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Athena-1
Credit - Lockheed Martin
Orbital launch vehicle. Country: USA. Status: Retired 2001.

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.

Manufacturer: Lockheed. Launches: 7. Failures: 2. Success Rate: 71.43%. First Launch Date: 1995-08-15. Last Launch Date: 2001-09-30. Launch data is: complete. Version:

Athena-1. All-solid orbital launch vehicle. Other Designations: LMLV. Manufacturer's Designation: LLV.

Basic version of the Athena with a Castor 120 first stage, Orbus second stage, and OAM Orbital Adjustment Module.

Launches: 4. Failures: 1. First Launch Date: 1995-08-15. Last Launch Date: 2001-09-30. LEO Payload: 820 kg (1,800 lb). to: 185 km Orbit. at: 28.50 degrees. Payload: 360 kg (790 lb). to a: Sun synchronouts, 800 km, 98.6 deg orbit trajectory. Associated Spacecraft: GemStar, Lewis, Oscar, ROCSAT, Sapphire, Starshine, Uosat. Liftoff Thrust: 1,449.000 kN (325,748 lbf). Total Mass: 66,300 kg (146,100 lb). Core Diameter: 2.36 m (7.74 ft). Total Length: 18.90 m (62.00 ft). Launch Price $: 17.000 million. in: 2000 price dollars.

  • Stage1: 1 x SR118. Gross Mass: 53,020 kg (116,880 lb). Empty Mass: 4,211 kg (9,283 lb). Motor: 1 x Castor 120. Thrust (vac): 1,606.594 kN (361,177 lbf). Isp: 286 sec. Burn time: 83 sec. Length: 10.70 m (35.10 ft). Diameter: 2.36 m (7.74 ft). Propellants: Solid.
  • Stage2: 1 x ESBM. Gross Mass: 10,810 kg (23,830 lb). Empty Mass: 1,030 kg (2,270 lb). Motor: 1 x SRM-1. Thrust (vac): 189.200 kN (42,534 lbf). Isp: 293 sec. Burn time: 150 sec. Length: 3.00 m (9.80 ft). Diameter: 2.30 m (7.50 ft). Propellants: Solid.
  • Stage3: 1 x OAM. Gross Mass: 714 kg (1,574 lb). Empty Mass: 360 kg (790 lb). Motor: 4 x MR-107. Thrust (vac): 882 N (198 lbf). Isp: 222 sec. Burn time: 1,500 sec. Length: 1.00 m (3.20 ft). Diameter: 2.30 m (7.50 ft). Propellants: Hydrazine.
Version:

Athena-2. All-solid orbital launch vehicle. Other Designations: LMLV 2. Manufacturer's Designation: LLV 2.

The Athena-2 version featured a Castor 120 first stage, Castor 120 second stage, Orbus third stage, and OAM Orbital Adjustment Module.

Launches: 3. Failures: 1. First Launch Date: 1998-01-07. Last Launch Date: 1999-09-24. LEO Payload: 2,065 kg (4,552 lb). to: 185 km Orbit. at: 28.50 degrees. Payload: 1,165 kg (2,568 lb). to a: Sun synchronouts, 800 km, 98.6 deg orbit trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: Ikonos, Lunar Prospector. Liftoff Thrust: 1,449.000 kN (325,748 lbf). Total Mass: 120,700 kg (266,000 lb). Core Diameter: 2.36 m (7.74 ft). Total Length: 28.20 m (92.50 ft). Launch Price $: 26.000 million. in: 2000 price dollars.

