高超声速飞行器双GPS/INS松组合导航姿态估计

Estimation of loosely-coupled dual GPS / INS integrated navigation attitude for hypersonic flight vehicles

为克服高超声速飞行器可能出现的"黑障效应",获得高超声速飞行器精确可靠的姿态信息,利用"黑障效应"头重尾弱的特性设计了一种双GPS/INS松组合导航系统估计姿态。首先,推导了沿载体纵轴独立分布的双GPS测姿的计算公式;然后,根据双GPS的几何关系计算载体纵轴矢量,并建立了双GPS/INS松组合导航系统观测方程;最后,对设计的导航系统进行了仿真。结果表明,与传统GPS/INS导航系统相比,双GPS/INS松组合导航系统不仅提高了飞行器姿态估计精度,而且增加了系统冗余度,提高了系统的可靠性。

In order to overcome ‘blackout environment effect＇ and obtain reliable and accurate attitude estimation of hypersonic flight vehicle, a kind of dual GPS and INS loosely-coupled integrated navigation system is designed relying on blackout phenomenon, which the plasma is severe in front of the vehicle and weak behind the vehicle. First, the principle of attitude determination by two separate GPS antennas placed along the longitudinal axis of a hypersonic flight vehicle is introduced. Second, using the known geometric relationship between two GPS antennas, the longitudinal axis vector is constructed. And the observation equation of loosely-coupled dual GPS/INS navigation is established based on it. The efficiency of the presented method is demonstrated by simulation. Simulation results show that the loosely-coupled dual GPS/INS navigation was shown to have better estimates of the attitude angles and increase the redundancy of system, which improves the reliability of system.