采用弱攻角补偿与脱敏设计的火星进入段制导

为提升火星进入段存在多种扰动时的制导末端精度，在现有三自由度脱敏设计的基础上，提出针对大气密度及升阻力系数波动的弱攻角补偿方法。通过攻角调整，协调升、阻力加速度测量值相对理论计算值的偏离程度，使加权形式的偏离程度指标趋近于1，从而降低气动参数波动对制导精度的影响。相平面分析和反证法证明了攻角调整过程的稳定性。蒙特卡洛仿真结果表明，该方法可达到较高的纵向末端状态精度。

Mars Entry Guidance with Weak Attack Angle Compensation and Desensitization Design

To improve the terminal guidance accuracy of Mars entry in the presence of multiple disturbances, based on the existing desensitization design of three freedom degree,an attack angle compensation method is proposed to handle “atmospheric density fluctuation” and “lift/drag coefficient fluctuation”. The deviation degree of the actual lift and drag acceleration with respect to their theoretical values is coordinated properly through attack angle adjustment,with the aim of the weighted deviation degree indicator be approaching to 1. Thus the influence of aerodynamic parameter fluctuations on guidance accuracy is minimized. Phase plane analysis and proof by contradiction demonstrate the stability of the attack angle adjustment process. Monte-Carlo simulation results show that by using the proposed method a relatively high longitudinal terminal state accuracy is achieved.