Encyclopedia Astronautica
Athena-3


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

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 Peackeeper 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 Peackeeper 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.

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

More... - Chronology...


Associated Countries
Associated Engines
  • Castor 120 Thiokol solid rocket engine. 1650 kN. Isp=280s. Motor similar in size to the Peacekeeper missile stage 1 motor; filled the gap between Castor 4A and the large segmented motors. First flight 1989. More...
  • SRM-1 CSD solid rocket engine. 181.5 kN. Used in TOS; IUS-1 on Shuttle, Titan 34D. Known by manufacturer as Orbus 21. Propellant: 86% solids made up of HTPB UTP-19360A. Shape: cylindrical. Isp=296s. First flight 1982. More...

See also
  • Athena Privately funded family of solid propellant satellite launch vehicles. Originally known as LMLV (Lockheed-Martin Launch Vehicle); LLV (Lockheed Launch Vehicle). Sales did not develop as hoped by the company after the MEO-satellite bubble burst in the 1990's. More...

Associated Manufacturers and Agencies
  • Lockheed American manufacturer of rockets, spacecraft, and rocket engines. Lockheed Martin, Sunnyvale, CA, USA. More...

Associated Stages
  • Castor 4A Solid propellant rocket stage. Loaded/empty mass 11,743/1,529 kg. Thrust 478.31 kN. Vacuum specific impulse 266 seconds. More...
  • ESBM Solid propellant rocket stage. Loaded/empty mass 10,810/1,030 kg. Thrust 189.20 kN. Vacuum specific impulse 293 seconds. More...
  • OAM Hydrazine propellant rocket stage. Loaded/empty mass 714/360 kg. Thrust 0.88 kN. Vacuum specific impulse 222 seconds. Monopropellant final stage providing precise orbital injection. Pressure-fed, indefinite number of restarts. More...
  • SR118 Solid propellant rocket stage. Loaded/empty mass 53,020/4,211 kg. Thrust 1,606.59 kN. Vacuum specific impulse 286 seconds. Modification of Peackeeper ICBM first stage. More...

Home - Browse - Contact
© / Conditions for Use