上海航天（中英文）2025，Vol.42Issue(6)：18-25,8.DOI:10.19328/j.cnki.2096-8655.2025.06.002
基于飞轮组输出能力的卫星姿态机动三段式参数设计与控制
Design and Control of Three-phase Parameterization for Satellite Attitude Maneuvering Based on the Output Capability of Flywheel Assembly
摘要
Abstract
The enhancement of satellite attitude maneuverability plays a crucial role in improving observation effectiveness.For large-angle rapid maneuvering missions with zero initial and final angular velocities,the strong coupling between the attitude dynamics and kinematics necessitates a two-layer control architecture comprising angular velocity trajectory planning and closed-loop tracking control.Conventional three-phase trajectory parameters(e.g.,angular acceleration and maximum angular velocity)are typically determined based on engineering experience,resulting in conservative constraints and underutilization of actuator potential.In this paper,grounded in the relationship between the flywheel and satellite attitude dynamics,the flywheel torque constraints are established,with which the conservative boundary values for trajectory parameters ensuring that all flywheel torques remain unsaturated are deduced.Furthermore,addressing the asymmetric output capacity of actuators across different Euler rotation axes(a characteristic of conservative trajectory parameters),a differentiated trajectory parameter design method is proposed.This approach optimizes the maneuvering trajectory by maximizing the angular acceleration around each Euler axis while preventing flywheel saturation,thereby achieving the fastest dynamically feasible trapezoidal maneuver.The numerical simulations demonstrate that the proposed method significantly enhances the actuator utilization efficiency and enables rapid,stable attitude control.关键词
敏捷机动/姿态轨迹规划/机动控制/损失力矩补偿/反作用轮组Key words
agile maneuvering/attitude trajectory planning/maneuvering control/loss torque compensation/reaction wheel assembly分类
航空航天引用本文复制引用
YAO Xiaosong,MA Zhijie,LIU Guohua,CHENG Jiao..基于飞轮组输出能力的卫星姿态机动三段式参数设计与控制[J].上海航天（中英文）,2025,42(6):18-25,8.基金项目
国家重点研发计划资助项目(2023YFB3907503) （2023YFB3907503）
