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1. 发明授权

US5631442A Missile having a pivotal warhead 失效
标题翻译：导弹有一个关键的弹头
公开(公告)号：US5631442A
公开(公告)日：1997-05-20
申请号：US641642
申请日：1996-05-01
申请人： Wilfried Becker , Dirk Kilfitt , Werner Grosswendt
发明人： Wilfried Becker , Dirk Kilfitt , Werner Grosswendt
IPC分类号： F42B12/14 , F42B12/20
CPC分类号： F42B12/204 , F42B12/14
摘要： A missile includes a warhead accommodated in an inner space at a front portion of the missile; a ball joint being in alignment with the longitudinal missile axis and pivotally supporting the warhead; and an aiming device for placing the warhead into a desired pivotal orientation. The aiming device includes a plurality of inflatable vessels arranged axially adjacent the warhead in a distribution about the missile axis. Each vessel has a first end oriented toward the warhead and a second end oriented away therefrom. The vessels are supported at their second end by a disk situated in the inner space of the missile. A gas generator is coupled to each vessel for charging the vessel with a gas to place the vessel into its inflated state. In the inflated state each vessel exerts a torque on the warhead about the ball joint by an engagement between the first end of the respective vessel and the warhead. Further, an electronic control system is accommodated in the inner space of the vessel. The electronic control system is connected to each gas generator for actuating a selected gas generator to place the warhead into a desired inclined orientation relative to the missile axis.
摘要翻译：导弹包括容纳在导弹前部内空间的弹头; 球形接头与纵向导弹轴线对齐并枢转地支撑弹头; 以及用于将弹头置于期望的枢转方向的瞄准装置。瞄准装置包括在围绕导弹轴线的分布中沿轴向邻近弹头布置的多个可充气容器。每个船舶具有朝向弹头的朝向的第一端和朝向其的第二端。船只在其第二端由位于导弹内部空间的盘支撑。气体发生器联接到每个容器，用于用气体对容器充电以将容器置于其充气状态。在充气状态下，每个船舶通过相应船舶的第一端和弹头之间的接合，在弹头上围绕球窝接头施加扭矩。此外，电子控制系统容纳在容器的内部空间中。电子控制系统连接到每个气体发生器，用于致动选定的气体发生器，以将弹头相对于导弹轴置于期望的倾斜方位。

2. 发明授权

US4244293A Projectile designed for recoilless and virtually noiseless firing 失效
标题翻译：射弹设计用于无后坐力和几乎无噪声的射击
公开(公告)号：US4244293A
公开(公告)日：1981-01-13
申请号：US807315
申请日：1977-06-09
申请人： Werner Grosswendt , Manfred Moll , Wilfried Becker
发明人： Werner Grosswendt , Manfred Moll , Wilfried Becker
IPC分类号： F41A1/10 , F41F3/02
CPC分类号： F41A1/10
摘要： A projectile to be fired from a tubular or rail-shaped launcher has a warhead integral with a rearwardly extending tube of smaller diameter which contains a propulsive charge inserted between the warhead and a sabot carrying a frangible inertial mass. The rear end of the tube has a constricted opening which, upon detonation of the charge, retains the rearwardly moving sabot while giving passage to the disintegrating mass as the projectile is propelled forwardly. The propulsion gases evolving within the tube are temporarily retained by one or more heat-destructible plugs in the sabot and/or in the tube which melt, burn or char to allow the delayed escape of the gases whereby an in-flight thrust is imparted to the projectile.
摘要翻译：从管状或轨道式发射器发射的射弹具有与直径较小的向后延伸的管一体的弹头，其包含插入在弹头和携带易碎惯性质量的炮弹之间的推进炸药。管的后端具有收缩开口，当开始爆炸时，当弹丸向前推进时，该开口保持向后移动的破坏物，同时通向碎裂物质。在管内释放的推进气体由一个或多个可破坏的塞子临时保持在膛体和/或管中，其熔化，燃烧或炭化以允许气体的延迟逸出，从而将飞行中的推力施加到射弹。

