EP0267474B1 - Lance-roquettes - Google Patents

Lance-roquettes Download PDF

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Publication number
EP0267474B1
EP0267474B1 EP87115531A EP87115531A EP0267474B1 EP 0267474 B1 EP0267474 B1 EP 0267474B1 EP 87115531 A EP87115531 A EP 87115531A EP 87115531 A EP87115531 A EP 87115531A EP 0267474 B1 EP0267474 B1 EP 0267474B1
Authority
EP
European Patent Office
Prior art keywords
housing
guide arrangement
guide device
rocket
arrangement
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP87115531A
Other languages
German (de)
English (en)
Other versions
EP0267474A1 (fr
Inventor
Rainer Schöffl
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Dynamit Nobel AG
Original Assignee
Dynamit Nobel AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Dynamit Nobel AG filed Critical Dynamit Nobel AG
Publication of EP0267474A1 publication Critical patent/EP0267474A1/fr
Application granted granted Critical
Publication of EP0267474B1 publication Critical patent/EP0267474B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/06—Rocket or torpedo launchers for rockets from aircraft
    • F41F3/065—Rocket pods, i.e. detachable containers for launching a plurality of rockets

Definitions

  • the invention relates to a launching container for rockets according to the preamble of patent claim 1.
  • Launch containers for rockets which have a guiding device in the form of a plurality of launch tubes, each of which receives a rocket.
  • the guide device is firmly connected to the container housing.
  • the container structure is either movable, e.g. with rocket launchers mounted on vehicles, or rigid, e.g. in the case of launch containers attached to aircraft, connected to the respective carrier (vehicle or aircraft).
  • the carrier has an inclined position when the rocket is launched, a directional error of the rocket trajectory occurs.
  • the inclined position has a particularly serious effect if the missile is provided with aerodynamic surfaces which act in only one direction and which have the task of changing the trajectory of the missile in a certain direction. If the launch container was tilted, the direction of flight of the rocket would be falsified. It is therefore necessary to bring the carrier into a horizontal position at the time of the rocket launch. This is the case with moving beams, e.g. Aircraft or vehicles, only imperfectly or not at all.
  • the invention has for its object to design a launching container according to the preamble of claim 1 so that it enables a rocket launch in a defined position regardless of the respective position of the carrier.
  • the guide device is rotatable relative to the housing, and a stabilizing device ensures that the angle of rotation of the guide device with respect to the housing is adjusted so that any changes in the angle of rotation of the housing are compensated for.
  • the guide device therefore takes up an angle of rotation with respect to the housing, which at the respective time is opposite to the angle of rotation of the housing relative to an earth-based reference system.
  • the stabilization device can have an angle detector for determining rotations of the housing or the guide device with respect to the reference system, and a mechanical rotary drive for the guide device.
  • the reference system can be defined, for example, by a gyroscope which determines the deviation of the actual roll position of the guide device from the desired roll angle, the gyroscope being able to be arranged either in the carrier or in the starting container.
  • An electromechanical or an electro-hydraulic system is preferably used as the drive system, but other systems can also be used, e.g. magnetic, pneumatic or pyrotechnic systems, where the energy required is either supplied by the carrier or generated in the starter itself.
  • the latter can exist, for example, in starter containers on airplanes by means of a ram air turbine and a connected power generator, so that a starter container that is completely autonomous in terms of roll stabilization can be created if the angle detector and the system specifying the reference position are also located in the starter container.
  • the starting container shown in Fig. 1 is attached to the outside of an aircraft. It has a housing 1 which is provided with suspension eyes 2 and in which the guide device 3 is arranged.
  • the housing 1 is open at the front ends, and it contains annular bearings 4, in which the guide device 3 is rotatable about the longitudinal axis of the housing.
  • the guide device 3 contains several starting tubes 5, which extend through the entire length of the housing 1 and are open at both ends.
  • the starting tubes 5 are arranged with their axes on a circle running coaxially to the longitudinal axis of the housing and distributed on this circle with uniform circumferential distances.
  • a servo motor 6 is fastened, the output shaft of which drives a sprocket segment 8 via a toothed wheel 7, which is fastened to the guide device 3 coaxially to its longitudinal axis.
  • the servo motor 6 can thus rotate the guide device 3 mounted in the bearings 4 around its longitudinal axis.
  • the control system 10, 11 for stabilizing the roll angle is located in a central tube 9 of the guide device which is closed at both ends.
  • An angle detector 10 gives the control electronics 11 a signal which corresponds to the deviation of the roll angle (the angle of rotation about the longitudinal axis of the guide device) with respect to a set roll angle defined on the basis of an earth-bound reference system. If the angle detector 10 detects a deviation of the actual position from the target position, the control electronics 11 send a corresponding control command to the servo motor 6, which then rotates the guide device 3 about its longitudinal axis so that it is independent of the position of the housing 1 or the carrier holding the housing always assumes the desired angle.
  • Fig. 2 shows schematically the main elements of the starting container of Fig. 1 with the corresponding control or signal lines.
  • the leadership device device 3 which is rotatably mounted in the housing 1, contains the control system 11, 12 with the angle detector 10 and the evaluation electronics 11.
  • the angle detector 10 is connected via signal and power lines 12 to the evaluation electronics 11.
  • a control line 13 leads from the evaluation electronics 11 to the servomotor 6.
  • the energy source 14 located in the aircraft is connected to the control system 10 and the servomotor 6 via supply lines 15, 16.
  • Fig. 3 to 5 show another embodiment of the starting container, in which an aerodynamically acting stabilizing device is provided.
  • the guide device 3 which contains a plurality of starting tubes 5 arranged in a ring shape, is rotatably mounted in pivot bearings 4.
  • two V-shaped guide elements 17 are fastened, which are arranged on the rear end of the guide device 3 protruding from the housing 1 and project laterally beyond the housing 1.
  • the guide elements 17 are exposed to the outside air flow, which strives to maintain the positions of the guide elements 17 and thus to prevent or minimize rotation of the guide device 3 about its longitudinal axis.
  • the guide device 3 is freely rotatably mounted in the housing 1 without a drive device being provided. If the carrier aircraft assumes an inclined position in flight, the aerodynamic forces acting on the guide elements 17 cause a moment that holds the guide device 3 in the desired position.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)

