EP0333681A1 - Aile ou ailette déployable pour missiles ou autres projectiles - Google Patents

Aile ou ailette déployable pour missiles ou autres projectiles Download PDF

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Publication number
EP0333681A1
EP0333681A1 EP19890850054 EP89850054A EP0333681A1 EP 0333681 A1 EP0333681 A1 EP 0333681A1 EP 19890850054 EP19890850054 EP 19890850054 EP 89850054 A EP89850054 A EP 89850054A EP 0333681 A1 EP0333681 A1 EP 0333681A1
Authority
EP
European Patent Office
Prior art keywords
wing
fin
plates
projectile body
projectile
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Withdrawn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
EP19890850054
Other languages
German (de)
English (en)
Inventor
Stig Johnsson
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.)
Saab Bofors AB
Original Assignee
Bofors AB
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 Bofors AB filed Critical Bofors AB
Publication of EP0333681A1 publication Critical patent/EP0333681A1/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Withdrawn legal-status Critical Current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 present invention relates to a novel type of unfurling wing or fin for missiles and other projectiles which, while being of the so-called wrap-around type may nevertheless be given a tangential or alternatively radial extent in relation to the cross-section of the projectile with optional wing or fin length and - by no means least equally important - an aerodynamic profile with a cross-sectional configuration conditioned by flight and steering considerations.
  • Guided missiles and projectiles may be steered or guided by means of rudders, impulse motors etc. Wings or fins are often employed to increase their steerability or to stabilize them.
  • Such missiles or projectiles as are discharged from barrels or launching tubes must, as a rule, be provided with wholly or partly furlable wings or fins (for purposes of simplification, the body of this specification will hereinafter refer solely to “projectiles” and “wings” without entailing any restriction of the scope of the invention whatever in respect of “missiles” and “fins”).
  • This art abounds in a plurality of designs of furlable wings.
  • One type is folded along a joint parallel to the longitudinal direction of the projectile. These wings may be straight or curved about the projectile. This latter type is normally referred to as a wrap-around wing.
  • Such folded "straight" wings take up considerable volume even in the furled position and/or can they be made as long as is often desirable.
  • Wrap-around wings may be constructed of considerable length, but because they usually retain, after being actuated and unfurled, a helical extent in relation to the cross-section of the projectile, they create a powerful interaction between the steering about the three spatial axes, which considerably impedes the steering control system if the projectile is to be guided.
  • a further drawback inherent in wrap-around wings is that these have hitherto of necessity usually been manufactured from simple plates, for which reason it has not been possible to impart to them a desirable aerodynamic profile with a wing cross-section conditioned by flight or steering considerations.
  • the present invention relates to a wing which consists of two plates which are cupped away from one another and mutually abut and, for example by welding or glueing, are interconnected along all edge sides along which they are not directly or indirectly anchored in the projectile body.
  • a wing which consists of two plates which are cupped away from one another and mutually abut and, for example by welding or glueing, are interconnected along all edge sides along which they are not directly or indirectly anchored in the projectile body.
  • a distinctive feature of the wing according to the present invention in addition to the above-outlined design of two cupped, mutually joined plates making for a desired aerodynamic design and wing surface even with very long wings - is that the actuating force requisite for unfurling the wing derives in all essentials from those tensions and flexural stresses which are positively imparted in the material as the wing is wrapped into its furled position.
  • the locking function necessary for retaining the wing in its furled position will not be dealt with in greater detail in this context, since it is not included in the present invention; but such function may for instance consist of a locking sleeve which is ejected as the projectile departs from the barrel or launching tube.
  • this wing type is wholly unribbed and, for its inherent rigidity, is completely dependent upon the shape of and material in the included cupped plates.
  • the cupped plates with at least certain central parts where the plates are substantially completely flat and run parallel to one another.
  • This design affords the particular advantage that these parts of the plates, on furling, are first urged into dead abutment against one another and preferably by means of cooperating bosses and apertures in the opposing plates which, on mutual compression thereof, enter into engagement with one another, are locked against relative lateral displacement before the wing is furled in against the projectile body.
