A HIGH ACCURACY FINE SUN SENSOR.

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Abstract:

Design and constructional details are given for a sensor suitable for fine guidance of sun pointing space vehicles. Factors affecting the accuracy and stability of the sensor are discussed and optimum values for certain critical parameters suggested for Skylark and satellite applications. Bias error measurement methods are described and it is concluded that, because of atmospheric turbulence, results using the real sun are unreliable an alternative method using a solar simulator is presented which has given results repeatable to about 2 arc sec. Author

Author(s):
Brookman, A. K.
Author Organization(s):
ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND)
Descriptive Note:
Technical rept.,
Pagination:
0029

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
RAE-TR-69157
 Subject Terms
Modernization Areas:
Space
Communities of Interest:
Space
Descriptor(s):
(*SPACECRAFT, *ATTITUDE CONTROL SYSTEMS), (*DETECTORS, DESIGN), SOUNDING ROCKETS, SATELLITES(ARTIFICIAL), ALIGNMENT, SOLAR CELLS, OPTICS, TARGET RECOGNITION, ACCURACY, RELIABILITY, ERRORS, ATMOSPHERIC MOTION, SOLAR DISTURBANCES, STABILITY, GREAT BRITAIN
Field(s)/Group(s):
Unmanned Spacecraft
Keyword(s):
ADJUSTING, NULL STABILITY, SKYLARK, *SUN SENSORS
Report Date:
1969 Jul 01