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1. 发明授权

US4623107A Regulating system for guided missiles traveling at supersonic speed 失效
标题翻译：以超音速行驶的导弹调节系统
公开(公告)号：US4623107A
公开(公告)日：1986-11-18
申请号：US668033
申请日：1984-11-05
申请人： Helmut Misoph
发明人： Helmut Misoph
IPC分类号： F42B10/64 , F42B15/02 , F42B25/24
CPC分类号： F42B10/64 , F42B10/661
摘要： A regulating system for guided ammunition flying at supersonic speed, such as missiles, rockets, or projectiles which includes an arrangement for effecting the guidance through a partially changeable flow pressure. Provided on the ammunition are one or more steering systems in the form of ring-shaped or quasi-annular guidance mechanisms which are divided into sectors, and wherein the sectors cause a medium which become effective within the sectors to selectively and controllably block the airflow.
摘要翻译：用于以超音速飞行的引导弹药的调节系统，例如导弹，火箭或射弹，其包括通过部分可变的流动压力实现引导的装置。提供在弹药上的是一个或多个环形或准环形引导机构形式的转向系统，其被划分为扇区，并且其中扇区引起在扇区内变得有效的介质以选择性地和可控地阻挡气流。

2. 发明授权

US4756253A Apparatus for deploying a flexible samara blade 失效
标题翻译：用于部署柔性samara刀片的装置
公开(公告)号：US4756253A
公开(公告)日：1988-07-12
申请号：US895244
申请日：1986-08-11
申请人： Dana C. Herring , Elbert W. Duvall
发明人： Dana C. Herring , Elbert W. Duvall
IPC分类号： F42B10/14 , F42B25/24 , F42B25/16
CPC分类号： F42B10/146
摘要： Apparatus is disclosed which provides for the controlled deployment of a flexible samara blade used to orient and decelerate a submunition cannister which is dispensed at altitude and allowed to free fall to earth. Spin pins are anchored in and extend outwardly from the downstream end of the cannister. Placement of the pins is such that the flexible samara blade can be wrapped around the pins to place the blade in a stowed condition within the periphery of the cannister end prior to launch of the submunition. Caps on the pins are used to inhibit the stowed blade from slipping off the pins. The blade is wrapped around the pins in a direction opposite to the direction of rotation of the submunition during launch. Launching the submunition in a spinning state creates a centrifugal force in the weighted tip of the samara blade causing the wing to unwrap from the stowed to the deployed state. The pins keep tension in the unfolding wing and preclude erroneous twist-up of the flexible blade.
摘要翻译：公开了一种设备，用于控制部署用于定向和减速子弹药罐的柔性samara刀片，所述子弹药罐在高度被分配并被允许自由落体。旋转销被锚固并从罐的下游端向外延伸。销的放置使得柔性samara刀片可以缠绕在销上，以在发射子弹药之前将刀片放置在罐末端的周边内的收纳状态。引脚上的盖子用于禁止收起的刀片从引脚上滑落。在发射期间，刀片沿着与子弹药旋转方向相反的方向缠绕在销上。在旋转状态下启动子弹药在萨马拉叶片的加重尖端产生离心力，导致机翼从收起的展开状态展开。针脚在展开的机翼中保持张力，并防止柔性叶片的错误扭曲。

