EP0731331B1 - Dispositif de lancement pour missiles autopropulsés, en particulier pour roquettes d'artillerie - Google Patents

Dispositif de lancement pour missiles autopropulsés, en particulier pour roquettes d'artillerie Download PDF

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Publication number
EP0731331B1
EP0731331B1 EP96102429A EP96102429A EP0731331B1 EP 0731331 B1 EP0731331 B1 EP 0731331B1 EP 96102429 A EP96102429 A EP 96102429A EP 96102429 A EP96102429 A EP 96102429A EP 0731331 B1 EP0731331 B1 EP 0731331B1
Authority
EP
European Patent Office
Prior art keywords
launch
support body
missile
contact pins
ready
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
EP96102429A
Other languages
German (de)
English (en)
Other versions
EP0731331A3 (fr
EP0731331A2 (fr
Inventor
Heinrich Gertz
Wolfram Vaihinger
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.)
Wegmann and Co GmbH
Original Assignee
Wegmann and Co 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 Wegmann and Co GmbH filed Critical Wegmann and Co GmbH
Publication of EP0731331A2 publication Critical patent/EP0731331A2/fr
Publication of EP0731331A3 publication Critical patent/EP0731331A3/fr
Application granted granted Critical
Publication of EP0731331B1 publication Critical patent/EP0731331B1/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
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A19/00—Firing or trigger mechanisms; Cocking mechanisms
    • F41A19/58—Electric firing mechanisms
    • F41A19/69—Electric contacts or switches peculiar thereto
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor

Definitions

  • the invention relates to a launcher for self-propelled missiles, especially artillery missiles, with the features from the preamble of Claim 1.
  • Such a launcher is for example in document US-A-36 10 095.
  • the known launcher supports the rocket on the inner wall of the launch tube over several their circumference arranged over most of it their length extending support body made of balsa wood or some other light material.
  • the invention has for its object a launcher the in the preamble of the claim 1 to create the type described which on the one hand is the electrical signal transmission to the missile is carried out so that no tearing cable connections are accepted must and which on the other hand opens possibilities to to prevent the support body after leaving of the launch tube in contact with parts of the missile can guess.
  • a basic idea of the invention initially exists in training the support body so that the electrical Energy transfer over under the force of Compression springs standing contact pins are made in the Ready to fire condition on counter contacts on the inside of the launch tube and each with also under the force of compression springs Contact pins are electrically connected to the electrical mating contacts on the outside of the Missile.
  • the power of the used Compression springs only serve to provide the necessary Contact pressure on the electrical contact pins too produce.
  • the support bodies are like this trained that they leave the launch tube get a strong momentum across the direction of launch and thus thrown outwards, so that they are at a sufficient distance from the missile when the tail leaves the launch tube Has. This momentum is spring loaded Tappet is generated which supports the missile from pull the trigger.
  • the force of the compression springs used for this is much greater than the force of the contact pressure on the electrical contact pins generating Compression springs.
  • a ready to fire Missile F which is at its aft end an empennage L on the inner wall of the launch tube A supports himself while he is in his front area over a total of four at equal angular intervals its circumference arranged support body S1, S2 on the The inner wall of the launch tube A is supported.
  • electrical lines Z which are arranged in the inner wall of the launch tube 8 electrical contacts GK1 are connected, electrical signals fed in below explained by the support body S1 and S2 through to electrical contacts GK2, which are located in the outer surface of the missile F.
  • the signals are the in a known manner Missile engine fed and the missile F sets moving in the direction of launch.
  • Fig. 2 shows a moment just before the full exit of the missile F from the launch tube A. The missile F is still within the launch tube via the tail unit L. A supported while the support body S1 and S2 - and two more, not shown Support body - led out of the launch tube A. and are explained in more detail below Construction after the exit a strong Pulse in the direction of arrow Q, i.e. the transverse direction to Firing direction.
  • Fig. 3 shows that due to this impulse after the complete exit of the Missile F from the launch tube 8, the support body S1 and S2 as far from the missile F in the transverse direction have moved away that no collision with the Tail L more occurs.
  • FIGS. 4 to 10 Structure of the support body S1 in Fig. 1 to 3 in more detail explained.
  • the remaining support bodies are exactly in built the same way.
  • the support body S1 has an upper part 1 and a lower part 2 connected to each other via a screw connection 3 are detachably connected. Through the upper and lower part an interior 13 is formed within the support body delimited.
  • the top of the top 1 is at least in partial areas 1.1 to the inner surface of the launch tube adjusted while the bottom 2.1 of the Lower part 2 adapted to the outer shape of the missile F. is. 4 is the distance between the Bottom 2.1 of the lower part 2 and the top 1.1 of the upper part 1 is shown as a radius section R, the difference in caliber between the missile F and the launch tube A determined.
  • each plunger 4 arranged at its rear end on guide pieces 2.2 with guide surfaces 2.3 in the direction of the bottom 2.1 are movably guided.
  • On the guide pieces 2.2 strong helical compression springs are supported 5 starting at each other with their other end rest a collar 4.2 of the plunger 4 and thus exert a force such that each outer end 4.1 of the plunger 4 in the shown in the figures, not installed condition of the support body from openings from the bottom 2.1 of the lower part 2 protrudes by a predetermined amount.
  • the front ends 4.1 of the plunger 4 are on guide surfaces 2.4 performed in the lower part 2.
  • the support body attached to the missile is on Missile over a under the action of a compression spring 10 guided guide part 9, which is in Extends longitudinally and with its outer part 9.1 in a corresponding groove on the surface of the Missile engages (see Figures 5 and 7).
  • Each of the bottom contact pins 7 is associated with an upper one Contact pin 6 connected via a spiral conductor 8, of both the function of an electrical conductor as well as the function of a compression spring, against the effect of the outer ends 6.1 and 7.1 of the contact pins can be pushed back.
  • I'm ready to fire State are the outer ends 7.1 or 6.1 of the contact pins on corresponding mating contacts GK2 or GK1 (see Fig. 1) of the missile or the Launch tube, the required contact pressure is generated by the spiral ladders 8.
  • the spiral ladders 8 Of course is the one that acts as compression springs Spiral head 8 generated pressure much lower than that generated by the helical compression springs 5 Pressure to push off the support body after the Launch.
  • the contact pins 6 and 7 can in addition to the Ignition signals further signals for the transmission of electrical information between one outside the Launch tube lying control device and Missiles are directed.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Elimination Of Static Electricity (AREA)

