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1. 发明授权

US06752352B1 Gun-launched rolling projectile actuator 有权
标题翻译：枪弹射弹执行机构
公开(公告)号：US06752352B1
公开(公告)日：2004-06-22
申请号：US10616337
申请日：2003-07-07
申请人： Michael C. May , Richard W. Schroeder , Allan A. Voigt , John M. Speicher , Che-Ram S. Voigt
发明人： Michael C. May , Richard W. Schroeder , Allan A. Voigt , John M. Speicher , Che-Ram S. Voigt
IPC分类号： F42B1064
CPC分类号： F42B10/64
摘要： An actuator system for controlling the external fins on a gun-launched projectile to control the flight path of the projectile. These actuator systems include an electric motor having a rotor and output shaft which is driven between travel limits that are less than 180 apart (less than 90 in either direction from a central rest position). Coupling from the motor shaft to the control shaft for the external fins is via a coupling between an eccentric ball on the motor shaft and an eccentric receptacle member on the fin shaft. As the angle of the motor shaft varies, the eccentric ball slides in a slot in the fin coupling member, causing the fin shaft angle to vary correspondingly. In another embodiment, the eccentric ball for controlling the fin shaft angle is mounted on a link arm that is coupled to the motor shaft, thereby permitting the motor to be mounted off the projectile axis and thus accommodating a shortened space in the projectile required for the actuator system and associated power supply.
摘要翻译：一个执行器系统，用于控制喷枪上的外部翅片，以控制射弹的飞行路径。这些致动器系统包括具有转子和输出轴的电动机，该转子和输出轴在小于180分的行程限制（在从中心静止位置的任一方向上小于90度）之间驱动。通过马达轴上的偏心球和翅片轴上的偏心容器之间的联接，从马达轴到外部翅片的控制轴的耦合。当电动机轴的角度变化时，偏心球在翅片联接构件的槽中滑动，导致翅片轴角度相应地变化。在另一个实施例中，用于控制翅片轴角度的偏心球安装在联接到马达轴的连杆臂上，从而允许马达安装在抛射体轴线之外，从而在弹丸所需的弹丸中容纳缩短的空间执行器系统和相关电源。

2. 发明授权

US5887821A Mechanism for thrust vector control using multiple nozzles and only two yoke plates 失效
标题翻译：使用多个喷嘴和仅两个轭板的推力矢量控制的机构
公开(公告)号：US5887821A
公开(公告)日：1999-03-30
申请号：US859917
申请日：1997-05-21
申请人： Allan A. Voigt , Richard W. Schroeder , Che-Ram S. Voigt , John M. Speicher
发明人： Allan A. Voigt , Richard W. Schroeder , Che-Ram S. Voigt , John M. Speicher
IPC分类号： B64C15/02 , F02K9/80 , F02K9/84 , F42B10/64
CPC分类号： B64C15/02 , F02K9/80 , F02K9/84 , F42B10/64 , F42B10/666
摘要： In a missile thrust vector control (TVC) system, two yoke plates are used which surround a pair of pivotably-mounted rocket nozzles. The rocket nozzles pass through corresponding elongated slots disposed on each yoke plate, the elongate slots engaging said rocket nozzles and operating to actuate the movement of the rocket nozzles in accordance with command signals issued by the missile autopilot. The actuator yoke plates are mounted for movement in orthogonal directions, and for rotation in unison. The orthogonal movement of the yoke plates effects corresponding movement of the rocket nozzles in the yaw and pitch directions. Simultaneous rotation of the yoke plates produces a relative twisting of the pivotably-mounted rocket nozzles causing thrust angles to deviate from the missile central axis in opposite directions but equal degree, thereby imparting a roll moment to the missile. In this fashion, any combination of movements of the missile during flight is made possible.
摘要翻译：在导弹推力矢量控制（TVC）系统中，使用了两个轭盘，围绕着一对可枢转安装的火箭喷嘴。火箭喷嘴穿过设置在每个轭板上的相应的细长槽，细长槽与所述火箭喷嘴接合，并根据导弹自动驾驶仪发出的命令信号操作以致动火箭喷嘴的运动。致动器轭板安装成在正交方向上运动，并且一致地旋转。轭板的正交运动影响火箭喷嘴在偏航和俯仰方向上的相应运动。轭板的同时旋转产生可枢转安装的火箭喷嘴的相对扭转，引起推力角在相反方向上偏离导弹中心轴线但相等程度，从而给导弹施加滚动时刻。以这种方式，飞行中导弹的任何移动组合都成为可能。

