CONTROL OVER SPACE OBJECT MOTION AFTER SEPARATION FROM OTHER SPACE OBJECT Russian patent published in 2015 - IPC B64G1/24 B64G1/64 

FIELD: physics, control.

SUBSTANCE: invention relates to control over motion of space object, for example, manned spacecraft, after its separation from the other space object, for example, carrier rocket. Spacecraft turn to required orientation is started at time moment ∆t counted down from spacecraft separation from carrier rocket. Spacecraft initial orientation is defined by carrier rocket nominal orientation at the moment of separation. After activation of spacecraft control system pickups in time moment ∆t received are data on spacecraft current angular velocity. Spacecraft angular motion model based on Euler equation is used to evaluate by back integration the spacecraft angular velocity at the moment of separation from carrier rocket. Then, initial conditions obtained with the help of said angular motion model are used to define (by forth integration) the spacecraft current orientation parameters. Train of pulses are applied to spacecraft their magnitude being defined by the difference between current and required orientation of spacecraft.

EFFECT: accelerated orientation after spacecraft separation from carrier rocket irrespective of light-and-shadow conditions in orbit.

6 dwg