公开(公告)号：US08505455B2

公开(公告)日：2013-08-13

申请号：US13021879

申请日：2011-02-07

申请人： Peter Gerd Fisch ,  Dirk Bross ,  Dominik Herrmann ,  Peter Mangold

发明人： Peter Gerd Fisch ,  Dirk Bross ,  Dominik Herrmann ,  Peter Mangold

IPC分类号： F42B15/10

CPC分类号： F42B15/36 ,  F42B10/46

摘要： A missile head has a shroud which forms its tip and which can be detached in its totality during flight from the fuselage of the missile. The missile head further has a rear part, which is connected to the fuselage, and a front nose, which can be disconnected from the rear part and forms the tip. A separating device separates the rear part from the fuselage and the nose from the rear part during flight. A physically small shroud can be achieved, and damage to the fuselage of the missile by separation of the shroud can be prevented, if the nose is split into at least two parts and the separating device is prepared to split the nose into these two parts during flight.

摘要翻译： 导弹头有一个形成其尖端的护罩，并且可以在从导弹的机身飞行中全部分离。 导弹头还具有连接到机身的后部和前部鼻部，其可以与后部分离并形成尖端。 分离装置在飞行期间将后部与机身和鼻部分离后部。 可以实现物理上的小护罩，并且如果鼻子分成至少两个部分，并且分离装置准备将鼻子分成这两个部分，则可以防止通过分离护罩来损坏导弹的机身 飞行。

公开(公告)号：US20110192308A1

公开(公告)日：2011-08-11

申请号：US13021879

申请日：2011-02-07

申请人： Peter Gerd Fisch ,  Dirk Bross ,  Dominik Herrmann ,  Peter Mangold

发明人： Peter Gerd Fisch ,  Dirk Bross ,  Dominik Herrmann ,  Peter Mangold

IPC分类号： F42B15/00

CPC分类号： F42B15/36 ,  F42B10/46

摘要： A missile head has a shroud which forms its tip and which can be detached in its totality during flight from the fuselage of the missile. The missile head further has a rear part, which is connected to the fuselage, and a front nose, which can be disconnected from the rear part and forms the tip. A separating device separates the rear part from the fuselage and the nose from the rear part during flight. A physically small shroud can be achieved, and damage to the fuselage of the missile by separation of the shroud can be prevented, if the nose is split into at least two parts and the separating device is prepared to split the nose into these two parts during flight.

摘要翻译： 导弹头有一个形成其尖端的护罩，并且可以在从导弹的机身飞行中全部分离。 导弹头还具有连接到机身的后部和前部鼻部，其可以与后部分离并形成尖端。 分离装置在飞行期间将后部与机身和鼻部分离后部。 可以实现物理上的小护罩，并且如果鼻子分成至少两个部分，并且分离装置准备将鼻子分成这两个部分，则可以防止通过分离护罩来损坏导弹的机身 飞行。

公开(公告)号：US07476145B2

公开(公告)日：2009-01-13

申请号：US11233425

申请日：2005-09-22

申请人： Hans-Georg Marquardt ,  Klaus-Dieter Knapp ,  Alfred Gaiser ,  Peter Gerd Fisch ,  Anton Dittler ,  Dirk Bross ,  Thomas Betz ,  Jörg Baumgart

发明人： Hans-Georg Marquardt ,  Klaus-Dieter Knapp ,  Alfred Gaiser ,  Peter Gerd Fisch ,  Anton Dittler ,  Dirk Bross ,  Thomas Betz ,  Jörg Baumgart

IPC分类号： G02B5/10 ,  B24B1/00

CPC分类号： B24B13/015 ,  Y10T428/12993

摘要： A method for producing a mirror (10) from a titanium-based material by using the technique of ultraprecision machining. The mirror produced using this method has both a shape accuracy and a surface roughness in the submicrometer region. The mirror (10) is made from a titanium-based material having a shape accuracy and a surface roughness in the submicrometer region, whose basic shape (11) has a has a reflecting surface (12) having a surface roughness of less than 60 nm, and in particular of less than 30 nm.

摘要翻译： 一种使用超精密加工技术从钛基材料制造反射镜（10）的方法。 使用该方法制造的反射镜在亚微米区域中具有形状精度和表面粗糙度。 反射镜（10）由具有形状精度和亚微米区域中的表面粗糙度的钛基材料制成，其基本形状（11）具有具有表面粗糙度小于60nm的反射表面（12） ，特别是小于30nm。

公开(公告)号：US5970842A

公开(公告)日：1999-10-26

申请号：US58216

申请日：1998-04-10

申请人： Klaus-Dieter Knapp ,  Peter Gerd Fisch ,  Dirk Bross

发明人： Klaus-Dieter Knapp ,  Peter Gerd Fisch ,  Dirk Bross

IPC分类号： B64D1/04 ,  B64D7/08 ,  F41F3/04 ,  F41F3/06

CPC分类号： B64D1/04 ,  B64D7/08 ,  F41F3/0406

摘要： A hanger assembly for missiles, in which a hanger, with opposite carrying rails to guide the missile in a launcher, is connected to the missile by means of a screwed connection. The hanger is screwed from the outside, with screws to a enlargement or increased thickness portion (16,60). Preferably a clamp, provided with a enlargement or increased thickness portion surrounds the airframe (Zelle) of the missile and is fixed thereto. The screw connection of the hanger is effected with screws the axes of which form an angle with the plane of the carrying rails.

