EP0259535A2 - Plan stabilisateur avec ailes déployables - Google Patents

Plan stabilisateur avec ailes déployables Download PDF

Info

Publication number
EP0259535A2
EP0259535A2 EP87102097A EP87102097A EP0259535A2 EP 0259535 A2 EP0259535 A2 EP 0259535A2 EP 87102097 A EP87102097 A EP 87102097A EP 87102097 A EP87102097 A EP 87102097A EP 0259535 A2 EP0259535 A2 EP 0259535A2
Authority
EP
European Patent Office
Prior art keywords
wing
bearing
sliding guide
missile
guide bearing
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.)
Withdrawn
Application number
EP87102097A
Other languages
German (de)
English (en)
Inventor
Dieter Dipl.-Ing. Böder
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 EP0259535A2 publication Critical patent/EP0259535A2/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F42B10/16—Wrap-around fins

Definitions

  • the invention relates to a tail unit with deployable wings for projectiles and missiles with the features of the preamble of claim 1.
  • tail assemblies which are used in particular in the case of submunitions which are ejected from carrier projectiles in the target area, are known, for example, from WO 86/02154 (international file number PCT / EPO 85/00452). So that the wing blades in the unfolded state have the same length and are constructed symmetrically, the slide bearing is constructed in these known tail units so that it has an interruption in its central region in which the wing root of the second wing blade with fixed bearing has space in the folded state. Seen in the projectile or missile axis direction, the fixed bearing and the plain bearing coincide in the folded state.
  • a tail unit is also known in which the fixed bearing and that sliding guide bearings are arranged one behind the other in the circumferential direction of the missile.
  • the sliding movement of the sliding guide bearing takes place coaxially with the center axis of the missile when the wing blades are deployed.
  • a disadvantage of this empennage is the fact that after the wing blades are unfolded, they are inclined to one side and therefore - depending on which side the wind power acts on - have a different stability.
  • the object of the present invention is to further develop an empennage of the type mentioned at the outset in such a way that it is simple and robust, and that when the wings are unfolded they are constructed symmetrically outside the shell of the missile.
  • FIG. 1 shows a schematic, perspective illustration of a missile 10 with a tail unit, which is arranged in the rear area and comprises expandable wings 11, the central axis of which is designated by 20. Missiles of this type and projectiles are fired from launch barley or from large-caliber barrel weapons, for example packaged in a carrier storey, and should be ejected from a great distance from the carrier storey and reach point targets with the greatest possible precision.
  • an empennage is required which should have optimal aerodynamic properties, but which is robust and space-saving in order to withstand high acceleration stresses that occur in particular when firing from barrel weapons, and on the other hand to claim as little as possible of the volume of the missile / projectile intended for payloads.
  • FIG. 2 shows an enlarged representation of a cross section through part of the missile 10 according to FIG. 1 with a view of the side edges of a wing 11 of the tail unit.
  • the wing 11 consists of two wing blades, 12, 12a, which are connected to one another on the tip side, for example riveted or electron-beam welded, and which are attached on the root side to separate bearings 17, 17a which can be changed with respect to their circumferential spacing such that the wing blades 12, 12a in unfolded state of the wing 11, which is shown in Fig. 2, are set up roof-like.
  • the blades 12, 12a themselves are made of an elastic and flexible material, such as. B. spring steel, a high-strength light metal alloy or made of a fiber-reinforced plastic, which facilitates their folding and accommodation in the volume of the missile 10, they form a very stable arrangement with excellent aerodynamic properties in the deployed state according to FIG. 2.
  • One of the bearings 17, 17a is an articulated fixed bearing 17, while the other bearing is an articulated sliding guide bearing.
  • This bearing arrangement enables - as can be seen in detail from FIG. 3 - a shot-proof and space-saving accommodation of the wing 11 in the circumferential region of the missile 10, namely that the wing blades 12, 12a are wound around the missile 10 in the circumferential direction in the folded state.
  • the wing 16 is held in rotation by the jacket 16 of the carrier projectile until the missile 10 has been ejected from the carrier projectile, as a rule in the axial direction.
  • the wing blades 12, 12a of each wing 11 lie closely adjacent to one another, which is achieved in that the sliding guide bearing 17a in the circumferential direction of the missile is immediately adjacent to the articulated fixed bearing 17 of each wing 11 is arranged.
  • the wings 11, seen in the radial direction can also be made comparatively long and therefore optimal in terms of aerodynamic requirements, since even these long wings can be accommodated in a space-saving manner.
  • the wing blades of a wing 11 cover at least the bearing area of an adjacent wing (not shown in FIG. 3).
  • the bearings 17, 17a of the wing blades 12, 12a are spaced apart from one another in the circumferential direction, so that the roof-shaped arrangement of the wing blades 12, 12a shown results.
  • the wing blades 12, 12a reach this position in that the articulated sliding guide bearing 17a is removed from the fixed bearing 17a in the circumferential direction when the wing 11 is unfolded.
  • the sliding guide bearing 17a is guided in a groove 15 in such a way that the sliding guide bearing 17a has an increasing distance from the missile center axis 20 with increasing distance from the fixed bearing 17. This measure ensures that the wing blades 12, 12a have a symmetrical structure to the respective wing axis 30 after deployment outside the jacket 16.