Claims (4)

  1. Dispositif de lancement pour engins volants autopropulsés (F), en particulier pour missiles d'artillerie, comportant un canon de lancement (A), dans lequel l'engin volant (F), à l'état prêt au lancement, est disposé de telle manière qu'il s'appuie sur son extrémité arrière par un empennage (L) et dans la région antérieure par plusieurs corps d'appui (51, 52) disposés sur son pourtour sur la paroi intérieure du canon (A), lesdits corps d'appui (51, 52) s'appliquant contre l'engin volant (F), de telle manière que, lors du lancement, ils sortent du canon (A) en même temps que l'engin volant (F), caractérisé en ce que chaque corps d'appui (S1) est composé d'une partie supérieure (1) qui s'applique à l'état prêt au lancement par sa face supérieure (1.1) contre la paroi intérieure du canon (A) et une partie inférieure (2) s'appliquant à l'état prêt au lancement par sa face inférieure (2.1) contre l'engin volant (F) et en ce que la partie supérieure (1) et la partie inférieure (2) sont assemblées mutuellement de manière solide par des liaisons détachables (3) et que dans la partie inférieure (2) sont disposées plusieurs tiges de contact électriques (7) inférieures, mobiles et se dirigeant sous isolement électrique par rapport au corps d'appui (S1) en direction de la face inférieure (2.1), lesdites tiges de contact (7) étant placées chacune sous l'effet d'un ressort de compression (8) de telle manière que leurs extrémités extérieures (7.1), à l'état non monté du corps d'appui, émergent dans une proportion prédéterminée d'orifices pratiqués sur la face inférieure (2.1), tandis qu'à l'état prêt au lancement elles sont en contact avec des contre-fiches électriques (GK2) présentes sur la face extérieure de l'engin volant (F) et que, dans la partie supérieure (1), sont disposées plusieurs tiges de contact électriques (6) supérieures mobiles et se dirigeant, sous isolement électrique par rapport au corps d'appui, en direction de la face supérieure (1.1), chaque tige de contact (6) étant placée sous l'effet d'un ressort de compression (8) de telle manière que leurs extrémités extérieures (6.1), à l'état non monté du corps d'appui, émergent dans une proportion prédéterminée d'orifices pratiqués sur la face supérieure (1.1), tandis qu'à l'état prêt au lancement elles sont en contact avec des contre-fiches électriques (GK1) présentes sur la face intérieure du canon de lancement (A) et que chaque tige de contact électrique (6) supérieure est reliée de manière électriquement conductrice à au moins une fiche de contact électrique (7) inférieure.
  2. Dispositif de lancement selon la revendication 1, caractérisé en ce que dans la partie inférieure sont disposés au moins deux pointeaux (4) mobiles et se dirigeant en direction de la face inférieure (2.1), ces pointeaux étant chacun sous l'effet d'un ressort de compression (5) de telle sorte que leurs extrémités extérieures (4.1), à l'état non monté du corps d'appui (S1), émergent dans une proportion prédéterminée d'orifices pratiqués sur la face inférieure (2.1) de la partie inférieure (2), tandis qu'à l'état prêt au lancement ils sont totalement enfoncés, sous pression dans ladite partie inférieure (2) en s'opposant à l'effet des ressorts de compression (5).
  3. Dispositif de lancement selon les revendications 1 ou 2, caractérisé en ce que la partie supérieure (1) et la partie inférieure (2) du corps d'appui (S1) sont reliées mutuellement par des boulonnages (3).
  4. Dispositif de lancement selon la revendication 2, caractérisé en ce que la liaison conductrice entre les tiges de contact électriques (6) supérieures et les tiges de contact électriques (7) inférieures s'effectue respectivement par un conducteur spiralé (8) lequel exerce l'effet d'un ressort sur les tiges de contact (6, 7) mutuellement reliées.
EP96102429A 1995-03-07 1996-02-17 Dispositif de lancement pour missiles autopropulsés, en particulier pour roquettes d'artillerie Expired - Lifetime EP0731331B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19508008 1995-03-07
DE19508008A DE19508008A1 (de) 1995-03-07 1995-03-07 Abschußvorrichtung für selbstangetriebene Flugkörper, insbesondere Artillerieraketen

