Adaptive entry guidance for the Tianwen-1 mission

Abstract To meet the requirements of Tianwen-1 mission, adaptive entry guidance for vehicles, with low lift-to-drag ratios, limited control authority, and large initial state bias, was presented. Typically, law is divided into four distinct phases: trim angle-of-attack phase, range heading alignment trim-wing deployment phase. In predictor—corrector algorithm improved by planning an on-board trajectory based on Mars Science Laboratory (MSL) algorithm. The nominal designed described using a combination downrange value other states, such as drag acceleration altitude rate. For modified onboard weighing landing accuracy, parachute altitude. biggest advantage this approach that it allows successful correction errors avoidance saturation. An overview optimal design process, including discussion flight path angle, relevant event trigger, transition conditions between phases, also Finally, telemetry data analysis post-flight assessment results were used to illustrate law, create good subsequent reduction power processes, gauge success mission.