火星探测器进入飞行气动测量方法研究

在火星探测任务的进入飞行过程中,开展气动测量将获取大量宝贵的气动特性数据,一方面可以验证进入探测器气动外形,掌握其准确的气动特性,另一方面,可以积累详实的火星大气数据,为后续任务提高落点精度等飞行性能提供支持. 本文针对火星探测器进入飞行任务,基于弹道重建和嵌入式大气数据传感系统(flushair data system, FADS),提出火星探测器进入飞行过程中的气动测量方法. 通过融合火星进入外测弹道信息,利用输出误差法实现攻角、侧滑角的高精度测量;基于嵌入式大气数据传感系统,利用最小二乘最优估计算法,建立了进入飞行动压的测量方法. 仿真分析表明,气动测量方案精度高,进入动压测量精度优于1%,攻角和侧滑角测量精度相较于当前火星探测器进入气动测量而言,至少提升1 个量级. 研究结果将为火星探测等深空探测任务的进入飞行气动测量提供技术参考. 

AERODYNAMIC CHARACTERISTICS MEASSUREMENT OF MARS VEHICLES DURING ENTRY FLIGHT

Performing aerodynamic measurement can acquire a mounts of data during Mars entry exploration. This work benefits for aerodynamic characteristics confirmation and improves key flight performance, such as landing accuracy. In this study, an aerodynamic measurement system scheme is proposed based on trajectory reconstruction and flush air data system. Angle of attack and angle of side slip are measured by output error method with measured trajectory; dynamical pressure is measured via Flush air data system and least square optimal estimation. By simulation, it shows that the proposed measurement scheme has high measure accuracy, and dynamical pressure accuracy is 1%, and angle of attack and angle of side slip accuracy are improved more than one time. This study is helpful for aerodynamic measurement of deep-space exploration entry flight, such as Mars exploration entry flight.