EP0180722A2 - Missile - Google Patents

Missile Download PDF

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Publication number
EP0180722A2
EP0180722A2 EP85109643A EP85109643A EP0180722A2 EP 0180722 A2 EP0180722 A2 EP 0180722A2 EP 85109643 A EP85109643 A EP 85109643A EP 85109643 A EP85109643 A EP 85109643A EP 0180722 A2 EP0180722 A2 EP 0180722A2
Authority
EP
European Patent Office
Prior art keywords
missile
wings
wing
tail unit
rest position
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.)
Granted
Application number
EP85109643A
Other languages
German (de)
English (en)
Other versions
EP0180722B1 (fr
EP0180722A3 (en
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 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 tail unit comprising a second wing 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.
  • the invention has for its object to provide a missile with a particularly effective and operationally reliable second tail.
  • 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 l tailplane 101 is arranged.
  • This second tail unit L02 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 project 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 illustration of an enlarged detailed illustration 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 an axially extending slot 20 arranged in the outer wall of the missile 100.
  • 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.
  • Special requirements are placed on the means which transfer the wings 14 of the second tail unit 102 from the rest position into their working position.
  • the means for unfolding the wings 14 comprise an inflatable body (airbag) 12, 12 'which, in the rest position of the wings 14, 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 its bearing point on the axes 21 facing end pieces of the sinks 14 recessed in the slots 20 rest on this folded body 12, 12 '.
  • airbag inflatable body
  • 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.
  • a force acting in the radial direction is exerted on the ends of the wings 14 so that they pivot about the axes of rotation 21 and get into their working position, in which they are essentially perpendicular to the Stand longitudinal axis 103 of the missile 100.
  • 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 direction of flight 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)
EP19850109643 1984-09-05 1985-07-31 Missile Expired - Lifetime EP0180722B1 (fr)

Applications Claiming Priority (2)

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

Publications (3)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103522248A (zh) * 2013-10-11 2014-01-22 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

Families Citing this family (22)

* 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
DE102017009671A1 (de) * 2016-11-03 2018-05-03 Diehl Defence Gmbh & Co. Kg Verfahren zum Abwerfen eines Flugkörpers
IL250433B (en) * 2017-02-02 2021-01-31 Israel Aerospace Ind Ltd Apparatus for a vehicle
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
US12007212B2 (en) 2021-10-08 2024-06-11 Simmonds Precision Products, Inc. Joule-Thompson cooler actuation systems
US12068422B2 (en) 2021-10-08 2024-08-20 Simmonds Precision Products, Inc. Systems and methods for cooling electronics
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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103522248A (zh) * 2013-10-11 2014-01-22 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
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

Also Published As

Publication number Publication date
DE3432614A1 (de) 1986-03-13
DE3586163D1 (de) 1992-07-09
US4659037A (en) 1987-04-21
EP0180722B1 (fr) 1992-06-03
ES8801027A1 (es) 1987-12-16
EP0180722A3 (en) 1990-03-21
ES546443A0 (es) 1987-12-16

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