  • the wing according to the present invention is a straight two-sided wing which is tangentially secured to the projectile body. Since such wings may, in the furled state, lie wrapped overlappingly against the projectile body, each respective wing half may be of a length which at most correspond to almost the entire circumference of the projectile, i.e. from one side of anchorage to the other side of the same anchorage.
  • a second variant of the present invention makes for radially projecting wings but in such a case it is usually most appropriate to provide the wing (or rather the wing half) with a pivotal anchorage which makes it possible to furl the wing to an at least tangential direction in relation to the projectile body before the wing is folded, or rather bent, in along the outer surface of the projectile body.
  • a reversible journal for the wing in the form of a journalling shaft which is separately locked in the fully unfurled and operative position and is provided with a substantially centred rectangular bottom groove disposed in its longitudinal direction, along whose one longitudinal side one of the cupped plates is secured along its inner edge side, while the second of the cupped plates is provided, along its inner edge side, with a locking bead which may engage in a cooperating groove in the other opposing inner edge side of the bottom groove.
  • locking means are provided in the form of a curved leaf spring which may snap in between the plates when the wing is fully unfurled and the cupped plates have reassumed their original form. The purpose of such locking means is to prevent the plates from being pressed together by the wing load during the flight of the projectile.
  • each cupped plate is provided with a substantially semicircular stub at each outer corner on its free inner edge side facing in towards the projectile.
  • these semicircular stub each pairwise form their complete stub end about which the wing may be furled into a position at least tangentially in relation to the projectile body.
  • the basic shape of the support for these assembled stubs in the projectile body is oval. Furling of the wing inwardly is then effected along one edge of the oval support, but in the fully open state, the plates splay apart and the semicircular stubs support against opposing edges of the oval supports.
  • This basic model for reversible wing journalling may then be supplemented with the same type of locking edge along the lower edge of the one plate as is to be found in the previously-­discussed wing type. The same also applies to the locking means between the plates.
  • the projectile P shown in Figs. 1-3 is provided with a superjacent furlable wing V and guide fins or rudders F.
  • the guide fins F may be of different design and will not be considered in greater detail in this context.
  • the wing V is formed of two cupped plates 1 and 2 which have been bent to the common longitudinal and profile cross-section which is apparent from Figs. 2 and 3.
  • the plates 1 and 2 are interconnected along their periphery by joints 3 which may consist of welded, glued or soldered joints but may also be provided by other optional means.
  • the main thing is that the joints offer a non-sliding connection between the plates and are capable of absorbing shear stresses.
  • the plates 1 and 2 are first urged into dead abutment against one another so that they become flat, whereafter they are wrapped around the projectile body K in the manner intimated by broken lines V1 in Fig. 2. As intimated in this Figure, the wing tips partially overlap.
  • the strain to which the plates 1 and 2 are exposed when they are wrapped about the projectile body consists of two components; first the strain which the compression and flattening of the cupped configuration of the plates give rise to, and secondly the strain occasioned by the operation of wrapping around the projectile.
  • This latter strain is determined by the double thickness of the plate and the diameter of the projectile, while the former is determined by the thickness of the plate and its radius of curvature in the bent state.
  • the elasticity limit of the plate must be sufficient to accommodate the combination of these strains. This imposes very high demands on the material in the plates but, at the same time, gives wings which, without specific mechanics, will be unfurled as soon as a locking function ceases to lock the wing in its furled and closed position.
  • the material in the wing must have an extremely high limit of elasticity and high mechanical strength.
  • suitable such materials are high-strength titanium alloys, spring steel and certain fibre-reinforced plastic materials.
  • other materials could also conceivably be used. The choice of material must be determined from case to case although at the present time titanium is ideally the most readily applicable alternative.
  • Figs. 1-3 Two different alternative wing anchorages are intimated in Figs. 1-3.