3. 发明授权

US5950963A Fin lock mechanism 失效
标题翻译：翅片锁定机构
公开(公告)号：US5950963A
公开(公告)日：1999-09-14
申请号：US948035
申请日：1997-10-09
申请人： John M. Speicher , Che-Ram S. Voigt , Craig D. Perry , Allan A. Voigt
发明人： John M. Speicher , Che-Ram S. Voigt , Craig D. Perry , Allan A. Voigt
IPC分类号： F42B10/64 , F41G7/00 , F42B10/00
CPC分类号： F42B10/64
摘要： A mechanism for locking the fins of a missile in place when the missile is not in use utilizes tabs inserted in slots of the output shafts of the fins to immobilize the output shafts and the fins. In one embodiment, the tabs are cantilevered on a locking plate from which they extend radially toward the output shafts. A cam plate slidably engages the tabs on the locking plate and simultaneously lifts all the tabs out of the slots when it is rotated. for disengagement of the locking mechanism. Operation of the locking mechanism can be effected either manually, using a specialized tool, or remotely, using for example a pyrotechnic actuation device.
摘要翻译：当导弹不使用时，用于将导弹的翅片锁定就位的机构利用插入翅片的输出轴的狭槽中的突舌来固定输出轴和翅片。在一个实施例中，突片在锁定板上是悬臂的，它们从它们径向向着输出轴延伸。凸轮板可滑动地接合在锁定板上的突片，并且当旋转时所有突出部件都从槽中提升。用于分离锁定机构。锁定机构的操作可以使用专门的工具手动地进行，或者使用例如烟火驱动装置远程地实现。

4. 发明授权

US5566087A Gimbal control system using a trackball 失效
标题翻译：云台控制系统使用轨迹球
公开(公告)号：US5566087A
公开(公告)日：1996-10-15
申请号：US358940
申请日：1994-12-19
申请人： Allan A. Voigt , John M. Speicher , Che-Ram S. Voigt
发明人： Allan A. Voigt , John M. Speicher , Che-Ram S. Voigt
IPC分类号： H04N5/232 , G09G5/08 , G06F17/50
CPC分类号： H04N5/232
摘要： A gimbal control system including a hand controller having a trackball and a mode select switch for determining the mode of gimbal control. The mode control switch is capable of selecting between four different control modes. The trackball is enabled to control movement of the gimbal in different control relationships depending on the control mode which is selected. The hand controller includes a plurality of other switches for enabling the trackball to provide additional system control capabilities. The hand controller is ergonomically designed to minimize operator stress and fatigue during extended missions. It has a particular shape and the various control elements are strategically positioned to provide ready access to an operator's manual digits when the controller is held in the right hand with both hands and arms in a naturally relaxed attitude oriented at approximately a right angle.
摘要翻译：包括具有轨迹球的手控制器和用于确定万向节控制模式的模式选择开关的万向节控制系统。模式控制开关能够在四种不同的控制模式之间进行选择。根据所选择的控制模式，轨迹球能够根据不同的控制关系来控制万向节的移动。手控制器包括多个其他开关，用于使轨迹球能够提供附加的系统控制能力。手动控制器符合人体工程学设计，可在延长任务期间尽量减少操作者的压力和疲劳。它具有特定的形状，并且当控制器以双手和手臂以大致直角定向的自然放松的姿势握在右手中时，策略性地定位各种控制元件以便准确地访问操作者的手动数字。

