Abstract

This paper considers attitude control systems for an orbital spacecraft based on the principle of a gyrocompass. The primary focus is the development of the method of spatial programmed rotation of the spacecraft for systems continuously adjusted by local-vertical plotters (LVPs). The main algorithm and block diagram of the gyrocompass, named the “spatial 3D gyrocompass,” have been obtained. The possibility of programmed attitude control of a spacecraft with a disabled gyrocompass correction loop without restrictions on the angles of programmed rotations is shown. A particular case, which is in demand in practice, of a plane rotation of the spacecraft along the course to an arbitrary programmed angle, is considered. A calibration method by means of autocompensation of deterministic errors of LVPs and gyroscopic angular velocity sensors is proposed, which significantly increases the attitude accuracy.

中文翻译：

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轨道航天器陀螺罗经

摘要

本文考虑了基于陀螺罗盘原理的轨道航天器姿态控制系统。主要重点是开发航天器空间程序旋转方法，用于由局部垂直绘图仪 (LVP) 连续调整的系统。获得了陀螺罗经的主要算法和框图，命名为“空间3D陀螺罗经”。显示了对具有禁用的陀螺罗经校正回路的航天器进行编程姿态控制的可能性，而不受编程旋转角度的限制。考虑到航天器沿航线平面旋转至任意编程角度的特殊情况，这在实践中是需要的。提出了一种利用LVP和陀螺角速度传感器确定性误差自动补偿的标定方法，