CAJ | 학술논문

面向火星精确着陆任务，文章提出了一种可以降低最优控制灵敏度的火星进入轨迹优化方法。首先，该方法充分考虑了火星探测器有限的控制能力，在标称轨迹优化性能指标中加入了不确定性因素对状态灵敏度项的影响，比较好地解决了当真实轨迹与标称轨迹相差太大时可能会出现因控制饱和而无法跟踪标称轨迹的情况。同时，在几乎不改变原来最优性能指标的同时有效地减小了大气密度、探测器状态等不确定因素对终端状态的影响，然后采用直接配点法将最优控制问题转化为非线性规划问题。最后，通过数学仿真对本文提到的方法进行验证，仿真结果表明，此方法可以有效减少控制饱和情况的出现，提高进入精度。
면향화성정학착륙임무，문장제출료일충가이강저최우공제령민도적화성진입궤적우화방법。수선，해방법충분고필료화성탐측기유한적공제능력，재표칭궤적우화성능지표중가입료불학정성인소대상태령민도항적영향，비교호지해결료당진실궤적여표칭궤적상차태대시가능회출현인공제포화이무법근종표칭궤적적정황。동시，재궤호불개변원래최우성능지표적동시유효지감소료대기밀도、탐측기상태등불학정인소대종단상태적영향，연후채용직접배점법장최우공제문제전화위비선성규화문제。최후，통과수학방진대본문제도적방법진행험증，방진결과표명，차방법가이유효감소공제포화정황적출현，제고진입정도。
This paper addresses the issue of Mars atmospheric entry trajectory optimization by use of de-sensitized optimal control. Firstly, the desensitized optimal control methodology is adopted to reduce the sensi-tivity of terminal state variables with respect to uncertainties and perturbations along the trajectory, in addition to optimizing the original performance. The optimal control will be well done when the true trajectory offsets from the normal trajectory. Then, Direct Collocation method is used to transform the optimal control problem into a Nonlinear Programming problem which can be easily solved. Monte Carlo simulations for error analysis show that the sensitivity of terminal state variables with respect to uncertainties and perturbations is significantly reduced, leading to improved entry precision.