Bodenseewerk Geratetechnik Gmbh

Diehl Bgt Defence Gmbh Co., Kg

Diehl Defence Gmbh & Co. Kg

Peter Gerd Fisch

Dirk Bross

Klaus-Dieter Knapp

Michael Gross

Hans Kordulla

Jörg Baumgart

Gerd Elsner

Dominik Herrmann

Peter Mangold

Bernd Lindenau

Siegfried Bosch

Alexander Stengele

Gerald Rieger

Anton Dittler

Alfred Gaiser

Hans-Georg Marquardt

Klaus Tondok

Roland Waschke

Thomas Betz

Ulrich Hochstein

Ferdinand Solfrank

Stefan Höhn

Michael Groß

Klaus Fischer

Ingo Weltin

Patrick Reis

Jakob Roth

Martin Walzer

René Freter

Tobias Korthals

Rainer Hezel

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.

Missile head and method for separating a shroud from a fuselage of a missile

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.

Guided missile

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

Jettisonable nosecone and missile with a jettisonable nosecone

A method for producing a mirror () 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 () is made from a titanium-based material having a shape accuracy and a surface roughness in the submicrometer region, whose basic shape () has a has a reflecting surface () having a surface roughness of less than 60 nm, and in particular of less than 30 nm.

Method for producing a mirror from a titanium-based material, and a mirror made from such a material

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.

Composite window transparent to electromagnetic radiation for use in supersonic and hypersonic target-tracking missiles

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.

Tube connection, in particular, for connecting two tubular fuselage

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.

Hanger assembly for missiles

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.

Tube connection in particular for connecting two tubular elements of the

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.

Hanger for a missile in a launcher

A connecting assembly serves for connecting a dome covering a seeker head with the structure of a missile. A holding ring extends over the rim of said dome, positively holding this dome and connected with the structure of the missile. An annular recess is provided underneath the holding ring along the rim of the dome. This recess contains a flexible sealing substance for establishing a seal between the holding ring and the dome. It is important, that no additional material bonding such as cementing or soldering is provided between the dome and the holding ring.

Connecting device for the dome of a missile

Growing community of inventors

Überlingen, Germany

Peter Gerd Fisch