风干扰引起的飞行器附加攻角和附加侧滑角计算方法

摘要

This paper studies the method of calculating additional attack angle and additional sideslip angle caused by wind disturbance based on zero-sideslip nominal lfight. The results in this paper are perfect over the simpliifed formulae widely used in China aerospace engineering. Formulae are given for calculating additional angle of attack and additional sideslip angle for given zero-sideslip nominal lfight state and wind disturbance. Formulae about the maximum and the minimum values of additional angle of attack and additional sideslip angle under different conditions are also given. These results are more accurate and more widely used than the traditional method and the engineering experience. Numerical results veriifed the correctness of the results. Results in this paper can be used for more properly determining inputs of other works during vehicle design, thus improving reliability and robustness of new vehicle. For vehicles in use, the results can also help in evaluating security margins more accurately.%研究了标称无侧滑飞行基础上受到水平风干扰时的飞行器附加攻角和附加侧滑角计算方法，完善了导弹与运载领域长期、广泛使用的传统的简化计算公式，修正了最大附加攻角和附加侧滑角出现条件的工程经验。提出了标称无侧滑飞行基础上受到水平风干扰时的飞行器附加攻角和附加侧滑角计算方法、水平风方向任意时附加攻角和附加侧滑角最大和最小值计算方法、倾侧角任意时附加攻角和附加侧滑角最大和最小值计算方法、水平风方向和倾侧角均任意时附加攻角和附加侧滑角最大和最小值计算方法，这些方法比航天传统方法使用范围更广、更准确，数值算例验证了其正确性。