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)
  • Toys (AREA)
  • Footwear And Its Accessory, Manufacturing Method And Apparatuses (AREA)
  • Support Of The Bearing (AREA)
EP87102097A 1986-06-05 1987-02-14 Plan stabilisateur avec ailes déployables Withdrawn EP0259535A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3618958 1986-06-05
DE3618958A DE3618958C1 (de) 1986-06-05 1986-06-05 Leitwerk mit entfaltbaren Fluegeln

Publications (1)

Publication Number Publication Date
EP0259535A2 true EP0259535A2 (fr) 1988-03-16

Family

ID=6302355

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87102097A Withdrawn EP0259535A2 (fr) 1986-06-05 1987-02-14 Plan stabilisateur avec ailes déployables

Country Status (5)

Country Link
US (1) US4736908A (fr)
EP (1) EP0259535A2 (fr)
DE (1) DE3618958C1 (fr)
IL (1) IL82683A0 (fr)
NO (1) NO161880C (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3730019C1 (de) * 1987-09-08 1988-12-22 Diehl Gmbh & Co Submunitions-Flugkoerper
DE3838738A1 (de) * 1988-11-15 1990-05-23 Diehl Gmbh & Co Projektil mit ausklappbaren fluegeln
SE508858C2 (sv) * 1997-03-25 1998-11-09 Bofors Ab Fenstabiliserad granat
SE508857C2 (sv) * 1997-03-25 1998-11-09 Bofors Ab Fenstabiliserad base-bleedgranat
DE19944379B4 (de) * 1999-09-16 2007-05-16 Rheinmetall Waffe Munition Patrone
US6435097B1 (en) * 2001-04-09 2002-08-20 The United States Of America As Represented By The Secretary Of The Army Protective device for deployable fins of artillery projectiles
US7448339B2 (en) * 2006-12-20 2008-11-11 Ultra Electronics Ocean Systems, Inc. Winged body having a stowed configuration and a deployed configuration
US8698059B2 (en) * 2012-05-03 2014-04-15 Raytheon Company Deployable lifting surface for air vehicle

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB745252A (en) * 1953-07-29 1956-02-22 Ml Aviation Co Ltd Improvements relating to rocket propelled projectiles
US2923241A (en) * 1957-09-09 1960-02-02 Aerojet General Co Folding stabilizing fins
US3103886A (en) * 1960-10-13 1963-09-17 Charles H Popenoe Coiling fin for tube launched missiles
DE1297514B (de) * 1965-08-03 1969-06-12 Dynamit Nobel Ag Leitwerk fuer Raketen
DE8428118U1 (de) * 1984-09-25 1986-07-03 Rheinmetall GmbH, 4000 Düsseldorf Leitwerk mit entfaltbaren Flügeln

Also Published As

Publication number Publication date
DE3618958C1 (de) 1987-06-25
NO161880C (no) 1989-10-04
NO870934L (no) 1987-12-07
US4736908A (en) 1988-04-12
NO870934D0 (no) 1987-03-06
NO161880B (no) 1989-06-26
IL82683A0 (en) 1987-11-30

Similar Documents

Publication Publication Date Title
DE2828251C1 (de) Patronierte Munition mit Geschoss und verbrennbarer oder teilverbrennbarer Huelse
DE19906969B4 (de) Aus einem Waffenrohr verschießbares leitwerkstabilisiertes Geschoß
EP0232267B1 (fr) Empennage avec ailes escamotables
DE3000347A1 (de) Schutzvorrichtung fuer kampfwagen mit geschuetzrohr
DE2757141C2 (de) Bremsvorrichtung für einen im Flug rotierenden Körper insbes. einen Abwurfkörper
DE3635738C2 (fr)
DE60005239T2 (de) Bremsvorrichtung für die Flugbahngeschwindigkeit eines Geschosses
EP1399706A1 (fr) Projectile d'artillerie a charge utile interchangeable
DE3618958C1 (de) Leitwerk mit entfaltbaren Fluegeln
DE2519507A1 (de) Munition zur bekaempfung von zielen, insbesondere flugzielen im vorbeiflug
DE3618956C1 (de) Leitwerk mit entfaltbaren Fluegeln fuer Geschosse und Flugkoerper
DE2227103A1 (de) Klappleitwerk
DE3643291A1 (de) Drallstabilisiertes traegergeschoss
DE3609865C1 (de) Gefechtskopf mit einer Hohlladung
DE3222378A1 (de) Vorrichtung zur verringerung der empfindlichkeit leitwerksstabilisierter, in luft und/oder wasser sich bewegender gefechtskoerper gegen seitliche anstroemung
DE3730019C1 (de) Submunitions-Flugkoerper
EP0253021A1 (fr) Projectile sous-calibré à portée limitée du type flèche pour arme à canon
DE1027561B (de) Laengsschwingbares Klappleitwerk fuer Raketengeschosse
DE2635676A1 (de) Leitwerk fuer raketen
DE3735481A1 (de) Treibkaefig geringer eigenmasse fuer ein unterkalibriges hochgeschwindigkeits-fluggeschoss
DE3414911A1 (de) Flugkoerper, insbesondere ballistische rakete
DE2721536A1 (de) Projektil mit leitflaechen
DE19509346C2 (de) Leitwerkstabilisierter Flugkörper
DE3016638C1 (de) Splitterbildendes Geschoss
DE3902761C2 (fr)

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): DE ES FR GB IT NL SE

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN

18W Application withdrawn

Withdrawal date: 19900208

RIN1 Information on inventor provided before grant (corrected)

Inventor name: BOEDER, DIETER, DIPL.-ING.