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    Hanger assembly for missiles
    2.
    发明授权
    Hanger assembly for missiles 失效
    导弹用吊架总成

    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。

    Tube connection in particular for connecting two tubular elements of the airframe of a missile
    3.
    发明授权
    Tube connection in particular for connecting two tubular elements of the airframe of a missile 失效
    管连接，特别用于连接导弹的机身的两个管状元件

    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。

    Missile head and method for separating a shroud from a fuselage of a missile
    4.
    发明授权
    Missile head and method for separating a shroud from a fuselage of a missile 有权
    导弹头和将导弹从导弹的机身分离的方法

    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。

    MISSILE HEAD AND METHOD FOR SEPARATING A SHROUD FROM A FUSELAGE OF A MISSILE
    5.
    发明申请
    MISSILE HEAD AND METHOD FOR SEPARATING A SHROUD FROM A FUSELAGE OF A MISSILE 有权
    用于从一个故障的分配中分离一个裂缝的头部和方法

    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。

    Tube connection, in particular, for connecting two tubular fuselage portions of a missile
    7.
    发明授权
    Tube connection, in particular, for connecting two tubular fuselage portions of a missile 有权
    管连接，特别是用于连接导弹的两个管状机身部分

    公开(公告)号：US6098928A

    公开(公告)日：2000-08-08

    申请号：US132263

    申请日：1998-08-11

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

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

    IPC分类号： F42B15/36 ,  B64C1/14

    CPC分类号： F42B15/36

    摘要： A connection is described for connecting two tubular fuselage portions of a missile. The inner diameter of the rim of a first tubular fuselage portion to be connected with a second tubular fuselage portion corresponds to the outer diameter of the rim of the second tubular fuselage portion to be connected to the first tubular fuselage portion, deducting a jointing tolerance, The rims of the tubular fuselage portion to be connected are provided with radial bores to accommodate connection screws, Clamp segments are mounted in the second tubular fuselage portion along the inner circumference thereof. The clamp segments define threaded bores, connection screws being screwed into these threaded bores.

    摘要翻译： 描述了用于连接导弹的两个管状机身部分的连接。 与第二管状机身部分连接的第一管状机身部分的边缘的内径对应于要连接到第一管状机身部分的第二管状机身部分的边缘的外径，减去接合公差， 要连接的管状机身部分的边缘设置有径向孔以容纳连接螺钉，夹紧段沿其内圆周安装在第二管状机身部分中。 夹紧段限定螺纹孔，连接螺钉拧入这些螺纹孔中。