  • Stage1: 1 x SR118. Gross Mass: 53,020 kg (116,880 lb). Empty Mass: 4,211 kg (9,283 lb). Motor: 1 x Castor 120. Thrust (vac): 1,606.594 kN (361,177 lbf). Isp: 286 sec. Burn time: 83 sec. Length: 10.70 m (35.10 ft). Diameter: 2.36 m (7.74 ft). Propellants: Solid.
  • Stage2: 1 x SR118. Gross Mass: 53,020 kg (116,880 lb). Empty Mass: 4,211 kg (9,283 lb). Motor: 1 x Castor 120. Thrust (vac): 1,606.594 kN (361,177 lbf). Isp: 286 sec. Burn time: 83 sec. Length: 10.70 m (35.10 ft). Diameter: 2.36 m (7.74 ft). Propellants: Solid.
  • Stage3: 1 x ESBM. Gross Mass: 10,810 kg (23,830 lb). Empty Mass: 1,030 kg (2,270 lb). Motor: 1 x SRM-1. Thrust (vac): 189.200 kN (42,534 lbf). Isp: 293 sec. Burn time: 150 sec. Length: 3.00 m (9.80 ft). Diameter: 2.30 m (7.50 ft). Propellants: Solid.
  • Stage4: 1 x OAM. Gross Mass: 714 kg (1,574 lb). Empty Mass: 360 kg (790 lb). Motor: 4 x MR-107. Thrust (vac): 882 N (198 lbf). Isp: 222 sec. Burn time: 1,500 sec. Length: 1.00 m (3.20 ft). Diameter: 2.30 m (7.50 ft). Propellants: Hydrazine.
Version:

Athena-3. All-solid orbital launch vehicle. Status: Out of production. Other Designations: LMLV 3. Manufacturer's Designation: LLV 3.

Planned but never flown heavier-lift version of Athena.

LEO Payload: 3,655 kg (8,057 lb). to: 185 km Orbit. at: 28.50 degrees. Liftoff Thrust: 2,140.000 kN (481,090 lbf). Total Mass: 146,800 kg (323,600 lb). Core Diameter: 2.36 m (7.74 ft). Total Length: 28.20 m (92.50 ft). Launch Price $: 27.000 million. in: 1994 price dollars.

  • Stage0: 2 x Castor 4A. Gross Mass: 11,743 kg (25,888 lb). Empty Mass: 1,529 kg (3,370 lb). Motor: 1 x Castor 4A. Thrust (vac): 478.309 kN (107,528 lbf). Isp: 266 sec. Burn time: 56 sec. Length: 9.12 m (29.92 ft). Diameter: 1.02 m (3.34 ft). Propellants: Solid.
  • Stage1: 1 x SR118. Gross Mass: 53,020 kg (116,880 lb). Empty Mass: 4,211 kg (9,283 lb). Motor: 1 x Castor 120. Thrust (vac): 1,606.594 kN (361,177 lbf). Isp: 286 sec. Burn time: 83 sec. Length: 10.70 m (35.10 ft). Diameter: 2.36 m (7.74 ft). Propellants: Solid.
  • Stage2: 1 x SR118. Gross Mass: 53,020 kg (116,880 lb). Empty Mass: 4,211 kg (9,283 lb). Motor: 1 x Castor 120. Thrust (vac): 1,606.594 kN (361,177 lbf). Isp: 286 sec. Burn time: 83 sec. Length: 10.70 m (35.10 ft). Diameter: 2.36 m (7.74 ft). Propellants: Solid.
  • Stage3: 1 x ESBM. Gross Mass: 10,810 kg (23,830 lb). Empty Mass: 1,030 kg (2,270 lb). Motor: 1 x SRM-1. Thrust (vac): 189.200 kN (42,534 lbf). Isp: 293 sec. Burn time: 150 sec. Length: 3.00 m (9.80 ft). Diameter: 2.30 m (7.50 ft). Propellants: Solid.
  • Stage4: 1 x OAM. Gross Mass: 714 kg (1,574 lb). Empty Mass: 360 kg (790 lb). Motor: 4 x MR-107. Thrust (vac): 882 N (198 lbf). Isp: 222 sec. Burn time: 1,500 sec. Length: 1.00 m (3.20 ft). Diameter: 2.30 m (7.50 ft). Propellants: Hydrazine.

Athena Chronology

1995 August 15 - 22:30 GMT - Vandenberg SLC6. LV Model: Athena-1 . LLV-1 DLV FAILURE: Destroyed by range safety 160 sec into flight after failure of thrust vector control system. GemStar 1 (VitaSat) Mass: 113 kg (249 lb). Spacecraft: GemStar. Agency: LMSC. Global Electronic Messaging Satellite;.

