Directory of U.S. Military Rockets and Missiles
Appendix 3: Space Vehicles
SLV-1
 
Copyright © 2003-2007 Jos Heyman
(HTML formatting by Andreas Parsch)

LTV (Vought) SLV-1 Scout

Development of the Scout launch vehicle by LTV (Vought) began in May 1958 to meet a NASA requirement for an economical launcher of limited capability. The launch vehicle that evolved was built up from a number of existing solid fuelled rockets and has been improved over the years. Correspondingly the orbiting capability increased from an original 59 kg to over 200 kg into a low-Earth orbit.

In 1959 the Department of Defense adopted the NASA design as the basis of four versions of the vehicle: three for sub-orbital missions and one for orbital missions. Initially the contract was awarded to Aeronutronic but by 1961 LTV was the prime contractor. The sub-orbital vehicles emerged as XRM-89 Blue Scout I, XRM-90 Blue Scout II and XRM-91 Blue Scout Junior whilst the orbital vehicle was named Scout and was designated XRM-92. The Blue Scout versions have been discussed in detail for the RM-89, RM-90 and RM-91 designations. The orbital Scout was also designated as SLV-1A by the Air Force. Other SLV-1 series designations, i.e. SLV-1B, LV-1B (SLV-1B(m)) and SLV-1C, all refer to suborbital Blue Scout Junior versions. It is probable that SLV-1 designations were assigned only to military Scout launches.

A typical Scout vehicle consisted of four stages. The first stage consisted of a version of the United Technologies Corp. (UTC) Algol sounding rocket whilst the second stage consisted of a Thiokol Castor version. The third stage was based on the Hercules Antares sounding rocket whilst the fourth stage was a development of the UTC Altair or the LPC/Redlands MG-18 solid fuelled upper stage. The total length of a Scout launch vehicle was app. 25 m, depending on the configuration and the fairing used.

These various stages were utilised as listed in the table:

TypeStage 1Stage 2Stage 3 Stage 4
XUTC Algol 1AdummyHercules Antares 1Adummy
X-1UTC Algol 1BThiokol Castor 1Hercules Antares 1AUTC Altair 1A
X-1AUTC Algol 1CThiokol Castor 1Hercules Antares 1AUTC Altair 1A
X-2UTC Algol 1DThiokol Castor 1Hercules Antares 2AUTC Altair 1A
X-2BUTC Algol 1DThiokol Castor 1Hercules Antares 2AUTC Altair 2
X-2MUTC Algol 1DThiokol Castor 1Hercules Antares 2ALPC/Redlands MG-18
X-3UTC Algol 2AThiokol Castor 1Hercules Antares 2AUTC Altair 1A
X-3AUTC Algol 2AThiokol Castor 1Hercules Antares 2AUTC Altair 1A
X-3CUTC Algol 2BThiokol Castor 1Hercules Antares 2AUTC Altair 1A
X-3MUTC Algol 2AThiokol Castor 1Hercules Antares 2ALPC/Redlands MG-18
X-4UTC Algol 2BThiokol Castor 1Hercules Antares 2AUTC Altair 2
X-4AUTC Algol 2AThiokol Castor 1Hercules Antares 2AUTC Altair 2
X-5AUTC Algol 2BThiokol Castor 2Hercules Antares 2A---
AUTC Algol 2DThiokol Castor 2Hercules Antares 2AUTC Altair 2
A-1UTC Algol 2CThiokol Castor 2Hercules Antares 2AUTC Altair 2
A-2UTC Algol 2CThiokol Castor 2Hercules Antares 2BUTC Altair 2
BUTC Algol 2BThiokol Castor 2Hercules Antares 2AUTC Altair 3
B-1UTC Algol 2CThiokol Castor 2Hercules Antares 2AUTC Altair 3
B-2UTC Algol 2CThiokol Castor 2Hercules Antares 2BUTC Altair 3
CUTC Algol 2CThiokol Castor 2Hercules Antares 2AUTC Altair 3 + Alcyone 1
D-1UTC Algol 3AThiokol Castor 2Hercules Antares 2AUTC Altair 3
E-1UTC Algol 3AThiokol Castor 2Hercules Antares 2AUTC Altair 3
F-1UTC Algol 3AThiokol Castor 2Hercules Antares 2BUTC Altair 3A
G-1UTC Algol 3AThiokol Castor 2Hercules Antares 3UTC Altair 3A

