DE102012020740B4 - A method of retrofitting ammunition for a shoulder-supportable weapon - Google Patents

Abstract

Method for converting an ammunition for a shoulder-supported weapon, which ammunition comprises a warhead (K), an engine (H) for accelerating the ammunition and a tail unit (L) for flight stabilization, which via a tail boom passing through the thrust jet of the engine (H) ( T) is connected to the engine (H), with the following steps: closing the thrust jet passage (I) between the engine (H) and the tail boom (T), introducing several nozzles (C) into the rear part of the engine (H) next to the shoulder of the tail boom (T), via which the thrust jet of the engine (H) can be guided past the tail boom (T) to the rear, introducing / attaching a path correction device (A1, A2; B1, B2) in and / or to the cavity (J) of the tail boom (T), the path correction device (A1, A2; B1, B2) having at least one sensor device (A1, A2) for sensing accelerations and rotary movements of the ammunition during flight and one Computing unit for generating path correction signals based on the data sensed by the sensor device (A1, A2), the path correction device (A1, A2; B1, B2) comprises at least one actuator (B1, B2) which, on the basis of the path correction signals, effects an angular momentum and / or a transverse thrust pulse on the ammunition in order to correct the trajectory of the ammunition, the at least one actuator pulse generator (B1, B2) comprises which are arranged on (B1) or in the tail unit (T) or on the tail unit (L) or at the level of the center of gravity (CG) of the ammunition or in front of (B2) the center of gravity (CG) of the ammunition.

Description

The invention relates to a method for converting an ammunition for a shoulder-supportable weapon, such as a bazooka. The ammunition includes a warhead, an engine for accelerating the ammunition, and a tail stabilizer for flight stabilization which is connected to the engine via a tail boom. Such ammunition is from the DE 42 25 704 A1 , of the US 2006/0 060 692 A1 , of the US 5,788,178 A , of the US Pat. No. 6,565,036 B1 , of the US 2012/0 048 991 A1 , of the US 2008/0 061 188 A1 , of the US 7 781 709 B1 , of the US Pat. No. 6,629,668 B1 and from the DE 196 34 457 B3 known.

In a one-man fired ammunition such as the bazooka, which is fired from the shoulder or from a rack, provides a rocket engine in the initial flight phase after launch for the acceleration of the ammunition. If the target distance is not very short, the ammunition will fly in the final flight phase purely ballistic to the target. In this technique targeting is unavoidable due to lateral, vertical and longitudinal deviations from the nominal trajectory.

It is therefore an object of the present invention to improve the performance of shouldered ammunition.

This object is achieved by the method for retrofitting an ammunition according to claim 1 and by the method for retrofitting an ammunition according to claim 2.

The ammunition has a track correction device for correcting the trajectory of the ammunition after its launch. As a result, side, height and longitudinal errors of the trajectory can be compensated. The performance of the ammunition is thus improved.

The web correction device has at least one sensor device for sensing accelerations and rotational movements of the ammunition during the flight. As a result, deviations from the nominal trajectory can be determined. In this case, it is provided that the ammunition further comprises a computing unit for generating path correction signals based on the data sensed by the sensor device. In this case, the arithmetic unit adopts the deviations from the nominal trajectory determined by the sensor device and prepares a predetermination of the deviation caused by these deviations in the target. The arithmetic unit then calculates path correction signals, by which the target filing is minimized.

The sensor device preferably comprises an inertial sensor system. The sensor device can be provided in or on the tail unit.

The path correction device has at least one actuator which, on the basis of the path correction signals, effects an angular momentum and / or a transverse thrust pulse on the ammunition in order to correct the trajectory of the ammunition. The actuators thus convert the track correction signals into physical pulses which alter the trajectory of the munition.

The at least one actuator comprises pulse generators which are arranged on or in the tail unit or on the tail unit or at the level of the center of gravity of the ammunition or in front of the center of gravity of the ammunition. These pulse generators can be realized by so-called micro-thruster, which can transmit a pulse to the ammunition by a pyrotechnically generated recoil. The arithmetic unit can cause targeted trajectory changes by appropriate selection of individual thrusters and by setting their duration of thrust. By providing a plurality of pulser both before, behind and at the height of the center of gravity of the ammunition both angular momentum and transverse thrust pulses can be transferred to the ammunition.

