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.

中文翻译：

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控件的计算，不生成四个控件矩回旋点的奇异点

摘要

本文演示了一种用于计算航天器（SC）的程序化定律的技术，该技术不会产生控制力矩陀螺系统的特殊，奇异状态，而是由两个共线的陀螺仪对组成。由于在新技术中使用了控制力矩回旋线圈系统的运动学配置来计算SC的控制，因此可以计算出不包含两对回旋线圈的奇异状态的编程取向定律。需要，调整虚拟飞轮轴的位置以解决新的姿态控制问题。如今，已计算出姿态控制的定律，以解决动力学的直接问题。这些定律包含陀螺系统的奇异状态，其中SC保持不可控状态。通过使用附加的陀螺仪系统和附加的控制从这些状态退出陀螺仪系统，可以恢复可控性。同时，SC的姿态控制过程在输出期间被中断。这些重大和暂时的损失需要寻找不包含陀螺仪系统特殊状态的姿态控制定律。通过解决用两个共线陀螺炔对对准空间望远镜的问题，证明了这种定律的计算。