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Bell 8247
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Government Designation: XLR81-BA-13. Designer: Bell. Developed in: 1962-1964. Propellants: Nitric acid/UDMH. Thrust(vac): 71.200 kN (16,006 lbf). Isp: 291 sec. Burn time: 240 sec. Mass Engine: 132 kg (291 lb). Diameter: 1.52 m (4.98 ft). Chambers: 1. Chamber Pressure: 34.00 bar. Area Ratio: 45.00. Oxidizer to Fuel Ratio: 2.57. Country: USA. Status: Out of Production. First Flight: 1963. Last Flight: 1987. Flown: 248. The Gemini-Agena Target Vehicle design was an adaptation of the basic
Agena-D vehicle using the alternate Model 8247 rocket engine and additional
program-peculiar equipment required for the Gemini mission. The XLR-8I-BA-13 was a liquid bi-propellant rocket
engine with a minimum capability of five starts and a demonstrated capability of fifteen starts under vacuum conditions.
This rocket engine consisted of the following major components:
- Thrust-chamber assembly
- Multiple-restart assembly
- Turbine-pump assembly
- Overspeed shutdown electronic-gate and cable assembly
- Turbine-exhaust duct
- Propellant manifolds
- Thrust-chamber nozzle extension
Fuel used was unsymmetrical dimethylhydrazine (UDMH); oxidizer used was
inhibited red fuming nitric acid (IRFNA). The propulsion system provided
the thrust necessary to place the GATV into a selected orbit and to accomplish
major orbital changes. A minimum of five starts was available for performing
these maneuvers.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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