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A sun acquisition sensor for spacecraft guidance and controlThe combination of a strap-down analog sun acquisition sensor (AS) and an on-board digital programmable signal processor results in a versatile guidance and control system. The combination can orient the rotation axis of a spin-stabilized spacecraft to the sun no matter what the initial attitude of the spacecraft. During the sun orientation process, spacecraft spin rate can be sensed and supplied as an input to the control algorithm. If needed, the AS-signal processor combination can be used to perform a rhumb-line turn maneuver. In case of unexpected spacecraft operating conditions, or unplanned pointing directions, the signal processor program can be updated via earth-based transmission of another program to cover the new situation. Using only three radiation-hard cadmium-sulfide detectors, containing no moving parts, needing only a few microwatts of power, included in a volume of 550 cubic cm (a redundant pair), and weighing only 540 grams, the AS is a small, simple, sturdy sensing device.
Document ID
19830060526
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Birnbaum, M. M.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Bunker, R. L.
(California Institute of Technology, Jet Propulsion Laboratory, Pasadena CA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Subject Category
Spacecraft Instrumentation
Report/Patent Number
AIAA PAPER 83-2284
Meeting Information
Meeting: Guidance and Control Conference
Location: Gatlinburg, TN
Start Date: August 15, 1983
End Date: August 17, 1983
Accession Number
83A41744
Distribution Limits
Public
Copyright
Other

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