5. 发明授权

US5907433A Compact variable field of view optical system 失效
标题翻译：紧凑型视场光学系统
公开(公告)号：US5907433A
公开(公告)日：1999-05-25
申请号：US874432
申请日：1997-06-16
申请人： Allan A. Voigt , John M. Speicher , Che-Ram S. Voigt
发明人： Allan A. Voigt , John M. Speicher , Che-Ram S. Voigt
IPC分类号： G02B15/02 , G02B13/06 , G02B23/00
CPC分类号： G02B15/02
摘要： An optical system is provided with a plurality of field of view optical groups for insertion into the optical path. The field of view optical groups each subtend a prescribed field of view angle and are rotatably mounted on a rotary assembly for insertion into an operational position in the optical path. The rotary assembly is provided with hard stop contacts which rotate along a path and interact with stationary stops to locate the optical groups in the operational position. Additionally, movable stops are reciprocated into the rotation path of the hard stop contacts to provide additional modes, including a calibration mode. The system is also provided with extender optical groups which can be inserted in the optical path to provide intermediate fields of view between those of the field of view optical groups, thereby doubling the total number of fields of view available. The intermediate fields of view ease the transitions between fields of view achieved by the field of view optical groups and provide an effective step zoom mode of operation with increased overall zoom ratio.
摘要翻译：光学系统设置有用于插入到光路中的多个视场光学组。视场光学组各自对准规定的视野角，并且可旋转地安装在旋转组件上以插入到光路中的操作位置。旋转组件设置有沿着路径旋转并与静止止动件相互作用的硬停止触点，以将光学组定位在操作位置。此外，可移动止动件往复运动到硬停止触点的旋转路径中以提供包括校准模式的附加模式。该系统还设置有可以插入光路中的扩展器光学组，以在视场光学组的视场之间提供中间视野，从而将可用视场的总数加倍。中间视野简化了由视场光学组实现的视野之间的转换，并提供了具有增加的总变焦比的有效的步进变焦操作模式。

6. 发明授权

US5630564A Differential yoke-aerofin thrust vector control system 失效
标题翻译：差速轭翼型推力矢量控制系统
公开(公告)号：US5630564A
公开(公告)日：1997-05-20
申请号：US483954
申请日：1996-03-19
申请人： John M. Speicher , Allan A. Voigt , Che-Ram S. Voigt
发明人： John M. Speicher , Allan A. Voigt , Che-Ram S. Voigt
IPC分类号： B64C15/02 , F02K9/84 , F42B10/64 , F42B10/06 , F16H29/20 , F42B15/01
CPC分类号： F42B10/663 , B64C15/02 , F02K9/84 , F42B10/64 , F42B10/666 , Y10T74/18816
摘要： An actuation system for controlling the steerable nozzle of a missile or like vehicle is combined with an aerofin control system, both of which are driven in unison by associated drive motors and gear assemblies, one set for each aerofin. The nozzle steering system comprises two essentially identical yoke plates mounted along a plane generally transverse to the missile axis and oriented orthogonally relative to each other about the missile axis for pivoting the nozzle through mutually orthogonal axes, thereby achieving omni-directional steering. The yoke plates are coupled at opposite ends to pinion gears which are driven by the same gear assemblies which drive the associated aerofins. The arrangement permits common directional control of the steerable nozzle and the aerofins while maintaining the nozzle in a neutral direction when the aerofins are rotated to a missile roll control mode.
摘要翻译：用于控制导弹或类似车辆的可转向喷嘴的致动系统与机翼控制系统组合，两者都由相关联的驱动马达和齿轮组件一致地驱动，一个用于每个机翼。喷嘴转向系统包括两个基本上相同的轭板，其沿着大致横向于导弹轴线的平面安装，并且围绕导弹轴线相对于彼此正交地定向，用于使喷嘴通过相互正交的轴线枢转，由此实现全方向转向。轭板在相对的端部联接到小齿轮上，小齿轮由相同的齿轮组件驱动，驱动相关联的机翼。当翼翼旋转到导弹控制模式时，该布置允许可操纵的喷嘴和机翼的共同的方向控制，同时将喷嘴保持在中性方向。

7. 发明授权

US5505408A Differential yoke-aerofin thrust vector control system 失效
标题翻译：差速轭翼型推力矢量控制系统
公开(公告)号：US5505408A
公开(公告)日：1996-04-09
申请号：US139939
申请日：1993-10-19
申请人： John M. Speicher , Allan A. Voigt , Che-Ram S. Voigt
发明人： John M. Speicher , Allan A. Voigt , Che-Ram S. Voigt
IPC分类号： B64C15/02 , F02K9/84 , F42B10/64 , F41G7/00
CPC分类号： F42B10/663 , B64C15/02 , F02K9/84 , F42B10/64 , F42B10/666 , Y10T74/18816
摘要： An actuation system for controlling the steerable nozzle of a missile or like vehicle is combined with an aerofin control system, both of which are driven in unison by associated drive motors and gear assemblies, one set for each aerofin. The nozzle steering system comprises two essentially identical yoke plates mounted along a plane generally transverse to the missile axis and oriented orthogonally relative to each other about the missile axis for pivoting the nozzle through mutually orthogonal axes, thereby achieving omni-directional steering. The yoke plates are coupled at opposite ends to pinion gears which are driven by the same gear assemblies which drive the associated aerofins. The arrangement permits common directional control of the steerable nozzle and the aerofins while maintaining the nozzle in a neutral direction when the aerofins are rotated to a missile roll control mode.
摘要翻译：用于控制导弹或类似车辆的可转向喷嘴的致动系统与机翼控制系统组合，两者都由相关联的驱动马达和齿轮组件一致地驱动，一个用于每个机翼。喷嘴转向系统包括两个基本上相同的轭板，其沿着大致横向于导弹轴线的平面安装，并且围绕导弹轴线相对于彼此正交地定向，用于使喷嘴通过相互正交的轴线枢转，由此实现全方向转向。轭板在相对的端部联接到小齿轮上，小齿轮由相同的齿轮组件驱动，驱动相关联的机翼。当翼翼旋转到导弹控制模式时，该布置允许可操纵的喷嘴和机翼的共同的方向控制，同时将喷嘴保持在中性方向。