3. 发明授权

US5433399A Device for guiding a missile 失效
标题翻译：导弹导弹装置
公开(公告)号：US5433399A
公开(公告)日：1995-07-18
申请号：US253036
申请日：1994-06-02
申请人： Wilfried Becker , Werner Grosswendt , Michael Schwenzer
发明人： Wilfried Becker , Werner Grosswendt , Michael Schwenzer
IPC分类号： F41G9/00 , F42B10/00 , F42B10/60 , F42B10/66 , F42B15/01
CPC分类号： F42B10/661
摘要： The invention relates to a device for guiding a missile (1; 30) with a missile tip (2) and a cylindrical section (3) adjoining the tip of the missile; the device is provided with at least one control block (4; 31, 32) with exhaust openings (13-15) of corresponding nozzle bodies (10-12) arranged perpendicularly in relation to the missile's surface.In order to accomplish effective guidance, particularly of high-speed missiles (1; 30), in a simple and cost-effective manner it is proposed that the control block (4; 31, 32) be constructed with a plurality of small, fast-burning rocket motors (7-9; 33-36) that are arranged radially on the missile's periphery (1; 30) and that are ignitable in a predeterminable sequence and number.
摘要翻译：本发明涉及一种引导导弹（1; 30）与导弹尖端（2）和邻接导弹尖端的圆柱形部分（3）的装置; 该装置设置有至少一个控制块（4; 31,32），其具有相对于导弹表面垂直布置的相应喷嘴体（10-12）的排气口（13-15）。为了实现特别是高速导弹（1; 30）的有效指导，以简单且具有成本效益的方式提出控制块（4; 31,32）由多个小型，快速的 - 发射火箭发动机（7-9; 33-36），其放射状地布置在导弹的周边（1; 30）上，并且以可预定的顺序和数量可点燃。

4. 发明授权

US5564651A Yaw angle free projectile 失效
标题翻译：无角自由射弹
公开(公告)号：US5564651A
公开(公告)日：1996-10-15
申请号：US391834
申请日：1989-08-04
申请人： Peter Wiemer , Werner Grosswendt
发明人： Peter Wiemer , Werner Grosswendt
IPC分类号： F41G7/00 , F42B10/02 , F42B10/28 , F42B10/62 , F42B12/04 , F42B15/00 , F42B15/01
CPC分类号： F42B10/661
摘要： A fin stabilized projectile for combatting a tank from above of the type including a rotating control unit disposed at the front of the projectile and containing a sensor for scanning the area to detect a target, and wherein the final phase of flying into the target is initiated by a force which acts on the tip of the projectile, particularly on the control unit. Since the control unit rotates relative to the warhead of the projectile to enable its sensor to detect the target, the gyro effect of this rotary movement generates pendulum movements in the projectile and thus causes deviations from the target at different target distances. To avoid yaw angles and lateral displacements of the projectile during the rotating-descending phase, a drive arrangement is provided within the projectile between the control unit and the warhead to impart an angular momentum to the warhead corresponding to the angular momentum of the control unit but directed in the opposite direction. Preferably this drive arrangement simultaneously serves as the drive for producing the rotation of the control unit.
摘要翻译：一种用于与上述类型相撞的坦克的稳定的弹丸，包括设置在射弹前部的旋转控制单元，并且包含用于扫描该区域以检测目标的传感器，并且其中启动飞入目标的最后阶段通过作用于射弹尖端的力，特别是在控制单元上。由于控制单元相对于弹丸的弹头旋转以使其传感器能够检测到目标，因此该旋转运动的陀螺效应在弹丸中产生摆动运动，从而在不同目标距离处产生与目标的偏差。为了避免在旋转下降阶段期间弹丸的偏航角度和侧向位移，在控制单元和弹头之间的射弹内提供驱动装置，以向对应于控制单元的角动量的弹头赋予角动量，但是指向相反的方向。优选地，该驱动装置同时用作用于产生控制单元的旋转的驱动器。

