Accession Number : AD0436110


Title :   A STUDY OF THE USE OF REDUNDANT INFORMATION ON SPACE GUIDANCE SYSTEMS TO ACHIEVE MALFUNCTION DETECTION AND CONTROL.


Descriptive Note : Final rept., 15 June 63-15 Jan 64,


Corporate Author : GENERAL ELECTRIC CO JOHNSON CITY N Y


Personal Author(s) : Haake,H B ; McCary,R O ; Rapacz,R ; Sendzuk,G T ; Smith,G K


Report Date : Apr 1964


Pagination or Media Count : 166


Abstract : A theoretical orbital navigation system was synthesized that employs techniques for achieving a high degree of reliability through the application of redundant equipment, and malfunction detection capability. Malfunction detection is used to implement standby redundancy, or to reorganize the system to permit continued operation, with fewer sensors, subsequent to measurement subsystem failures. The latter case results in progressive performance degradation. The resulting potential modes of operation are defined, and the level of performance, in terms of orbit determination accuracy, has been evaluated for each. The mission assumed was to provide for attitude control and guidance for relatively infrequent orbital maneuvers for an unmanned satellite surveillance unmanned mission has precluded the use of manual repair techniques. The reliability goal has been to achieve a system capable of a 40,000 hour equivalent mean time to failure for a 10,000 hour mission, with a growth capability to 270,000 hours equivalent mean-timeto failuje. (Author)


Descriptors :   *SPACE NAVIGATION , RELIABILITY , DIGITAL COMPUTERS , REDUNDANT COMPONENTS , FAILURE , DETECTION , ORBITS , OPTICAL SCANNING , MONITORS , ERRORS , RADIO ALTIMETERS , RADAR NAVIGATION , DATA STORAGE SYSTEMS , HORIZON SCANNERS , RECONNAISSANCE SATELLITES , SATELLITE ATTITUDE , ATTITUDE CONTROL SYSTEMS , ATOMIC CLOCKS , FAILURE(MECHANICS) , COMPUTER LOGIC


Distribution Statement : APPROVED FOR PUBLIC RELEASE