基于多目标优化的航天器姿态辅助热控制方法研究OA

Conventional spacecraft thermal control systems feature high power consumption,com-plexity,and limited environmental adaptability.A dynamic attitude-assisted thermal-control method based on multi-objective optimization is proposed in this paper.A coupled model of the spacecraft orbital thermal environment and attitude is established.The effects of external heat fluxes are considered.They include direct solar radiation,Earth infrared radiation,and Earth al-bedo radiation.A complete energy-balance equation is derived.A multi-objective cost function is formulated.Temperature variance,temperature change rate and attitude variation are taken as optimization objectives.Constraints cover attitude angles,angular velocity,solar-array orienta-tion,and temperature safety.Online optimization is implemented using a receding-horizon opti-mization framework and a sequential quadratic programming algorithm.Simulation results show that compared with the conventional mode alternating between Sun-pointing and Earth-gazing at-titudes of the Z-face,the proposed method reduces the spacecraft temperature variation range by approximately 14℃.It effectively relieves the burden on the thermal-control system.This meth-od provides a theoretical basis and a technical approach for integrated attitude-orbit-thermal control.