5. 发明授权

US4557437A Process for flight-attitude-adjustment of a flying body and/or activation of live load carried by the flying body and arrangement for carrying out the process 失效
标题翻译：用于飞行体的飞行姿态调整和/或飞行体承载的活载活动的处理和用于执行该过程的装置
公开(公告)号：US4557437A
公开(公告)日：1985-12-10
申请号：US405417
申请日：1982-08-05
申请人： Jens Seidensticker , Werner Grosswendt
发明人： Jens Seidensticker , Werner Grosswendt
IPC分类号： F41G7/20 , F41G7/34 , F42C13/06 , F41G7/00
CPC分类号： F42C13/06 , F41G7/20 , F41G7/34
摘要： A process for controlling the flight attitude of a flying body and/or the activation of a useful live load on a flying body and the arrangement for carrying out the process. At least one receiving-emitting-unit for emitting and receiving energy in the form of ultra soundwaves is first emitted in bundled form from the unit and then reflected from the region immediately adjoining the flying body, for example, the ground surface, and received by the unit, whereupon the soundwaves are converted into electrical signals. By means of time lapse measurements of the emitted and reflected soundwaves there can, for example, be measured the distance of the flying body from the ground. If the flying body deviates from a predetermined flight path, control surfaces for correcting the flight path are adjusted by control means. Moreover, by means of the receiving-emitting-unit and via the control means a useful live load can be activated.
摘要翻译：用于控制飞行体的飞行姿态和/或激活飞行体上有用的活载的过程和用于执行该过程的装置。用于发射和接收超声波形式的能量的至少一个接收发射单元首先从该单元以捆绑形式发射，然后从紧邻飞行体（例如地面）的区域反射，并由该单元，因此声波被转换成电信号。通过发射和反射的声波的时间流逝测量，可以例如测量飞行体与地面的距离。如果飞行体偏离预定的飞行路径，则通过控制装置调整用于校正飞行路径的控制面。此外，通过接收发射单元并且经由控制装置，可以激活有用的有功负载。

6. 发明授权

US5438930A Mine 失效
标题翻译：矿
公开(公告)号：US5438930A
公开(公告)日：1995-08-08
申请号：US301907
申请日：1994-09-07
申请人： Werner Grosswendt , Klaus Gersbach , Joachim Fiebrich
发明人： Werner Grosswendt , Klaus Gersbach , Joachim Fiebrich
IPC分类号： F42B5/02 , F42B12/58 , F42B23/00
CPC分类号： F42B12/58 , F42B5/02
摘要： The invention relates to a mine with at least one ejectable sub-munitions body disposed in a cup-shaped starting device and with a propulsion device for propelling the sub-munitions body into a selectable altitude range. For achieving that the propulsion device requires only a small structural volume, entails low cost because of the use of reduced amounts of propulsion charges and in addition operates safely and dependably. It has been proposed to dispose the propulsion device not in or on the sub-munitions body, but in the bottom part of the cup-shaped starting device. In this case the propulsion device advantageously consists of a high pressure chamber facing the bottom of the starting device, in which the propellant charge is contained, and of a low pressure chamber facing the sub-munitions body. The high pressure and low pressure chambers are separated from each other by a perforated plate provided with jets (holes).
摘要翻译：本发明涉及一种具有设置在杯形起动装置中的至少一个可弹出的子弹体的矿井，以及用于将子弹体推进可选择的高度范围的推进装置。为了实现推进装置仅需要小的结构体积，由于使用减少的推进装料量而需要低成本，并且另外安全可靠地运行。已经提出将推进装置配置在子弹体内或在子弹体上，而在杯形起动装置的底部。在这种情况下，推进装置有利地包括面向起动装置的底部的高压室，其中包含推进剂装料以及面向子弹体的低压室。高压和低压室通过设有喷嘴（孔）的多孔板彼此分离。