8. 发明授权

US06446906B1 Fin and cover release system 有权
标题翻译：翅片和盖子释放系统
公开(公告)号：US06446906B1
公开(公告)日：2002-09-10
申请号：US09825808
申请日：2001-04-04
申请人： Allan A. Voigt , Che-Ram S. Voigt , John S. Speicher , Charles R. Ericson
发明人： Allan A. Voigt , Che-Ram S. Voigt , John S. Speicher , Charles R. Ericson
IPC分类号： B64C936
CPC分类号： F42B10/14 , B64C9/36 , B64D7/08
摘要： Pyrotechnic actuator cover/fin release system designed for high G forces of gun-launched-systems. As safety feature, system allows the pyrotechnic actuator to be installed as one of the last steps of the final testing sequence and removed safely on disassembly. A first cam action develops initial ejection. Subsequently firing the pyrotechnic pushes both the fins and the covers outward via a second cam surface. The release system both holds covers securely latched until commanded to release and then unlatches covers prior to pushing them open. The cover eject sequence results in the flight forward edge of cover being kicked into air stream. Thereafter the cover is lifted and rotates about its aft release hinge until, at about 30 degrees of rotation, the hinge disengages. The fins then are driven into the fully deployed state by a spring and piston/wedge mechanism on the actuator shaft.
摘要翻译：烟火执行器盖/散热片释放系统设计用于枪支发射系统的高G力。作为安全特征，系统允许将烟火执行器安装为最终测试顺序的最后一个步骤，并在拆卸时安全拆除。第一个凸轮动作开始初始喷射。随后点燃烟火通过第二凸轮表面向外推动翅片和盖子。释放系统均将盖子牢固地锁定，直到被释放，然后在将它们打开之前将盖子解开。盖弹出顺序导致盖的飞行前沿被踢入气流。此后，盖被提起并绕其后释放铰链旋转，直到约30度的旋转，铰链脱离。然后，翅片通过致动器轴上的弹簧和活塞/楔形机构被驱动到完全展开状态。

9. 发明授权

US5662290A Mechanism for thrust vector control using multiple nozzles 失效
标题翻译：使用多个喷嘴进行推力矢量控制的机理
公开(公告)号：US5662290A
公开(公告)日：1997-09-02
申请号：US679849
申请日：1996-07-15
申请人： Che-Ram S. Voigt
发明人： Che-Ram S. Voigt
IPC分类号： F02K9/84 , F42B10/66 , B05B12/00 , F02K9/80
CPC分类号： F02K9/84 , F42B10/666
摘要： An interface yoke plate is employed to impart directional control of multiple rocket nozzles. The interface yoke plate is rotated and translated in two orthogonal directions in accordance with steering commands from the missile autopilot and effects control along the yaw, pitch, and roll axes of the missile. One actuator yoke plate translates the interface yoke plate along one axis while another actuator yoke plate translates the interface yoke plate along a second axis. The interface yoke plate may also be rotated by one or both actuator yoke plates, causing a relative twisting of the multiple rocket nozzles and thereby directing their thrust in opposing directions and inducing a roll motion of the missile.
摘要翻译：采用接口轭板来对多个火箭喷嘴进行方向控制。接口轭板根据导弹自动驾驶仪的转向指令在两个正交方向上旋转和平移，并沿着导弹的偏航，俯仰和滚动轴线进行效果控制。一个致动器轭板将接口轭板沿着一个轴平移，而另一个致动器轭板沿着第二轴平移接口轭板。接口轭板也可以由一个或两个致动器偏转板旋转，引起多个火箭喷嘴的相对扭转，从而将它们的推力指向相反的方向并引起导弹的滚动运动。

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