| 惯性系下GPS/SINS紧组合导航算法研究 |
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| 引用本文： | 王楠,王龙.惯性系下GPS/SINS紧组合导航算法研究[J].现代电子技术,2011,34(20):93-95. |
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| 作者姓名： | 王楠 王龙 |
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| 作者单位： | 中国空空导弹研究院,河南洛阳,471000 |
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| 基金项目： | 航空科学基金项目(20090112006) |
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| 摘 要： | 针对新一代远程空空导弹的特点,研究了在导弹发射惯性坐标系下,基于伪距/伪距率的GPS/SINS紧组合导航算法,推导了该坐标系下的惯导一阶误差传播方程,建立了该坐标系下GPS/SINS组合导航系统的状态方程和量测方程,并进行了相关数学仿真验证。仿真结果表明,在该坐标系中GPS/SINS紧组合导航算法有较高的导航精度。
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| 关 键 词： | 伪距 伪距率 GPS/SINS 导弹惯性系 |
Research of GPS/SINS Tightly Integrated Navigation Algorithm in Inertial Coordinate |
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| WANG Nan,WANG Long.Research of GPS/SINS Tightly Integrated Navigation Algorithm in Inertial Coordinate[J].Modern Electronic Technique,2011,34(20):93-95. |
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| Authors: | WANG Nan WANG Long |
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| Affiliation: | WANG Nan,WANG Long(China Airborne Missile Academe,Luoyang 471000,China) |
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| Abstract: | In view of the characteristics of the long-distance AAM,the GPS/SINS tightly integrated navigation algorithm based on pseudo-range/pseudo-range rate in the missile inertial coordinate is studied.The first-order error spread equations were derived in ile inertial coordinate.The state equations and measurement equations for GPS/SINS tightly integrated navigation system are established.The simulation results indicate that this GPS/SINS algorithm can improve navigation accuracy effectively. |
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| Keywords: | pseudo-range pseudo-range rate GPS/SINS missile inertial coordinate |
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