EP0232267B1 - Empennage avec ailes escamotables - Google Patents

Empennage avec ailes escamotables Download PDF

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Publication number
EP0232267B1
EP0232267B1 EP85904619A EP85904619A EP0232267B1 EP 0232267 B1 EP0232267 B1 EP 0232267B1 EP 85904619 A EP85904619 A EP 85904619A EP 85904619 A EP85904619 A EP 85904619A EP 0232267 B1 EP0232267 B1 EP 0232267B1
Authority
EP
European Patent Office
Prior art keywords
leaves
wing
tail unit
pin
fact
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
Application number
EP85904619A
Other languages
German (de)
English (en)
Other versions
EP0232267A1 (fr
Inventor
Dieter 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 EP0232267A1 publication Critical patent/EP0232267A1/fr
Application granted granted Critical
Publication of EP0232267B1 publication Critical patent/EP0232267B1/fr
Expired 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.
  • a tail unit of the type mentioned is known from DE-C-3 026 409.
  • This Leitverk preferably comprises a wing element made of flexible cloth material, which is double-walled and by means of a plurality, for. T. telescopic struts comprising holding device can be folded out.
  • the holding device consists of a large number of parts which take up a relatively large space within the missile and thus represent a considerable dead load component. In addition, the production of these parts requires considerable costs. Finally, problems arise in the design of the holding device for the high acceleration values that occur when projectiles are fired.
  • each wing comprising two wing blades, which are connected on the tip side and are attached on the root side to separate bearings which can be changed in terms of their circumferential spacing, the wing blades in deployed roof-like condition.
  • a particularly disadvantage of these known wings is that the wing blades are not constructed symmetrically to one another.
  • the invention has for its object to provide a tail unit of the type mentioned, which can be manufactured inexpensively and withstands the highest acceleration stresses when firing projectiles and has a high stability against laterally acting air forces.
  • Fig. 2 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 are fired from launchers or from large-caliber barrel weapons and are intended to reach point targets at great distances with the greatest possible precision.
  • a stabilizer is required for trajectory stabilization and / or final phase steering, 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 guns, and on the other hand as little as possible of that intended for payloads To claim the volume of the missile / projectile.
  • Fig. 1 shows an enlarged view of a cross section through part of the missile 10 of FIG. 2 with a view of the side edges of a wing 11 of the tail unit.
  • the vane 11 is composed of two diegelblä t tern, 12, 12a, the tip side connected to each other, for example riveted, and the root side variable to separate, with respect to their circumferential spacing bearings 17, 17a are mounted so that the blades 12, 12 in the unfolded State of the wing 11, which is shown in Fig. 1, 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 17, 17a is an articulated fixed bearing 17a, while the other bearing is an articulated sliding guide bearing. The exact structure of these bearings will be explained in more detail later with reference to other figures of the drawing (Fig. 4, Fig. 5).
  • 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 peripheral region of the missile 10, namely in the folded state, the wing blades 12, 12a are wound circumferentially around the rear part of the missile 10.
  • This principle is known per se from conventional winding tail units. However, these are only connected linearly to the outer surface of a projectile or missile and therefore, when unfolded, do not have the stability required for precision approaches.
  • the wing blades 12, 12 a of each wing 11 lie closely adjacent to one another, which is achieved in that the sliding guide bearing 17 is arranged in parallel directly next to the articulated fixed bearing 17 a of each wing 11.
  • 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.
  • 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 13, 13a shown results.
  • the wing blades 13, 13a reach this position in that the articulated sliding guide bearing 17 is removed from the fixed bearing 17a in the circumferential direction when the wing 11 is unfolded.
  • the structure of the wing root and its attachment in the area of the bearings 17, 17a is explained in more detail below with reference to FIGS. 4 and 5.
  • FIG. 4 shows a view of a part of the wing blade 12a and the jacket 16 of the missile 10 with a view from the direction of the arrow 4 according to FIG. 1. Only details of the articulated sliding guide bearing 17 are shown in FIG. 4, while the articulated fixed bearing 17a, to which the other wing 12 is attached is not visible.
  • FIG. 5, shows a section through the wing 11, along the line 5 - 5 according to FIG. 1, with a view of parts of the casing 16 of the missile 10. In this figure, the articulated fixed bearing 17a can also still be seen.
  • Each bearing 17, 17a comprises a hinge part 13, 13a which is rotatably mounted around a pin 31, 31a, 31b, which is fixedly arranged in the jacket 16 of the missile 10 and is slidably mounted.
  • Each of the pins 31 consists of at least two parts 31 a, 31 b to facilitate the assembly of the wing blade 12, 12a.
  • the wing leaves 12, 12a are fastened in the hinge parts 13, 13a, riveting or gluing preferably being offered for the fastening.
  • the slidably mounted pin 31 of the articulated slide guide bearing 17 (FIG. 4) can slide in parallel slideways 15 between two end positions. In the first end position - in this case, the vanes 11 are folded in according to FIG.
  • the pins 31 of both bearings 17, 17a are arranged immediately adjacent to one another.
  • the pin 31 of the sliding guide bearing 17 is max. arranged away from the pin 31 of the articulated fixed bearing 17a, which corresponds to the unfolded state of the wing 11 according to FIG. 1.
  • the wing blades 12, 12a are expediently curved in the direction of their longitudinal extension, so that they practically form part of a cylinder jacket.
  • This curvature can the wing blades 12, 12a made of an elastic material by known manufacturing processes, such as. B. rollers, are impressed.
  • the expedient curvature of the wing blades 12, 12a can also be brought about in that the hinge parts 13, 13a have a clamping slot for fastening the wing blades 12, 12a, which slot is arc-shaped in accordance with the desired curvature.
  • the curvature of the wing blades 12, 12a is temporarily pressed flat, so that the wing blades 12, 12a come to lie closely one above the other in a space-saving manner.
  • the wing blades 12, 12a tend to take up the embossed curvature again, so that the unfolding process is thereby promoted.
  • This curvature gives the wing blades 12, 12a excellent kink stability under pressure and thus ensures the advantageous aerodynamic properties of the tail unit.
  • a second curvature is also impressed on the wing blades 12, 12a, for example by rolling, which likewise promotes their unfolding and their stability in the unfolded state.
  • This curvature also contributes to the fact that the wing blades 12, 12a are still biased in the unfolded state in such a way that the slidably mounted pins 31, 31a, 31b are resiliently pressed into their end position and held there.
  • the hinge part 13 of the fixed bearing 17a does not run over the entire width of the wing leaf 12, but leaves space on both sides for the two lying in alignment in the folded state Partial hinges of the articulated sliding guide bearing 17.
  • the wing leaf 12a connected to the sliding guide bearing 17 contains a window-shaped recess in the middle, while that with the articulated fixed bearing 17 connected wing blade 12 has recesses in the side region of the bearing.
  • the missile 10 is around its Longitudinal axis rotates, i.e. has a twist.
  • This swirl can be imparted to the missile 10 in a simple manner in that at least one of the wing blades 12, 12a of the wing 11 is turned or twisted with respect to the longitudinal axis of the missile 10.
  • This employment is expediently achieved in that the slideways 15 are of different lengths, so that the locking pins 32 engage at different distances from the pin 31 and thereby twist the wing blade connected to them.