3. 发明授权

US4492166A Submunition having terminal trajectory correction 失效
标题翻译：子弹药具有终点轨迹校正
公开(公告)号：US4492166A
公开(公告)日：1985-01-08
申请号：US791805
申请日：1977-04-28
申请人： William O. Purcell
发明人： William O. Purcell
IPC分类号： F41G7/22 , F42B10/14 , F42B12/58 , F42B25/16 , F42B25/24
CPC分类号： F42B10/14 , F41G7/222 , F41G7/2233 , F41G7/2253 , F41G7/2293 , F42B10/661 , F42B12/58
摘要： A submunition having an infrared detector disposed in a nose portion thereof, the detector having a narrow angularly-displaced field of view, and vanes for causing the submunition to rotate at an essentially constant rate while in flight, thus to cause the infrared detector to scan a target area and to detect the presence of a target having a selected higher temperature than the background infrared radiation. The submunition includes a small explosive charge sheet disposed on its outer surface and concentrated in one area, and firing pulse generation means for firing the charge. When the infrared detector scans past a detectable target within the target area, it produces a detection signal that triggers a firing pulse from the firing pulse generation means, thereby firing the explosive charge to create a lateral impulse or offset of the submunition. Timing means is provided to cause the impulse to be produced in the exact direction to correct the terminal trajectory of the submunition to intercept the detected target, so that the warhead carried by the submunition can cripple or destroy the target. This novel correctable-trajectory submunition is therefore seen to be a low-cost device having high kill probability when air-dropped in clusters, thereby providing very high cost effectiveness.
摘要翻译：具有设置在其鼻部中的红外检测器的子弹药，所述检测器具有窄的角度位移视野，以及用于使所述子弹药在飞行中以基本恒定的速率旋转的叶片，从而使所述红外检测器扫描目标区域并且检测具有比背景红外辐射选择的较高温度的目标的存在。子弹药包括设置在其外表面上并集中在一个区域中的小型炸药，以及用于点燃电荷的点火脉冲产生装置。当红外检测器扫描目标区域内的可检测目标时，它产生一个检测信号，该检测信号触发起动脉冲发生装置的点火脉冲，从而点燃炸药以产生子弹药的横向脉冲或偏移。提供定时手段，使精确方向产生冲击，以纠正子弹头的终点轨迹，以拦截检测到的目标，使子弹药携带的弹头可以摧毁或摧毁目标。因此，这种新型的可校正轨迹子弹药被认为是一种低成本的装置，其具有在集群中空降时具有高的杀伤概率，从而提供非常高的成本效益。

4. 发明授权

US3954057A Radio controlled wing rotor bomblet 失效
标题翻译：无线电控制翼转子炸弹
公开(公告)号：US3954057A
公开(公告)日：1976-05-04
申请号：US568682
申请日：1966-07-28
申请人： Abraham Flatau
发明人： Abraham Flatau
IPC分类号： F41G9/02 , F42B10/26 , F42B10/64 , F42B15/10 , F42B25/24
CPC分类号： F42B10/64 , F41G9/02 , F42B10/26 , F42B15/105
摘要： The invention is directed to controlling the flight of an autorotating wingotor comprising an elongated wing rotor, actuating means remotely controlled, plates coaxially secured to each end of the said rotor, flight control means, said actuating means driving said flight control means axial movement along means mounted adjacent each end of said rotor and thereby effecting the trajectory of the autorotating wing rotor.
摘要翻译：本发明涉及控制自动驾驶翼转子的飞行，其包括细长翼转子，远程控制的致动装置，同轴固定在所述转子的每一端的板，飞行控制装置，所述致动装置驱动所述飞行控制装置沿轴向运动安装在所述转子的每一端的装置，从而实现自转机翼转子的轨迹。

5. 发明授权

US3611930A Spherical shaped body with aerodynamic torque ribs 失效
标题翻译：具有动力学扭矩RIBS的球形体
公开(公告)号：US3611930A
公开(公告)日：1971-10-12
申请号：US3611930D
申请日：1966-06-27
申请人： HONEYWELL INC
发明人： KENSINGER ROBERT S
IPC分类号： F42B10/06 , F42B10/26 , F42B25/20 , F42B25/24
CPC分类号： F42B10/26 , F42B10/06
摘要： 1. A generally spherically shaped member having a plane of symmetry and an axis passing substantially through the geometric center of said member normal to said plane of symmetry, said member further having external aerodynamic features which will cause it, when placed into an airstream, to spin about said axis regardless of the orientation of said member relative to the airstream, said aerodynamic features including a plurality of torque ribs, each of said ribs having: AN AERODYNAMIC FORCE CENTERED ON SAID PLANE OF SYMMETRY AND EXTENDING A SHORT DISTANCE TO EITHER SIDE OF IT; A FRONT FACE HAVING A FIRST PART EXTENDING FROM ONE SIDE OF SAID AERODYNAMIC FENCE FOR A SHORT DISTANCE SUBSTANTIALLY PARALLEL TO SAID PLANE OF SYMMETRY, THEN CURVING IN A CIRCULAR RADIUS AWAY FROM SAID PLANE OF SYMMETRY INTO A SEGMENT AT AN ANGLE TO SAID PLANE OF SYMMETRY, SAID FACE FURTHER HAVING A SECOND PART EXTENDING FROM THE OTHER SIDE OF SAID AERODYNAMIC FENCE, SAID SECOND PART BEING SUBSTANTIALLY SYMMETRICAL TO SAID FIRST PART WITH REFERENCE TO SAID PLANE OF SYMMETRY; AND A REAR FACE PROVIDING A SMOOTH STREAMLINED SURFACE EXTENDING TOWARDS THE REAR AND DOWNWARD FROM THE UPPER EDGE OF SAID FRONT FACE AND MERGING WITH THE SPHERICAL SURFACE OF THE MEMBER.