摘要翻译： 用于导弹的吊架组件，其中具有相对的承载导轨以将导弹引导到发射器中的悬挂架通过螺纹连接连接到导弹。 衣架从外部拧紧，用螺钉拧紧，以扩大或增加厚度部分（16,60）。 优选地，设置有放大或增加的厚度部分的夹具围绕导弹的机身（Zelle）并且固定到其上。 悬挂器的螺钉连接通过其轴线与承载轨道的平面形成一角度的螺钉来实现。

公开(公告)号：US5876072A

公开(公告)日：1999-03-02

申请号：US845028

申请日：1997-04-21

申请人： Dirk Bross ,  Peter Gerd Fisch

发明人： Dirk Bross ,  Peter Gerd Fisch

IPC分类号： F16L23/00 ,  F16L23/04 ,  F16L25/00 ,  B64C1/00

CPC分类号： F16L21/06 ,  F16L21/08 ,  F16L23/00 ,  F16L23/04 ,  Y10S285/913

摘要： In a tube connection, particularly for connecting two tubular elements of the airframe of a substantially tubular a missile, the tubular elements to be interconnected have end portions of substantially identical shapes. Each end portion has a smaller-diameter first circumferential section extending through substantially 180.degree. and a larger-diameter second circumferential section also extending through substantially 180.degree.. The larger-diameter circumferential section of each tubular element overlies the smaller-diameter circumferential section of the other tubular element. The circumferential sections are provided with radial bores for connection screws. Arcuate elements having threaded bores are arranged inside the thus interconnected circumferential sections. These threaded bores are aligned with the radial bores of the circumferential sections and threadedly receive the connecting screws.

摘要翻译： 在管连接中，特别是用于连接基本上管状的导弹的机身的两个管状元件，要互连的管状元件具有基本相同形状的端部。 每个端部具有延伸大致180°的较小直径的第一圆周部分和也大致延伸大致180°的较大直径的第二圆周部分。 每个管状元件的较大直径圆周部分覆盖在另一个管状元件的较小直径圆周部分上。 周向部分设有用于连接螺钉的径向孔。 具有螺纹孔的弧形元件布置在这样相互连接的圆周部分的内部。 这些螺纹孔与周向部分的径向孔对齐并且螺纹地接收连接螺钉。

公开(公告)号：US07661625B2

公开(公告)日：2010-02-16

申请号：US11438825

申请日：2006-05-23

申请人： Gerald Rieger ,  Roland Waschke ,  Gerd Elsner ,  Klaus Tondok ,  Peter Gerd Fisch

发明人： Gerald Rieger ,  Roland Waschke ,  Gerd Elsner ,  Klaus Tondok ,  Peter Gerd Fisch

IPC分类号： F42B15/36 ,  F42B15/10

CPC分类号： F42B10/46 ,  F42B15/36

摘要： A jettisonable nosecone (10) for a missile is specified, which nosecone (10) is longitudinally split into at least two parts (15, 16) and is held together by detachable connecting structures, in which case the connecting structures are designed to actively move the at least two parts (15, 16) away from one another when released. A missile having a correspondingly designed nosecone (10) is also provided. A nosecone (10) of this type allows simple jettisoning during every flight phase of the missile, and is also suitable for retrofitting to an already existing missile.

摘要翻译： 规定了用于导弹的可抛弃的十字头（10），其中鼻锥（10）纵向分成至少两个部分（15,16），并通过可拆卸的连接结构保持在一起，在这种情况下，连接结构被设计成主动移动 所述至少两个部分（15,16）在释放时彼此远离。 还提供了具有相应设计的鼻锥（10）的导弹。 这种类型的十字头（10）在导弹的每个飞行阶段都允许简单的放弃，也适用于已经存在的导弹的改装。

公开(公告)号：US06273362B1

公开(公告)日：2001-08-14

申请号：US09360758

申请日：1999-07-26

申请人： Peter Gerd Fisch ,  Siegfried Bosch

发明人： Peter Gerd Fisch ,  Siegfried Bosch

IPC分类号： F41G700

CPC分类号： F42B10/46 ,  F42B15/34 ,  H01Q1/28 ,  H01Q1/422

摘要： The invention relates to a window for use in a supersonic or hypersonic target-tracking missile, the window being transparent to electromagnetic radiation. The window consist of several window layers which support each other and which are commonly supported, wherein the materials, the thickness and the arrangement of said window layers are selected to reduce mechanical stresses due to temperature during supersonic or hypersonic flight as compared to a continuously homogeneous window. In one embodiment the window layers are fixedly interconnected with their surfaces facing each other and consist of materials having different thermal coefficients of dilatation such that, with the temperature gradient occurring in said window during supersonic or hypersonic flight, substantially identical thermal dilatations are achieved in each of said window layers. A further measure is to provide a slip or lubricant layer between the window layers, which slip or lubricant layer allows a relative motion of the window layers parallel to the surfaces facing each other, thereby reducing transmission of stresses between the window layers.

