【作者】 杨洪森；

【导师】 吴杰；

【作者基本信息】 国防科学技术大学 ， 航空宇航科学与技术， 2005， 硕士

【摘要】 本论文对SINS／双星组合导航方法及其在战术弹道导弹导航中的应用进行了深入的研究。SINS／双星组合导航方法克服了“北斗一号”双星定位导航系统需要用户发射定位申请信号的有源定位模式，直接测量载体至双星导航系统两颗卫星的距离和距离变化率信息，然后在此基础上实时辨识并修正SINS工具误差，从而获得更高的导航精度。 论文深入分析了SINS／双星组合导航的基本原理，建立了发射坐标系中的SINS状态方程、包含16项工具误差的SINS误差状态方程以及距离和距离变化率的双星观测方程。 论文建立了适用于SINS／双星组合导航系统的Kalman滤波模型，并研究了Kalman滤波模型中SINS工具误差的反馈修正方法以及弹载SINS／双星组合导航的精度分析方法。 论文详细叙述了弹载SINS／双星组合导航的仿真研究方法及流程。通过仿真计算分析了组合导航时段、导弹发射点地理位置、发射方位角等因素对弹载SINS／双星组合导航落点精度的影响。 仿真研究结果表明当导弹发射点在我国本土，SINS／双星组合导航时段为发射后的180s～480s，测距偶然误差为3m(1s)、测速偶然误差为0.02m／s(1s)的双星接收机与一定精度的SINS进行SINS／双星组合导航的导弹落点CEP小于60m，明显优于单纯SINS的导航精度。更多还原

【Abstract】 A Missile-Borne SINS/Double-Satellite integrated navigation system is discussed in this thesis. Instead of sending signal of positioning quest, instrument errors of SINS can be identified and corrected via the range and range rate between the carrier and satellites of "Beidou" Double-Satellite Positioning Navigation System in order to improve the navigation accuracy.The basic theory of SINS/Double-Satellite integrated navigation is lucubrated. The state equations, the state error equations with a common-used model of SINS instrument errors and the observation equations with range and range rate of SINS/Double-Satellite integrated navigation system are presented based on the launch coordinate.A Kalman filter is given to fit the systems. The feedback amendable technique of instrument errors and the accuracy assessment of fall points are also discussed.Simulation of SINS/Double-Satellite integrated navigation system is discussed in detail and the calculate error of simulation is analyzed. The launch parameters and the integrated navigation time’s effects on accuracy of fall points are discussed.The simulation results show that accuracy(Circular error probable) of missile fall points is less than 60m with a Double-Satellite receiver and a SINS of one kind when the launch point is on our mainland, the integrated navigation time is 180s~480s after the missile launched, the range error is 3m(1s) and the range rate error is 0.02m/s(1s).更多还原