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Athena-2

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Athena-1 Athena-1 Launch Vehicle Credit: Lockheed Martin

AKA: LLV 2;LMLV 2. Status: Retired 1999. First Launch: 1998-01-07. Last Launch: 1999-09-24. Number: 3 . Payload: 2,065 kg (4,552 lb). Thrust: 1,449.00 kN (325,748 lbf). Gross mass: 120,700 kg (266,000 lb). Height: 28.20 m (92.50 ft). Diameter: 2.36 m (7.74 ft). Apogee: 185 km (114 mi).

LEO Payload: 2,065 kg (4,552 lb) to a 185 km orbit at 28.50 degrees. Payload: 1,165 kg (2,568 lb) to a 800 km SSO. Launch Price $: 26.000 million in 2000 dollars.

Stage Data - Athena-2

• 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.

• Lunar Prospector - . Payload: Discovery 3. Mass: 295 kg (650 lb). Nation: USA. Agency: NASA Ames. Manufacturer: Lockheed. Program: Discovery series. Class: Moon. Type: Lunar probe. Spacecraft Bus: LM-100. Spacecraft: Lunar Prospector. Decay Date: 1999-07-31 . USAF Sat Cat: 25131 . COSPAR: 1998-001A.

  The Lunar Prospector was designed for a low polar orbit investigation of the Moon, including mapping of surface composition and possible polar ice deposits, measurements of magnetic and gravity fields, and study of lunar outgassing events. Data from the 1 to 3 year mission will allow construction of a detailed map of the surface composition of the Moon, and will improve understanding of the origin, evolution, current state, and resources of the Moon. After launch, the Lunar Prospector had a 105 hour cruise to the Moon, followed by insertion into a near-circular 100 km altitude lunar polar orbit with a period of 118 minutes. The nominal mission duration was one year.

• Ikonos 1 - . Mass: 726 kg (1,600 lb). Nation: USA. Agency: Martin. Class: Surveillance. Type: Civilian surveillance satellite. Spacecraft Bus: LM-900. Spacecraft: Ikonos.

  Tracking stations downrange did not pick up the spacecraft. It was later determined that the rocket nose fairing failed to separate four minutes after launch. The extra mass caused the vehicle to reenter over the South Pacific on the first partial orbit. Space Imaging's Ikonos 1 was to have been the first commercial imaging satellite with a high a resolution camera.

• Ikonos - . Mass: 726 kg (1,600 lb). Nation: USA. Agency: SpaceIm. Manufacturer: Lockheed. Class: Surveillance. Type: Civilian surveillance satellite. Spacecraft Bus: LM-900. Spacecraft: Ikonos. USAF Sat Cat: 25919 . COSPAR: 1999-051A. Apogee: 679 km (421 mi). Perigee: 678 km (421 mi). Inclination: 98.10 deg. Period: 98.30 min. Commercial / civilian high resolution (1 metre resolution) photograhic satellite..