Dynamit Nobel Aktiengesellschaft

Walter Helmut Diesinger

Axel Homburg

Rainer Schoffl

Erich Alker

Hans-Joachim Eickmann

Klaus Peter Kosiolek

A seeker head and an associated electronic system are mounted to the front end of a warhead in order to guide the missile to the target and to initiate detonation at the right time. To prevent the seeker head and the electronic system from confusing an impeding the hollow-charge jet produced by the hollow charge, the components arranged in front of the warhead are accelerated away from the warhead by a pyrotechnical charge shortly before hitting the target so that the seeker head and electronic system separate from the warhead and the hollow-charge jet produced by the warhead can thus hit the target without obstacle.

Missile with remote-controlled warhead

A spin-stabilized training missile is equipped with a stabilizer device for reducing spinning in order to decrease the flight range. The training missile is designed so that its stabilization attainable solely by the spin upon firing is not sufficient for a stable flight in the practice range. The required additional stabilizing in the practice range is obtained by a stabilizer device or control airfoil effecting simultaneously, after leaving the practice range, such a spin reduction that the training missile becomes unstable and the range of flight is controlled.

Spin-stabilized training missile

A sensor for rocket engines having at least one combustion chamber including a pressure-sensitive sensing device responsive to pressure in the combustion chamber for providing an output signal to a control device in response to the pressure in the combustion dropping below and/or rising above at least one predetermined pressure. The pressure-sensitive sensing device includes a piston arranged for displacement between first and second positions. The piston is displaceable from at least the first position to the second position in response to a first predetermined pressure value in the combustion chamber. A restoring force is effective for displacing the piston from the second position toward the first position in accordance with a second predetermined pressure value in the combustion chamber. The piston is arranged for triggering a signal in at least one of the first and second positions thereof.

Sensor for rocket engines

A training projectile having an auxiliary drive mechanism for counteracting the aerodynamic resistance to which the projectile is exposed during the training flight phase of projectile travel. The auxiliary drive mechanism preferably is in the form of a rocket or jet drive. The training projectile is also provided with a mass so that the ratio of the resultant axial force to the mass of the training projectile is at least approximately equal to the ratio of the resistance force to the mass of a corresponding live projectile during the training flight phase.

Training projectile

A partition arrangement for rocket motors with at least two mutually independent thrust stages and nozzle and nose sides. The partition arrangement includes a partition member separating a combustion chamber on the nozzle side from another chamber on the nose side with the partition member being provided with at least one flow aperture therein. A sealing element is disposed on the nozzle side for sealing the at least one flow aperture of the partition member with the sealing element being displaceable for freeing the at least one flow aperture of the partition member and being maintained within the another chamber on the nozzle side upon displacement. At least the partition member and/or the sealing element is provided with only one flow aperture for permitting propellant gases from the nose side combustion chamber to enter the another chamber on the nozzle side only in a central direction.

Growing community of inventors

Bergisch-Gladbach, Germany

Walter Helmut Diesinger