某型靶弹高度导航系统的设计

Design of Height Navigation System of Target Missile

为某型靶弹设计高度导航系统；由于靶弹是模拟飞机的巡航飞行，其高度在12000-15000m，所以靶弹对其高度导航精度要求较高；通过对大气数据包括气压随高度的变化、温度随高度的变化、空气密度随高度的变化等的研究，设计了一套大气机惯导组合导航系统，硬件系统用MOTOROLA MPX2100压力传感器、单片机和XW—IMU5200惯导等为主的器件搭建，硬件系统设计为以固定时间间隔气压传感器修正惯导系统；通过对惯导误差、气压高度模型和大气数据等的分析，并针对靶弹飞行特性，简化了气压高度公式；在软件上应用了卡尔曼滤波进一步提高其计算精度；该系统具有精度高、可靠性强、重量轻体积小、造价低廉等优点。

For the need of some kind of target missile, this paper proposes a method to design a height navigation system, which is made of MOTOROLA MPX2100 pressure sensor, MCU and XW--IMU5200 inertial navigation chip. The taget missile is used to simulate the cruise flight of plane for a height range of 12000-15000 m , thus a higher precision of height navigation is required. According to the atmospheric data involved , air pressure , temperature and air density change with height , designed a inertial navigation system. The design of hardware system used fixed time interval air pressure sensor to modify navigation system and simplify the equation of pressure altitude, by analysing the inertial navigation system error, atmospheric pressure height model and atmospheric data, also the flight height range of target missile. Applying Kalman filtering to improve further computational accuracy on software. This system has some advantage such as high precision, high reliability, light weight, small volume, low cost etc.