Rheinmetall Gmbh

Tzn Forschungs- Und Entwicklungszentrum Unterluss Gmbh

Rheinmetall Industrie Gmbh

Other

Rheinmetall W & M Gmbh

Firma Rheinmetall Gmbh

Rudolf Romer

Bernhard Bisping

Christian Jaeneke

Klaus Gersbach

Peter Wallow

Karl W Bethmann

Manfred Moll

Gerd Wollmann

Walter Simon

Jurgen Winkelmann

Helmut Misoph

Hans W Luther

Michael Schwenzer

Hendrik R Lips

Hans Orth

Reinhard Synofzik

Benjamin Furch

Rolf Hellwig

Horst Sabinski

Dietmar Karius

Juergen Boecker

Jurgen Boecker

Reinhart Fuchs

Hans-Egon Schepp

Winfried Rossmann

Wilfried Becker

Gunter Sikorski

Dieter Boeder

Klaus W Klein

Juergen Winkelmann

Raimund Germershausen

Guenter Sikorski

Wolf Trommsdorff

Bernahrd Bisping

Klaus Gerbach

A projectile having a longitudinal axis, a sensor disposed in the substantially pointed front end of the projectile for detecting a respective target, and electronics connected to the output of the sensor for igniting a correction charge to effect a correction of the flight path of the projectile by a predetermined angle (.delta..sub.0). In order to install the apparatus for flight-path correction into the respective projectile completely and in a space-saving manner, so that, unlike in known projectiles, corresponding evaluation and signal-transmission units in the respective weapon carrier can be omitted and complicated gyroscopic systems in the projectile can be omitted, the sensor determines the angle (.delta.) between the longitudinal axis of the projectile and the line (target line) connecting the projectile and the target, and when an angle (.delta..sub.0) is reached that is identical in size/magnitude to the deviation caused by the respective correction charge, the electronics ignite this charge.

Projectile having an apparatus for flight-path correction

A method and apparatus for determining the roll angle position of a rotating flying body (2) relative to a fixed station (1) with the aid of a laser (3) light beam (4, 24) emitted by the fixed station (1) and received by the flying body (2). To determine the roll angle position of the flying body located at an arbitrary position within the guide beam (4) precisely and simply, a phase-coded laser light beam (guide beam) is produced with the aid of an optical element, particularly a holographic optical element (6). This guide beam (14) is then decoded in a receiving apparatus (8) of the flying body by means of a further holographic element (11) that is rigidly connected to the flying body (2). The further holographic element (11) is configured such that maximum brightness or intensity only occurs at the receiving detector (13) if it is located parallel to the holographic element (11) on the side of the laser (3), i.e., non-mirror-symmetric information must be impressed upon the guide beam (4).

Method and apparatus for determining the roll angle position of a

An apparatus for flight path correction of flying bodies, such as projectiles, rockets and the like, with the aid of a laser guide beam, wherein the course of the respective flying body is determined and processed in a measuring apparatus associated with the firing apparatus and containing an optical receiving detector in order to obtain an appropriate correction signal, and wherein the correction signal is then transmitted, through encoding of the laser guide beam, to a receiving apparatus disposed in the tail portion of the flying body. To determine the course of the flying body in a simple manner, both an optical light source for producing a light beam and an optical receiving detector are disposed on the measuring apparatus, and triple reflector or mirror elements, that reflect the incident light beam back in its initial direction independently of the respective angle of incidence, are disposed on the bottom of the flying body or at the ends of the guiding mechanism of the flying body. In rotating flying bodies, the triple mirror elements are preferably distributed at irregular intervals in a circle, perpendicular to the longitudinal axis of the flying body. This arrangement makes it possible to use the signals reflected by the triple mirror elements to determine the roll position of the respective flying body.

Apparatus for flight path correction of flying bodies

A method and an apparatus for flight path correction of one or more projectiles (2-6) with the aid of a guide beam (9), wherein target data, such as speed, range and direction of movement, are continuously acquired in a fire-guidance system associated with the firing device (1), for example, an automatic cannon, and are transmitted to the laser apparatus (21) that produces the guide beam (9), and wherein each projectile includes a receiving apparatus (31) which receives the guide beam (9). To be able to correct, in a simple manner with a pulse correction, both individual projectiles as well as a plurality of projectiles flying closely behind one another in time and having different courses, the guide beam (9) is aimed toward the collision point (15) calculated on the basis of the target data, and the guide beam (9) is subdivided into a plurality, at least five, partial beams (guide beam segments 10-14) including a central guide beam segment (10) which is aimed at the collision point (15) and around which the remaining partial beams or beam segments are disposed. The guide beam segments (10-14) are all modulated differently. Each projectile (2-6), with the aid of its respective receiving apparatus (31), then determines the angular position necessary for the correction, with respect to the collision point (15), from the modulation of the respective received guide beam segment (10-14).