1997 August 23 - 06:51 GMT - Vandenberg SLC6. LV Model: Athena-1 . LMLV-1 LM-002 Lewis Spacecraft: Lewis. Agency: TRW/NASA. Perigee: 124 km (77 mi). Apogee: 134 km (83 mi). Inclination: 97.50 deg. Period: 87.10 min. Reentered Sep 28

1998 January 7 - 02:28 GMT - Cape Canaveral LC46. Athena-2 LM-004 Lunar Prospector Spacecraft: Lunar Prospector. Agency: NASA ARC. 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.

1999 January 27 - 00:34 GMT - Cape Canaveral LC46. Athena-1 LM-006 ROCSAT-1 Mass: 400 kg (880 lb). Spacecraft: ROCSAT. Agency: NSPO. Perigee: 606 km (376 mi). Apogee: 653 km (405 mi). Inclination: 35.00 deg. Taiwan's first satellite, with experimental communications, ocean imagery, and ionospheric studies instruments. The Primex OAM placed itself and the payload into an elliptical transfer orbit. A second OAM burn circularized the orbit, and ROCSAT separated into a 588 x 601 km x 35.0 deg orbit.

1999 April 27 - 18:22 GMT - Vandenberg SLC6. Athena-2 LM-005 FAILURE: Payload shroud failed to separate four minutes after launch. Ikonos 1 Spacecraft: Ikonos. Agency: LMA/Denver. 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.

1999 September 24 - 18:21 GMT - Vandenberg SLC6. Athena-2 LM-007 Ikonos Mass: 726 kg (1,600 lb). Spacecraft: Ikonos. Agency: SpaceIm. Perigee: 678 km (421 mi). Apogee: 679 km (421 mi). Inclination: 98.20 deg. Commercial / civilian high resolution (1 metre resolution) photograhic satellite.

2001 September 30 - 02:40 GMT - Kodiak -. Athena-1 LM-001 Starshine 3 Mass: 67 kg (147 lb). Spacecraft: Starshine. Agency: U.S. Air Force (U.S.). Perigee: 472 km (293 mi). Apogee: 472 km (293 mi). Inclination: 67.00 deg. Possibly last Athena flight. Launch delayed from September 1, 18, 22, 23, 25, 28. This was the first orbital launch from Alaska's Kodiak Island launch site (Foul weather and auroral conditions had delayed the launch many times) . The Lockheed Martin Athena-1's Orbit Adjust Module's (OAM) four MR-107 hydrazine engines fired for 12 minutes to put the payloads in a 237 x 815 km transfer orbit. After a coast to apogee above East Africa, a second burn at 0337 GMT circularized the orbit. USAF Space Test Program satellites Picosat, Sapphire and PCSat were deployed into an 790 x 800 km x 67 deg orbit between 0344 and 0352 GMT; the OAM then made a perigee lowering burn to a 470 x 800 km orbit. Another burn half an orbit later put OAM in a 467 x 474 km orbit, from wish Starshine 3 was deployed. Finally, the OAM made a perigee-lowering depletion burn which left in a 215 x 403 km x 67.2 deg orbit from which would reenter in a few months.

Starshine-3 was a 90 kg, 0.9 m geodetic sphere that was to be observed by students. The NASA satellite was basically a passive light-reflecting sphere, consisting of 1,500 student-built mirrors (polished by kindergarten and grade school students from many countries) and 31 laser "retroreflectors". A few solar cells provide enough power to send a beacon at 145.825 MHz every minute. Ham operators around the world were expected to obtain signal strengths from which the decay (due to magnetic torque) of its spin rate could be determined. The project was managed by NASA GSFC and Starshine was built by the Naval Research Laboratory.


Bibliography:

  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: http://www.planet4589.org/jsr.html.
  • Krebs, Gunter, Gunter's Space Page, University of Frankfurt, 1996. Web Address when accessed: http://www.skyrocket.de/space.
  • Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition).
  • Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al.
  • NASA GSFC Orbital Parameters,
  • National Space Science Center Planetary Page, As of 19 February 1999.. Web Address when accessed: http://nssdc.gsfc.nasa.gov/planetary/planetary_home.html.


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© Mark Wade, 1997 - 2008 except where otherwise noted.