火星大气进入不确定性量化及制导规划

There are large uncertainties in the Martian atmospheric density and related aerodynamic parameters. The Mars entry vehicles usually adapt small lifting body configuration, which leads to low control authority. Large uncertainties and low control authority are the biggest challenge for future Mars high-precision entry guidance. Traditional Mars entry guidance algorithms mainly utilize advanced control theory to compensate and suppress the adverse effects caused by uncertain factors. Very few studies have focused on Mars entry uncertainty evolution from the view point of mechanism, and therefore the guidance performance is difficult to further improve. .Therefore, it is necessary to develop Martian entry uncertainty quantification algorithms and Mars entry guidance planning algorithms under uncertainty with considering the constraint conditions mentioned above. The project intends to systematically investigate the innovative methods and key technologies involved in the next-generation Mars entry guidance planning from the following three aspects, Mars entry uncertainty quantification and analysis, Mars entry trajectory planning under large uncertainty and Mars entry adaptive optimal guidance under large uncertainty. A large number of mathematical simulations and semi-physical simulations will be performed to confirm the effectiveness of Mars entry uncertainty quantification algorithms and guidance planning algorithms, which will provide the necessary technical reserves for China's upcoming Mars exploration missions and future Mars Sample return.

火星进入过程中大气密度和相关气动参数存在的较大不确定性以及小升力体构型所导致的低控制能力是制约火星进入制导精度进一步提高的最大瓶颈。传统的火星进入制导主要借助于先进的控制算法补偿或抑制不确定因素给制导性能所带来的不利影响，很少从机理上关注进入过程中不确定性的演化规律，因而制导精度很难进一步提高。因此，有必要在考虑上述约束的前提条件下，发展适合于火星大气进入的不确定性量化方法和大不确定性条件下火星进入制导规划方法。本项目拟从火星大气进入不确定性量化分析、大不确定性条件下火星进入轨迹规划和火星进入自适应最优制导三个方面出发对火星进入不确定性量化基础理论和大不确定性条件下火星进入制导规划方法进行全面深入的研究，并通过数学仿真和半实物仿真对所发展的制导规划方法进行仿真验证，从而为我国即将进行火星探测任务和未来的火星采样返回提供技术支持。

火星进入过程中大气密度和相关气动参数存在的较大不确定性以及小升力体构型所导致的低控制能力是制约火星进入制导精度进一步提高的最大瓶颈。传统的火星进入制导主要借助于先进的控制算法补偿或抑制不确定因素给制导性能所带来的不利影响，很少从机理上关注进入过程中不确定性的演化规律，因而制导精度很难进一步提高。因此，有必要在考虑上述约束的前提条件下，发展适合于火星大气进入的不确定性量化方法和大不确定性条件下火星进入制导规划方法。通过四年的研究，本项目从火星大气进入不确定性量化分析、大不确定性条件下火星进入轨迹规划和火星进入自适应最优制导三个方面出发对火星进入不确定性量化基础理论和大不确定性条件下火星进入制导规划方法进行了全面深入的研究，并通过数学仿真对所发展的制导规划方法进行仿真验证。仿真结果表明，本项目所发展的火星大气进入不确定性量化及制导规划方法能定量演化火星进入动力学不确定性，具有比蒙特卡洛方法更高的精度和效率，从而为我国的火星探测任务和未来的火星采样返回任务提供一定技术支持。