СПОСОБ УПРАВЛЕНИЯ ДВИЖЕНИЕМ КОСМИЧЕСКОГО АППАРАТА

摘要

FIELD: cosmonautics; approach and tethering in the course of docking. ^ SUBSTANCE: proposed method includes determination of errors of angle and angular velocity of spacecraft, application of control actions to spacecraft for correction of is attitude and determination of disturbing acceleration at application of control actions for correction of motion of spacecraft center of mass. Advance control actions are applied to spacecraft from the moment of application of control actions for correction of motion of center of mass till completion of application of these actions for correction of spacecraft attitude. Duration of both kinds of actions is proportional to each other at proportionality factor equal to ratio of magnitude of disturbing acceleration to control angular acceleration. Duration of control actions is increased for correction of attitude at excess of preset angle and angular velocity magnitudes by magnitude of advance control action duration. Magnitude of disturbing acceleration is determined by test application of control actions for correction of motion of spacecraft center of mass for definite length of time calculating this acceleration by increment of spacecraft angular velocity at preset time interval. During this test, application of control actions for correction of control actions is zeroed in case angle and angular velocity exceeds preset limits. Duration of test connection and interval for noting the increment of angular velocity is dictated by minimum effect of dynamic error on determination of disturbing acceleration. ^ EFFECT: enhanced accuracy of stabilization of spacecraft at simultaneous improvement of quality of transients at presence of external disturbing moment. ^ 2 cl