Bell 8247

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Bell 8247

Part of Bell 8000

Bell Nitric acid/UDMH rocket engine. Out of Production. Version of Agena engine for the Gemini-Agena Target Vehicle. Minimum capability of five restarts and a demonstrated capability of fifteen restarts. First flight 1963.

AKA: XLR81-BA-13. Status: Out of Production. Date: 1962-1964. Number: 248 . Thrust: 71.20 kN (16,006 lbf). Unfuelled mass: 132 kg (291 lb). Specific impulse: 291 s. Burn time: 240 s. Diameter: 1.52 m (4.98 ft).

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.

Engine: 132 kg (291 lb). Chamber Pressure: 34.00 bar. Area Ratio: 45. Propellant Formulation: RFNA/UDMH. Oxidizer to Fuel Ratio: 2.57. Coefficient of Thrust vacuum: 1.829. Restarts: 13.

Family: Storable liquid. Country: USA. Propellants: Nitric acid/UDMH. Agency: Bell.

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