EP0180722B1 - Missile - Google Patents

Missile Download PDF

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Publication number
EP0180722B1
EP0180722B1 EP19850109643 EP85109643A EP0180722B1 EP 0180722 B1 EP0180722 B1 EP 0180722B1 EP 19850109643 EP19850109643 EP 19850109643 EP 85109643 A EP85109643 A EP 85109643A EP 0180722 B1 EP0180722 B1 EP 0180722B1
Authority
EP
European Patent Office
Prior art keywords
missile
blades
rest
fact
longitudinal axis
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
EP19850109643
Other languages
German (de)
English (en)
Other versions
EP0180722A3 (en
EP0180722A2 (fr
Inventor
Klaus Unterstein
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall 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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0180722A2 publication Critical patent/EP0180722A2/fr
Publication of EP0180722A3 publication Critical patent/EP0180722A3/de
Application granted granted Critical
Publication of EP0180722B1 publication Critical patent/EP0180722B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/20—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces

Definitions

  • the invention relates to a missile according to the preamble of patent claim 1.
  • Missiles are to be understood as rockets launched from launcher tubes as well as projectiles fired from tubular weapons which have a tail unit for stabilizing the trajectory.
  • a second wing-surrounding tail unit is often provided, which is arranged in front of the tail unit in the direction of flight. A particularly great effect can be achieved with this second tail unit if the wings of this tail unit protrude far beyond the diameter of the missile.
  • a missile which corresponds to the features of the preamble of claim 1.
  • a pyrotechnically drivable motor is used to swing open the front stabilizing wings folded into the housing.However, it is arranged in the area of the wing bearing racks and therefore requires a considerable amount of energy to open, with none of the holding means securing the idle wing wings and releasing them for the opening process Disclosures are disclosed.
  • the invention has for its object to provide a missile corresponding to the features of the preamble of claim 1 with a particularly effective and reliable working second tail unit, which can be safely opened even after a very long storage time and with large acceleration loads.
  • FIG. 1 shows a schematic representation in side view of a missile 100 with a tail unit 101 provided for the trajectory stabilization and a tail unit 102 comprising a second wing 14, which seen in the direction of flight before the Tail unit 101 is arranged.
  • This second tail 102 enables the flight path of the missile 100 to be influenced particularly precisely in the final phase of its flight path.
  • Wings 14, which are designed to protrude far beyond the diameter of the missile 100, are particularly effective for this purpose.
  • the wings 14 of this second tail unit 102 are designed to be retractable, at least during the launch or launch process and only afterwards, but at the latest at the beginning of the final phase of the trajectory, by means explained in more detail below, in order to get into their working position.
  • FIG. 2 shows a partial sectional view of an enlarged detail of the missile according to FIG. 1, namely the middle part at the height of the second tail unit 102.
  • a wing 14 that is folded out in the working position and a wing 14 that is folded in the rest position can be seen.
  • the wing 14 In the rest position, the wing 14 is in an axially extending slot 20 arranged in the outer wall of the missile 100.
  • the wings 14 In order to move from the rest position into the working position, the wings 14 are rotatably mounted about axes 21 arranged perpendicularly with respect to the longitudinal axis 103 of the missile 100.
  • the opening is expediently against the direction of flight of the missile 100, so that attacking air forces support the opening process.
  • the means for unfolding the wings 14 comprise an inflatable body (airbag) 12, 12 'which, when the wings 14 are in the rest position, is folded up in a confined space essentially in the area of the longitudinal axis 103 of the missile 100 in such a way that their bearing point on the axes 21 facing end pieces of the sinks 14 sunk in the slots 20 rest on this folded body 12, 12 '. From this folded position, this inflatable body 12, 12 'can be inflated by supplying gas, it preferably expanding in the radial direction and being inflatable to an essentially disk-shaped structure.
  • airbag inflatable body
  • Reference number 12 denotes the inflatable body in the folded state; Reference number 12 'the inflated state.
  • a high-tension gaseous medium for acting on the body 12, 12 ' is carried in a compressed gas container 3 which is connected to the inflatable body 12, 12' via gas channels 4, 6 with the interposition of an optionally electrically remote-controlled pressure reducing valve 5.
  • the compressed gas container 3 is closed by a gas-tight closure 2.
  • This closure 2 is removed in order to initiate the opening process of the wings 14, for example by means of a pyrotechnic primer 1.
  • high-tension gas for the purpose of unfolding the wing 14 acts on the inflatable body 12, 12 'and gives it the shape clearly recognizable in FIG. 4, a fuse must first be removed which locks the wing 14 in the rest position within the axial slot 20.
  • This fuse consists of a slide 7, which is slidably mounted in the gas channel 6 in the direction of the longitudinal axis 103 and which carries a cup-shaped retaining disk 8, which engages with its side wall 8 'in a recess 23 arranged in the outer edge 22 of the wing 14.
  • gas flowing out of the compressed gas container 3 after removal of the closure 2 reaches the gas channel 6 via the gas channel 4 and the pressure reducing valve 5 and moves the slide 7 so far in the flight direction along the axis 103 that the side wall 8 'of the cup-shaped holding disk 8 disengages from the recess 23 of the wing 14 and thereby releases it.
  • the movement of the slide 7 then opens a bore 11 in the gas channel 6, which connects it to the inflatable body 12, 12 'and enables it to be inflated by the gas pressure present in the gas channel 6. Due to the radial expansion of the inflatable body 12, 12 ', the wings 14 are swung around suddenly and thus get into their working position in which they are locked by spring-loaded bolts 24 which engage in recesses 25 arranged in the vicinity of the axis of rotation 21 in the wing 14.
  • the means provided according to the invention for unfolding the wings 14 can be accommodated in a comparatively narrow space and work even after a very long storage time even under high acceleration loads
  • the wings 14 of the tail unit are arranged in the radial direction and are arranged inside the shell of the missile 100. Its end pieces facing the missile axis rest on an inflatable body 12 which is folded up in the idle state. When this inflatable body 12 is subjected to a gas pressure, it expands and pushes the wings 14 outward in the radial direction, so that they get into their working position.
  • the inflatable body 12, 12 ′ consists of a gas-tight material that can withstand high pressure loads.
  • a fabric-reinforced rubber cover or a cover made of a plastic is particularly suitable.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (4)

