RU93041284A - METHOD OF MANAGING THE TURNING MANEUVER OF SPACE APPARATUS - Google Patents

Claims (1)

The method of controlling the rotational maneuver of a spacecraft is designed to transfer it from an arbitrary initial angular position Ln to a given final angular position Lc for a certain time Tk with high accuracy. The proposed method combines a free turn and a turn around the axis of Euler, which combines the advantages of both methods and eliminates their disadvantages. The proposed method of controlling the rotational maneuver of the spacecraft implements a turn along the path of free movement. In this method, it is assumed to automatically determine the parameters of the falling trajectory - the vector and angle of rotation. To do this, in the control system, using the iteration method, the boundary value problem is solved algorithmically - determining such initial angular velocities so that from the angular position Ln as a result of uncontrolled rotation of the spacecraft it takes the angular position Lx after a specified time Tk. Having solved it, the control system informs the object of the calculated angular velocity, after which it provides it to itself. The moment of transition to the area of rotation of the spacecraft around the axis of Euler is determined from the condition of minimum fuel consumption per dovorot. For this, the control function Gy is continuously calculated in the control system. At the moment of time when Gy becomes minimal, the docking of the spacecraft is carried out in a highly accurate and easily realizable way. The proposed synthesis of a free turn with the subsequent turning around the Euler axis allows, at a rather low fuel consumption, to achieve a high turn accuracy with any unknown disturbances. High efficiency of the method is achieved by the absence of controls on the most part of the turn.