RM-81.

The Atlas Agena A combination had a capacity to place a 490 kg payload into orbit and four were launched between 26 February 1960 and 31 January 1961, of which two launches failed. It had a maximum length of 31.10 m.

Photo: via Jonathan McDowell's collection
Atlas Agena A


Stage Length Diameter Engine Fuel Thrust
120.30 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,517,466 N
+ 363,231 N
24.70 m1.50 m1 Bell LR81-BA-5 N2O4/UDMH68,900 N

Specifications for Atlas Agena A


The Atlas Agena B introduced an improved and longer Agena engine. Between 12 July 1961 and 7 June 1966 28 were launched of which five failed. The combination, which had a length of up to 33 m, was capable to place a payload of 2627 kg into low-Earth orbit.

Photo: via Jonathan McDowell's collection
Atlas Agena B


Stage Length Diameter Engine Fuel Thrust
120.70 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,645,026 N
+ 386,395 N
27.20 m1.50 m1 Bell LR81-BA-7 N2O4/UDMH71,100 N

Specifications for Atlas Agena B


The Atlas Agena D combination, with a length of up to 35 m, was capable of orbiting payloads of up to 2718 kg. The first flight was on 12 July 1963 and until the last flight on 8 April 1978, 76 were launched of which 5 failed. Many of these launches placed multiple satellites into orbit.

Photo: Author's collection
Atlas Agena D


Stage Length Diameter Engine Fuel Thrust
120.70 m3.05 m 2 Rocketdyne LR89-NA-7 +
1 Rocketdyne LR105-NA-7
Lox/kerosene1,896,085 N
+ 386,395 N
27.20 m1.50 m 1 Bell LR81-BA-9N2O4/UDMH71,100 N

Specifications for Atlas Agena D


There was also a version of the Atlas Agena D with a third stage based on the Burner II, with a Star-37 solid fuelled engine which had a diameter of 0.70 m, a length of 0.80 m and a thrust of 43,552 N with a further fourth stage with a Thiokol TE-M-364-2 Star-17) solid fuelled engine with a diameter of 0.40 m, a length of 1.00 m and a thrust of 19,614 N.

In addition there was a single flight, on 27 June 1978, which used an Atlas F as the first stage.

Atlas Antares II

The Atlas launch vehicle was also combined with an Antares-II solid fuelled sounding rocket as upper stage. It was used on 22 May 1965 for a sub-orbital flight designated as Fire-2.

Stage Length Diameter Engine Fuel Thrust
120.70 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,645,026 N
+ 386,395 N
22.90 m0.80 m1 ABL X-259Solid 93,098 N

Specifications for Atlas Antares II

Atlas Burner II

The Atlas F was matched with the Burner II upper stage. The vehicle had an orbiting capacity of 215 kg into low-Earth orbit and between 16 August 1968 and 24 February 1979 three flights were conducted of which one failed.

Stage Length Diameter Engine Fuel Thrust
120.70 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,645,026 N
+ 386,395 N
20.80 m0.70 m1 Thiokol TE-M-364-2solid 43,552 N

Specifications for Atlas Burner II

Atlas Centaur

The Centaur upper stage was initially developed by General Dynamics to place military communications satellites into orbit. When the programme was cancelled, the launcher was handed over for civilian use by NASA. The first stage was based on surplus military Atlas D missiles. The Atlas G was also used as a first stage after all Atlas D launch vehicles had been depleted. The first stages only differed in minor detail and the combinations that occurred were:

Atlas typeCentaur typeNumber
LV-3CA1
LV-3CB1
LV-3CC3
LV-3CD7
SLV-3CD17
SLV-3DD1A6
SLV-3DD1AR26
GD1AR7

The stage allowed the combination, which had a length of up to 38 m, depending on the size of the payload bay, to have an initial orbiting capability of 4670 kg into low-Earth orbit but this has been improved over time.

In two instances (viz. the Pioneer-10 and -11 launches) a further Thiokol TE-M-364 upper stage was carried.

Photo: Author's collection
Atlas Centaur


The Atlas Centaur A version was the prototype of which one was launched on 8 May 1962. The launch failed.

Stage Length Diameter Engine Fuel Thrust
125.00 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,517,466 N
+ 363,231 N
29.10 m3.05 m2 P&W RL-10A-1Lox/LH2 133,453 N

Specifications for Atlas Centaur A


The next prototype was the Atlas Centaur B. Only one was flown on 27 November 1963.

Stage Length Diameter Engine Fuel Thrust
125.00 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,517,466 N
+ 363,231 N
29.10 m3.05 m2 P&W RL-10A-3Lox/LH2 133,453 N

Specifications for Atlas Centaur B


Three Atlas Centaur C launch vehicles were flown between 30 June 1964 and 2 March 1965 but only one was successful.

