 Takeoff of Jupiter-A CC-39 | |
| Manufacturer | Redstone Arsenal, Chrysler |
|---|---|
| Country of origin | United States |
| Size | |
| Height | 69.50 feet (21.18 m) |
| Diameter | 5.83 feet (1.78 m) |
| Mass | 64,060 pounds (29,060 kg) |
| Stages | 1 |
| Capacity | |
| Payload to Low Earth Orbit | |
| Mass | 11 kg (24 lb) |
| Launch history | |
| Status | Retired |
| Launch sites | LC-5 and 6, Cape Canaveral Missile Annex, Florida |
| Total launches | 25 |
| First flight | 1955-09-22 |
| Last flight | 1958-06-12 |
| First stage – Redstone | |
| Powered by | 1 North American Aviation (Rocketdyne) 75-110 A-3, A-4, A-6 |
| Maximum thrust | 91,350 lbf; 406.33 kN (41,434 kgf) |
| Specific impulse | 265 s (2.60 km/s) |
| Burn time | 155 s |
| Propellant | LOX/Ethanol, LOX/Hydyne |
The Jupiter-A was an American sounding rocket and test vehicle derived from the Redstone ballistic missile, developed in the mid-1950s by Redstone Arsenal and Chrysler. It was the first variant of the Redstone to fly, and served as a testbed for components intended for use in the PGM-19 Jupiter medium-range ballistic missile (MRBM).
Components tested aboard Jupiter-A flights included the Redstone ST-80 inertial guidance platform, Jupiter angle-of-attack sensors, warhead fuzing systems, and explosive bolts. The vehicle stood 21.20 metres (69.6 ft) tall with a diameter of 1.78 metres (5.8 ft).
A total of twenty-five launches were conducted from Cape Canaveral Air Force Station, Florida, using Launch Complexes 5 and 6, between September 1955 and June 1958.12
Description
Jupiter-A was 21.20 metres (69.6 ft) tall, with a body diameter of 1.78 metres (5.8 ft) and fins extending 4 metres (13 ft) in height.31
The first two flights, RS-11 and RS-12 (launched on September 22, 1955 and December 6, 1955), were powered by a Rocketdyne NAA 75-110 A-3 engine. Starting with Jupiter-A RS-18 on March 15, 1956 the A-4 rocket engine was used. From October 2, 1957 the A-6 engine was used (the A-5 version never entered service).
The rocket used a fuel consisting of 75% ethanol cut with 25% water and liquid oxygen as oxidizer. Jupiter-A RS-22 tested an A-4 rocket engine burning Hydyne as fuel, with a mixture of 60% UDMH and 40% DETA.32
Flight history
Twenty-five Jupiter-A launch attempts were made between 1955 and 1958 from Cape Canaveral, Florida.124
| Flight No. | Serial number | Launch date | Launch pad | Notes | Result |
|---|---|---|---|---|---|
| 1 | RS-11 /
RS-HH |
September 22, 1955 | LC-6 | First flight with full guidance system | Failure |
| 2 | RS-12 /
RS-HU |
December 6, 1955 | LC-6 | First flight successful with inertial guidance | Success |
| 3 | RS-18 /
RS-HL |
March 15, 1956 | LC-6 | The first launch of Jupiter A by the ABMA, a modified Redstone missile equipped with elements of the Jupiter IRBM's navigation and inertial control system. | Failure |
| 4 | RS-19 /
RS-HE |
May 16, 1956 | LC-6 | Failure | |
| 5 | CC-13 /
CC-HN |
July 19, 1956 | LC-5 | First missile built by the Chrysler Corporation | Failure |
| 6 | RS-20 /
RS-UX |
August 8, 1956 | LC-6 | Success | |
| 7 | CC-14 /
CC-HT |
October 18, 1956 | LC-6 | Success | |
| 8 | RS-25 /
RS-US |
October 31, 1956 | LC-6 | Ground cutoff command given after 10 seconds of flight due to a yaw gyroscope malfunction. | Failure |
| 9 | RS-28 /
RS-UL |
November 14, 1956 | LC-6 | LEV-3 guidance system used instead of ST-80 | Failure |
| 10 | CC-15 /
CC-HS |
November 29, 1956 | LC-6 | Success | |
| 11 | RS-22 /
RS-UU |
December 19, 1956 | LC-6 | Hydyne fuel used | Failure |
| 12 | CC-16 /
CC-HV |
January 19, 1957 | LC-6 | Failure | |
| 13 | RS-32 | March 14, 1957 | LC-6 | First missile shipped directly from Chrysler to the test site | Failure |
| 14 | CC-30 /
CC-NX |
March 28, 1957 | LC-6 | Success | |
| 15 | CC-31 /
CC-NH |
June 26, 1957 | LC-6 | Failure | |
| 16 | CC-35 /
CC-NS |
July 12, 1957 | LC-6 | Success | |
| 17 | CC-37 /
CC-NI |
July 26, 1957 | LC-6 | Success | |
| 18 | CC-38 /
CC-NL |
September 11, 1957 | LC-6 | Failure | |
| 19 | CC-39 /
CC-NE |
October 2, 1957 | LC-6 | First flight test of the Rocketdyne A-6 engine with a sea-level thrust of 78,000 lbf (350 kN). | Success |
| 20 | CC-41 /
CC-TH |
October 31, 1957 | LC-6 | Failure | |
| 21 | CC-42 /
CC-TU |
December 11, 1957 | LC-6 | Hardtack adapter kit test | Success |
| 22 | CC-45 /
CC-TS |
January 15, 1958 | LC-6 | Hardtack gondola test | Success |
| 23 | CC-46 /
CC-TV |
February 12, 1958 | LC-6 | Hardtack adapter kit test | Success |
| 24 | CC-43 /
CC-TN |
February 27, 1958 | LC-6 | Success | |
| 25 | CC-48 /
CC-TL |
June 11, 1958 | LC-6 | Failure |
Gallery
-
Jupiter-A RS-18, March 15, 1956 -
Jupiter-A RS-19, May 16, 1956 -
Jupiter-A CC-14, October 18, 1956 -
Jupiter-A RS-25, October 31, 1956 -
Jupiter-A CC-35, July 12, 1957 -
Jupiter-A CC-39, October 2, 1957
References
References
- "JUPITER A FACT SHEET | Spaceline". Retrieved 2025-12-03.
- "Space Launch Report". spacelaunchreport.com. Archived from the original on 2014-04-01. Retrieved 2025-12-03.
- "Jupiter A". www.astronautix.com. Retrieved 2025-12-03.
- Grimwood, James; Strowd, Frances (27 July 1962). "Appendix 7 - Jupiter A firings". History of the Jupiter missile system (PDF). U. S. Army Ordnance Missile Command. pp. 151–155.