配备1DoF万向节推力器和两个反作用轮的自旋稳定航天器的万向节执行器建模
Gimbal Actuator Modeling for a Spin-Stabilized Spacecraft Equipped with a 1DoF Gimbaled-Thruster and two Reaction Wheels
AI总结：
本文为配备1DoF万向节推力器和两个反作用轮的自旋稳定航天器建立了包含直流电机方程的万向节执行器数学模型，证明工业直流电机可用于脉冲轨道机动中的姿态控制。
摘要：
航天器在脉冲式轨道机动过程中的姿态控制是一项关键任务。许多航天器和运载火箭在轨道机动过程中使用万向节推力矢量控制（TVC）作为其姿态控制系统。万向节执行器的数学建模是一项重要任务，因为我们需要展示万向节TVC在航天器中的适用性。本文考虑了一种配备单自由度（DoF）万向节推力器和两个反作用轮（RWs）的自旋稳定航天器。控制目标是基于一个DoF万向节执行器和两个RWs实现干扰抑制和推力矢量（自旋轴）稳定。假设万向节配备有减速箱和直流电机。该执行器必须提供万向节扭矩以旋转航天器喷管。所述所提航天器的数学模型根据直流电机方程进行了扩展。为了研究所提方法的适用性，为万向节执行器考虑了工业直流电机。仿真结果证明，工业直流电机能够用于所述航天器的姿态控制。仿真结果表明所提控制方法在脉冲式轨道机动中的适用性。
英文摘要：
Attitude control of spacecraft during an impulsive orbital maneuver is a vital task. Many spacecraft and launchers use the gimbaled thrust vector control (TVC) in their attitude control system during an orbital maneuver. Mathematical modeling of the gimbal actuator is an important task because we should show the applicability of the gimbaled-TVC in a spacecraft. In this paper, a spin-stabilized spacecraft equipped with one degree of freedom (DoF) gimbaled-thruster and two reaction wheels (RWs) is considered. The control goals are disturbance rejection and thrust vector (spin-axis) stabilization based on one DoF gimbal actuator and two RWs. The gimbal is assumed to be equipped with a gearbox and a DC electric motor. This actuator must supply the gimbal torque to rotate the spacecraft nozzle. The mathematical model of the mentioned spacecraft is extended with respect to the DC motor equations. In order to investigate the applicability of the proposed method, an industrial DC electric motor is considered for the gimbal actuator. The simulation results prove that an industrial DC electric motor is able to be used for attitude control of the mentioned spacecraft. The simulation results indicate the applicability of the proposed control method in an impulsive orbital maneuver.
机构、总结、中文摘要均由AI分析而来，可能存在错误，请以论文正文为准。
