Mars Atmospheric Entry Guidance Design by Sliding Mode Disturbance Observer-Based Control
One of the demands for future Mars exploration is pin-point landing,in which the landing precision should be less than one hundred meters and is two orders of magnitude higher than the current level.In the process of the high-speed vehicle entering a rarefied atmosphere with highly uncertainties as the Mars atmosphere,the trajectory deviation caused by entry guidance can be the major part of the total landing errors.Due to modeling errors such as the atmospheric modeling error and the vehicles aerodynamic model inaccuracy,the more the guidance law depends on the models,the larger the trajectory dispersion can be.To reduce the impact of model errors on guidance performance,a guidance law based on the second-order sliding mode variable structure control is developed for reference trajectory tracking.The guidance law which is tested in a real entry scenario is proved to be evident in reducing the control gain and the requirement for control ability.The proposed guidance law also shows accurate tracking for the reference trajectory and high precision of the landing sites.Compared with the predictor-corrector guidance which is dependent on models,the guidance law based on sliding mode control has low demand for computing ability,thus has the potential to be applied to online guidance.
Sliding mode Sliding observer Mars Entry guidance
Huang Yuechen Li Haiyang Zhang Jin Du Xin
National University of Defense Technology,410073 Changsha,Peoples Republic of China
国际会议
2014 Asia-Pacific International Symposium on Aerospace Technology(2014亚太航空航天技术学术会议)
上海
英文
1-13
2014-09-24（万方平台首次上网日期，不代表论文的发表时间）