EP3637035B1 - Rail de lancement pour un missile - Google Patents

Rail de lancement pour un missile Download PDF

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Publication number
EP3637035B1
EP3637035B1 EP19199162.9A EP19199162A EP3637035B1 EP 3637035 B1 EP3637035 B1 EP 3637035B1 EP 19199162 A EP19199162 A EP 19199162A EP 3637035 B1 EP3637035 B1 EP 3637035B1
Authority
EP
European Patent Office
Prior art keywords
missile
holding device
launch rail
rail
launch
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.)
Active
Application number
EP19199162.9A
Other languages
German (de)
English (en)
Other versions
EP3637035A1 (fr
Inventor
Stefan Lehmann
Marco STERN
Andreas Schneider
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.)
MBDA Deutschland GmbH
Original Assignee
MBDA Deutschland GmbH
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 MBDA Deutschland GmbH filed Critical MBDA Deutschland GmbH
Publication of EP3637035A1 publication Critical patent/EP3637035A1/fr
Application granted granted Critical
Publication of EP3637035B1 publication Critical patent/EP3637035B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F41F3/0406—Rail launchers
    • 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

Definitions

  • the present invention relates to a launch rail for a missile with a detachable holding device.
  • a launch rail is for example in U.S. 5,094,140A disclosed.
  • a starting process that is as stable as possible is of great importance for the flight behavior of unmanned missiles, such as guided missiles or the like.
  • Launch rails are used for this purpose, which ensure that the missile moves in a straight line until it has reached a certain speed and emerges from the launch rail.
  • brackets are attached to the missiles, which allow the respective missile to be arranged on a launch rail.
  • the weight and the aerodynamic properties of the contour have a major impact on the flight behavior and functionality of a missile. Therefore, it would be desirable to be able to dispense with externally attached mounts on a missile.
  • the object of the present invention is to improve the aerodynamic properties of a missile with additional weight savings by means of an improved launch rail.
  • a launch rail for a missile has a rail body, a releasable holding device mounted on the rail body for holding the missile on the launch rail, and a release mechanism mounted on the rail body for releasing the holding device from the missile.
  • the holding device has a locking element for locking the missile on the holding device and the triggering mechanism is designed to open the locking element.
  • the locking element is designed as a pin, which is designed to positively engage in the missile from above, wherein the locking element can be lifted out of the missile and the locking of the missile can thereby be opened.
  • the holding device is designed to hold the tail of the missile, and the holding device has a support element for supporting the missile, the support element being designed as a pin and the pin being designed to positively engage the tail of the missile from behind.
  • One idea on which the present invention is based is to design the holder with which the missile is held on the launch rail so that it can be detached from the missile. Accordingly, weight can be saved in the missile, since there are no components attached to the missile for mounting on the launch rail. Furthermore, the omission of external components for mounting allows an advantageous aerodynamic shape of the missile.
  • the locking element advantageously prevents the missile from detaching prematurely from the holding device.
  • a design of the locking element as a pin, which engages in the missile in a form-fitting manner, represents a design of a locking element that is advantageously easy to implement.
  • the holding device has a support element for supporting the missile, the launch process of the missile can be advantageously stabilized.
  • the fact that the support element is designed as a pin according to the invention represents an embodiment of a support element that is advantageously easy to construct.
  • the missile can be detached from the holding device in a particularly stable manner.
  • the holding device is designed to hold the tail end of the missile allows the holding device to be detached from the missile in an advantageously easy manner.
  • the mechanism can have a ramp section which is designed to guide the pin out of the missile.
  • the holding device can be mounted on the rail body so that it can move linearly along the rail body.
  • the missile can be held by the holding device throughout the launch process, as a result of which a stable launch process can be implemented.
  • the triggering mechanism can be arranged at an exit end of the rail body. This advantageously maximizes the path length over which the missile is sustained during launch.
  • the triggering mechanism can have a projection which is designed to stop a movement of the holding device. This represents a particularly easy-to-manufacture embodiment of a triggering mechanism for releasing the missile from the holding device.
  • Fig. 1a shows a schematic view of a launch rail 100 according to an embodiment of the present invention before the launch of a missile 200 held in the launch rail.
  • the launch rail 100 has a rail body 110 , a releasable holding device 120 and a release mechanism 130 .
  • the holding device 120 is arranged at a bearing end of the rail body 110 .
  • the trigger mechanism 130 is located at the opposite exit end of the rail body 110 .
  • the holding device 120 holds the tail of a missile 200.
  • the triggering mechanism 130 also has a projection 131 on.
  • Fig. 1b shows the in Fig. 1a shown launch rail 100 during the launch process of the missile 200.
  • the missile 200 moves forward along the track body 110 .
  • the holding device 120 holding the missile 200 moves together with the missile 200 and keeps it stable during the launch process. to the in Fig. 1b shown point in time, the holding device 120 hits the triggering mechanism 130. As a result, the holding device 120 is released from the missile 200.
  • FIG. 1c shows the in Fig. 1a shown launch rail 100 after the launch process of the missile 200.
  • the missile 200 released from the holding device 120 and thus from the launch rail 100, continues its movement in the forward direction.
  • the holding device 120 was released from the missile 200 by the triggering mechanism 130 and remains on the launch rail 100.
  • FIG. 2 shows a schematic rear view of the launch rail 100 and the missile 200.
  • the holding device 120 is movably mounted on the rail body 110 .
  • the holding device has two locking elements 121 .
  • the locking elements 121 are in the form of pins which engage in a form-fitting manner in the missile 200 from above.
  • the holding device 120 has two support elements 122 .
  • the support elements 122 are in the form of pins which engage in a form-fitting manner in the missile 200 from behind.
  • the locking elements 121 and support elements 122 prevent movement of the missile 200 relative to the holding device 120.
  • the missile 200 is accordingly held securely by the holding device 120 on the launch rail 100.
  • An optional further locking device is not shown, which can be provided in order to prevent a movement of the holding device 120 until shortly before the planned launch of the missile 200.
  • FIG. 3 shows a schematic sectional view of the holding device 120.
  • the holding device 120 has a locking element 121 and a support element 122 .
  • the locking element 121 is designed as a pin which engages in a form-fitting manner in the missile 200 from above.
  • the support element 122 is designed as a pin which engages in the tail of the missile 200 from behind in a form-fitting manner.
  • FIG. 4 shows a schematic sectional view of the interaction of the triggering mechanism 130 and the holding device 120.
  • the trigger mechanism 130 includes a ramp portion 132 .
  • the missile 200 After the drive of the missile 200 has been ignited, it moves forward together with the movably mounted holding device 120 in the direction of the triggering mechanism 130.
  • the head of the locking element 121 designed as a pin engages in the ramp section 132 of the triggering mechanism 130.
  • the sliding of the head of the pin causes the locking element 121 to move vertically upwards, as indicated by an arrow P1.
  • the locking element 121 is thereby lifted out of the missile 200, as a result of which the locking of the missile 200 is opened.
  • figure 5 shows a further schematic sectional view of the interaction of triggering mechanism 130 and holding device 120.
  • the holding device 120 comes into contact with the projection 131 of the triggering mechanism 130.
  • the projection 131 thereby stops the further movement of the holding device 120, as indicated by an arrow P2 pointing to the right.
  • the locking element 121 has already been pushed up the ramp section 132 to such an extent that it is no longer in contact with the missile 200 .
  • the holding device 120 is released from the missile 200 .

