| 火箭控制系统闭环模飞测试中惯性器件激励的实现方法 |
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| 引用本文： | 张洁,孙凝生.火箭控制系统闭环模飞测试中惯性器件激励的实现方法[J].航天控制,1999(4). |
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| 作者姓名： | 张洁 孙凝生 |
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| 作者单位： | 北京航天控制研究所!100854 |
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| 摘 要： | 根据火箭控制系统闭环模飞的方案, 讨论了平台系统中惯性器件激励电流的计算方法, 其中考虑了地球自转对陀螺的影响。根据工程需要对公式进行了简化
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| 关 键 词： | 运载火箭 控制系统 惯性测量装置 |
Exciting Methods of Inertial Instruments in Close-Loop\;Flight Simulation of Launch Vehicle |
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| Zhang Jie,Sun Ningsheng,Beijing Aerospace Automatic Control Institute.Exciting Methods of Inertial Instruments in Close-Loop\;Flight Simulation of Launch Vehicle[J].Aerospace Control,1999(4). |
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| Authors: | Zhang Jie Sun Ningsheng Beijing Aerospace Automatic Control Institute |
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| Institution: | Zhang Jie Sun Ningsheng Beijing Aerospace Automatic Control Institute 100854 |
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| Abstract: | Simply introduces close-loop flight simulation project of launch vehicle control system. Discusses the calculation methods of exciting current of inertial instruments, including the influences of the rotation of the Earth. Simplifies the formula. |
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| Keywords: | Launch vehicle Control system Inertial measurement unit |
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