火星探测器多次分离气动捕获自主导航与随机制导

Autonomous Navigation and Stochastic Guidance of Mars Probe Aerocapture Through Multi-event Jettison

研究多次分离阻力控制探测器在火星气动捕获过程中的导航与制导问题,建立了气动捕获过程中的动力学模型与测量模型,提出了将火星大气密度建模为高斯过程,结合无迹施密特-卡尔曼滤波对探测器的系统状态进行估计,给出了系统状态的统计信息。采用随机制导策略,通过无迹变换传播系统状态的均值和协方差信息,将其纳入制导目标的设计中,并最终优化阻力裙分离时间。仿真结果验证了所提算法在提高气动捕获导航精度和减小最终入轨所需速度增量方面的有效性,为火星气动捕获及其他深空探测任务提供了理论和技术支持。

The navigation and guidance challenges are researched for multi-event jettison resistance control probe during Mars aerocapture.A dynamic and measurement model for multi-event jettison drag modulation probe during Mars aerocapture is developed.Mars atmospheric density is modeled as a Gaussian process that is combined with unscented Schmidt-Kalman filtering to take into account the impact of atmospheric density uncertainties on the probe′s system state and provides statistical information of state.A stochastic guidance strategy is employed,using unscented transform to propagate statistical information,which is incorporated into guidance target design and optimizes drag-skirt separation timing.Simulation results validate the approach′s effectiveness by enhancing navigation precision and reducing required velocity increments for orbit entry.These advancements improve the success rate of Mars aerocapture and can serve as theory reference and technical supports for precise navigation and guidance in deep space exploration tasks.