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    Ideal trajectory shaping for anti-armor missiles via time optimal controller autopilot
    1.
    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

    Applicant: Robert E. Yates ,  John P. Leonard ,  Robert E. Alongi

    Inventor： Robert E. Yates ,  John P. Leonard ,  Robert E. Alongi

    IPC: F41G7/22 ,  F41G7/34 ,  F42B15/02

    CPC classification number: F41G7/343 ,  F41G7/008 ,  F41G7/2253 ,  F41G7/226 ,  F41G7/2293 ,  G05D1/107

    Abstract: 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.

    Abstract translation: 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。

    Trajectory shaping of anti-armor missiles via tri-mode guidance
    2.
    发明授权
    Trajectory shaping of anti-armor missiles via tri-mode guidance 失效
    通过三模式导弹进行防弹导弹的轨迹成形

    公开(公告)号：US4277038A

    公开(公告)日：1981-07-07

    申请号：US034088

    申请日：1979-04-27

    Applicant: Robert E. Yates ,  John P. Leonard ,  Robert E. Alongi ,  Wilfredo V. Albanes ,  Charles M. Bishop

    Inventor： Robert E. Yates ,  John P. Leonard ,  Robert E. Alongi ,  Wilfredo V. Albanes ,  Charles M. Bishop

    IPC: F41G7/00 ,  F41G7/22 ,  F41G7/34 ,  F42B15/02

    CPC classification number: F41G7/008 ,  F41G7/22 ,  F41G7/2253 ,  F41G7/226 ,  F41G7/2293 ,  F41G7/343

    Abstract: 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.

    Abstract translation: 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。

    Feedback PDM encoder and method for actuating a pneumatic actuator with a digital autopilot
    3.
    发明授权
    Feedback PDM encoder and method for actuating a pneumatic actuator with a digital autopilot 失效
    反馈PDM编码器和用于启动具有数字自动驾驶仪的气动执行器的方法

    公开(公告)号：US4033525A

    公开(公告)日：1977-07-05

    申请号：US638476

    申请日：1975-12-08

    Applicant: John P. Leonard ,  Robert E. Yates

    Inventor： John P. Leonard ,  Robert E. Yates

    IPC: F41G7/30 ,  G05D1/02 ,  G05D3/18 ,  F42B13/30

    CPC classification number: F41G7/301 ,  G05D1/0202 ,  G05D3/18

    Abstract: A feedback PDM encoder and method is presented which permits utilization ofneumatic pulse duration modulation (PDM) actuators with potentiometer position pickoffs in a digital autopilot loop. The actuator is directly driven by a signal derived in the digital autopilot which is in the pulse duration modulation (PDM) format. This signal is derived within the autopilot digital computer using conventional digital techniques. Analog feedback from the potentiometer which indicates angular excursion of the actuator is formatted into a PDM format. This method yields all signals necessary to operate the actuator in a closed loop missile control system.

    Abstract translation: 提出了一种反馈PDM编码器和方法，其允许在数字自动驾驶仪环路中利用具有电位计位置传感器的气动脉冲持续时间调制（PDM）致动器。 致动器由在数字自动驾驶仪中得到的信号直接驱动，该信号处于脉冲宽度调制（PDM）格式。 该信号是使用传统的数字技术在自动驾驶仪数字计算机内导出的。 来自电位计的模拟反馈表示执行器的角度偏移被格式化为PDM格式。 该方法产生在闭环导弹控制系统中操作执行器所需的所有信号。

    Ideal trajectory shaping for anti-armor missiles via gimbal angle controller autopilot
    4.
    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

    Applicant: Robert E. Alongi ,  Robert E. Yates ,  John P. Leonard

    Inventor： Robert E. Alongi ,  Robert E. Yates ,  John P. Leonard

    IPC: F41G7/00 ,  F41G7/22

    CPC classification number: F41G7/008 ,  F41G7/2253 ,  F41G7/226 ,  F41G7/2293

    Abstract: 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.

    Abstract translation: 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。

    Reversible mounting bracket for electronic devices
    5.
    发明授权
    Reversible mounting bracket for electronic devices 失效
    用于电子设备的可逆安装支架

    公开(公告)号：US5174539A

    公开(公告)日：1992-12-29

    申请号：US711029

    申请日：1991-10-06

    Applicant: John P. Leonard

    Inventor： John P. Leonard

    IPC: F16M13/00

    CPC classification number: F16M11/22 ,  F16M13/02

    Abstract: A bracket for mounting components in a housing in which a first set of two legs extend from and substantially perpendicular to one surface of a plate and a second set of at least two legs extend from and perpendicular to the opposite surface of the plate. The bracket is connectable to the floor of the housing to support a first component at a predetermined height in said housing and is reversible to support a component of a greater height than the first component.

    Abstract translation: 一种用于将部件安装在壳体中的支架，其中第一组两个腿从板的一个表面延伸并且基本上垂直于板的一个表面，并且第二组至少两个腿从板的相对表面延伸并垂直于板的相对表面。 支架可连接到壳体的底板，以支撑在所述壳体中预定高度的第一部件，并且是可逆的以支撑比第一部件高的部件。

    Guided missile using fluidic sensing and steering
    9.
    发明授权
    Guided missile using fluidic sensing and steering 失效
    导弹使用流体感应和转向

    公开(公告)号：US3979085A

    公开(公告)日：1976-09-07

    申请号：US513015

    申请日：1974-10-08

    Applicant: John P. Leonard

    Inventor： John P. Leonard

    IPC: F42B10/66 ,  F42B15/18

    CPC classification number: F42B10/66

    Abstract: A missile using fluidic sensors for determination of net aerodynamic forcend moment on the missile. The force and moment thus determined are processed and summed by fluidic amplifiers and integrators to provide control signals for fluidic thrusters or other steerers for the missile. The sensors are diametrically opposed pairs of pressure taps located axially and circumferentially in the missile skin. Net aerodynamic force on the missile is taken as the algebraic sum from all the sensors in a linear fluidic summer, and net aerodynamic moment is taken from the proportional sum of the sensors in accordance with their position along the axis of the missile. This proportional sum is made in a fluidic vortex summer.

    Abstract translation: 使用流体传感器确定导弹上净空气动力和力矩的导弹。 由此确定的力和力矩由流体放大器和积分器进行处理和求和，为流体推进器或导弹的其他导向器提供控制信号。 传感器在导弹皮肤中沿轴向和周向定位的直径相对的压力抽头对。 在线性流动夏季，导弹上的净空气动力学作为所有传感器的代数和，并根据其沿导弹轴线的位置从传感器的比例和获取净空气动力学力矩。 这个比例总和是在流体涡旋夏季进行的。

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