The invention discloses a Mars lander parachute avoidance method based on parachute drop point offline analysis, relates to the technical field of guidance control, and aims to solve the problem that a parachute back cover assembly covers a lander when the lander falls to the ground after the lander is separated from the parachute back cover assembly in the prior art. According to the application, the drop point dispersion of the parachute back cover assembly is determined off line through a Monte Carlo simulation method, and the shortest and longest space time of the parachute and different wind direction combinations are ensured to be included in simulation by using aerodynamic parameter pulling deviation in the simulation analysis process, so that the dispersion ellipse of the parachute covers various extreme working conditions; and the result is more conservative and reliable. In the landing process, the landing point of the lander is predicted based on polynomial guidance, maneuvering avoidance is only applied to the situation that the lander falls in a parachute landing point scattering area, and a maneuvering target enables the lander to move by the shortest distance to reach the position outside the parachute scattering area.
基于降落伞落点离线分析的火星着陆器降落伞规避方法,涉及制导控制技术领域,针对现有技术中着陆器与降落伞背罩组合体分离后会发生降落伞背罩组合体落地时覆盖着陆器的问题的问题,本申请通过蒙特卡洛仿真方法离线确定降落伞背罩组合体的落点散布,且在仿真分析过程中利用气动参数拉偏保证了降落伞最短和最长留空时间与不同风向组合包含在仿真中,使降落伞散布椭圆覆盖了各种极端工况,结果更加保守可靠。在着陆过程中,基于多项式制导预测着陆器落点,仅对落在降落伞落点散布区域内的情形施加机动规避,且机动目标是使着陆器移动最短距离到达降落伞散布区域之外。
Parachute avoidance method for Mars lander based on parachute drop point offline analysis
基于降落伞落点离线分析的火星着陆器降落伞规避方法
2022-03-01
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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