用卡尔曼滤波方法确定再入体空气动力系数

本文用广义卡尔曼滤波方法来确定再入体主要的空气动力系数。重点解决在没有轨道观测数据的情况下,如何利用再入飞行中的测量数据进行状态和参数估值。数据包括体轴角速率和过载,由固连于飞行体的速率陀螺和加速计给出。在六自由度运动方程的基础上建立一种数学模型。考虑了弹道式再入和机动再入两种情况。数值模拟和实测换算表明,本文方法得到了较为满意的结果。

DETERMINATION OF AERODYNAMIC COEFFICIENTS FOR A RE-ENTRY BODY BY MEANS OF AN EXTENDED KALMAN FILTER

An extended Kalman filter is used to determine the major aerodynamic coefficients of a re-entry body in this paper. The emphasis is put on estimating the states and parameters only on the basis of the re-entry on-board measurement data in the absence of trajectory observation data. The measured data include angular rates and acceleration obtained from the rate gyros and acce-lerometers installed in the vehicle. A mathematical model presented is based u-pon the 6-degree-of-freedom motion equations. Both ballistic and maneuvering re-entries are considered. The numerical simulation and real data extraction show that the presented method can provide satisfactory results.