| 某型探空火箭组合导航系统设计 |
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| 引用本文： | 王晓晖,齐鑫,杜浩.某型探空火箭组合导航系统设计[J].计算机测量与控制,2011,19(4). |
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| 作者姓名： | 王晓晖 齐鑫 杜浩 |
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| 作者单位： | 中国航天科技集团公司第四研究院第四十一所,固体火箭发动机燃烧、热结构与内流场国防科技重点实验室,陕西,西安,710025 |
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| 摘 要： | 为解决某型探宅火箭由于无控制系统造成的毪行弹道偏差及落点散布较大的问题,提出由MIMU/GPS组合导航设备、液体姿控发动机、飞控计算机等组成的低成本简控系统方案;组合导航算法采用速度位置间接匹配、反馈校正的Kalman滤波组合法;组合导航设备选用TMS32C67完成导航算法实时解算及信息融合,CPLD完成MIMU及温度传感器的数据采集,MCS51单片机完成GPS板的串口通信;数学仿真结果表明:在475s飞行时间内,火箭姿态控制精度不大于1°,飞行轨迹与理想弹道基本重合,相比原无控火箭有很大改善.
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| 关 键 词： | 探空火箭 组合导航 惯性器件 |
MIMU/GPS Integrated Navigation System Design of Certain Space Exploration Rocket |
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| Wang Xiaohui,Qi Xin,Du Hao.MIMU/GPS Integrated Navigation System Design of Certain Space Exploration Rocket[J].Computer Measurement & Control,2011,19(4). |
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| Authors: | Wang Xiaohui Qi Xin Du Hao |
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| Affiliation: | Wang Xiaohui1,Qi Xin1,Du Hao2(National Key Laboratory of Combustion,Flow and Thermo-Structure,41st Institute of the Fourth Academy of CASC,xi'an 710025) |
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| Abstract: | To solve the issue of the flying trajectory error and bigger falling points of a uncontrolled space exploration rocket due to an uncontrol system,this paper proposed an low cost simple control method composed of the MIMU/GPS integrated navigation,liquid attitude control engine,flying control computer.The algorithm of the integrated navigation applied indirect matching method of velocity and position and Kalman algorithm with feedback and emendation.The integrated navigation equipment applied TMS32C67 to com... |
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| Keywords: | GPS |
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