DESCRIPTION |
Online Reference: http://wundow.wustl.edu/clbin/clsearch.pl
Instrument Overview
===================
On Clementine 1 there were two star tracker cameras, A Star and
B Star Tracker Cameras. They were mounted on opposite sides of
the spacecraft, allowing at least one to obtain star field
coverage at all times without interference from the Sun. Each
could provide three-axis attitude determination from a single
image provided the Sun, Moon, and Earth were not in the field
of view.
The primary function of the star tracker cameras was to provide
stellar images that were processed against an onboard star
catalog to find pointing, thus establishing absolute angular
references for attitude determination. The scientific uses of
the cameras were secondary. Only broad band operation was
available. Owing to the line-transfer electronic shuttering,
imaging was limited to dim targets such as the lunar surface
illuminated by earth shine.
The Wide-Field-of-View Star Tracker cameras have a concentric
optics design with a fiber optic field flattener to couple the
image surface to a CCD array. The CCD is kept cleared by
continuously shifting lines and reading out pixels at the 5 MHz
base rate, which is approximately 100 microseconds per line.
Image acquisition is accomplished by stopping this clearing
process for the appropriate integration time (13-bit
programmable), then proceeding with a second line-shifting
operation into a readout buffer.
The Thomson focal plane array (FPA) used is a frame-transfer
device, accomplishing electronic shuttering by rapidly shifting
the active pixel area into the storage area, pausing for the
13-bit programmable shuttering system spectral integration
time, then rapidly shifting the captured image into a storage
buffer from which the image is read out. Post-FPA electronics
allow three gain states followed by 5 bits of offset that span
248 counts in the analog regime to augment the basic 8-bit
analog/digital (A/D) conversion. Gain is A/D digitization
noise limited, so proper exposure is critical. System noise is
about 1.0 bits rms at the highest sensitivity setting.
Scientific Objectives
=====================
Science observations of the star tracker cameras were limited
to dim targets such as the lunar surface illuminated by earth
shine and observations of the earth illuminated by moon shine
during the low earth orbit phase. Additionally the star
tracker camera was used to acquire lunar 'horizon glow'
observations and solar corona observations prior to sun rise
over the Moon.
Calibration
===========
The Star Tracker cameras were calibrated before launch.
Laboratory observations of a flat field under various operating
temperatures and camera operation modes provides information
about the sensitivity of the camera under expected spaceflight
conditions. During inflight operations, a variety of
calibration observations were made including images of stars
with known radiance (Vega).
Operational Considerations
==========================
Most star tracker observations used for spacecraft attitdue
determination were acquired prior to and after a pass over the
sunlit side of the Moon. No star tracker observations were
made on the sunlit side of the lunar surface due to the extreme
sensitivity of the cameras and the potential for damage.
Operational Modes
=================
The Star Tracker Cameras had three operating modes:
1. 13-bit programmable integration time. The range of integration
times (in microseconds) is given by:
Integration Time = [(N+3)*94.5 - 45, N=0,2,3...2**13]
2. Gain Mode. The gain mode represents the multiplicative constant
applied to the image data passing through the A/D converter.
Three gain state settings were available (1,2,4) although gain
setting 4 was seldom used during lunar observations.
3. Offset Mode. The offset mode represents the additive constant
applied to the image data passing through the A/D converter.
There were 14 offset mode settings (1-14) although offset modes
1 and 6 were predominantly used during systematic lunar
observations.
Camera Specifications
=====================
Thomson Focal Plane Array Detectors
-----------------------------------
Type : Si Charge Coupled Device
Thomson TH7863
Pixel format : 576x384
Pixel size : 23x23 microns
Readout rate : 5MHz
Wavelength : 0.5 to 1.1 microns
Field of view : 43 deg. x 28 deg.
Pixel IFOV : 1.3 microradians
Point spread : 2 pixels
Electronics
-----------
A/D resolution : 8 bits
Readout time : 54.8 ms
Integration time : 0.2-733 ms
Digitization gain : 75, 150, 350 electrons/count
Offset control : 248 gray levels
Power : 4.5 W
Filters
-------
The Star Tracker cameras did not have a filter wheel
assembly. They acquired only broad band images in the range
.5 to 1.1 microns.
Optics
------
Clear aperture : 14nm
Speed : F/1.3
Mechanical
----------
Mass : 290 grams
Size : 11.7 cm x 11.7 cm x 13.2 cm
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REFERENCES |
Kordas, J.F., I.T. Lewis, B.A. Wilson, D.P. Nielson, H. Park, R.E. Priest,
R.F. Hills, M.J. Shannon, A.G. Ledebuhr, and L.D. Pleasance, Star Tracker
Stellar Compass for the Clementine Mission, Proceedings of the Society of
Photo-optical Instrumentation Engineers (SPIE), 2466, pp. 70-83, 1995.
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