6. 发明授权

US5874727A Method and apparatus for combatting helicopters operating with concealment 失效
标题翻译：与隐蔽作战的直升机作战方法和装置
公开(公告)号：US5874727A
公开(公告)日：1999-02-23
申请号：US603320
申请日：1996-02-10
申请人： Egbert Harraeus , Bernt Obkircher
发明人： Egbert Harraeus , Bernt Obkircher
IPC分类号： F41G7/22 , F42B25/24
CPC分类号： F41G7/2226 , F41G7/2253 , F41G7/2293
摘要： The invention provides a method for continuous acquisition, identification, and attack of helicopters operating with concealment, using a missile with an integrated target search head computer control. The visual field of the search head is adapted optimally in both the search phase and in the target tracking phase. During the search phase, the missile travels a flight path roughly parallel to the surface of the ground, and the axis of the line of sight is directed diagonally downward at a suitable angle. During a target tracking, the line of sight runs collinearly with the missile axis. The natural radiation of the helicopter modulated by the rotor blade movement is used for target recognition.
摘要翻译：本发明提供了一种用于使用具有集成目标搜索头计算机控制的导弹来连续地采集，识别和攻击使用隐蔽操作的直升机的方法。在搜索阶段和目标跟踪阶段中，搜索头的视野被最佳地适应。在搜索阶段，导弹行进大致平行于地面的飞行路径，视线的轴线以适当的角度向下倾斜。在目标跟踪期间，视线与导弹轴线共线运行。由转子叶片运动调制的直升机的自然辐射用于目标识别。

7. 发明授权

US4711178A Ammunition incorporating searching fuse with trajectory correctable during its final flight phase and method for combating armored target objects 失效
标题翻译：弹药在其最终飞行阶段包含搜索保险丝和可纠正的轨迹，并且用于对抗装甲目标物体的方法
公开(公告)号：US4711178A
公开(公告)日：1987-12-08
申请号：US855078
申请日：1986-04-22
申请人： Nikolaus Argyrakis
发明人： Nikolaus Argyrakis
IPC分类号： F41G7/22 , F42B10/56 , F42C13/00 , F42B25/24
CPC分类号： F42B10/56 , F41G7/222 , F42C13/006
摘要： Ammunition incorporating a sensing fuse and a parachute, and which has the trajectory thereof correctable during its final flight phase, and a method for the combating of armored target objects with the utilization of such ammunition. The ammunition with the sensing fuse is equipped with a pulse transmitter for a course alignment or correction in the direction towards the lateral or sideways offset of a target object which has been detected by the sensing fuse, and with devices for suspending the action of a parachute during the approach to a target by the ammunition along a quasi-ballistic trajectory.
摘要翻译：包含感测保险丝和降落伞的弹药，其具有在其最终飞行阶段期间可校正的轨迹，以及使用这种弹药来对抗装甲目标物体的方法。具有感测保险丝的弹药配备有脉冲发射器，用于沿着被感测保险丝检测到的目标物体的侧向或侧向偏移的方向进行航向对准或校正，以及用于暂停降落伞的作用的装置在准弹道导弹期间，弹药进入目标。