7. 发明授权

US5037040A Fin stabilized subammunition body 失效
标题翻译：鳍稳定子弹体
公开(公告)号：US5037040A
公开(公告)日：1991-08-06
申请号：US485900
申请日：1990-03-01
申请人： Gerhard Goltz , Werner Grosswendt , Helmut Peller , Jens Seidensticker
发明人： Gerhard Goltz , Werner Grosswendt , Helmut Peller , Jens Seidensticker
IPC分类号： F41G7/22 , F42B15/01
CPC分类号： F42B10/661 , F41G7/2233 , F41G7/2253 , F41G7/2293 , F42B15/01
摘要： A fin stabilized subammunition body including a target detection device and being ejectable in a target area from a spin stabilized artillery carrier projectile. The target detection device includes a fixed sensor for detecting a target and producing target signals representing characteristics of the detected target, a reference platform for producing inertial reference signals, and a controller connected to the fixed sensor and the reference platform for producing drive control signals for selectively actuating a plurality of microreaction drive mechanisms arranged for producing transverse acceleration forces for aligning the body with a detected target.
摘要翻译：一种翅片稳定的子弹体，包括目标检测装置，并且可以从旋转稳定的炮兵运载体射出在目标区域中。目标检测装置包括用于检测目标并产生表示检测到的目标的特性的目标信号的固定传感器，用于产生惯性参考信号的参考平台，以及连接到固定传感器和参考平台的控制器，用于产生用于选择性地致动多个微反应驱动机构，所述多个微反应驱动机构布置成产生横向加速力，以使主体与检测到的目标对准。

8. 发明授权

US4889053A Projectile equipped with braking parachute 失效
标题翻译：抛射体配备制动降落伞
公开(公告)号：US4889053A
公开(公告)日：1989-12-26
申请号：US272777
申请日：1988-10-17
申请人： Werner Grosswendt , Klaus Unterstein , Walter Simon
发明人： Werner Grosswendt , Klaus Unterstein , Walter Simon
IPC分类号： F42B10/56
CPC分类号： F42B10/56
摘要： The invention relates to a projectile including a cylindrical receiving chamber (4) delimited by an interior wall (3) for a braking parachute (17) which can be ejected by way of a piston (9) that is longitudinally displaceable in the projectile, with the piston (9) being chargeable by an ignitable pyrotechnic charge (10). The braking parachute (17) is encased in a longitudinally divided sleeve (18) one side of which is in engagement with the piston (9). In order to completely or partially recover the projectile and not to impede deployment of the braking parachute (17), it is provided that the rear of the receiving chamber (4) is sealed by a cover (23) which can be ejected by way of the piston (9), is equipped with a rotational imbalance (26) and is in engagement with the other side of the sleeve (18). The braking parachute (17) is fastened to the piston (9). The projectile or a part (1) thereof connected with projectile components to be recovered is provided with a catch ring (21) disposed at the rear exit end of the receiving chamber (4) for the piston (9). The sleeve (18) is able to pass through the catch ring. Guides (19, 28) for the sleeve (18) are provided at the interior wall (3) of the receiving chamber (4).
摘要翻译： PCT No.PCT / EP88 / 00022 Sec。 371日期：1988年10月17日 102（e）日期1988年10月17日PCT提交1988年1月14日PCT公布。出版物WO88 / 06267 日本1988年8月25日。本发明涉及一种抛射物，其包括由用于制动降落伞（17）的内壁（3）限定的圆柱形容纳室（4），其可以通过活塞（9）可在弹丸中纵向移动，活塞（9）可由点燃的烟火充电（10）充电。制动降落伞（17）被封装在纵向分开的套筒（18）中，其一侧与活塞（9）接合。为了完全或部分地回收抛射物并且不妨碍制动降落伞（17）的部署，设置接收室（4）的后部由盖（23）密封，盖（23）可以通过活塞（9）配备有旋转不平衡部（26）并且与套筒（18）的另一侧接合。制动降落伞（17）固定在活塞（9）上。与要回收的射弹部件连接的射弹或其部分（1）设置有设置在用于活塞（9）的接收室（4）的后出口端的卡环（21）。套筒（18）能够穿过卡环。用于套筒（18）的导向件（19,28）设置在容纳室（4）的内壁（3）处。

