103 lines
3.5 KiB
Plaintext
103 lines
3.5 KiB
Plaintext
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SUBJECT: CLEMENTINE MISSION GENERAL INFORMATION FILE: UFO2396
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This file obtained from FTP site: clementine.s1.gov
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Original filename: general_info
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Original file date: March 8, 1994
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CLEMENTINE MISSION GENERAL INFORMATION
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--------------------------------------
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This file contains additional technical information about the mission timeline,
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the spacecraft, orbital parameters and sensors.
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Mission Timeline
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Design of the Clementine spacecraft was begun on March 24, 1992.
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The spacecraft was launched on January 25, 1994.
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The spacecraft departed low Earth orbit for the Moon on February 3.
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After two phasing loops, the spacecraft was injected into lunar orbit on
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February 19. Systematic observation of the lunar suface began on Febuary 26.
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The spacecraft will leave lunar orbit on May 5. After two phasing loops
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around the Earth, the spacecraft will proceed towards Geographos on June 3.
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Clementine will pass by Geographos on August 31, 1994
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Spacecraft Characteristics
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The Clementine spacecraft weighed 3400 lbs at launch including the solid
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rocket moter used for injection towards the Moon.
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The dry mass of the spacecraft at launch was 508 lbs.
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The total fuel available for maneuvers was 480 lbs.
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The spacecraft will use approximately 120 lbs of fuel to enter and leave
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lunar orbit.
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The spacecraft has three axis control with either reaction wheels or
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thrusters.
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Orbital Characteristics
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The Clementine spacecraft is in polar orbit about the Moon traveling from
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South to North.
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The orbital period is approximately 5 hours.
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The transit from south pole to north pole takes 90 minutes.
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Periselene is 400 km nominal at -20 degrees south latitude.
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At 3/5/94 17:40 UT, the spacecraft is just to the East of the Mare Orientale
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which is on the western edge of the Moon. (NOTE: Mare Orientale has a west
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longitude on a lunar map. However, looking at the moon in the southern sky at
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night, we would see Mare Orientale on the edge to our left of center. When
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facing south, East is to your left; thus the name "Orientale.")
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Aposelene is nominally 2900 km.
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At the south pole the spacecraft is approximately 780 km above the surface.
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At the north pole the spacecraft is approximately 1800 km above the surface.
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The Sun is approximately overhead at periselene.
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The orbital ground track rotates to the west about 2.3 degrees per revolution.
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Sensor Characteristics
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The Clementine spacecraft carries six cameras and a laser transmitter:
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Two wide field of view cameras (Star Tracker)
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Si CCD, 384 x 576 pixels, 1.3 mrad IFOV, 28 x 42 degree FOV
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A uv/visible camera (Uv/Vis)
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Si CCD, 384 x 288 pixels, .255 mrad IFOV, 5.6 x 4.2 degree FOV
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A high resolution visible camrra (HiRes)
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Si CCD, 384 x 288 pixels, 0.018 mrad IFOV, 0.4 x 0.3 degree FOV
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A near infrared camera (NIR)
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InSb FPA, 256 x 256 pixels, 0.385 mrad IFOV, 5.6 x 5.6 degree FOV
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A long wave infrared camera (LWIR)
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HgCdTe FPA, 128 x 128 pixels, 0.136 mrad IFOV, 1.0 x 1.0 degree FOV
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A laser transmitter used to measure the distance from the spacecraft to
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the surface of the Moon.
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Diode-pumped Nd-YAG laser
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1.06 <20>m wavelength, 180 mJ, 0.4 mrad divergence
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The UV/Vis, HiRes, and NIR cameras have multiple spectral filters and the
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payload provides images of varying resolution at 18 different wavelengths.
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---EOF
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**********************************************
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* THE U.F.O. BBS - http://www.ufobbs.com/ufo *
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**********************************************
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