FIELD: aviation.
SUBSTANCE: measurement of present angular position of solar battery (SB) and in the event of difference between it and given direction, SB rotation instruction is formed. In the event of no difference, SB rotation cessation instructions are formed and constant sufficiently high rotational speed of output shaft of SB rotation device is set up. Time and SB boost angle is determined from rotation instruction issue to steady-state value of SB rotational speed. The same is determined for SB slowdown after rotation cessation instruction has been issued. The drop-away of less than 45° and not less than 0° is set. Operation threshold of not less than the sum of acceleration and release angles and not exceeding 45° is set. Error signal is formed, if the angle between the specified angle and present one exceeds the operation threshold. This signal generation is stopped, if during SB rotation error angle will be less than release threshold or equal to 0°. The same is done, if error angle character at the beginning of rotation does not coincide with error character at the end of rotation where the specified angle does not exceed the operation threshold. Control time threshold value is set as the ratio discrete sector of angle transmitter to SB sustained rotation rate during acceleration and deceleration. SB rotation time is controlled up to rotation cessation instruction. At the end of deceleration the current control time as well as moments of rotation redirection shall be reset. Rotation cessation instruction and failure signal for SB rotation controlling device is formed when current control time exceeds control time threshold value.
EFFECT: enhancement of method of controlling space vehicle solar battery position by imposing controls of SB angular position reorientation during rotation.
3 dwg
