高超声速飞行器惯性导航系统仿真研究  

The Simulation of the INS on the Hypersonic Vehicle

作　　者：贾阳阳[1] 宋丹[1] 杜小菁[1] 许承东[1] 

机构地区：[1]北京理工大学,北京100081

出　　处：《计算机仿真》2016年第1期72-76,共5页Computer Simulation

摘　　要：在高超声速飞行器实现精确打击问题的研究中,为确保打击的高精度,导航技术是关键。飞行轨迹控制的真实性严重影响对导航系统性能的测试评估。为了真实的反映飞行器运动状态并提高导航精度,依据高超声速飞行器运动特性把高超声速飞行器任务分成三种典型运动模式,设计了其在三种运动模式下的轨迹生成方案。采用上述方案产生的飞行轨迹数据进行惯导元器件的仿真和SINS解算。动态情况下仿真结果验证了轨迹设计方案的可行性和系统设计方案的正确性。利用仿真结果分析了高超声速飞行器姿态变化时对惯性导航的影响,为飞行器导航优化控制提供了依据。To realize the precision and ensure the high precision, navigation technology is the key for hypersonic flight vehicle in the modem war. The authenticity of the Flight path has serious influence on the test evaluation of the navigation system. In order to reflect the real vehicle motion state and improve the navigation precision, this work, basing on the features of hypersonic flight vehicle, split the hypersonic aircraft task into three typical motion modes, design the path generation scheme in three kinds of motion mode. Using the Flight path data from the scheme simulate the data of inertial navigation components and do SINS calculating. Dynamic circumstance simulation results verify the feasibility of trajectory design and the correctness of the system design scheme. The influence of the inertial navigation from the hypersonic aircraft posture changing is analysed by using the results of simulation.

关 键 词：高超声速飞行器 惯性导航 系统仿真 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]