Method and apparatus for flight path correction of projectiles

Ammunition preferaqbly for use in high-angle fire to be fired from a cannon suitable for flat trajectory ammunition and with direct participation of the cannon barrel, the ammunition being made of one piece as an ammunition unit having the same outer dimensions as a comparable ammunition unit which is intended to be fired from the same cannon exclusively with an essentially flat trajectory, the ammunition unit including a propellant charge and a payload projectile having a rear portion occupying a region corresponding to that occupied by a portion of the propellant charge of the comparable unit.

Ammunition, preferably for use in high-angle fire

A subcaliber projectile has a small-diameter projectile body extending along and centered on an axis, having a radially outwardly directed outer surface, and adapted to move in a predetermined axial back-to-front direction, and a sabot formed of a plurality of similar segments annularly surrounding at least a portion of the body, the segments forming an inner surface generally on the outer surface of the body and having an extreme front end and an extreme rear end. This projectile is formed on one of these surfaces at the extreme rear end of the sabot with a radially projecting ridge of generally semicircular shape having a center of curvature. The other of the surfaces is formed at the extreme rear end of each segment of the sabot with a radially open recess complementary to and receiving the ridge. In addition the segments are pivotal about the center of curvature without the ridge leaving the recess from a position with the respective inner surface lying on the outer projectile-body surface and a position with the inner surface projecting at an angle away therefrom.

Subcaliber projectile with pivotally separable drive cage

Method of actuating a proximity fuze and device for implementing the

An improved cartridge ammunition which includes an at least partially combustible shell casing and a projectile with a fin-stabilizing tail section mounted in a neck portion of the shell casing which thereby forms a first connection between the projectile and shell casing. A second connection between the projectile and shell casing is formed by means of a support element which is form-lockingly connected to both. The shell casing has a support region axially extending forwardly inside the shell casing from its bottom. The support element being mounted on said support region and being instrumental in assuring, due to its form-locking connections, that a predetermined axial force occurs in said support of element prior to disintegration thereof, between the tail section and the support region due to gas pressure build-up in the shell casing at firing of the ammunition.

Cartridge ammunition with at least a partially combustible propellant

An armor piercing breaking projectile using a stack of prepenetrating partial cores with interfitting centering bosses and respective cutting edges for piercing successive layers of armor.

Impact projectile

An armor-piercing projectile has a steel jacket threadedly or otherwise positively connected with a core which has a forwardly projecting point and leaves a space to the rear of the jacket receiving an incendiary charge and a winged tail unit mechanically connected with that charge. Upon penetration of an armor plate, the tail unit is torn from the jacket and extracts the incendiary charge which then ignites and destroys the surrounding armor.

Anti-tank shell

A charge formed of a mass of packed propellant is generally centered on an axis and is of radially generally uniformly and radially outwardly increasing density. This charge has a predetermined size and shape and is made by first filling particulate propellant into a chamber centered on an axis and defined by side walls extending at least generally parallel to the axis. This chamber is radially somewhat larger than the predetermined size and shape for the charge. At least some of the side walls are then displaced radially inward to reduce the volume of the chamber until the reduced chamber generally has the size and shape for the charge. The weight of the particulate propellant filled into the chamber is equal to the desired weight for the charge. The tail of a projectile is positioned in the chamber before filling the particulate propellant into the chamber. The projectile downwardly closes the chamber and can be raised after the mass is packed to push it up out of the chamber.

Graduated-density packed propellant charge

A multi-range ammunition unit for firing at a high angle and with preselected muzzle velocities. The ammunition unit includes at least two partial propellant charges, a first one of which is fixedly mounted to the bottom of the shell casing and the second one or ones of which are fixedly mounted to the bottom of the projectile of the ammunition unit. All partial propellant charges are coaxially arranged with respect to the shell casing. Mechanical and/or electrical ignition means are provided to first ignite the first propellant charge and then selectively sequentially ignite the second propellant charge or charges.

Multiple purpose ammunition

A method and apparatus for covering a target area with ammunition, wherein a container, which contains active bodies W arranged on different decks 30.1, 30.2 and which is to be brought over the target area, releases the active bodies W through release openings 34 on its sides to become effective from above on respective individual flight paths against objects, for example armored vehicles, present in the target area.

Method and apparatus for covering a target area with ammunition

A sabot consists of a plurality of segments which define an air pocket for detaching the segments from a fin-stabilized subcaliber penetrator projectile. The air pocket is defined by a rear support region of the sabot. A front support region of the sabot includes a plurality of webs between each adjacent pair of which an air-through-streaming passage is defined. At least the web portion of each segment is made of synthetic material and such web portion has a curved part defining a fracture zone.

Segmented sabot

Growing community of inventors

Kaarst, Germany

Rudolf Romer