Engineering:Able (rocket stage)
thumb|right|Able rocket stage, is the second stage in the Vanguard rocket cutaway view thumb|right|Able rocket stage engine in the foreground
The Able rocket stage was a rocket stage manufactured in the United States by Aerojet as the second of three stages of the Vanguard rocket used in the Vanguard project from 1957 to 1959. The rocket engine used nitric acid and UDMH as rocket propellants. The Able rocket stage was discontinued in 1960. The improved Ablestar version was used as the upper stage of the Thor-Ablestar two stage launcher. The Ablestar second stage was an enlarged version of the Able rocket stage, which gave the Thor-Ablestar a greater payload capacity compared to the earlier Thor-Able. It also incorporated restart capabilities, allowing a multiple-burn trajectory to be flown, further increasing payload, or allowing the rocket to reach different orbits. It was the first rocket to be developed with such a capability and development of the stage took a mere eight months.[1]
A version of the AJ10 engine used for the Able rocket stage was used as the engine of Apollo Service Module.[2] The Able stage name represents its place as the first in the series, from the Joint Army/Navy Phonetic Alphabet.[3]
To save weight Aerojet used an aluminum tube for the engine thrust chamber. The engine used on Vanguard was an AJ10-37. On later Able models rockets the AJ10-41 and AJ10-42 engines were used. Aerojet made 21 Able rocket stages for use on launchers.[4] The Vanguard project launched 11 Able stages. Three put satellites into orbit: Vanguard 1, Vanguard 2 and Vanguard 3. The Able rocket stage and the Vanguard project were an important part of the space race between the US and Soviet union.[citation needed] The AJ10 engines used in the Able rocket stage continue to be used on later rockets and are still in use. In honor of the rocket stage during an animals in space test, a rhesus monkey name Miss Able, flew with Miss Baker on May 28, 1959.[5]
Specifications
- Loaded gross mass: 1,884 kg (4,154 lb)
- Empty (unfueled) mass 429 kg (946 lb)
- Thrust 34.69 kN (7,800 lbf)
- Specific impulse (vacuum) 270 seconds (2.6 km/s)
- Height: 5.67 m (18.6 ft)
- Diameter: 0.81 m (2 ft 8 in)
- Span: 0.84 m (2 ft 9 in)
- Burn time: 115 seconds.
See also
- Thor (rocket family)
- Atlas-Able
- Thor-Ablestar
- Multistage rocket
References
- ↑ Wade, Mark. "Delta". Encyclopedia Astronautica. http://www.astronautix.com/lvs/delta.htm.
- ↑ The First Space Race: Launching the World's First Satellites, By Matt Bille, Erika Lishock, page 163 and page 174
- ↑ Helen T. Wells; Susan H. Whiteley; Carrie E. Karegeannes. Origin of NASA Names. NASA Science and Technical Information Office. p. 5.
- ↑ astronautix.com Able Stage
- ↑ David Darling, Able
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