The invention provides a spacecraft attitude jet control method and system based on a delta-sigma modulator, and the method comprises the steps: collecting an attitude angle and an attitude angle rate of a spacecraft, and feeding back the attitude angle and the attitude angle rate to an outer loop and an inner loop respectively; in the outer loop, an angular rate instruction is calculated according to the feedback attitude angle and an attitude angle instruction input into the outer loop, and the angular rate instruction is input into the inner loop; acquiring an angular rate deviation signal according to the angular rate instruction and a feedback attitude angular rate in an inner loop; in an inner loop, the angular rate deviation signal is converted into a spray pipe relative thrust instruction, and the spray pipe relative thrust instruction is modulated into a spray pipe switch instruction with an adjustable duty ratio; and converting the spray pipe switch instruction into an electromagnetic valve on-off signal of the spray pipe, and controlling the forward spray pipe and the reverse spray pipe to execute the air injection action according to the electromagnetic valve on-off signal. On the premise that the number of times of air injection of the spray pipe is increased, continuous control over the attitude angle and the angular rate of the spacecraft is achieved, and the control precision of the attitude of the spacecraft is improved.
本申请提供一种基于Δ‑Σ调制器的航天器姿态喷气控制方法及系统,该方法包括:采集航天器的姿态角和姿态角速率,分别反馈至外回路和内回路;在外回路,根据反馈的姿态角和输入外回路的姿态角指令,计算角速率指令,并将角速率指令输入内回路;在内回路,根据角速率指令和反馈的姿态角速率,获取角速率偏差信号;在内回路,将角速率偏差信号转换为喷管相对推力指令,将喷管相对推力指令调制为占空比可调的喷管开关指令;并将喷管开关指令转换为喷管的电磁阀通断信号,根据电磁阀通断信号,控制正向喷管和反向喷管执行喷气动作。本申请在避免喷管喷气次数增加前提下,实现航天器姿态角及角速率的连续控制,并提高对航天器姿态的控制精度。
Spacecraft attitude jet control method and system based on delta-sigma modulator
基于Δ-Σ调制器的航天器姿态喷气控制方法及系统
2023-03-21
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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