一种火星进入段在线脱敏轨迹设计方法  

An Online Desensitized Trajectory Design Method for Mars Entry Guidance

作　　者：龙也[1,2] 刘一武[1,2] 

机构地区：[1]北京控制工程研究所,北京100190 [2]空间智能控制技术重点实验室,北京100190

出　　处：《空间控制技术与应用》2016年第2期20-25,共6页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(61403030)

摘　　要：为降低轨迹求解难度,提升脱敏制导的适应性,针对火星进入段提出一种在线脱敏轨迹设计方法.首先,采用预测的末端航程偏差和状态敏感度作为性能指标,利用该指标为倾侧角凸函数的特性将最优求解问题转换为简单的动态寻优过程;其次,结合任务要求和估计的进入点状态,通过迭代得到同时满足航程和横程要求的三自由度脱敏轨迹.仿真表明该方法可达到与现有脱敏设计相近的末端状态精度.To reduce the difficulties in trajectory optimization and improve the adaptability of desensitization guidance,a novel online desensitized trajectory design method is proposed for Mars entry. The weighted value of predicted terminal sail error and state sensitivity are adopted as performance indexes,which are actually convex functions of bank angle. Taking use of this property,the original optimization problem is converted into a simple dynamic optimizing process. Then,according to the mission requirement and estimated entry state,a three-degree-of-freedom desensitized trajectory that simultaneously satisfies the requirement for range and cross range can be found via iteration process. Numerical simulations show that the terminal state accuracy of the proposed method is close to the existing desensitization design.

关 键 词：鲁棒制导 在线脱敏设计 火星进入段制导 脱敏最优控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]