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1. 发明申请

WO0000781A9 MISSILE FOR COMBATING STATIONARY AND/OR MOVING TARGETS 审中-公开
标题翻译：导弹袭击了固定和/或运动目标
公开(公告)号：WO0000781A9
公开(公告)日：2000-08-03
申请号：PCT/DE9901863
申请日：1999-06-25
申请人： LFK GMBH , GAUGGEL ROLAND , ARNOLD MICHAEL , KRUEGER REINHARD , TRAENAPP NORBERT
发明人： GAUGGEL ROLAND , ARNOLD MICHAEL , KRUEGER REINHARD , TRAENAPP NORBERT
IPC分类号： F42B15/36
CPC分类号： F42B15/36
摘要： The invention relates to a missile for combating stationary and/or moving targets comprising a seeker head (100), an effective charge which is arranged behind said seeker head in the direction of flight, a thruster such as a solid fuel booster having lateral outlet nozzles which is arranged behind the effective charge in the direction of flight, and a guiding section (104) which is arranged behind the thruster in the direction of flight. The guiding section comprises controllable aerofoils (105a, 105b) such as lateral and/or tail fins, and a guiding device. The missile also comprises a cruise engine (107) which is arranged on the tail, whereby the cruise engine is detachably connected to the guiding section by means of a first quick-acting closure (109a, 109b) such as a manually operable bayonet closure or the like. At least one auxiliary thruster (108), if required, can be mounted between the guiding section and the cruise engine by means of a second quick-acting closure such as a manually operable bayonet closure or the like.
摘要翻译：本发明涉及一种导弹用于与扫描头（100），一个设置在飞行方向后面的活性电荷，设置在的活性电荷发动机，后面飞行方向如带有侧向出口喷嘴的固体起动发动机的汽缸，一个在后面在飞行方向打击静止和/或移动目标布置成将发动机的转向部分（104），所述可控转向节翼（105A，105B），侧向和/或后部的航班，和转向装置具有，和，布置在后巡航发动机（107），其中，所述巡航发动机（由第一速效封闭的手段 109A，109B被连接），例如手动操作的卡口式连接或可释放地连接到转向部等; 并且可以通过第二速效闭合的装置中使用，所有的手动操作的卡口式连接或转向部分，并根据需要在巡航发动机之间等，至少一个推进器（108）。

2. 发明申请

WO0000779B1 METHOD FOR REMOTE CONTROLLED COMBAT OF NEAR-SURFACE AND/OR SURFACE TARGETS 审中-公开
标题翻译：遥控地面和/或土壤目标的方法
公开(公告)号：WO0000779B1
公开(公告)日：2000-04-27
申请号：PCT/DE9901862
申请日：1999-06-25
申请人： LFK GMBH , GAUGGEL ROLAND , ARNOLD MICHAEL , KRUEGER REINHARD , TRAENAPP NORBERT
发明人： GAUGGEL ROLAND , ARNOLD MICHAEL , KRUEGER REINHARD , TRAENAPP NORBERT
IPC分类号： F41G7/22 , F42B15/01
CPC分类号： F41G7/2206 , F41G3/02 , F41G3/165
摘要： The invention relates to a method for combating near-surface and/or surface targets such as tanks or the like by using a missile comprising a seeker head, an effective charge and at least one thruster. According to the invention, the missile is redirected into an essentially horizontal cruising and seeking phase after completing an essentially vertical start phase. During said cruising and seeking phase, the missile scans the terrain ahead of it using the seeking head, whereupon an approaching phase which is directed in an essentially downward direction follows after the finally ensues head locks onto an identified target. An external reconnaissance system in an appropriate aircraft and/or spacecraft such as in a helicopter, a drone or in a satellite receives information for guiding the missile which is transmitted to the same.
摘要翻译：本发明涉及防治地面和/或基于地面的目标，如罐或类似物，由寻的头，有源电荷和至少一个具有导弹发动机，的装置的方法，其中所述的导弹，一个基本垂直的起始阶段之后，在大致水平的Marsch- 和搜索阶段被偏转，其中，导弹由搜索头，于是，最后，随后基本上向下指向的进场阶段施加搜索头检测到的目标，其中，在一个合适的空气的外部侦察系统之后和/手段他之前扫描场或者诸如直升机，无人机或卫星的航天器接收关于导弹传输到导弹的导向的信息。