Configuration of Scout versions

Scout launch vehicles were used to place military as well as scientific satellites into orbit, including satellites from European Space Research Organisation (ESRO) (5), France (2), Germany (3), Great Britain (6), Germany (3), Italy (5) and The Netherlands (1). Most of the launches took place from Wallops Island and Vandenberg but there were also nine launches from the Italian operated San Marco launch platform in the Indian Ocean off the coast of Kenya.

Individual Scout launch vehicles were initially identified by the prefix ST followed by a number. Commencing with the eleventh vehicle, the identification was changed to S111 etc.

Scout X

The first flight of a Scout X, fitted with a dummy second and fourth stage, took place on 18 April 1960 from Wallops Island. Designated as SX-1, the launch was a failure. A second flight, designated ST-1, took place on 1 July 1960 and was successful. The third and final flight took place on 4 October 1960. All three flights were sub-orbital.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet XM-68-Asolid 382,473 N
26.19 m0.76 mdummy------
32.90 m0.76 m1 ABL X-254solid 64,480 N
41.49 m0.51 mdummy------

Specifications for Scout X

Scout X-1

The Scout X-1 was the first complete four stage vehicle. Five launches were conducted between 4 December 1960 and 19 December 1961. Two flights placed satellites into orbit, two failed to place satellites into orbit and one was a sub-orbital. The satellites had a mass of up to 84 kg into a low-Earth orbit.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet XM-68-Bsolid 382,473 N
26.19 m0.76 m1 Thiokol TX-33solid 244,690 N
32.90 m0.76 m1 ABL X-254solid 64,480 N
41.49 m0.51 m1 ABL X-248solid 13,615 N

Specifications for Scout X-1

Scout X-1A

The Scout X-1A had an upgraded first grade and was only used once on 1 March 1962 for a sub-orbital flight.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet XM-68-Csolid 382,473 N
26.19 m0.76 m1 Thiokol TX-33solid 244,690 N
32.90 m0.76 m1 ABL X-254solid 64,480 N
41.49 m0.51 m1 ABL X-248solid 13,615 N

Specifications for Scout X-1A

Scout X-2

The Scout X-2 version had a further improved first stage and an upgraded third stage. Only two flights were conducted. One of these, on 29 March 1962, was sub-orbital whilst the second flight, on 26 April 1962, failed to place a satellite into orbit. The Scout X-2 had a launch capability of 6 kg into a low-Earth orbit.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet XM-68-Dsolid 382,473 N
26.19 m0.76 m1 Thiokol TX-33solid 244,690 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
41.49 m0.51 m1 ABL X-248solid 13,615 N

Specifications for Scout X-2

Scout X-2B

The Scout X-2B was similar to the Scout X-2 but had an upgraded fourth stage. Only one was launched, on 27 September 1963, but failed to place a 40 kg satellite into orbit. There is no reference to a Scout X-2A version.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet XM-68-Dsolid 382,473 N
26.19 m0.76 m1 Thiokol TX-33solid 244,690 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
41.49 m0.51 m1 ABL X-258solid 22,250 N

Specifications for Scout X-2B

Scout X-2M

The next version used a different upper stage, the MG-18. Three launches were conducted between 23 May 1962 and 26 April 1963 but only one succeeded in placing a satellite into orbit. It was capable of placing a 90 kg payload into a low-Earth orbit.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet XM-68-Dsolid 382,473 N
26.19 m0.76 m1 Thiokol TX-33solid 244,690 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
41.49 m0.51 m1 LPC/Redlands MG-18solid ?

Specifications for Scout X-2M

Scout X-3

The Scout X-3 introduced a new first stage which allowed a payload of up to 87 kg to be placed into a low-Earth orbit. Six launches took place from 16 December 1962 to 27 March 1964. Of these one failed and one was sub-orbital.

