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Athena-3
Part of Athena Family
American all-solid orbital launch vehicle. Planned but never flown heavier-lift version of Athena.

AKA: LLV 3;LMLV 3. Status: Out of production. Payload: 3,655 kg (8,057 lb). Thrust: 2,140.00 kN (481,090 lbf). Gross mass: 146,800 kg (323,600 lb). Height: 28.20 m (92.50 ft). Diameter: 2.36 m (7.74 ft). Apogee: 185 km (114 mi).

LEO Payload: 3,655 kg (8,057 lb) to a 185 km orbit at 28.50 degrees. Launch Price $: 27.000 million in 1994 dollars.

Stage Data - Athena-3

  • Stage 0. 2 x Castor 4A. Gross Mass: 11,743 kg (25,888 lb). Empty Mass: 1,529 kg (3,370 lb). Thrust (vac): 478.309 kN (107,528 lbf). Isp: 266 sec. Burn time: 56 sec. Isp(sl): 237 sec. Diameter: 1.02 m (3.34 ft). Span: 1.02 m (3.34 ft). Length: 9.12 m (29.92 ft). Propellants: Solid. No Engines: 1. Engine: Castor 4A. Status: In Production.
  • Stage 1. 1 x Castor 120. Gross Mass: 53,020 kg (116,880 lb). Empty Mass: 4,211 kg (9,283 lb). Thrust (vac): 1,606.594 kN (361,177 lbf). Isp: 286 sec. Burn time: 83 sec. Isp(sl): 229 sec. Diameter: 2.36 m (7.74 ft). Span: 2.36 m (7.74 ft). Length: 10.70 m (35.10 ft). Propellants: Solid. No Engines: 1. Engine: Castor 120. Status: In Production. Comments: Modification of Peacekeeper ICBM first stage.
  • Stage 2. 1 x Castor 120. Gross Mass: 53,020 kg (116,880 lb). Empty Mass: 4,211 kg (9,283 lb). Thrust (vac): 1,606.594 kN (361,177 lbf). Isp: 286 sec. Burn time: 83 sec. Isp(sl): 229 sec. Diameter: 2.36 m (7.74 ft). Span: 2.36 m (7.74 ft). Length: 10.70 m (35.10 ft). Propellants: Solid. No Engines: 1. Engine: Castor 120. Status: In Production. Comments: Modification of Peacekeeper ICBM first stage.
  • Stage 3. 1 x ESBM. Gross Mass: 10,810 kg (23,830 lb). Empty Mass: 1,030 kg (2,270 lb). Thrust (vac): 189.200 kN (42,534 lbf). Isp: 293 sec. Burn time: 150 sec. Diameter: 2.30 m (7.50 ft). Span: 2.30 m (7.50 ft). Length: 3.00 m (9.80 ft). Propellants: Solid. No Engines: 1. Engine: SRM-1. Status: In Production.
  • Stage 4. 1 x OAM. Gross Mass: 714 kg (1,574 lb). Empty Mass: 360 kg (790 lb). Thrust (vac): 882 N (198 lbf). Isp: 222 sec. Burn time: 1,500 sec. Diameter: 2.30 m (7.50 ft). Span: 2.30 m (7.50 ft). Length: 1.00 m (3.20 ft). Propellants: Hydrazine. No Engines: 4. Engine: MR-107. Status: In Production. Comments: Monopropellant final stage providing precise orbital injection. Pressure-fed, indefinite number of restarts.



Family: all-solid, orbital launch vehicle. Country: USA. Stages: OAM, Castor 4A engine, Castor 120, SRM-1. Agency: Lockheed.

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