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For the issues of attitude strong coupling and the increments of attitude errors of upper stage during multi-satellite disposing,a three-axis stability nonlinear attitude control algorithm via feedback linearization is presented.By the definitions of coordinates and the attitude angle during multi-satellite disposing,the attitude dynamics and kinematics equations with Euler angles described are built.And the equations are equivalently linearized based on feedback linearization theory.A three-axis nonlinear predictive control algorithm is designed and the system robustness is analyzed.An example of mathematical simulation is completed using the Matlab/Simulink environment.Simulation results showed that the control algorithm has good disturbance rejection,rapidity,stability and robustness. 相似文献
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For the missile with passive seeker,the improvement of passive ranger’s precision is one of the key issues in development of the defense penetrate strategy. On the offensive warheads,the infrared imaging device was used to measure the line-of-sight angle information of the blocker,and then using the algorithm of Kalman Filter under polar coordinates,the distance from the blocker to the warheads was obtained. The simulation result under polar coordinates was compared with that of Cartesian coordinate. The validity of the method was analyzed,and the schemes of improvement were brought out. 相似文献
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为了提高空间飞行器的快速入轨能力,满足空间飞行器弹道/轨道设计工作的快速、精确、可靠要求,对空间飞行器弹道/轨道一体化快速设计方法进行了研究。首先,对空间飞行器进行动力学建模,分析弹道/轨道一体化设计需要满足的过程约束和终端约束,给出空间飞行器的飞行时序;为保证求解效率,针对传统的弹道设计数值求解算法进行了创新改进,综合应用改进牛顿迭代法、Broyden秩1方法和最速下降方法,保证算法在初值不准的条件下仍能快速收敛;最后,研究了一种新的内外多层次求解策略,同时将弹道段和轨道段分轮进行一体化设计,进一步提高了算法的可靠性。仿真结果表明,本文所研究的空间飞行器弹道/轨道一体化快速设计方法可在30s内实现弹道/轨道设计,设计精度为0.5m。该设计算法可靠、快速、精确,可应用于空间飞行器的快速入轨设计中。 相似文献
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运载火箭上面级惯性与天文组合导航系统设计 总被引:3,自引:1,他引:2
针对运载火箭上面级惯性导航随时间累积而误差增大以至不能满足长时间工作要求的问题,对采用星敏感器和地球敏感器修正惯性导航误差的方案进行了研究。首先,导出了上面级常用坐标系定义和姿态转换矩阵。然后,根据惯性导航的误差传播特性、星敏感器测量方程和地球敏感器的模拟测量方程,给出了组合导航的状态方程和观测方程。最后,设计了基于Matlab/dSpace仿真平台的星敏感器在导航回路中的半物理仿真实验。实验结果表明,组合导航使惯性导航位置误差矢量和从1.1719×104m减小到1.0367×103m,速度误差矢量和从11.2827m/s减小到3.6626m/s,姿态误差从0.1°减小到5′,说明了该组合导航方案能够有效修正惯性导航时间累积误差,半实物仿真实验验证了惯性/天文组合导航方案的可行性与正确性。 相似文献
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