Stage Length Diameter Engine Fuel Thrust
125.00 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,517,466 N
+ 363,231 N
29.10 m3.05 m2 P&W RL-10A-3Lox/LH2 133,453 N

Specifications for Atlas Centaur C


The Atlas Centaur D was the first production version of which 24 were flown between 11 August 1965 and 21 August 1972. Two of these were failures.

Stage Length Diameter Engine Fuel Thrust
125.00 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,517,466 N
+ 363,231 N
29.10 m3.05 m2 P&W RL-10A-3-1 or -3Lox/LH2 131,227 N

Specifications for Atlas Centaur D


Six examples of the Atlas Centaur D1A were flown between 6 April 1973 and 22 May 1975. One of these failed.

Stage Length Diameter Engine Fuel Thrust
125.00 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,517,466 N
+ 363,231 N
29.10 m3.05 m2 P&W RL-10A-3-3Lox/LH2 131,227 N

Specifications for Atlas Centaur D1A


The next version was the Atlas Centaur D1AR which flew for the first time on 26 September 1975. Up to 25 September 1989 33 were launched, including two failures.

Stage Length Diameter Engine Fuel Thrust
125.00 m3.05 m 2 Rocketdyne LR89-NA-5 +
1 Rocketdyne LR105-NA-5
Lox/kerosene1,517,466 N
+ 363,231 N
29.10 m3.05 m2 P&W RL-10A-3-3Lox/LH2 131,227 N

Specifications for Atlas Centaur D1AR


Since then the Atlas Centaur has been referred to as simply Atlas I or Atlas II.

Atlas I

The next version was the Atlas I. Some sources use the number '1' to indicate this version but formal sources (i.e. Lockheed Martin) use the Roman numeral. The Atlas I was similar to the earlier Atlas Centaur and had a length of up to 43.90 m, depending on the payload bay employed. It had a capability to place 3,630 kg into a low-Earth orbit. The first flight designated as such was on 25 July 1990 and 11 were launched until 25 April 1997. Two of these were failures.

Stage Length Diameter Engine Fuel Thrust
122.00 m3.05 m 2 Rocketdyne LR89-NA-7 +
1 Rocketdyne LR105-NA-7
Lox/kerosene1,896,085 N
+ 386,395 N
29.10 m3.05 m2 P&W RL-10A-3-3ALox/LH2 146,810 N

Specifications for Atlas I

Atlas II

The basic Atlas II had an improved engine as well as a larger tankage. With a length of up to 47.40 m, the orbiting capability was up to 6580 kg into low-Earth orbit. 13 were launched between 7 December 1991 and 9 October 1998.

Photo: Lockheed Martin
Atlas II (SB-2A)


Stage Length Diameter Engine Fuel Thrust
124.95 m3.05 m 2 Rocketdyne RS-56-OBA +
1 Rocketdyne RS-56-OSA
Lox/kerosene2,093,795 N
+ 356,975 N
210.06 m3.05 m2 P&W RL-10A-3-3ALox/LH2 146,810 N
30.70 m2.90 m2 Marquardt R-4D N2O4/MMH9,807 N

Specifications for Atlas II

Atlas IIA

The Atlas IIA introduced an improved engine on the Centaur stage, thereby increasing the orbiting capability to 7280 kg into low-Earth orbit. It had a length of 47.40 m. Another major change was the deletion of the two small Rocketdyne LR101 vernier engines which had been used on previous versions to provide directional control during the launch. Instead a hydrazine roll control system was fitted. The first flight was on 3 August 1994 and up to 31 December 2005 20 were flown.

Stage Length Diameter Engine Fuel Thrust
124.95 m3.05 m 2 Rocketdyne RS-56-OBA +
1 Rocketdyne RS-56-OSA
Lox/kerosene2,093,795 N
+ 356,975 N
210.06 m3.05 m2 P&W RL-10A-4Lox/LH2 185,019 N

Specifications for Atlas IIA

Atlas IIAS

The Atlas IIAS incorporated two Thiokol Castor solid fuelled boosters which were attached to the first stage. This enhanced the orbiting capability to as much as 8610 kg into low-Earth orbit. The length was 47.40 m. The first flight was on 16 December 1993 and up to 31 December 2005 30 were flown.