  1. Missile, avec un empennage arrière (101) et un second empennage (102) disposé à l'avant du précédent, dont les ailettes (14) sont constituées de façon à se déployer dans la direction opposée à la direction du vol, grâce à des moyens prévus à cet effet, les ailettes (14) étant disposées en position de repos dans des fentes axiales (20) dans la paroi extérieure du missile (100) et pouvant tourner autour d'axes (21) disposés perpendiculairement à l'axe longitudinal (103) du missile (100), caractérisé en ce que pour le blocage des ailettes (14) en position de repos, il est prévu un poussoir (7) coulissant dans une conduite de gaz (6), dans la direction de l'axe longitudinal (103), et porta t un disque d'arrêt (8) en forme de cuvette, dont la paroi latérale (8') pénètre dans un évidement (23) pratiqué dans le bord extérieur (22) de l'ailette (14), et en ce que les moyens prévus pour déployer les ailettes (14) à l'extérieur sont constitués par un corps (12) pouvant être alimenté en gaz sous pression (sac gonflable) par l'intermédiaire de la conduite de gaz (6).
  2. Missile selon la revendication 1, caractérisé en ce que dans la position de repos de l'ailette (14), le sac gonflable est replié, essentiellement dans la zone de l'axe longitudinal (103) du missile (100), de telle sorte que les parties terminales, opposées à leurs points de montage sur les axes (21), des ailettes (14) enfoncées dans la fente (20), reposent sur lui et en ce qu'il peut se gonfler, de préférence radialement, pour former un corps essentiellement en forme de disque.
  3. Missile selon la revendication 1 ou 2, caractérisé en ce que les moyens pour déployer les ailettes (14) comprennent un réservoir de gaz sous pression (3), et en ce que le corps (12, 12') peut être relié au réservoir de gaz sous pression (3) au moyen des conduites (4, 6) faisant passer le gaz.
  4. Missile selon l'une des revendications 1 à 3, caractérisé en ce que pour le blocage de l'ailette, il est prévu un boulon (24) contraint par un ressort qui, après le déploiement de l'ailette (14), pénètre dans un évidement (25) situé dans l'ailette (14) au voisinage de l'axe de rotation (21).
EP19850109643 1984-09-05 1985-07-31 Missile Expired - Lifetime EP0180722B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19843432614 DE3432614A1 (de) 1984-09-05 1984-09-05 Flugkoerper
DE3432614 1984-09-05

Publications (3)

Publication Number Publication Date
EP0180722A2 EP0180722A2 (fr) 1986-05-14
EP0180722A3 EP0180722A3 (en) 1990-03-21
EP0180722B1 true EP0180722B1 (fr) 1992-06-03

Family

ID=6244693

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19850109643 Expired - Lifetime EP0180722B1 (fr) 1984-09-05 1985-07-31 Missile

Country Status (4)

Country Link
US (1) US4659037A (fr)
EP (1) EP0180722B1 (fr)
DE (2) DE3432614A1 (fr)
ES (1) ES8801027A1 (fr)

