Athena-1 - Athena-1 Launch Vehicle Credit: Lockheed Martin. 37,942 bytes. 294 x 400 pixels.

Privately funded solid propellant satellite launch vehicle. Basic version with Castor 120 first stage, Castor 120 second stage, Orbus third stage, and OAM Orbital Adjustment Module. Formerly LMLV 2 (Lockheed-Martin Launch Vehicle); LLV 2 (Lockheed Launch Vehicle) .

Launches: 3. Failures: 1. Success Rate: 66.67% pct. First Launch Date: 07 January 1998. Last Launch Date: 24 September 1999. LEO Payload: 2,065 kg. to: 185 km Orbit. at: 28.5 degrees. Payload: 1,165 kg. to a: Sun synchronouts, 800 km, 98.6 deg orbit trajectory. Liftoff Thrust: 147,800 kgf. Total Mass: 120,700 kg. Core Diameter: 2.4 m. Total Length: 28.2 m. Launch Price $: 26.00 million. in 2000 price dollars.

• Stage Number: 1. 1 x Castor 120 Gross Mass: 53,020 kg. Empty Mass: 4,211 kg. Thrust (vac): 163,827 kgf. Isp: 286 sec. Burn time: 83 sec. Isp(sl): 229 sec. Diameter: 2.4 m. Span: 2.4 m. Length: 10.7 m. Propellants: Solid No Engines: 1. Castor 120

• Stage Number: 2. 1 x Castor 120 Gross Mass: 53,020 kg. Empty Mass: 4,211 kg. Thrust (vac): 163,827 kgf. Isp: 286 sec. Burn time: 83 sec. Isp(sl): 229 sec. Diameter: 2.4 m. Span: 2.4 m. Length: 10.7 m. Propellants: Solid No Engines: 1. Castor 120

• Stage Number: 3. 1 x ESBM Gross Mass: 10,810 kg. Empty Mass: 1,030 kg. Thrust (vac): 19,300 kgf. Isp: 293 sec. Burn time: 150 sec. Diameter: 2.3 m. Span: 2.3 m. Length: 3.0 m. Propellants: Solid No Engines: 1. SRM-1

• Stage Number: 4. 1 x OAM Gross Mass: 714 kg. Empty Mass: 360 kg. Thrust (vac): 90 kgf. Isp: 222 sec. Burn time: 1,500 sec. Diameter: 2.3 m. Span: 2.3 m. Length: 1.0 m. Propellants: Hydrazine No Engines: 4. MR-107

• Lunar Prospector Spacecraft: Lunar Prospector.

  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. A two year extended mission following this was possible, during which the orbit was to be lowered to 50 km and then 10 km altitude to obtain higher resolution measurements.

• Ikonos 1 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 Spacecraft: Ikonos. Mass: 726 kg.

  Commercial / civilian high resolution (1 metre resolution) photograhic satellite.

• 42 - Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991.
• 61 - Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al.