文章陈述了自旋稳定通信卫星姿态确定的矩阵方法及其工程应用的七种情况。
The matrix method of the attitude determination for spin-stabilized geostationary communication satellite and its cases of practical engineering application are described in this paper.
仿真结果表明，采用联邦滤波器对多敏感器卫星姿态确定系统进行信息融合，具有计算量小、精度高、可靠性好等优点。
Simulation results show that federated filtering based information fusion method for the multi-sensor satellite system is characterized by small computation cost, high precision and good reliability.
在确定卫星姿态确定的状态估计法中，经典的扩展卡尔曼滤波(ekf)和新提出的非线性预测滤波(NPF)这两种实时滤波算法各有优缺点。
In state estimation of satellite attitude determination, both traditional extended Kalman filter (EKF) and the proposed nonlinear predictive filter (NPF) have their own merits and defects.
提出了一种利用姿态测量数据确定卫星初始轨道的新方法。
A new method of determining the satellite initial orbit with attitude data is presented.
文章给出在发射静止卫星过程中，固体远地点发动机点火时间和点火姿态的最佳值确定方法。
This paper provides a method for determining the optimum time and attitude in process of geostationary satellite launch at which the solid-apogee motor to be fired.
结合矢量观测的特点，基于最小模型误差准则给出了一种确定卫星姿态的实时估计算法，称为预测滤波算法。
Considering the character of vector observation, a real time predictive filter based on minimum model error (MME) criterion is presented for satellite attitude estimation.
研究了刚体卫星在控制输入饱和、外干扰和参数不确定性存在时的姿态调节控制问题。
This paper deals with the problem of attitude regulation control of rigid satellite subject to control input saturation, external disturbance and parametric uncertainty.
研究了具有参数不确定性和外部干扰的卫星姿态跟踪控制问题。
The attitude tracking control problem for a satellite with parameter uncertainties and external disturbances is considered in this paper.
为了达到卫星三轴姿态确定的精度要求，以某一对地定向的小卫星为研究对象，提出了基于滤波算法的星敏感器和光纤陀螺组合定姿的方案。
A filtering algorithm for high precision attitude determination of a specific satellite is presented based on star-sensors and fiber optic gyroscopes (FOG).
编队卫星的控制和应用需要确定编队卫星的运动状态，包括卫星绝对的和相对的位置、姿态以及钟差。
Control and application of satellite formation require measurement of the formation states, including absolute and relative position, attitude and clock bias separately.
建立了小卫星相对轨道和姿态的误差动力学模型，根据作业任务和姿态指向要求确定了小卫星相对轨道和姿态的期望运动；
Positional and attitude error dynamics model of small satellite relative to a target satellite was derived, then the desired relative orbit and desired attitude of small satellite were designed.
建立了小卫星相对轨道和姿态的误差动力学模型，根据作业任务和姿态指向要求确定了小卫星相对轨道和姿态的期望运动；
Positional and attitude error dynamics model of small satellite relative to a target satellite was derived, then the desired relative orbit and desired attitude of small satellite were designed.
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