3. 发明申请

WO2012130211A4 RADIATING ELEMENT FOR FOCUSSED ENERGY 审中-公开
标题翻译：斯特拉尔直接能源
公开(公告)号：WO2012130211A4
公开(公告)日：2012-12-06
申请号：PCT/DE2012000288
申请日：2012-03-16
申请人： LFK GMBH , GEIDEK FRANZ , PROTZ RUDOLF , ZOZ JUERGEN , NISSL NORBERT
发明人： GEIDEK FRANZ , PROTZ RUDOLF , ZOZ JUERGEN , NISSL NORBERT
IPC分类号： F41H13/00 , B23K26/06 , G02B27/14
CPC分类号： F21V7/0025 , B23K26/0608 , F21V7/06 , F41H13/0062 , G02B27/14 , G02B27/143 , H01S3/005
摘要： The invention relates to a radiating element (1) for focussed energy, comprising a device for coupling in rays from at least one beam generator (34) and a beam combining device (1'), which merges the beams to combined beams, wherein the beam combining device (1') comprises a telescopic lens having a collimation mirror (2) and a secondary mirror (3) and the device for receiving directed rays from a plurality of light guide devices (35) is formed from the at least one beam generator (34).
摘要翻译：这是一个散热器（1）设置有用于从所述至少一个辐射发生器（34）辐射的耦合定向能量和光束组合装置（1“），它结合了光束组合成组合光束，其中所述光束组合装置（1）的伸缩光纤与准直镜（2）和捕捉镜（3）以及用于接收来自多个光导装置（35）的定向光束的装置由至少一个光束发生器（34）形成。

4. 发明申请

WO2009015649A3 SIGHT 审中-公开
公开(公告)号：WO2009015649A3
公开(公告)日：2009-04-02
申请号：PCT/DE2008001235
申请日：2008-07-26
申请人： LFK GMBH , RUEGER RODERICH
发明人： RUEGER RODERICH
IPC分类号： F41G3/32
CPC分类号： F41G3/326 , F41G3/165 , F41G7/303
摘要： The arrangement according to the invention allows adjustment-free axis harmonization even in spatially highly confined sight housings, by the omission of a central spectrally acting beam splitter.
摘要翻译：根据本发明的装置通过消除中央光谱有效分束器，即使在空间狭窄的遮阳壳体中也允许无调节的Achsharmonisierung。

5. 发明申请

WO0036361B1 HYDRAULIC MANIPULATOR 审中-公开
标题翻译：液压机械手
公开(公告)号：WO0036361B1
公开(公告)日：2000-07-27
申请号：PCT/DE9903887
申请日：1999-12-03
申请人： LFK GMBH , BAUMGARTEN KLAUS
发明人： BAUMGARTEN KLAUS
IPC分类号： F15B7/00 , F15B7/10 , F41F3/052 , F41A27/26 , F41G5/04
CPC分类号： F15B7/10 , F15B7/006 , F41F3/052
摘要： The aim of the invention is to create a cost-effective hydraulic manipulator which can be ergonomically handled and which has a good response characteristic. To this end, the drive element of the manipulator is embodied as a hydraulic pump (2) with two directions of delivery and the drive movement is introduced as a rotational movement on the drive shaft (29) of the hydraulic pump. Losses of liquid due to leakage are compensated for by means of hydraulic accumulators (12, 19) or by spring-loading (15) one side of the double cylinder (9) or of the divided piston (18).
摘要翻译：本发明的目的是提供一种廉价的液压机械手，其具有符合人体工程学的操作和良好的转印特性。该目的创造性地实现，即，操纵器的驱动元件是一个液压泵（2）与两个输送方向上，并且其相对于液压泵的驱动轴（29）驱动运动被引入作为一个旋转运动。通过液压蓄能器（12，19）的装置或由双气缸（9）或分开的活塞（18）的一侧上的弹簧加载（15）的流体损失，由于泄漏被补偿。

