The problem of attitude takeover control of spacecraft by using cellular satellites with limited communication, actuator faults and input saturation is investigated. In order to lighten the communication burden of cellular satellites, an event-triggered control strategy is adopted. The filtered attitude information needs to be transmitted only when the defined measurement error reaches the event-triggered threshold in this strategy. Then, to deal with the unknown inertia matrix, actuator faults, external disturbances and the errors caused by event-triggered scheme, fuzzy logic systems is introduced to estimate the uncertainties directly. Combining fuzzy logic control strategy and the event-triggered method, the first event-triggered adaptive fuzzy control law is developed. Then, torque saturation of cellular satellites is further considered in the second control law, where the upper bound of the uncertainties is estimated by fuzzy logic systems. The resulting closed-loop systems under the two control laws are guaranteed to be bounded. Finally, the effectiveness of two proposed control laws is verified by the numerical simulations.

研究了通信受限，执行器故障和输入饱和的蜂窝卫星对航天器的姿态接管控制问题。为了减轻蜂窝卫星的通信负担，采用了事件触发的控制策略。在此策略中，仅当定义的测量误差达到事件触发的阈值时才需要发送已过滤的姿态信息。然后，针对未知惯性矩阵，执行器故障，外部干扰以及事件触发方案引起的误差，引入模糊逻辑系统直接估计不确定性。结合模糊逻辑控制策略和事件触发方法，建立了第一个事件触发的自适应模糊控制律。然后，第二控制定律进一步考虑了蜂窝卫星的转矩饱和，其中不确定性的上限由模糊逻辑系统估算。保证在两个控制定律下产生的闭环系统是有界的。最后，通过数值仿真验证了所提出的两种控制律的有效性。