Rheinmetall Gmbh

Manfred Moll

Rudolf Romer

Christian Jaeneke

Karl W Bethmann

Wilfried Becker

Wolfram Witt

Werner Grosswendt

A rocket engine according to the invention has a body generally extending along an axis and adapted to move through the air in a predetermined axial back-to-front direction. This body is formed with axially spaced front and rear fuel-containing combustion chambers. A nozzle centered on the axis and extending axially backward in the body from the front chamber has a rear nozzle end directed axially backward so that gases generated in the front chamber by combustion of the fuel therein form a fan-shaped jet extending axially backward from the rear nozzle end. The injector of this invention comprises a front tube centered on the axis, having an upstream end sealed to the nozzle upstream of the rear nozzle end, and having a rear downstream end formed with an outside bevel and located axially downstream of the jet formed by the nozzle, and a rear tube secured to and coaxial with the front tube, radially surrounding same and forming therewith an annular gap open axially upstream, and having an upstream end formed with a bevel and positioned axially forward of the rear nozzle end. A diffuser is provided in or on the body for deflecting outside air axially back into the gap.

Air-breathing jet engine

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 weapons system, especially for foot attack upon armored vehicles, has a recoilless firing tube and a discus-shaped projectile. The projectile is provided with a fork having an upper arm and a lower arm and a stabilizer connected to the fork and including a tube having a longitudinal axis and fins at the opposite end. An explosive charge is carried by a hub of the fork and a disk-shaped body is rotatable about the hub between the arms of the fork by a portion of propellant gases to stabilize the projectile along its flight toward a target.

Discus-shaped projectile

In the method and apparatus for covering a target area with ammunition, 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.

The invention relates to a wing-stabilized projectile having a transverse thrust steering arrangement. The transverse thrust steering arrangement is constructed in such a way that the release of thrust impulses out of control nozzles is achieved, independently from each other and oscillation free, whereby an excess pressure in the drive system of the transverse thrust steering mechanism is avoided. This is achieved in that in a control block there is provided at least one movable sealing member which is connected with a signal converter as well as with a control conduit having a centrally arranged sealing member, whereby by unloading the end surface of the sealing member it is opened and permits the outstreaming of generator gases which form a radial thrust impulse F via a control nozzle effecting a flight correction. The pressure loading of the end surface of the sealing member produces a closing process of the closing member at the end of the flight correction whereby the prior closed control member which is centrally mounted in the control block is pressure-unloaded via a throttle, so that the generator gas can be drawn off via of feed conduit and a draw-off conduit in a momentum-free manner.

Wing-stabilized projectile

A warhead unit carrying a pay load and being suspended from a parachute which brakes the descent of the warhead unit. The pay load includes a sensor for detecting a target and a projectile-forming charge which is fired from the pay load when activated by the sensor. The pay load is rotated by jet nozzles first about a longitudinal axis and then about a diagonal axis after the point of suspension has been shifted from the center of the top surface of the pay load to a corner of the top surface of the pay load.

Warhead unit

A projectile to be fired from a tubular or rail-shaped launcher has a warhead integral with a rearwardly extending tube of smaller diameter which contains a propulsive charge inserted between the warhead and a sabot carrying a frangible inertial mass. The rear end of the tube has a constricted opening which, upon detonation of the charge, retains the rearwardly moving sabot while giving passage to the disintegrating mass as the projectile is propelled forwardly. The propulsion gases evolving within the tube are temporarily retained by one or more heat-destructible plugs in the sabot and/or in the tube which melt, burn or char to allow the delayed escape of the gases whereby an in-flight thrust is imparted to the projectile.

Projectile designed for recoilless and virtually noiseless firing

There is described a spin stabilized projectile assembly including a projectile, a sabot, and a guide ring. The projectile is provided with a shoulder at the rear end of which abuts the sabot, the projectile and sabot being connected by the guide ring which extends around the projectile and part of the sabot. The guide ring is arranged so that after the projectile assembly has been fired and has left the barrel of the weapon the sabot and the projectile separate. The sabot has a diameter substantially equal to that of the projectile; the guide ring is secured to the sabot against relative movement in a longitudinal direction but is rotatable with respect to the sabot.

Spin stabilized projectile assembly

An improved arrangement for more efficiently igniting and thereafter maintaining an optimum burning efficiency of a hollow, solid propellant charge cartridge disposed in a combustion chamber at the rear end of a rocket or other ballistic projectile is described. A support tube is mounted for extension coaxially into the hollow interior of the charge cartridge with a radial clearance therebetween. The rear end of the support tube is carried within the locking member at the rear end of the combustion chamber, so that upon bursting of a rupture disc between the locking member and the rear end of the combustion chamber, both the locking member and the support tube can be propelled axially rearwardly out of the combustion chamber. The advantageous function of the support tube to absorb radial acceleration forces during firing of the rocket, is preserved, while thereafter the deleterious effect of having the support tube remain in place during the ignition of the main propellant charge is obviated.

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Dusseldorf, Germany

Manfred Moll