8. 发明授权

US4595157A Control system particularly for wingless guided ammunition 失效
标题翻译：特别是无翼导弹的控制系统
公开(公告)号：US4595157A
公开(公告)日：1986-06-17
申请号：US523430
申请日：1983-08-16
申请人： Heiko Uhle
发明人： Heiko Uhle
IPC分类号： B64C15/14 , F41G9/00 , F42B25/24
CPC分类号： F42B10/663
摘要： A control system for an ammunition having a longitudinal axis and adapted to move in a flight direction, particularly a wingless ammunition falling in ballistic flight, comprises a body having a rear curved surface with a gas generator in the body for producing gas under pressure. A nozzle is mounted to the body and oriented to direct a gas jet produced from the pressurized gas rearwardly and tangentially over the curved surface with respect to the flight direction of the ammunition. The gas jet produces reduced pressure on its side of the ammunition to alter the flight thereof.
摘要翻译：具有纵向轴线并适于沿飞行方向移动的弹药的控制系统，特别是落在弹道飞行中的无翼弹药包括具有后曲面的主体，该主体具有气体发生器，用于在压力下产生气体。喷嘴安装到主体并且被定向成将从加压气体产生的气体射流相对于弹药的飞行方向向后和切向地引导到弯曲表面上。喷气机在弹药的一侧产生压力，以改变其飞行。

9. 发明授权

US3854678A Rotary valve jet flap control system 失效
标题翻译：旋转阀喷嘴翼片控制系统
公开(公告)号：US3854678A
公开(公告)日：1974-12-17
申请号：US39803973
申请日：1973-09-17
申请人： US NAVY
发明人： GERES R
IPC分类号： B64C9/38 , F42B25/24
CPC分类号： B64C9/38 , F42B10/663 , Y02T50/32
摘要： A jet flap control system for bombs, missiles and aircraft that is deployed along the trailing edge of a wing for achieving high lift at zero angle of attack. The jet flap can be utilized to provide wing lift, roll control and a small amount of altitude control without appreciatively increasing the drag.
摘要翻译：一种用于炸弹，导弹和飞机的喷气翼片控制系统，其沿翼的后缘部署，以实现零攻角的高升力。喷气翼可用于提供机翼提升，滚动控制和少量的高度控制，而不会明显增加阻力。

10. 发明授权

US4635553A Maneuvering air dispensed submunition 失效
标题翻译：机动空气分配子弹药
公开(公告)号：US4635553A
公开(公告)日：1987-01-13
申请号：US787452
申请日：1985-10-15
申请人： Thomas A. Kane
发明人： Thomas A. Kane
IPC分类号： F42B10/64 , F42B25/24
CPC分类号： F42B10/64
摘要： An air dispensed assembly in the form of a submunition cannister is disclosed which has the capability to perform a lateral maneuver during the final 1500 ft. of descent before impact. Maneuvering is accomplished by deploying a samara blade shaped wing from the rear of the submunition cannister after ejection from the casing of the launching shell. The wing is sized and provided with an angle of attack which causes the cylindrical shaped cannister to spin as it descends downward at approximately a constant rate of descent. A passive infrared sensor in the nose of the cannister provides target information to a data processor which generates steering commands to appropriately alter the wing angle of attack so as to bring about a corrective lateral change in direction. When within lethal range of the sensed target, the warhead in the submunition is detonated.
摘要翻译：公开了一种子弹药罐形式的空气分配组件，其具有在冲击之前的最后1500英尺的下降期间执行横向操纵的能力。通过在从发射壳体的壳体上弹出之后，从子弹药罐的后部部署萨马拉叶片形翼来实现机动。机翼的尺寸和设置有一个迎角，使得圆筒形的罐子以大致恒定的下降速度向下下降时旋转。食筒鼻子中的被动红外传感器向数据处理器提供目标信息，数据处理器产生转向命令以适当地改变机翼迎角，从而导致方向上的校正横向变化。在感测目标的致命范围内，子弹药弹头被引爆。

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