EP0254796A2 - Plan stabilisateur avec ailes déployables pour projectiles et missiles - Google Patents

Plan stabilisateur avec ailes déployables pour projectiles et missiles Download PDF

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Publication number
EP0254796A2
EP0254796A2 EP87102419A EP87102419A EP0254796A2 EP 0254796 A2 EP0254796 A2 EP 0254796A2 EP 87102419 A EP87102419 A EP 87102419A EP 87102419 A EP87102419 A EP 87102419A EP 0254796 A2 EP0254796 A2 EP 0254796A2
Authority
EP
European Patent Office
Prior art keywords
wing
blades
buckling
wing blades
projectiles
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Withdrawn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
EP87102419A
Other languages
German (de)
English (en)
Other versions
EP0254796A3 (fr
Inventor
Dieter Böder
Michael Primus
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 EP0254796A2 publication Critical patent/EP0254796A2/fr
Publication of EP0254796A3 publication Critical patent/EP0254796A3/fr
Withdrawn legal-status Critical Current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
    • F42B10/16—Wrap-around fins

Definitions

  • the invention relates to a tail unit with deployable wings for projectiles and missiles, as defined by the features of the preamble of claim 1.
  • tail assemblies are known for example from WO 86/02154 (international file number PCT / EPO 85/00452). These known tail units have the disadvantage that when the air pressure is strong, the latter can bend or bulge near the wing root. The wing blade facing away from the air attack is particularly at risk.
  • Fig. 1 shows a schematic, perspective view of a missile 10 with a tail unit arranged in the rear area and comprising expandable wing 11.
  • Missiles of this type and projectiles in particular are packaged as submunitions in carrier-shell casings, fired from launchers or from large-caliber barrel weapons and are intended to reach point targets with the greatest possible precision at great distances.
  • Fig. 2 shows a cross section through part of the missile 10 of FIG. 1 with a view of the side edges of a wing 11 of the tail unit, for. B. after ejection from the carrier shell in the target area.
  • 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 13, 13a which can be changed with respect to their circumferential distance in such a way that the wing blades 12 and 12a in the unfolded state of the wing 11, which is shown in Fig. 2, are set up like a roof.
  • the blades 12, 12a themselves are made of an elastic and flexible material, such as. B.
  • One of the bearings 13, 13a is an articulated fixed bearing 13a, while the other bearing 13 is an articulated sliding guide bearing which is guided in a groove 14.
  • the wing blade facing away from the air pressure forces which is designated by 12 in FIG. 2, is particularly at risk of kinking or bulging.
  • the air pressure forces were indicated with an arrow 16.
  • wing blades 12, 12a there is a buckling or bulging outwards or inwards.
  • 2 shows an example in which the wing blade 12 begins to bend outwards, while in FIG. 3 the beginning of the bend of the wing blade 12 is shown inwards.
  • the buckling or bulging of the wing blades is prevented when at the root end, ie. H.
  • a buckling device is arranged between them.
  • FIG. 4 An exemplary embodiment of such a buckling protection is shown in FIG. 4. It essentially consists of at least one wire 125 which is fastened to the wing blades 12 and 12a (for example, inserted and soldered through bores made in the wing blades). The solder joints are labeled 126 and 126a.
  • Fig. 5 the corresponding wing blades are shown in the folded state, with 15 the jacket of the carrier floor is identified.
  • a prerequisite for the effectiveness of the kink protection shown in FIGS. 4 and 5 is, however, that the wing blades tend to buckle or bulge outward without a kink protection. Because the wires only act as tension elements and not as pressure elements, as would be required if the wing blades buckle inwards (Fig. 3).
  • FIGS. 6a to 6c The example of a wing, in which the buckling of the wing blade is guaranteed without kink protection to the outside, is shown in FIGS. 6a to 6c.
  • FIG. 6a shows the side view of the corresponding wing blade 12a, the other parts of the projectile being omitted for the sake of a better overview.
  • the central region 127 is curved outwards, while the edge regions 128 are bent inwards. With this measure, it is achieved that buckling or bulging takes place without kink protection to the outside, and that the kink stability is extremely high without kink protection.
  • the corresponding solder joints of the wires are again designated 126.
  • the kink protection consists of four wires arranged in parallel.
  • 6c shows a sectional illustration of the wing blade 12a along the line A - B.
  • the curved area 127, the edge area 118 and the kink protection 125 consisting of four wires can be clearly seen.
  • 6b shows a view of the wing 11 in the direction of the projectile axis from the rear part of the projectile.

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)
  • Control Of Electric Motors In General (AREA)
  • Feedback Control In General (AREA)
EP87102419A 1986-06-05 1987-02-20 Plan stabilisateur avec ailes déployables pour projectiles et missiles Withdrawn EP0254796A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3618956A DE3618956C1 (de) 1986-06-05 1986-06-05 Leitwerk mit entfaltbaren Fluegeln fuer Geschosse und Flugkoerper
DE3618956 1986-06-05

Publications (2)

Publication Number Publication Date
EP0254796A2 true EP0254796A2 (fr) 1988-02-03
EP0254796A3 EP0254796A3 (fr) 1990-05-23

Family

ID=6302354

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87102419A Withdrawn EP0254796A3 (fr) 1986-06-05 1987-02-20 Plan stabilisateur avec ailes déployables pour projectiles et missiles

Country Status (4)

Country Link
US (1) US4736909A (fr)
EP (1) EP0254796A3 (fr)
DE (1) DE3618956C1 (fr)
NO (1) NO871149L (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1903296A3 (fr) * 2006-09-22 2010-03-17 LFK-Lenkflugkörpersysteme GmbH Palier et verrouillage d'une aile déployable flexible

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE460738B (sv) * 1988-03-16 1989-11-13 Bofors Ab Foer missiler och andra projektiler avsedd utfaellbar vinge
DE3933100A1 (de) * 1988-12-19 1990-06-28 Diehl Gmbh & Co Leitwerk fuer ein unterkalibriges uebungspfeilgeschoss
DE3916690C1 (de) * 1989-05-23 1998-10-01 Bodenseewerk Geraetetech Ausklappbare Flügelanordnung für Flugkörper
US5642867A (en) 1995-06-06 1997-07-01 Hughes Missile Systems Company Aerodynamic lifting and control surface and control system using same
US5927643A (en) * 1997-11-05 1999-07-27 Atlantic Research Corporation Self-deploying airfoil for missile or the like
US6834828B1 (en) 2003-09-23 2004-12-28 The United States Of America As Represented By The Secretary Of The Navy Fin deployment system
DE102006006160B4 (de) * 2006-02-10 2017-05-24 Mbda Deutschland Gmbh Wickelflügel für einen Flugkörper
US8698059B2 (en) * 2012-05-03 2014-04-15 Raytheon Company Deployable lifting surface for air vehicle

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1986002154A1 (fr) * 1984-09-25 1986-04-10 Rheinmetall Gmbh Empennage avec ailes escamotables

Family Cites Families (4)

* 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

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1986002154A1 (fr) * 1984-09-25 1986-04-10 Rheinmetall Gmbh Empennage avec ailes escamotables

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1903296A3 (fr) * 2006-09-22 2010-03-17 LFK-Lenkflugkörpersysteme GmbH Palier et verrouillage d'une aile déployable flexible

Also Published As

Publication number Publication date
NO871149L (no) 1987-12-07
US4736909A (en) 1988-04-12
DE3618956C1 (de) 1987-11-19
NO871149D0 (no) 1987-03-20
EP0254796A3 (fr) 1990-05-23

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Inventor name: BOEDER, DIETER