Photo: via Mark Wade
Scout X-3


Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Asolid 458,183 N
26.19 m0.76 m1 Thiokol TX-33solid 244,690 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
41.49 m0.51 m1 ABL X-248solid 13,615 N

Specifications for Scout X-3

Scout X-3A

The Scout X-3A tested new equipment on a single sub-orbital flight on 31 August 1962.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Asolid 458,183 N
26.19 m0.76 m1 Thiokol TX-33solid 244,690 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
41.49 m0.51 m1 ABL X-248solid 13,615 N

Specifications for Scout X-3A

Scout X-3C

Whilst there is no reference to a Scout X-3B version, the Scout X-3C used an upgraded first stage on its one and only sub-orbital flight on 9 October 1964.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Bsolid 511,582 N
26.19 m0.76 m1 Thiokol TX-33solid 244,690 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
41.49 m0.51 m1 ABL X-248solid 13,615 N

Specifications for Scout X-3C

Scout X-3M

The Scout X-3M used the MG-18 upper stage. Two flights took place on 19 February 1963 and 20 July 1963, of which the first placed a 40 kg payload into orbit.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Asolid 458,183 N
26.19 m0.76 m1 Thiokol TX-33solid 244,690 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
41.49 m0.51 m1 LPC/Redlands MG-18solid ?

Specifications for Scout X-3M

Scout X-4

Thirteen flights were conducted with the Scout X-4 between 28 June 1963 and 6 December 1965. One of these failed whilst another one was sub-orbital. The Scout X-4 was capable of placing a 103 kg payload into low-Earth orbit.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Bsolid 511,582 N
26.19 m0.76 m1 Thiokol TX-33solid 244,690 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
41.49 m0.51 m1 ABL X-258solid 22,250 N

Specifications for Scout X-4

Scout X-4A

The Scout X-4A used an upgraded first stage. Three sub-orbital flights to test re-entry vehicles, were conducted between 18 August 1964 and 24 June 1968.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Asolid 458,183 N
26.19 m0.76 m1 Thiokol TX-33solid 244,690 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
41.49 m0.51 m1 ABL X-258solid 22,250 N

Specifications for Scout X-4A

Scout X-5A

The Scout X-5A was the only three stage version of the Scout launcher and one was flown on a sub-orbital flight on 27 April 1968.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Bsolid 511,582 N
26.19 m0.76 m1 Thiokol TX-354solid 280,285 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N

Specifications for Scout X-5A

Scout A

The Scout A was used for launches in the Transit NNSS series, placing two satellites in orbit at the same time. Twelve such flights were conducted between 21 December 1965 and 27 August 1970. In addition, one was used to launch a British scientific satellite. The launch capability was 122 kg into a low-Earth orbit.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Dsolid ?
26.19 m0.76 m1 Thiokol TX-354solid 280,285 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
41.49 m0.51 m1 ABL X-258solid 22,250 N

Specifications for Scout A

Scout A-1

The Scout A-1 version was only used once on 30 October 1973 to launch a 58 kg satellite.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Csolid 564,265 N
26.19 m0.76 m1 Thiokol TX-354solid 280,285 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
41.49 m0.51 m1 ABL X-258solid 22,250 N

Specifications for Scout A-1

Scout A-2

The Scout A-2 version was never used.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Csolid 564,265 N
26.19 m0.76 m1 Thiokol TX-354solid 280,285 N
32.90 m0.76 m1 ABL X-259Bsolid 124,550 N
41.49 m0.51 m1 ABL X-258solid 22,250 N

Specifications for Scout A-2

Scout B

Between 10 August 1965 and 15 November 1971 25 Scout B flights took place. Of these five were sub-orbital whilst 2 failed. The Scout B had a launch capability of 143 kg into low-Earth orbit.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Bsolid 511,582 N
26.19 m0.76 m1 Thiokol TX-354solid 280,285 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
42.50 m0.60 m1 UTC FW-4Ssolid 24,998 N

Specifications for Scout B

Scout B-1

Between 16 August 1971 and 22 May 1976 five Scout B-1's were launched to place satellites with a mass up to 129 kg into orbit.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Csolid 564,265 N
26.19 m0.76 m1 Thiokol TX-354solid 280,285 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
42.50 m0.60 m1 UTC FW-4Ssolid 24,998 N

