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公开(公告)号：US4277038A
公开(公告)日：1981-07-07
申请号：US034088
申请日：1979-04-27
CPC分类号： F41G7/008 , F41G7/22 , F41G7/2253 , F41G7/226 , F41G7/2293 , F41G7/343
摘要： In a missile system, a simple way to guide a missile in a predetermined tectory from launch to the impacting with a target for optimum warhead penetration of armor by a guided missile. Initially, the missile is guided in yaw by proportional navigation. Subsequently it is guided in pitch first by a pitch programmer until the missile reaches a predetermined gimbal angle between a line of sight of a seeker of the missile and a centerline of the missile, then in pitch by a pseudo-time-optimal closed loop controller to direct the missile pitch attitude at a predetermined rate toward a target until said missile reaches another predetermined gimbal angle, and finally by proportional navigation in pitch of the missile to the target.
摘要翻译： 在导弹系统中，一种简单的方法来指导导弹在预定轨迹上从发射到受到导弹的最佳弹头穿透铠甲的目标。 最初，导弹通过比例导航在偏航中引导。 随后，它由音高编程员首先由音高引导，直到导弹达到导弹的探测器的视线与导弹的中心线之间的预定的万向角，然后通过伪时间最优的闭环控制器 以预定的速率朝向目标直接引导导弹俯仰姿态，直到所述导弹达到另一个预定的万向角，最后通过导弹到目标的俯仰比例导航。
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2.发明授权Ideal trajectory shaping for anti-armor missiles via gimbal angle controller autopilot 失效通过万向角控制器自动驾驶仪的反铠弹导弹的理想轨迹整形
公开(公告)号：US4383662A
公开(公告)日：1983-05-17
申请号：US885721
申请日：1978-03-13
CPC分类号： F41G7/008 , F41G7/2253 , F41G7/226 , F41G7/2293
摘要： Apparatus and method of anti-armor missile trajectory shaping for optimum rhead penetration of armor by a guided missile. The guidance system utilizes a terminal homing guidance unit in conjunction with a programmed control signal through the missile's autopilot to cause the missile to cruise at low altitudes and then dive onto the armor target. The terminal dive angle can be selected dependent upon the target's armor characteristics.
摘要翻译： 反导弹导弹轨迹整形装置和方法，用导弹对装甲进行最佳弹头穿透。 引导系统通过导弹的自动驾驶仪，结合编程的控制信号，利用终端归位引导单元，使导弹在低空巡航，然后潜水到装甲目标上。 终点潜水角度可以根据目标的装甲特征进行选择。
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3.发明授权Ideal trajectory shaping for anti-armor missiles via time optimal controller autopilot 失效通过时间优化控制器自动驾驶仪，进行反铠装导弹的理想轨迹整形
公开(公告)号：US4198015A
公开(公告)日：1980-04-15
申请号：US910307
申请日：1978-05-30
CPC分类号： F41G7/343 , F41G7/008 , F41G7/2253 , F41G7/226 , F41G7/2293 , G05D1/107
摘要： A missile system in which a missile is guided in a predetermined trajectoryrom launch or shortly thereafter in yaw by proportional navigation and in pitch first by a pitch programmer until said missile reaches a predetermined angle between a line of sight of a seeker of the missile and a centerline of the missile, then in pitch by a time optimal controller to direct the missile at a predetermined angle toward a target and finally by proportional navigation in pitch of the missile to the target.
摘要翻译： 一种导弹系统，其中导弹在预定轨迹中从发射引导或不久之后通过比例导航在偏航中被引导，并且首先由俯仰编程员进行俯仰，直到所述导弹达到导弹的引导者的视线之间的预定角度， 导弹的中心线，然后按时间优化控制器，将导弹以预定角度瞄准目标，最后通过导弹到目标的俯仰比例导航。
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