Publications (3)

Publication Number Publication Date
EP0731331A2 EP0731331A2 (fr) 1996-09-11
EP0731331A3 EP0731331A3 (fr) 1996-11-27
EP0731331B1 true EP0731331B1 (fr) 1998-04-15

Family

ID=7755900

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96102429A Expired - Lifetime EP0731331B1 (fr) 1995-03-07 1996-02-17 Dispositif de lancement pour missiles autopropulsés, en particulier pour roquettes d'artillerie

Country Status (2)

Country Link
EP (1) EP0731331B1 (fr)
DE (2) DE19508008A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008017437A1 (de) * 2008-04-03 2009-10-08 Rheinmetall Waffe Munition Gmbh Treibkäfiggeschoss
IT1400621B1 (it) * 2010-05-13 2013-06-14 Oto Melara Spa Sistema di comunicazione dati ad una spoletta di un'arma da fuoco.
WO2015082701A1 (fr) * 2013-12-06 2015-06-11 Rheinmetall Waffe Munition Gmbh Dispositif de contact modulaire, permettant en particulier la mise en contact électrique d'une arme dans laquelle se trouve une munition
DE102014016340B3 (de) * 2014-11-05 2015-08-20 Bundesrepublik Deutschland, vertreten durch das Bundesministerium der Verteidigung, vertreten durch das Bundesamt für Ausrüstung, Informationstechnik und Nutzung der Bundeswehr Programmiergerät zum Programmieren einer programmierbaren Artilleriemunition
FR3099393B1 (fr) 2019-08-01 2022-07-08 Psa Automobiles Sa Presse d’emboutissage avec lancement de galet
DE102021000884B4 (de) 2021-02-19 2023-07-27 Mbda Deutschland Gmbh Nutzlastträger sowie dichtungs-kit und verbindungsverfahren zum abdichten eines zwischenraumes
CN113357963B (zh) * 2021-06-15 2023-03-07 湖北航天技术研究院总体设计所 一种用于控制发射装置辅助支腿下放的方法和系统

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE310009C (fr) *
US2998780A (en) * 1956-05-28 1961-09-05 William B Anspacher High velocity, fin stabilized projectile, rifled barrel gun system
US3120784A (en) * 1962-02-19 1964-02-11 William M Magers Booster contactor
US3610095A (en) * 1967-06-29 1971-10-05 Us Army Rocket means for driving a free punch
IL37041A (en) * 1971-06-14 1976-02-29 State Of Il Ministry Of Def Forward sabot for sub-calibre projectile with delayed detachment
US4455916A (en) * 1982-02-22 1984-06-26 The United States Of America As Represented By The Secretary Of The Navy Armament shorting arrangement
DE3211011A1 (de) * 1982-03-25 1983-09-29 Dynamit Nobel Ag, 5210 Troisdorf Uebungsrakete
DE3414911A1 (de) * 1984-04-19 1985-10-24 Dynamit Nobel Ag, 5210 Troisdorf Flugkoerper, insbesondere ballistische rakete
US4638739A (en) * 1986-02-14 1987-01-27 The United States Of America As Represented By The Secretary Of The Army Sabot for an electromagnetically-accelerated, unguided hypervelocity penetrator
USH405H (en) * 1987-08-24 1988-01-05 The United States Of America As Represented By The Secretary Of The Army Rocket/launcher interface
DE3939037C2 (de) * 1989-11-25 1994-01-27 Diehl Gmbh & Co Rohrwaffenförmige Starteinrichtung für Unterwasser-Projektil

Also Published As

Publication number Publication date
EP0731331A3 (fr) 1996-11-27
DE19508008A1 (de) 1996-09-12
DE59600152D1 (de) 1998-05-20
EP0731331A2 (fr) 1996-09-11

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