融合惯导与飞控系统信息的飞行大气全参数估计算法

Calculation method for air data based on information from inertial navigation system and flight control system

针对嵌入式大气数据系统高空飞行精度低、跨大气层易失效等问题,提出一种融合惯导与飞控系统信息的飞行大气全参数估计算法.基于飞行器气动模型及动力学方程,建立惯导信息与大气参数之间的函数关系,进而利用扩展卡尔曼滤波实现大气参数的实时精确估计.仿真结果表明,该方法具有较高的精度、良好的稳定性和鲁棒性,而且可以提高大气数据系统的测量范围和可靠性,能够适用于全飞行包线下攻角、侧滑角、真空速的测量.

The flush air data system（FADS） gets low accuracy during high altitude flight, which can easily fail if the vehicle travel through the atmosphere. Therefore, a calculation method for air data based on inertial navigation system（INS） and flight control system（FCS） is proposed. On the base of the aerodynamic model, force equations, and moment equations,the mathematic relationship between INS and air data is established. Real-time estimation of air data is achieved by using EKF. The simulation results show that, this method not only has high precision, favorable stability and robustness, but also improves the measurement range and reliability of the air data system, which can effectively be used to measure the angle of attack, the angle of sideslip and true airspeed within full flight envelope.