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (6)

  1. Rail de lancement (100) pour un missile (200), comportant un corps de rail (110) ;
    un dispositif de retenue amovible (120) monté sur le corps de rail (110) pour retenir le missile (200) sur le rail de lancement (100), et
    un mécanisme de déclenchement (130) monté sur le corps de rail (110) pour libérer le dispositif de retenue (120) du missile (200) ;
    le dispositif de retenue (120) présentant un élément de verrouillage (121) pour verrouiller le missile (200) sur le dispositif de retenue (120) et le mécanisme de déclenchement (130) étant conçu pour ouvrir l'élément de verrouillage (121) ;
    l'élément de verrouillage (121) étant conçu comme une broche qui est conçue pour s'engager par le haut, par complémentarité de forme, dans le missile (200) ; l'élément de verrouillage (121) pouvant être retiré du missile (200) et permettant ainsi l'ouverture du verrouillage du missile (200) ;
    le dispositif de retenue (120) étant conçu pour retenir l'arrière du missile (200) et le dispositif de retenue (120) présentant un élément d'appui (122) pour soutenir le missile (200), l'élément d'appui (122) étant conçu comme une broche et la broche étant conçue pour s'engager par l'arrière, par complémentarité de forme, dans l'arrière du missile (200).
  2. Rail de lancement (100) selon la revendication 1,
    dans lequel le mécanisme de déclenchement (130) présente une partie rampe (132) qui est conçue pour guider la broche hors du missile (200).
  3. Rail de lancement (100) selon l'une des revendications précédentes,
    dans lequel le dispositif de retenue (120) est monté sur le corps de rail (110) de manière à pouvoir se déplacer linéairement le long du corps de rail (110).
  4. Rail de lancement (100) selon la revendication 3,
    dans lequel le mécanisme de déclenchement (130) est disposé à une extrémité de sortie du corps de rail (110).
  5. Rail de lancement (100) selon la revendication 4,
    dans lequel le mécanisme de déclenchement (130) présente une saillie (131) qui est conçue pour arrêter un déplacement du dispositif de retenue (120).
  6. Système de lancement de missile comprenant un rail de lancement (100) selon l'une des revendications précédentes et un missile (200).
EP19199162.9A 2018-10-10 2019-09-24 Rail de lancement pour un missile Active EP3637035B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018008008.1A DE102018008008A1 (de) 2018-10-10 2018-10-10 Startschiene für einen Flugkörper

Publications (2)

Publication Number Publication Date
EP3637035A1 EP3637035A1 (fr) 2020-04-15
EP3637035B1 true EP3637035B1 (fr) 2022-08-17

Family

ID=68066596

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19199162.9A Active EP3637035B1 (fr) 2018-10-10 2019-09-24 Rail de lancement pour un missile

Country Status (2)

Country Link
EP (1) EP3637035B1 (fr)
DE (1) DE102018008008A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112361873A (zh) * 2020-11-03 2021-02-12 西安航天动力技术研究所 一种轨道式发射火箭的入轨装填机构

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3040629A (en) * 1960-04-11 1962-06-26 Garnett C Duncan Missile launcher
DE3016925A1 (de) * 1980-05-02 1981-11-12 Dornier Gmbh, 7990 Friedrichshafen Starteinrichtung zum tragen und starten von flugkoerpern, insbesondere fuer luftfahrzeuge
US4660456A (en) * 1983-10-03 1987-04-28 Frazer-Nash Limited Airborne missile launcher of modular construction
US5094140A (en) * 1991-03-11 1992-03-10 Techteam, Inc. Missile launcher assembly

Also Published As

Publication number Publication date
DE102018008008A1 (de) 2020-04-16
EP3637035A1 (fr) 2020-04-15

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