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3507677A1 (de) * 1985-03-05 1986-09-11 Diehl GmbH & Co, 8500 Nürnberg Flugkoerper mit ueberkalibrigem leitwerk
FR2812936A1 (fr) * 1986-08-12 2002-02-15 Aerospatiale Missile a voilure variable
DE3721512C1 (de) * 1987-06-30 1989-03-30 Diehl Gmbh & Co Flugkoerper mit ueberkalibrigem Leitwerk
DE3918244A1 (de) * 1989-06-05 1990-12-06 Diehl Gmbh & Co Von einem flugkoerper wegklappbarer fluegel
US5120947A (en) * 1990-03-29 1992-06-09 International Totalizator Systems, Inc. Apparatus and method for processing a ticket
DE4020897C2 (de) * 1990-06-30 1993-11-11 Diehl Gmbh & Co Einrichtung zum Entriegeln und Ausschwenken der Ruderblätter eines Projektiles
DE4105142A1 (de) * 1991-02-20 1992-08-27 Diehl Gmbh & Co Projektil mit ausklappbarem leitwerk
US5211358A (en) * 1991-05-13 1993-05-18 General Dynamics Corporation Airfoil deployment system for missile or aircraft
US6073880A (en) * 1998-05-18 2000-06-13 Versatron, Inc. Integrated missile fin deployment system
US6186443B1 (en) 1998-06-25 2001-02-13 International Dynamics Corporation Airborne vehicle having deployable wing and control surface
DE10162136B4 (de) 2001-12-18 2004-10-14 Diehl Munitionssysteme Gmbh & Co. Kg Aus einem Rohr zu verschießender Flugkörper mit überkalibrigem Leitwerk
DE10205043C5 (de) 2002-02-07 2010-06-17 Diehl Bgt Defence Gmbh & Co. Kg Aus einem Rohr zu verschließender Flugkörper mit überkalibrigem Leitwerk
US7800031B2 (en) * 2005-09-07 2010-09-21 Omnitek Partners Llc Actuators for gun-fired projectiles and mortars
FR2909972B1 (fr) * 2006-12-18 2009-10-23 Novadem Sarl Aeronef a decollage vertical
FR2952712A1 (fr) 2009-11-16 2011-05-20 Nexter Munitions Corps de projectile equipe d'appendices deployables
CN103522248B (zh) * 2013-10-11 2015-08-05 北京航天新风机械设备有限责任公司 一种用于舵/翼面折叠的专用工装
EP3318490B1 (fr) * 2016-11-03 2019-06-12 Diehl Defence GmbH & Co. KG Procédé d'éjection d'un missile
IL250433B (en) * 2017-02-02 2021-01-31 Israel Aerospace Ind Ltd Device for car
US11300390B1 (en) 2018-03-05 2022-04-12 Dynamic Structures And Materials, Llc Control surface deployment apparatus and method of use
CN112525016A (zh) * 2020-12-22 2021-03-19 湖北航天化学技术研究所 一种气体产生装置及驱动装置
US12068422B2 (en) 2021-10-08 2024-08-20 Simmonds Precision Products, Inc. Systems and methods for cooling electronics
US12007212B2 (en) 2021-10-08 2024-06-11 Simmonds Precision Products, Inc. Joule-Thompson cooler actuation systems
CN113899265A (zh) * 2021-10-12 2022-01-07 西安现代控制技术研究所 一种基于光电元件的折叠舵翼张开时间测量装置

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3047257A (en) * 1958-04-24 1962-07-31 Martin Marietta Corp Device for changing airfoil profile
US3633846A (en) * 1970-05-28 1972-01-11 Us Navy Expandable aerodynamic fin
DE2342783C2 (de) * 1973-08-24 1983-12-22 Rheinmetall GmbH, 4000 Düsseldorf Mit einem Leitwerk versehenes Geschoß
DE2518593C3 (de) * 1975-04-26 1979-12-06 Diehl Gmbh & Co, 8500 Nuernberg Mörsergeschoß
SE428969B (sv) * 1977-02-09 1983-08-01 Bofors Ab Anordning vid fenstabiliserad granat
US4143838A (en) * 1977-08-22 1979-03-13 The United States Of America As Represented By The Secretary Of The Navy Folding fin assembly detent
US4203569A (en) * 1977-10-17 1980-05-20 Bei Electronics, Inc. Fin and nozzle unit for a free-flight rocket
DE7804927U1 (de) * 1978-02-18 1978-06-01 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Vorrichtung zum ausklappen von schwenkfluegeln
US4364531A (en) * 1980-10-09 1982-12-21 Knoski Jerry L Attachable airfoil with movable control surface
US4478150A (en) * 1983-01-12 1984-10-23 The United States Of America As Represented By The Secretary Of The Army Cartridge with elastic pusher cup
US4586681A (en) * 1983-06-27 1986-05-06 General Dynamics Pomona Division Supersonic erectable fabric wings

Also Published As

Publication number Publication date
ES546443A0 (es) 1987-12-16
ES8801027A1 (es) 1987-12-16
EP0180722A3 (en) 1990-03-21
US4659037A (en) 1987-04-21
DE3586163D1 (de) 1992-07-09
DE3432614A1 (de) 1986-03-13
EP0180722A2 (fr) 1986-05-14

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