摘要翻译： 本发明涉及一种用于超音速或超音速目标跟踪导弹的窗口，该窗口对于电磁辐射是透明的。 窗口由几个相互支撑并且通常被支撑的窗口层组成，其中选择所述窗口层的材料，厚度和布置以减少由于超音速或超音速飞行期间的温度而导致的机械应力，与连续均匀的 窗口。 在一个实施例中，窗口层彼此面对的固定地互连，并由具有不同热膨胀系数的材料构成，使得随着在超音速或超音速飞行期间在所述窗口中发生的温度梯度，在每一个实现相同的热膨胀 的所述窗口层。 进一步的措施是在窗口层之间提供滑动或润滑剂层，其滑动或润滑剂层允许窗口层相对于彼此面对的表面的相对运动，从而减少窗口层之间的应力传递。

公开(公告)号：US20090230234A1

公开(公告)日：2009-09-17

申请号：US12402523

申请日：2009-03-12

申请人： Peter Gerd Fisch ,  Michael Gross

发明人： Peter Gerd Fisch ,  Michael Gross

IPC分类号： F41G7/00 ,  F42B17/00 ,  F42B15/00

CPC分类号： F42B15/10

摘要： A guided missile has a sensor unit, a propulsion unit, and a payload unit. A missile casing forms the outer contour, extends along a longitudinal direction, and accommodates the sensor unit, the propulsion unit, and the payload unit. At least two of the units can be fitted alongside one another in the longitudinal direction. In comparison to conventional guided missiles, the guided missile is distinguished by increased modularity and thus by increased flexibility with regard to different operational scenarios.

摘要翻译： 导弹具有传感器单元，推进单元和有效载荷单元。 导弹套管形成外轮廓，沿纵向方向延伸，并容纳传感器单元，推进单元和有效载荷单元。 至少两个单元可以沿纵向彼此并排安装。 与传统的导弹相比，导弹的区别在于模块化程度的提高，从而在不同的作战场景下增加灵活性。

公开(公告)号：US5831200A

公开(公告)日：1998-11-03

申请号：US780277

申请日：1997-01-09

申请人： Peter Gerd Fisch

发明人： Peter Gerd Fisch

IPC分类号： B64D7/08 ,  F42B15/00 ,  F41F5/00 ,  F41F7/00

CPC分类号： F42B15/00 ,  B64D7/08

摘要： A hanger of steel for guiding a missile in a launcher has arcuate flanges matching the shape of the missile an a guiding element of substantially T-shaped cross section. A longitudinal recess is defined on the outer side of the transverse bar of the "T". The surfaces of the transverse bar facing the flanges define rest surfaces and the adjacent lateral surfaces of the vertikal bar of the "T" serve as lateral guiding surfaces for the missile. A longitudinal, rounded recess is provided between each of the lateral surfaces and the adjacent rest surface, in order to increase the notch radius. The surface of the material is treated to generate internal compressive stress in the regions of the recesses.

摘要翻译： 用于在发射器中引导导弹的钢吊架具有与导弹的形状匹配的弧形法兰，具有基本上T形横截面的引导元件。 纵向凹槽限定在“T”横向杆的外侧。 面向凸缘的横向杆的表面限定了搁置表面，“T”的垂直杆的相邻侧面用作导弹的侧向引导表面。 为了增加切口半径，在每个侧表面和相邻的搁置表面之间提供纵向圆形凹槽。 处理材料的表面以在凹部的区域中产生内部压缩应力。

公开(公告)号：US07893390B2

公开(公告)日：2011-02-22

申请号：US12402523

申请日：2009-03-12

申请人： Peter Gerd Fisch ,  Michael Gross

发明人： Peter Gerd Fisch ,  Michael Gross

IPC分类号： B64C1/00 ,  F42B15/00 ,  B64G1/22 ,  F41G7/00

CPC分类号： F42B15/10

摘要： A guided missile has a sensor unit, a propulsion unit, and a payload unit. A missile casing forms the outer contour, extends along a longitudinal direction, and accommodates the sensor unit, the propulsion unit, and the payload unit. At least two of the units can be fitted alongside one another in the longitudinal direction. In comparison to conventional guided missiles, the guided missile is distinguished by increased modularity and thus by increased flexibility with regard to different operational scenarios.

摘要翻译： 导弹具有传感器单元，推进单元和有效载荷单元。 导弹套管形成外轮廓，沿纵向方向延伸，并容纳传感器单元，推进单元和有效载荷单元。 至少两个单元可以沿纵向彼此并排安装。 与传统的导弹相比，导弹的区别在于模块化程度的提高，从而在不同的作战场景下增加灵活性。