Photo: Lockheed Martin
Atlas IIAS (SB-2B)


Stage Length Diameter Engine Fuel Thrust
0------4 Thiokol Castor 4A TX-780Solid 478,326 N
each
124.95 m3.05 m 2 Rocketdyne RS-56-OBA +
1 Rocketdyne RS-56-OSA
Lox/kerosene2,093,795 N
+ 356,975 N
210.06 m3.05 m2 P&W RL-10A-4Lox/LH2 185,019 N

Specifications for Atlas IIAS

Atlas III

Initially known as Atlas IIAR, the Atlas III differed from the traditional Atlas II launch vehicle in that the first stage was propelled by a single Energomash RD-180 engine. The RD-180 was expected to be more reliable than the traditional Atlas. Matched with the Centaur upper stage it is capable to deliver 8640 kg into a low-Earth orbit. The Centaur stage was either fitted with a single engine, as in the Atlas IIIA, or two engines as in the Atlas IIIB. The total length of the launch vehicle was 51.88 m for the Atlas IIIA, and 53.10 m for the Atlas IIIB. The first flight, of an Atlas IIIA, was on 24 May 2000 and up to 31 December 2005 two had flown. The first Atlas IIIB flight was on 21 February 2002 and as 31 December 2005 four had flown.

Photo: Lockheed Martin Photo: International Launch Services
Atlas IIIAAtlas IIIB


Stage Length Diameter Engine Fuel Thrust
129.00 m3.05 m1 Energomash RD-180Lox/kerosene 4,142,520 N
210.06 m3.05 m1 P&W RL-10A-4-1Lox/LH2 99,158 N

Specifications for Atlas IIIA


Stage Length Diameter Engine Fuel Thrust
129.00 m3.05 m1 Energomash RD-180Lox/kerosene 4,142,520 N
211.68 m3.05 m2 P&W RL-10A-4-1Lox/LH2 198,317 N

Specifications for Atlas IIIB

Atlas IV

There was no Atlas IV.

Atlas V

The latest development of the Atlas vehicle is the Atlas V to meet the US Air Force's Evolved Expendable Launch Vehicle (EELV) programme requirements. The feature that sets the Atlas V apart is the new rigid body Common Core Booster (CCB) that serves as the rocket's first stage. The CCB replaces the "balloon" pressure-stabilized stage used by previous Atlas vehicles. The stage is common and will be used in all the various configurations of the Atlas V family. The stretched Centaur also will be common across the Atlas V fleet. The total length of the launch vehicle is 58.28 m with the type 4 payload fairing, and 62.18 m with the type 5 payload fairing.

The different configurations are achieved by different sizes of payload bays as well as the number of solid-fueled rockets strapped to the first stage. In addition, the number of Centaur engines can be varied.

Stage Length Diameter Engine Fuel Thrust
0------Aerojet SRM strap-ons as requiredSolid 1,274,910 N
each
132.37 m3.81 m1 Energomash RD-180Lox/kerosene 4,142,520 N
211.68 m3.05 m1 P&W RL-10A-4-2Lox/LH2 99,158 N

Specifications for Atlas V


Photos: International Launch Services
Atlas V 401Atlas V 431


There are three distinct versions of Atlas V rockets -- the 400 series, 500 series and Heavy -- each dedicated to launching a certain class of satellite cargo into orbit. In this designation the first digit indicates the payload bay (4 m or 5 m), the second digit the number of strap-ons and the third digit the number of engines on the Centaur upper stage.

TypePayload BayStrap-onsCCB CentaurKg load GTO
4014 m01 RD 1801 RL 10A-4-24975
4024 m1 Aerojet1 RD 1802 RL 10A-4-2 
4114 m1 Aerojet1 RD 1801 RL 10A-4-25980
4214 m2 Aerojet1 RD 1801 RL 10A-4-26865
4314 m3 Aerojet1 RD 1801 RL 10A-4-27680
5015 m01 RD 1801 RL 10A-4-23990
5025 m01 RD 1802 RL 10A-4-2 
5115 m1 Aerojet1 RD 1801 RL 10A-4-25298
5125 m1 Aerojet1 RD 1802 RL 10A-4-2 
5215 m2 Aerojet1 RD 1801 RL 10A-4-26318
5325 m2 Aerojet1 RD 1802 RL 10A-4-2 
5315 m3 Aerojet1 RD 1801 RL 10A-4-27238
5325 m3 Aerojet1 RD 1802 RL 10A-4-2 
5415 m4 Aerojet1 RD 1801 RL 10A-4-28022
5425 m4 Aerojet1 RD 1802 RL 10A-4-2 
5515 m5 Aerojet1 RD 1801 RL 10A-4-28715
5525 m5 Aerojet1 RD 1802 RL 10A-4-2 
Heavy  3 RD 180  

Photos: Pat Corkery/Lockheed Martin
Atlas V 551


The first Atlas V flight was on 21 August 2002 and was of the 401 configuration. Up to 31 December 2007 there had been 12 flights. Versions included in these flights were Atlas V 401, 411, 421, 431 and 521.


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





Last Updated: 18 January 2008