Alternatively, a cruise engine is arranged in the tail unit. The cruise engine (so-called Sustainer) serves not primarily to increase the speed of the ammunition achieved by the engine, but primarily the steerability of the ammunition and the maintenance of the achieved speed by providing a comparatively small and relatively constant thrust. Preferably, the actuator described above is then implemented by an integrated thruster for deflecting the thrust jet of the cruise engine or by a swivel of a thruster in the thrust jet of the cruise engine. The thruster deflects the thrust jet exiting through a nozzle at the rear of the tail unit, thereby enabling thrust vector control. The actuating action of the actuator can also be realized by a pivoting of the nozzle of the cruise engine.

In all the alternatives described above, the target trays can be corrected by continuous or discrete thrusts or pulse transmissions.

In order to guide the thrust jet of the main engine obliquely backwards past the tail boom, several outlet nozzles are formed at the rear part of the engine next to the shoulder of the tail boom arranged, via which the thrust jet of the main engine can escape.

The present invention relates to a method for converting a conventional ammunition into an ammunition as previously described. Such a conventional ammunition, on which the conversion according to the invention is carried out, preferably has a warhead, an engine for accelerating the conventional ammunition and a stabilizer for stabilizing the flight, which is connected via a the thrust jet of the engine passing tail unit with the engine. According to the invention, the following steps are performed on this conventional ammunition (in any order):
Closing the thrust jet passage between the engine and tail unit, introducing a plurality of nozzles in the rear part of the engine adjacent to the approach of the tail boom, over which the thrust jet of the engine on Leitwerksträger over past backwards,
Introduction or attachment of a web correction device - as has been described above for the various alternatives of ammunition, taking into account their various elements sensor device, processing unit and actuators - in and / or on the cavity of the tail boom.

According to a preferred embodiment of the inventive method according to claim 2, a nozzle for the exit of the thrust jet of the cruise engine can be additionally arranged in a further step at the rear end of the tail boom.

As an alternative to all the steps described above (except the step of introducing several nozzles in the rear of the engine) and the tail boom of the conventional ammunition can be separated at its approach to the engine, in the cavity of the tail boom the web correction device are introduced, then at the severed end be closed and then firmly connected to the rear of the engine, preferably by welding.

The invention will be explained in more detail below on the basis of its advantageous embodiments with reference to the drawings.

In the drawings show:

1 the result of the two Umrüstverfahren invention (cumulative in a drawing), and

2 a conventional ammunition, which by means of Umrüstverfahren invention with special consideration of the oval edged part in the 1 can be converted into an improved ammunition.

1 shows cumulatively the result of both inventive Umrüstverfahren. In particular, all alternatives of the web correction device A1, A2; B1, B2; D, E, F, G shown in a single figure. However, it is emphasized that both the use of a web correction device only with the features A1, A2; B1, B2 and the use of a web correction device only with the features A1, A2; D, E, F, G fulfills the purpose of the invention.

The 1 shows an ammunition for a shoulder-supportable weapon, comprising a warhead K, an engine H for accelerating the ammunition and a tail L for flight stabilization, which is connected via a tail boom T to the engine H. Furthermore, a track correction device A1, A2; B1, B2; D, E, F, G provided for correcting the trajectory of the ammunition after its launch.

The path correction device has a sensor device A1 and / or A2 for sensing accelerations and rotational movements of the ammunition during the flight. Furthermore, a computing unit (not shown) is provided for generating path correction signals on the basis of the data sensed by the sensor device A1, A2. The sensor device A1, A2 may comprise an inertial sensor. In addition, a GPS module for detecting the position in the room may also be provided. The sensor device A1 can be provided in the tail unit T. Alternatively or cumulatively, the sensor device A2 can be provided on the tailplane support T.

The web correction device comprises at least one actuator B1, B2; D, E, F, G which, on the basis of the trajectory correction signals, cause an angular momentum and / or a transverse thrust pulse on the ammunition to correct the trajectory of the ammunition.

One possible form of implementation of the actuators is the arrangement of pulse generators B1, B2, which are arranged on the (B1) tail carrier T or before (B2) the center of gravity CG of the ammunition. These pulse generators B1, B2 can be realized by micro-thruster, which can cause a pulse on the ammunition via pyrotechnically generated recoil. Another possible realization of the actuator is the provision of a cruise engine D, which is arranged in the tailplane T. By an integrated jet rudder G for deflecting the thrust jet of the cruise engine D or by a Einschwenkbarkeit a thruster F in the thrust of the cruise engine D or by a pivoting E of the nozzle of the cruise engine D, a track-correcting pulse can be transferred to the ammunition.