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)
  • Tents Or Canopies (AREA)
  • Pivots And Pivotal Connections (AREA)

Abstract

Une aile escamotable (11) permettant une économie d'espace, pour aérostat ou missile (10), composée de deux éléments d'aile (12, 12a) de préférence convexe, qui sont reliés à leurs pointes, mais sont attachés à leur racine en divers points (17, 17a). Un des supports (17a) est fixe et articulé, alors que le deuxième (17) est coulissant et articulé. Dans l'état replié les éléments d'aide (12, 12a) sont enroulés directement autour de la circonférence de l'aérostat (10) et les supports (17, 17a) sont juxtaposés. Dans l'état déplié de l'aile (11) les supports (17, 17a) sont disposés à une certaine distance l'un de l'autre, de sorte que les éléments d'aile (12, 12a), une fois montés, assument la forme d'un toit.

Claims (6)

1. Empennage comportant des ailettes déployables (11) pour engins balistiques et missiles (10), chaque ailette (11) comprenant deux lames (12, 12a) qui sont reliées l'une à l'autre par la pointe et sont fixées à leur base par des appuis (17, 17a) séparés dont l'écartement périphérique est variable, de façon qu'à l'état déployé les lames (12, 12a) des ailettes (11) soient dressées en formant une sorte de toit, que les appuis (17, 17a) consistent en un appui fixe (17) et un appui articulé à glissière (17a) et que ce dernier appui (17a) comprend une partie charnière (13) qui repose avec pivotement possible sur un pivot (31) monté glissant dans l'enveloppe (16) de l'engin (10), caractérisé en ce qu'également l'appui fixe (17) est articulé et repose sur un pivot (31) en pouvant tourner, en ce que les deux lames (12, 12a) de l'ailette sont établies symétriquement l'une par rapport à l'autre, et en ce que les lames (12, 12a) des ailettes sont chacune cintrées, suivant leur direction longitudinale et perpendiculairement à cette direction.
2. Empennage selon la revendication 1, caractérisé en ce que chaque pivot (31, 31 a, 31 b) est constitué par au moins deux parties (31 a, 31 b).
3. Empennage selon l'une des revendications 1 ou 2, caractérisé en ce qu'il est prévu, reposant sur l'axe longitudinal du pivot (31) supporté avec possibilité de glissement, deux chevilles d'arrêt (32) supportées avec possibilité de glissement du pivot (31) dans la direction longitudinale, lesquelles s'encliquètent, sollicitées par des ressorts de compression (30) et après avoir atteint l'extrémité d'un guide à glissement (15) dans un renfoncement (15a) disposé à cet endroit et verrouillent par suite la lame (12a) de l'ailette.
4. Empennage selon l'une des revendications 1 à 3, caractérisé en ce que les lames (12, 12a) de l'ailette sont reliées aux parties charnière (13, 13a), en étant de préférence rivetées, et en ce que la courbure des lames d'ailette (12, 12a) leur est imprime par une conformation correspondante de la fente de fixation prévue dans les parties de charnière (13, 13a) pour fixer les lames de l'ailette.
5. Empennage selon l'une des revendications 1 à 4, caractérisé en ce que les guides à glissement sont de longueur différente, de sorte que les chevilles d'arrêt (32) s'encliquètent à une distance d'écartement différente par rapport au pivot (31) et par suite produisant le gauchissement de la lame d'ailette (12a) qui leur est liée.
6. Empennage selon l'une des revendications 1 à 5, caractérisé en ce que les lames (12, 12a) de l'ailette sont encore précontraintes, même à l'état déployé, de sorte que les pivots (31, 31a, 31b), supportés avec possibilité de glissement, sont maintenus en position d'extrémité par une force de ressort.
EP85904619A 1984-09-25 1985-09-06 Empennage avec ailes escamotables Expired EP0232267B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3435063 1984-09-25
DE3435063 1984-09-25