Specifications for Scout B-1

Scout B-2

The Scout B-2 was a version which was not flown.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Csolid 564,265 N
26.19 m0.76 m1 Thiokol TX-354solid 280,285 N
32.90 m0.76 m1 ABL X-259Bsolid 124,550 N
42.50 m0.60 m1 UTC FW-4Ssolid 24,998 N

Specifications for Scout B-2

Scout C

The proposed Scout C version was to include a fifth stage Alcyone-1 to increase the payload capacity. The version was not proceeded with.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 Aerojet 40KS-Csolid 564,265 N
26.19 m0.76 m1 Thiokol TX-354Asolid 274,890 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
42.50 m0.60 m1 UTC FW-4Ssolid 24,998 N
5??1 Hercules BE-3solid 26,200 N

Specifications for Scout C

Scout D-1

Between 13 August 1972 and 27 June 1983 16 Scout D-1 flights were conducted. One of these was a sub-orbital flight. The improved capacity of the D-1 version gave it an orbiting capability of 185 kg into a low-Earth orbit.

Photo: via Mark Wade
Scout D-1


Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 UTC Algol 3solid 622,745 N
26.19 m0.76 m1 Thiokol TX-354solid 280,285 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
42.50 m0.60 m1 UTC FW-4Ssolid 24,998 N

Specifications for Scout D-1

Scout E-1

The Scout E-1 differed from the Scout D-1 in some of the equipment carried on board. It was used on only one flight, on 3 June 1974 to place a 27 kg satellite in orbit.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 UTC Algol 3solid 622,745 N
26.19 m0.76 m1 Thiokol TX-354solid 280,285 N
32.90 m0.76 m1 ABL X-259Asolid 93,907 N
42.50 m0.60 m1 UTC FW-4Ssolid 24,998 N

Specifications for Scout E-1

Scout F-1

The Scout F-1 had an improved fourth stage which increased the launch capability to 193 kg into low-Earth orbit. The first flight was on 7 May 1975 whilst a second flight, on 5 December 1975, failed to orbit.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 UTC Algol 3solid 622,745 N
26.19 m0.76 m1 Thiokol TX-354solid 280,285 N
32.90 m0.76 m1 ABL X-259Bsolid 124,550 N
42.50 m0.60 m1 Thiokol TE-M-640solid 27,460 N

Specifications for Scout F-1

Scout G-1

The final version of the Scout launcher was the G-1 version with a capability to place a 210 kg payload into a low-Earth orbit. Between 30 October 1979 and 9 May 1994 17 were launched.

Stage Length Diameter Engine Fuel Thrust
19.14 m1.14 m1 UTC Algol 3solid 622,745 N
26.19 m0.76 m1 Thiokol TX-354solid 280,285 N
32.90 m0.76 m1 Thiokol TE-M-762solid 82,890 N
42.50 m0.60 m1 Thiokol TE-M-640solid 27,460 N

Specifications for Scout G-1

In total 120 Scout launch vehicles were used for orbital and sub-orbital flights. LTV made various attempts to extend the life of the launcher family and one of the proposals was a version with four solid fuelled strap-ons. In this configuration the launch vehicle would have been capable to place 600 kg into a circular orbit.

Scout 2

Italy always had a connection with the Scout launch vehicle, through the San Marco launch platform as well as the San Marco satellites. It was therefore fitting for the Italian space industry to consider an Italian/European built development under the general designation of Scout 2. The proposed vehicle would have been capable of placing 521 kg payloads into low-Earth orbit.

Photo: ESA
Scout 2


Stage Length Diameter Engine Fuel Thrust
0------2 Nissan SPB 7-35solid 690,020 N
19.14 m1.14 m1 UTC FW-4S/TE-M-640Asolid 622,745 N
26.19 m0.76 m1 Thiokol TX-354solid 280,285 N
31.50 m0.76 m1 SEP Mage-2solid 45,485 N
42.50 m0.60 m1 Thiokol TE-M-640solid 27,460 N

Specifications for Scout 2


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Last Updated: 9 July 2007