 |

Clementine
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 stabilized. 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.
Launch Facts
 |
 |
Name | Int'l Desig. | Date | Site | Vehicle | Orbit | Mass(kg) |
Notes |
 |
 |
Clementine (DSPSE) | 1994-004A | 1/25/94 | WSMC | Titan 2 | Lunar | 424 |
SDIO sensor technology demonstration; mapped lunar surface; planned asteroid flyby cancelled due to spacecraft failure |
 |
Information in The Mission and Spacecraft Library is provided without
warranty or guarantee. USE AT YOUR OWN RISK.
|
 |