Of course, according to a particularly preferred embodiment of the present invention, both actuator realization forms - that is to say thruster and thrust vector control - can also be used cumulatively in the retrofitting method according to the invention. As a result, a particularly high agility and optimal performance of the ammunition can be achieved.

2 shows a possible configuration of a conventional ammunition for a shoulder-supportable weapon. This conventional ammunition has a warhead K, an engine H for accelerating the ammunition and a stabilizer L for flight stabilization, which is connected via a the thrust jet of the engine H durchlietenden tail boom T with the engine H. Such a conventional ammunition may take into account the in 1 oval outlined part of the drawing for improved ammunition according to 1 to be converted. For this purpose, the thrust jet passage I between engine H and tail unit T is closed. Furthermore, a plurality of nozzles C are introduced into the rear part of the engine H in addition to the approach of the tail boom T, via which the thrust jet of the engine M on the tail unit T can be passed over to the rear. Finally, a web correction device according to the description of the figures becomes 1 in and / or on the cavity J of the tail boom T on / attached.

• A1, A2

  Sensor device (inertial sensor)

  B1, B2

  Pulse generator (micro-thruster)

  C

  Nozzles (from H)

  CG

  Focus of the ammunition

  D

  Cruise engine

  e

  swiveling nozzle (from D)

  F

  Swiveling thruster

  G

  integrated thruster

  H

  engine

  I

  Thrust jet passage (between H and T)

  J

  Cavity (from T)

  K

  warhead

  L

  tail

  T

  tail boom

Claims (2)

A method for converting an ammunition for a shoulder-supportable weapon, which ammunition comprises a warhead (K), an engine (H) for accelerating the ammunition and a stabilizer (L) for flight stabilization, which via a thrust jet of the engine (H) by Leitleitsträger ( T) is connected to the engine (H), with the following steps: Closing the thrust jet passage (I) between engine (H) and tail unit (T), Introducing a plurality of nozzles (C) in the rear part of the engine (H) adjacent to the approach of the tail boom (T), over which the thrust jet of the engine (H) on the tail boom (T) is passed backwards, Introducing / attaching a web correction device (A1, A2, B1, B2) into and / or to the cavity (J) of the tail carrier (T), wherein the web correction device (A1, A2, B1, B2) comprises at least one sensor device (A1, A2) for sensing accelerations and rotational movements of the ammunition during flight and a computation unit for generating trajectory correction signals based on the data sensed by the sensor device (A1, A2), wherein the path correcting device (A1, A2, B1, B2) comprises at least one actuator (B1 B2), which on the basis of the track correction signals causes an angular momentum and / or a transverse thrust pulse on the ammunition to correct the trajectory of the ammunition, wherein the at least one actuator comprises pulse generators (B1, B2), which at the (B1) or in the Tailplane (T) or on the tail (L) or at the height of the center of gravity (CG) of the ammunition or before (B2) the center of gravity (CG) of the ammunition are arranged. A method for converting an ammunition for a shoulder-supportable weapon, which ammunition comprises a warhead (K), an engine (H) for accelerating the ammunition and a stabilizer (L) for flight stabilization, which via a thrust jet of the engine (H) by Leitleitsträger ( T) is connected to the engine (H), comprising the following steps: closing the thrust jet passage (I) between the engine (H) and tail unit (T), introducing a plurality of nozzles (C) in the rear part of the engine (H) adjacent to the approach of the tail boom (T) via which the thrust jet of the engine (H) can be conducted past the tail boom (T), introduction / attachment of a track correction device (A1, A2, D, E, F, G) into and / or to the Cavity (J) of the tail carrier (T), wherein the web correction means (A1, A2, D, E, F, G) at least one sensor means (A1, A2) for sensing accelerations and rotational movements of the ammunition during the flight and a computation unit for generating path correction signals on the basis of the data sensed by the sensor device (A1, A2), wherein the path correction device (A1, A2; D, E, F, G) comprises at least one actuator (D, E, F, G) which, on the basis of the track correction signals, causes an angular momentum and / or a transverse thrust pulse on the ammunition to correct the trajectory of the ammunition, wherein Tailplane (T) a cruise engine (D) is arranged, wherein the at least one actuator by an integrated thruster (G) for deflecting the thrust jet of the cruise engine (D) or by a Einschwenkbarkeit a thruster (F) in the thrust jet of the cruise engine (D) or by a pivoting (E) of the nozzle of the cruise engine (D) is realized.

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