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公开(公告)号：US07566026B2
公开(公告)日：2009-07-28
申请号：US11392131
申请日：2006-03-29
申请人： Frank C. Lam , Gerald C. Chiang
发明人： Frank C. Lam , Gerald C. Chiang
摘要： A guidance method for a powered ballistic missile involves using an onboard computer to numerically simulate the flight path of the missile in real time, using a model with at least 3 degrees of freedom. The results of this simulation are used to update in real time an aim point and/or a predicted intercept point. An iterative process may be used in adjusting the aim point and/or the predicted intercept point. The process may be carried out until a specified number of steps have been completed, and/or until a specified heading error threshold of the aim point and a specified time of flight threshold have been achieved. The use of real time updating of an aim point of the missile advantageously takes into account variations in missile velocity and position due to individual variations in the rocket motor of the missile.
摘要翻译： 用于动力弹道导弹的指导方法涉及使用机载计算机实时模拟导弹的飞行路径，使用具有至少3个自由度的模型。 该仿真的结果用于实时更新瞄准点和/或预测的截距点。 迭代过程可用于调整目标点和/或预测截点。 可以执行该过程直到指定数量的步骤已经完成，和/或直到目标点的指定航向误差阈值和指定的飞行时间阈值达到。 使用实时更新导弹的目标点有利地考虑到由于导弹的火箭发动机的个体变化导弹速度和位置的变化。
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公开(公告)号：US20090127377A1
公开(公告)日：2009-05-21
申请号：US11392131
申请日：2006-03-29
申请人： Frank C. Lam , Gerald C. Chiang
发明人： Frank C. Lam , Gerald C. Chiang
IPC分类号： F42B15/01
摘要： A guidance method for a powered ballistic missile involves using an onboard computer to numerically simulate the flight path of the missile in real time, using a model with at least 3 degrees of freedom. The results of this simulation are used to update in real time an aim point and/or a predicted intercept point. An iterative process may be used in adjusting the aim point and/or the predicted intercept point. The process may be carried out until a specified number of steps have been completed, and/or until a specified heading error threshold of the aim point and a specified time of flight threshold have been achieved. The use of real time updating of an aim point of the missile advantageously takes into account variations in missile velocity and position due to individual variations in the rocket motor of the missile.
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公开(公告)号：US08306674B2
公开(公告)日：2012-11-06
申请号：US12572138
申请日：2009-10-01
申请人： Frank C. Lam
发明人： Frank C. Lam
IPC分类号： G01C23/00
摘要： A system and method is provided for thruster control in a flight vehicle. The system and method uses a proportional derivative matrix control technique to determine thrust commands in a Divert and Attitude control (DAC) system. The proportional derivative matrix control system is configured to receive pitch, roll and yaw commands as inputs, and generate thrust commands as outputs. The performance of the proportional derivative matrix controller is such that the thrust commands can achieve the desired attitude angles quickly and with reduced fuel consumption. The matrix control system can efficiently control a variety of thrusters, including asymmetric thrusters having different moment arms. The matrix control system is particularly suitable to the control of DAC systems with asymmetric thrusters that are configured for attitude control.
摘要翻译： 提供了一种用于飞行器中的推进器控制的系统和方法。 该系统和方法使用比例导数矩阵控制技术来确定转向和姿态控制（DAC）系统中的推力命令。 比例导数矩阵控制系统被配置为接收俯仰，俯仰和偏航指令作为输入，并产生推力命令作为输出。 比例导数矩阵控制器的性能使得推力命令可以快速实现所需的姿态角并降低燃料消耗。 矩阵控制系统可以有效地控制各种推进器，包括具有不同力矩臂的不对称推进器。 矩阵控制系统特别适用于配置为姿态控制的不对称推进器的DAC系统的控制。
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公开(公告)号：US20110082604A1
公开(公告)日：2011-04-07
申请号：US12572138
申请日：2009-10-01
申请人： Frank C. Lam
发明人： Frank C. Lam
摘要： A system and method is provided for thruster control in a flight vehicle. The system and method uses a proportional derivative matrix control technique to determine thrust commands in a Divert and Attitude control (DAC) system. The proportional derivative matrix control system is configured to receive pitch, roll and yaw commands as inputs, and generate thrust commands as outputs. The performance of the proportional derivative matrix controller is such that the thrust commands can achieve the desired attitude angles quickly and with reduced fuel consumption. The matrix control system can efficiently control a variety of thrusters, including asymmetric thrusters having different moment arms. The matrix control system is particularly suitable to the control of DAC systems with asymmetric thrusters that are configured for attitude control.
摘要翻译： 提供了一种用于飞行器中的推进器控制的系统和方法。 该系统和方法使用比例导数矩阵控制技术来确定转向和姿态控制（DAC）系统中的推力命令。 比例导数矩阵控制系统被配置为接收俯仰，俯仰和偏航指令作为输入，并产生推力命令作为输出。 比例导数矩阵控制器的性能使得推力命令可以快速实现所需的姿态角并降低燃料消耗。 矩阵控制系统可以有效地控制各种推进器，包括具有不同力矩臂的不对称推进器。 矩阵控制系统特别适用于配置为姿态控制的不对称推进器的DAC系统的控制。
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