The SOC design and implementation of the spacecraft system bus was studied, for example of the 1553b bus controller.
以1553 B总线控制器为例，采用SOC设计方法，研究了航天器系统总线的设计和实现。
It is presented in this paper a multivariable generalized predictive adaptive controller based on CARMA model and its application in the orbit control of spacecraft.
本文导出了基于对象CARMA模型的多变量广义预测自适应控制器，并将这种新的控制方法应用于航天器轨道控制中。
Then, the expected orientation of spacecraft with zero angular velocity was derived with a new attitude parameterization and LQR controller was designed based on the linearized system.
利用一种新的姿态描述形式推导出了角速度为零时航天器的目标姿态，然后基于线性化后的系统设计了线性二次型最优控制器。
Once a fault is detected and isolated, controller parameters can be reconfigured to compensate the loss of performance and keep the good attitude tracking accuracy of the spacecraft.
当诊断出故障时，重构控制律的参数对系统进行补偿控制，使得故障下飞行器的姿态跟踪精度得以维持。
Once a fault is detected and isolated, controller parameters can be reconfigured to compensate the loss of performance and to keep the good attitude tracking accuracy of the spacecraft.
当诊断出故障时，重构控制律的参数对系统进行补偿控制，使得故障下飞行器的姿态跟踪精度得以维持。
A modified sliding mode fault tolerant controller is developed for flexible spacecraft attitude stabilization control in the presence of loss of actuator effectiveness fault and actuator stuck fault.
针对挠性航天器执行器卡死与失效故障的姿态稳定控制问题，提出了一种结构简单、计算量小的改进型滑模容错控制策略。
A modified sliding mode fault tolerant controller is developed for flexible spacecraft attitude stabilization control in the presence of loss of actuator effectiveness fault and actuator stuck fault.
针对挠性航天器执行器卡死与失效故障的姿态稳定控制问题，提出了一种结构简单、计算量小的改进型滑模容错控制策略。
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