Accession Number : AD0466584


Title :   THE ACQUISITION OF SUN POINTING ATTITUDE BY SPACE VEHICLES WITHOUT THE USE OF RATE GYROSCOPES.


Descriptive Note : Technical rept.,


Corporate Author : ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (UNITED KINGDOM)


Personal Author(s) : Abbott, J K


Report Date : May 1965


Pagination or Media Count : 24


Abstract : An attempt is made to define the initial conditions from which a sun pointing satellite with a simple ''on-off'' jet control system is capable of acquiring attitude control. The control system was assumed to be stabilised by means of phase advance of the error signal rather than by the use of rate gyros. The study was carried out mainly by digital computation. The maximum initial angular velocity from which satisfactory acquisition performance could be achieved increased with increasing available angular acceleration and fell as the inertia configuration was made more unsymmetrical. The results are strictly applicable only to control systems of the type outlined above. Suggestions are made of alternative arrangements which might be worth study. (Author)


Descriptors :   *ARTIFICIAL SATELLITES , *SATELLITE ATTITUDE , ATTITUDE CONTROL SYSTEMS , SUN , MATHEMATICAL ANALYSIS , DIGITAL COMPUTERS , UNITED KINGDOM


Distribution Statement : APPROVED FOR PUBLIC RELEASE