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Agena A Stage
Credit - © Mark Wade
Engine Model: Bell 8048. Government Designation: LR81-B-1. Designer: Bell. Propellants: Nitric acid/UDMH. Thrust(vac): 68.900 kN (15,489 lbf). Isp: 276 sec. Burn time: 120 sec. Mass Engine: 127 kg (279 lb). Diameter: 1.52 m (4.98 ft). Length: 2.16 m (7.08 ft). Chambers: 1. Chamber Pressure: 10.00 bar. Area Ratio: 20.00. Thrust to Weight Ratio: 55.36. Country: USA. Status: Out of production. First Flight: 1959. Last Flight: 1961. Flown: 20.

Harry Meyers made a major contribution to the development of Bell's Rascal and Agena engines. Although both of these engines were made of aluminum, the Agena started with a thick walled cylinder, and used a series of adjacent 3/16 inch drilled holes to create the same effect as stacked spaghetti rubes. These thrust chambers were coated, and worked well in the Agena engine.

Engine Model: Bell 8081. Government Designation: XLR81-BA. Designer: Bell. Propellants: Nitric acid/UDMH. Thrust(vac): 71.200 kN (16,006 lbf). Isp: 285 sec. Burn time: 240 sec. Mass Engine: 130 kg (280 lb). Diameter: 1.52 m (4.98 ft). Chambers: 1. Chamber Pressure: 10.00 bar. Area Ratio: 45.00. Oxidizer to Fuel Ratio: 2.55. Thrust to Weight Ratio: 55.82. Country: USA. Status: Out of production. First Flight: 1960. Last Flight: 1968. Flown: 156.

Engine Model: Bell 8096. Government Designation: YLR81-BA. Designer: Bell. Propellants: Nitric acid/UDMH. Thrust(vac): 71.200 kN (16,006 lbf). Isp: 293 sec. Burn time: 265 sec. Mass Engine: 132 kg (291 lb). Diameter: 1.52 m (4.98 ft). Chambers: 1. Chamber Pressure: 35.00 bar. Area Ratio: 45.00. Oxidizer to Fuel Ratio: 2.55. Thrust to Weight Ratio: 54.98. Country: USA. Status: Out of production. First Flight: 1963. Last Flight: 1987. Flown: 175.

Engine Model: Bell 8247. 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.
Bell 8000 used on Rocket Stages
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© Mark Wade, 1997 - 2008 except where otherwise noted.