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ATTITUDE CHANGE CONTROLLER AND ATTITUDE CHANGE CONTROL METHOD FOR SPACECRAFT

机译：航天器的姿态变化控制器和姿态变化控制方法

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摘要

PPROBLEM TO BE SOLVED: To provide an attitude change controller and an attitude control method for a spacecraft capable of changing an attitude at a high speed with high accuracy. PSOLUTION: An attitude change plan command generator 4 calculates a maximum torque value necessary for the next attitude change on the basis of an attitude change request time, a target attitude angle and an attitude rotary shaft vector transmitted as an attitude angle decision signal 18, an attitude angular velocity decision signal 19 and telemetry data 33 from a ground station 32, and outputs the calculation result as an attitude change command signal 20. An attitude change means selection device 5 compares the maximum torque value with output maximum torque values of an RW 12, an RCS 13 and a CMG 14, and selects an optimum combination of the RW 12, the RCS 13 and the CMG 14 as an attitude control actuator to be driven. The selected actuator is driven to apply torque to a spacecraft dynamics 15. PCOPYRIGHT: (C)2003,JPO

机译：

要解决的问题：提供一种航天器的姿态改变控制器和姿态控制方法，该航天器能够以高速度高精度地改变姿态。解决方案：姿态改变计划命令生成器4基于姿态改变请求时间，目标姿态角和作为姿态角判定信号发送的姿态旋转轴矢量，计算下一次姿态改变所需的最大转矩值。参照图18，来自地面站32的姿态角速度判定信号19和遥测数据33，将计算结果作为姿态改变命令信号20输出。姿态改变装置选择装置5将最大扭矩值与输出的最大扭矩值进行比较。 RW 12，RCS 13和CMG 14，并选择RW 12，RCS 13和CMG 14的最佳组合作为要被驱动的姿态控制致动器。驱动选定的执行器以将扭矩施加到航天器动力学15。

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公开/公告号JP2003252298A

专利类型
公开/公告日2003-09-10

原文格式PDF
申请/专利权人 NEC CORP;
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申请/专利号JP20020058580
发明设计人 YAMASHITA TOSHIAKI;
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申请日2002-03-05
分类号B64G1/24;
国家 JP
入库时间 2022-08-22 00:14:44

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