6. 发明申请

WO0000781B1 MISSILE FOR COMBATING STATIONARY AND/OR MOVING TARGETS 审中-公开
标题翻译：用于打击固定和/或便携式目标的飞机
公开(公告)号：WO0000781B1
公开(公告)日：2000-02-24
申请号：PCT/DE9901863
申请日：1999-06-25
申请人： LFK GMBH , GAUGGEL ROLAND , ARNOLD MICHAEL , KRUEGER REINHARD , TRAENAPP NORBERT
发明人： GAUGGEL ROLAND , ARNOLD MICHAEL , KRUEGER REINHARD , TRAENAPP NORBERT
IPC分类号： F42B15/36
CPC分类号： F42B15/36
摘要： The invention relates to a missile for combating stationary and/or moving targets comprising a seeker head (100), an effective charge which is arranged behind said seeker head in the direction of flight, a thruster such as a solid fuel booster having lateral outlet nozzles which is arranged behind the effective charge in the direction of flight, and a guiding section (104) which is arranged behind the thruster in the direction of flight. The guiding section comprises controllable aerofoils (105a, 105b) such as lateral and/or tail fins, and a guiding device. The missile also comprises a cruise engine (107) which is arranged on the tail, whereby the cruise engine is detachably connected to the guiding section by means of a first quick-acting closure (109a, 109b) such as a manually operable bayonet closure or the like. At least one auxiliary thruster (108), if required, can be mounted between the guiding section and the cruise engine by means of a second quick-acting closure such as a manually operable bayonet closure or the like.
摘要翻译：本发明涉及一种导弹用于与扫描头（100），一个设置在飞行方向后面的活性电荷，设置在的活性电荷发动机，后面飞行方向如带有侧向出口喷嘴的固体起动发动机的汽缸，一个在后面在飞行方向打击静止和/或移动目标布置成将发动机的转向部分（104），所述可控转向节翼（105A，105B），侧向和/或后部的航班，和转向装置具有，和，布置在后巡航发动机（107），其中，所述巡航发动机（由第一速效封闭的手段（例如手动操作的卡口卡扣等）可释放地连接到转向部分; 并且可以通过第二速效闭合的装置中使用，所有的手动操作的卡口式连接或转向部分，并根据需要在巡航发动机之间等，至少一个推进器（108）。

7. 发明申请

WO2010031377A3 FLYING OBJECT COMPRISING AT LEAST ONE BRAKE PARACHUTE AND FIXING DEVICE FOR FIXING A BRAKE PARACHUTE TO A FLYING OBJECT 审中-公开
标题翻译：与至少一个制动伞的导弹和固定装置，用于固定漏斗形减速伞IN A导弹
公开(公告)号：WO2010031377A3
公开(公告)日：2010-06-10
申请号：PCT/DE2009001240
申请日：2009-09-03
申请人： LFK GMBH , FASOL DIETER , GRABMEIER MICHAEL
发明人： FASOL DIETER , GRABMEIER MICHAEL
IPC分类号： B64D17/80 , B64D17/38 , F16B31/00 , F42B10/56
CPC分类号： F42B10/56 , F16B31/007
摘要： The invention relates to a flying object comprising at least one brake parachute (2), said flying object (1; 1') being provided with at least one fixing device (3; 3', 3") for the brake parachute (2) and with a drag line (4) between the fixing device (3; 31, 3") and the brake parachute (2). The object is characterised in that the fixing device (3; 3', 3") is attached to the flying object (1; 1') in such a way that when the brake parachute (2) is open and filled with air, the imaginary extension (G) of the straight line formed by the drag line (4) runs through the centre of gravity (S) of said flying object (1; 11).
摘要翻译：具有至少一个漏斗形减速伞（2），其中，所述导弹（1; 1“）一种导弹与至少一个紧固装置（3; 3”，3“），用于制动降落伞（2）的固定装置（3之间，并且其中; 3' ，3“）和制动降落伞（2）一个拉绳（4）设置，其特征在于，所述固定装置（3; 3”，3" ，在这样的方式）上的导弹（1; 1' ）被安装在通过导弹的比重（S）的中心在它的假想延长（G）的线（4）刚刚形成的线的空气制动降落伞（2）的入射流量的展开状态（1; 11）。

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