针对一种微小型制导弹药结合气动计算和基于加速度计的弹体攻角估算方法, 进行了攻角辨识研究。建立了气动模型, 计算得到制导弹药典型飞行条件下的气动与平衡攻角数据。利用气动力特征建立了一种攻角辨识模型, 提出一种弹上惯性测量单元(IMU)硬件布局方案。结合试验数据, 给出了制导弹药的攻角辨识结果。与仿真结果的对比分析表明, 基于飞行试验数据的攻角辨识结果与气动仿真结果较为一致, 证明所提出的攻角辨识方法合理可行。

On the basis of aerodynamic calculation and accelerometer-based method for estimating the angle of attack of the guided munitions, this paper studies the angle of attack identification of a miniature guided munition. By establishing an aerodynamic model, the aerodynamic and balanced angle of attack data under the typical flight conditions of the guided munitions are calculated out. Based on the aerodynamic characteristics, an angle of attack identification model is established, and a layout scheme of the missile-board inertial measurement units is proposed. Combined with the test data, the angle of attack identification results of the guided munitions are calculated out. The comparison with the simulation results shows that, the angle of attack identification based on flight test data is consistent with the aerodynamic simulation results, which proves that the proposed angle of attack identification method is reasonable and feasible.