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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。
In this paper, the generalized Kalman filter method is used to determine the main aerodynamic coefficients of reentry body. The key point is how to make use of the measured data in reentry flight to estimate the state and parameters in the absence of orbital observation data. The data include body-axis angular velocity and overload, given by the rate gyro and accelerometer attached to the flying body. A mathematical model is established on the basis of six degrees of freedom equations of motion. Considered both ballistic reentry and maneuver reentry. Numerical simulation and measured conversion show that this method has been more satisfactory results.