Publications (2)

Publication Number Publication Date
EP0232267A1 EP0232267A1 (fr) 1987-08-19
EP0232267B1 true EP0232267B1 (fr) 1989-03-29

Family

ID=6246238

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85904619A Expired EP0232267B1 (fr) 1984-09-25 1985-09-06 Empennage avec ailes escamotables

Country Status (5)

Country Link
US (1) US4699334A (fr)
EP (1) EP0232267B1 (fr)
DE (3) DE8428118U1 (fr)
ES (1) ES296987Y (fr)
WO (1) WO1986002154A1 (fr)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3618956C1 (de) * 1986-06-05 1987-11-19 Rheinmetall Gmbh Leitwerk mit entfaltbaren Fluegeln fuer Geschosse und Flugkoerper
DE3618958C1 (de) * 1986-06-05 1987-06-25 Rheinmetall Gmbh Leitwerk mit entfaltbaren Fluegeln
US4752052A (en) * 1986-12-17 1988-06-21 The Marquardt Company Projectile
US4796835A (en) * 1986-12-17 1989-01-10 The Marquardt Company Projectile
DE3916690C1 (de) * 1989-05-23 1998-10-01 Bodenseewerk Geraetetech Ausklappbare Flügelanordnung für Flugkörper
US5615846A (en) * 1994-11-04 1997-04-01 Gec Marconi Dynamics Inc. Extendable wing for guided missles and munitions
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
US6186443B1 (en) 1998-06-25 2001-02-13 International Dynamics Corporation Airborne vehicle having deployable wing and control surface
DE102006006160B4 (de) * 2006-02-10 2017-05-24 Mbda Deutschland Gmbh Wickelflügel für einen Flugkörper
US7841559B1 (en) 2006-02-16 2010-11-30 Mbda Incorporated Aerial vehicle with variable aspect ratio deployable wings
DE102006022248B3 (de) * 2006-05-12 2007-11-08 Lfk-Lenkflugkörpersysteme Gmbh Vorrichtung an Wickelflügeln eines Flugkörpers
DE102006044945A1 (de) * 2006-09-22 2008-04-03 Lfk-Lenkflugkörpersysteme Gmbh Lagerung und Verriegelung für einen Wickelflügel
RU2453476C2 (ru) * 2010-02-08 2012-06-20 Юрий Михайлович Киселев Авиационный контейнер для эвакуации пассажиров
US8946607B2 (en) 2011-12-13 2015-02-03 The Boeing Company Mechanisms for deploying and actuating airfoil-shaped bodies on unmanned aerial vehicles
US8698059B2 (en) * 2012-05-03 2014-04-15 Raytheon Company Deployable lifting surface for air vehicle
US10124880B1 (en) * 2016-02-03 2018-11-13 Lockheed Martin Corporation Rotatable control surface assembly for an unmanned aerial vehicle
DE102017003797A1 (de) 2017-04-19 2018-10-25 Mbda Deutschland Gmbh Zweigeteilter klappflügel für flugkörperleitwerke

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE30264C (de) * CH. TH. M. V. de bange in Paris Abfeuerungsvorrichtung für Geschütze
GB189523823A (en) * 1895-12-12 1896-11-14 Martns Stevenson Calvert Improvements in Projectiles.
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
US4203569A (en) * 1977-10-17 1980-05-20 Bei Electronics, Inc. Fin and nozzle unit for a free-flight rocket
US4351499A (en) * 1979-09-24 1982-09-28 General Dynamics Double fabric, retractable, self-erecting wing for missle

Also Published As

Publication number Publication date
ES296987U (es) 1988-09-01
DE3569151D1 (en) 1989-05-03
WO1986002154A1 (fr) 1986-04-10
US4699334A (en) 1987-10-13
DE8428118U1 (de) 1986-07-03
DE3533994A1 (de) 1986-04-30
ES296987Y (es) 1989-03-16
DE3533994C2 (de) 1996-10-24
EP0232267A1 (fr) 1987-08-19

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