The rapid attitude manoeuvre is a control challenge for a CubeSat in low magnetic environments, which include lunar orbits, geosynchronous (GEO) orbits or other higher Earth orbits. Therefore, a rapid attitude manoeuvre control method based on the segmented sliding mode was proposed for CubeSat in a low magnetic environment. The segmented sliding mode control algorithm was applied to the CubeSat attitude manoeuvre control, where the segmented sliding mode surface was designed to guarantee fast convergence to the origin point of the whole attitude manoeuvre process, and the hyperbolic tangent function was used in the reaching law of the controller to alleviate reaction saturation of the wheels. In addition, innovative control strategies were proposed for the hybrid actuators of the reaction wheels and microthrusters, and a guide rail of the microthruster was innovatively designed to move the microthruster to offset the change in moment of inertia caused by propellant consumption. Finally, hardware-in-loop simulation results reveal that our method has a stronger anti-saturation ability and faster manoeuvre speed than the traditional control method, and the operational life cycle of the thrusters can be accordingly increased.

快速姿态机动是 CubeSat 在低磁环境中的控制挑战，包括月球轨道、地球同步 (GEO) 轨道或其他更高的地球轨道。为此，针对CubeSat提出了一种基于分段滑模的低磁环境下的快速姿态机动控制方法。将分段滑模控制算法应用于CubeSat姿态机动控制，其中分段滑模面的设计保证了整个姿态机动过程快速收敛到原点，并在到达定律中使用了双曲正切函数。控制器，以减轻车轮的反应饱和。此外，针对反作用轮和微型推进器的混合执行器提出了创新的控制策略，创新性地设计了微型推进器的导轨来移动微型推进器，以抵消推进剂消耗引起的转动惯量变化。最后，硬件在环仿真结果表明，与传统控制方法相比，我们的方法具有更强的抗饱和能力和更快的机动速度，可以相应地增加推进器的运行寿命周期。