LAUSR

Abstract This paper demonstrates the technology for calculating spacecraft’s (SC’s) programmed laws of orientation that does not generate special, singular, states of the control moment gyro systems and consists of two collinear gyrodyne pairs. The calculation of the programmed orientation laws that do not contain singular states for two pairs of gyrodynes is possible due to the use of the kinematic configuration of the system of the control moment gyrodynes in the new technology for calculating the SC’s controls, which allows, if required, adjusting the position of the virtual flywheel axes for new attitude control problems. Today, the laws of programmed attitude control are calculated as a solution to the direct problem of dynamics. These laws contain singular states of the gyro system in which the SC remains uncontrollable. The controllability is restored by withdrawing the gyro system from these states using an additional gyro system and additional control. At the same time, the attitude control process of the SC is interrupted for the duration of the output. These material and temporary losses require searching for attitude control laws that do not contain special states of the gyro system. The calculation of such laws is demonstrated in solving the problem of orienting a space telescope with two collinear gyrodyne pairs.