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Clementine -

Credit: USAF. 11,822 bytes. 288 x 216 pixels.

Class: Planetary. Type: Lunar. Nation: United States. Agency: BMDO, NASA. Manufacturer: Naval Research Laboratory, Lawrence Livermore Nati.

Clementine was jointly sponsored by BMDO and NASA as the Deep Space Program Science Experiment (DSPSE). The principal objective was to space qualify lightweight imaging sensors and component technologies for the next generation of DOD spacecraft. Intended targets for these sensors included the Moon, a near-Earth asteroid (1620 Geographos), and the spacecraft's interstage adapter. After entering lunar orbit, Clementine providing over 1.6 million images of the Moon's surface. After the lunar mapping phase was completed, the spacecraft left lunar orbit for a planned encounter with Geographos, but was unable to rendezvous due to a spacecraft anomaly. Spacecraft: 3-axis stabilised. Dual GaAs solar arrays with 1-axis articulation. Fixed 1.1 m HGA. S-Band downlink to NASA DSN and DOD tracking stations with downlink rate up to 128 kbps.1.9 Gbit solid state recorder. Bipropellant system with 489 N thruster. Hydrazine system with 10 x 5.3 N and 7 x 22 N thrusters.32-bit R3000 processor. Lightweight RLG and IFOG (1 deg/hr). NiH2 CPV battery (15 AHr). Lightweight reaction wheels and star tracker cameras. JPEG image compression chip (from Matra Marconi). Payload: Two miniature star tracker cameras. UV/Visible camera. Near-IR camera. Long wave IR camera. High resolution camera. Laser transmitter. Charged particle telescope. Dosimeters (4). Radiation experiment. Orbital meteoroid and debris counting experiment. Total payload is 8 kg and 68 watts.
$ 80 million total project cost. Mapped moon. Asteroid flyby cancelled 1994.07.21 (due to computer failure 1994.05.17). Used Titan II/converted ICBM as launch vehicle.


Design Life: 7 months. Total Length: 1.9 m. Maximum Diameter: 1.1 m. Total Mass: 424 kg.

Clementine Chronology

25 January 1994 Clementine 1 Launch Site: Vandenberg . Launch Vehicle: Titan 2. Mass: 424 kg. Perigee: 804 km. Apogee: 409,890 km. Inclination: 63.8 deg.

SDIO sensor technology demonstration; mapped lunar surface; planned asteroid flyby cancelled due to spacecraft failure. After two Earth flybys, lunar insertion was achieved on February 21. Lunar mapping took place over approximately two months, in two parts. The first part consisted of a 5 hour elliptical polar orbit with a perilune of about 400 km at 28 degrees S latitude. After one month of mapping the orbit was rotated to a perilune of 29 degrees N latitude, where it remained for one more month. This allowed global imaging as well as altimetry coverage from 60 degrees S to 60 degrees N. After leaving lunar orbit, a malfunction in one of the on-board computers on May 7 at 14:39 UTC (9:39 AM EST) caused a thruster to fire until it had used up all of its fuel, leaving the spacecraft spinning at about 80 RPM with no spin control. This made the planned continuation of the mission, a flyby of the near-Earth asteroid Geographos, impossible. The spacecraft remained in geocentric orbit and continued testing the spacecraft components until the end of mission. Additional Details: Clementine 1.

21 July 1994 Clementine asteroid flyby cancelled

After the lunar mapping phase was completed, the spacecraft left lunar orbit for a planned encounter with Geographos, but a computer fialure on 17 May 1994 led to the flyby being cancelled.


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Last update 12 March 2001.
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© Mark Wade, 2001 .