9. 发明授权

US5275355A Antitank weapon for combating a tank from the top 失效
标题翻译：反坦克武器从顶部打一个坦克
公开(公告)号：US5275355A
公开(公告)日：1994-01-04
申请号：US18567
申请日：1987-02-04
申请人： Werner Grosswendt , Gerhard Glotz , Helmut Peller
发明人： Werner Grosswendt , Gerhard Glotz , Helmut Peller
IPC分类号： F42B12/10 , F42B15/00 , F42B10/66 , F42B12/16
CPC分类号： F42B12/10 , F42B10/661 , F42B15/00
摘要： A projectile for a surface-to-surface weapon to combat a target from the top. The projectile includes a warhead; a propulsion system for accelerating the projectile directly after the projectile is placed in flight; a stabilizing guide assembly; a sensor for detecting a target in a longitudinal and lateral direction; and a pulse generator for turning the projectile about its center of gravity. The projectile additionally includes electronics for activating the warhead and for controlling the propulsion system and the pulse generator. A control unit rotates independently of the shaped charge warhead and houses the sensor, pulse generator and electronics. The pulse generator is arranged offset with respect to the sensor in the circumferential direction of the control unit. The electronics actuates the pulse generator in response to the sensor detecting a target, at a given distance ahead of such target, to produce a measured and radially directed control pulse to pivot the projectile so that it is aimed directly at the top of the target. The propulsion system additionally includes a drive assembly which is fired to accelerate the projectile toward a target, immediately after the projectile has been pivoted toward the target by the pulse generator. A mechanism is provided for preventing a restoring force generated by the ambient air from returning the projectile to the direction of flight existing prior to being pivoted.
摘要翻译：一种用于从顶部对抗目标的地面武器的射弹。射弹包括弹头; 在抛射体飞行后直接加速射弹的推进系统; 稳定导向组件; 用于在纵向和横向方向上检测目标的传感器; 以及用于围绕其重心转动射弹的脉冲发生器。弹头还包括用于激活弹头和用于控制推进系统和脉冲发生器的电子装置。控制单元独立于成形的充电弹头旋转，并容纳传感器，脉冲发生器和电子设备。脉冲发生器在控制单元的圆周方向上相对于传感器偏移地布置。电子装置响应于传感器检测目标，在该目标之前的给定距离处起动脉冲发生器，以产生测量和径向定向的控制脉冲以使射弹枢转，使其直接瞄准目标的顶部。推进系统另外包括一个驱动组件，该驱动组件在射弹已经被脉冲发生器枢转到目标物之后立即被发射以将射弹加速到目标。提供了一种用于防止环境空气产生的恢复力使弹丸返回到在枢转之前存在的飞行方向的机构。

10. 发明授权

US4889030A Projectile equipped with deployable parachute 失效
标题翻译：弹药装备有可部署的降落伞
公开(公告)号：US4889030A
公开(公告)日：1989-12-26
申请号：US254680
申请日：1988-09-22
申请人： Werner Grosswendt , Klaus Unterstein
发明人： Werner Grosswendt , Klaus Unterstein
IPC分类号： F42B10/56 , F42B15/36
CPC分类号： F42B15/36 , F42B10/56
摘要： A projectile has at two parts (3, 4) axially arranged one behind the other and mutually linked, of which at least one contains a deployable parachute (6, 6'). In order to achieve a design that ensures a smooth and reliable separation of the parts (3, 4), followed by the deployment of the parachute (6, 6'), both parts (3, 4) are mutually linked by radial bolts (19) that can be radially actuated by the gas pressure generated by at least one pyrotechnic load (15) and radially moved by the gas pressure, thus separating the two parts (3, 4). The pyrotechnic load (15) can be ignited by a fuse (9).
摘要翻译： PCT No.PCT / EP87 / 00674 Sec。 371日期：1988年9月22日 102（e）1988年9月22日PCT PCT日期：1987年11月5日PCT公布。出版物WO88 / 05523 日期：1988年7月28日。射弹具有两个部分（3,4），轴向布置在彼此之间并相互连接，其中至少一个包含可展开的降落伞（6,6'）。为了实现确保部件（3,4）平滑可靠分离的设计，随后部署降落伞（6,6'），两个部件（3,4）都通过径向螺栓（ 19），其可以由至少一个烟火负载（15）产生的气体压力并由气体压力径向移动，从而分离两个部分（3,4）。烟火负载（15）可以被保险丝（9）点燃。

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