Claims (4)

1. Conteneur de lancement de roquettes, comportant une enveloppe (1) dans laquelle est agence un dispositif de guidage (3) pour recevoir au moins une roquette, cette enveloppe (1) pouvant être assemblée à un porteur, caractérisé par le fait que le dispositif de guidage (3) peut tourner dans l'enveloppe (1) et par le fait qu'il est prévu un dispositif stabilisateur (6, 7, 8, 10, 11, 17) qui compense les rotations de l'enveloppe (1) par des rotations antagonistes du dispositif de guidage (3) par rapport à l'enveloppe.
2. Conteneur de lancement selon revendication 1, caractérisé par le fait que le dispositif stabilisateur (6, 7, 8, 10, 11) présente un détecteur d'angle (10) pour la détermination des rotations de l'enveloppe (1), ou du dispositif de guidage (3), par rapport à un système de référence lié au sol, et présente un système d'entraînement mécanique (6, 7, 8) pour la rotation du dispositif de guidage (3).
3. Conteneur selon revendication 1, caractérisé par le fait que le dispositif stabilisateur est constitué par des éléments du dispositif de guidage (3) qui agissent aérodynamiquement, et par le fait que le dispositif de guidage (3) est monté à rotation libre dans le conteneur (1).
4. Conteneur selon l'une des revendications 1 à 3, caractérisé par le fait que le dispositif de guidage (3) peut tourner autour d'un axe longitudinal parallèle à l'axe des roquettes.
EP87115531A 1986-11-07 1987-10-23 Lance-roquettes Expired - Lifetime EP0267474B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3637986 1986-11-07
DE19863637986 DE3637986A1 (de) 1986-11-07 1986-11-07 Startbehaelter fuer raketen

Publications (2)

Publication Number Publication Date
EP0267474A1 EP0267474A1 (fr) 1988-05-18
EP0267474B1 true EP0267474B1 (fr) 1990-03-14

Family

ID=6313401

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87115531A Expired - Lifetime EP0267474B1 (fr) 1986-11-07 1987-10-23 Lance-roquettes

Country Status (2)

Country Link
EP (1) EP0267474B1 (fr)
DE (2) DE3637986A1 (fr)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2802398A (en) * 1951-01-16 1957-08-13 Lockheed Aircraft Corp Aircraft rocket launcher
US2971731A (en) * 1955-03-10 1961-02-14 Graw Messgerate G M B H Dr Ejection container for radio probes
US4475436A (en) * 1980-04-21 1984-10-09 The Boeing Company Missile launcher

Also Published As

Publication number Publication date
DE3761922D1 (de) 1990-04-19
EP0267474A1 (fr) 1988-05-18
DE3637986A1 (de) 1988-05-11

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