  • the lower wing plate 2 is provided with guiding beads or pins 5 and 6 which fit into recesses 7 and 8 in the projectile body and thereby positionally fix the wing against twisting at the same time as the wing is held in place by a flexible but not extensible band 4 which is tensioned across the upper surface of the wing and secured in the projectile body.
  • the band 4 can be folded together at the same time as the wing portions 1 and 2 are urged together as a preparatory measure for furling the wings inwardly.
  • the wing has been positionally fixed against twisting in that the lower wing plate 2 is secured to the projectile body by means of bolts 9 and 10 with shims 11 and 12.
  • bolts 9 and 10 In order for the bolts 9 and 10 to be mounted in place, and in order for the plates 1 and 2 to be completely clamped together, two apertures 13 and 14 are provided in the upper wing plate 1. In this fastening, it is not always necessary to supplement the arrangement with the flexible band 4 even if this may occasionally be needed in view of the aerodynamic forces acting on the wing.
  • Fig. 4 illustrates such a projectile.
  • Figs. 4-11 refer to the first variant and Figs. 12 and 13 to the second.
  • the wing 15 consists of two cupped plates 16 to 17 which are interconnected along their common edges by the joint 18, while the fourth edge of each respective plate is free and provided with anchorage fittings 19 and 20 respectively.
  • the joint 18 may, as in the previously described embodiment according to Figs. 1-3, be a soldered, glued or welded joint.
  • the plates 16 and 17 are first urged into dead abutment with one another, whereafter the wing is folded down towards the projectile body K about an axially directed reversible journal, whereafter the wing is furled, from a substantially tangential position in relation to the projectile body K, around said projectile body K.
  • the wings may also overlap in this case. This is facilitated by the formation of an abrupt longitudinal notch in the projectile body at each wing anchorage (see for example Fig. 5).
  • the furled positions of the wings are apparent from the broken lines V11 in Figs. 5 and 6.
  • One such measure may be to apply a flat surface 21 along the projectile body in immediate association with the reversibly pivotal anchorage of the wing so that the wing, when it is furled around the projectile body, need not be deformed (flexed) further in the immediate proximity of the pivotal shaft and the free end edges of the plates.
  • the second measure is to provide the plates with fixing means cooperating in the compressed state, for instance in the form of plugs 22 on the one plate and corresponding apertures 23 in the second plate.
  • the fixing means may be designed in a large variety of manners and could, for instance, also consist of folds or creases in the plates. With the aid of these fixing means, the plates are forced to follow one another when they are furled around the projectile body.
  • the fixing means and the "straight" portion of the projectile periphery are solutions which may be applicable in all types of radial wings.
  • the reversibly pivotal anchorage may be of different designs.
  • the anchorage fitting 19 consists of a rod of a substantially semicircular cross-section which is secured to the inner free end or edge side of the flat or straight portion 24 of the plate 16.
  • the reason for this is that the compression of the plates constituting the wings and their furling around the projectile body is always facilitated if the plates constituting the wings are provided with a straight or flat portion disposed centrally between the edge joints flush with the anchorage of the wing to the projectile body.
  • the ends of the rod 19 are extended beyond the "straight" portion of the plate by substantially semicircular journal pins 30, 31.
  • the anchorage fitting 20 also consists of a rod designed as two end-to-end semicircular journal pins 32, 33 and a locking bead 26 secured along the flat portion 25 of the plate 17 and being of rectangular cross-section. With the plates in the compressed state, there will thus be obtained circular composite stub shafts at each respective end edge of the planar plate portions.
  • That part of the projectile which retains the wings is designed as a first ring 17 (Fig. 10) and two retaining rings 28, 29 (Fig. 11) on either side thereof, these latter being both provided with pairwise corresponding oval holes 34 and 35 for the stub shafts 30-32 and 31-33, respectively.
  • the wings are mounted on the ring 27, whereafter the retaining rings 28, 29 are mounted so that the projecting journal pins 30, 31, 32, 33 of the anchorage fittings will project into the oval holes 34 and 35 in the retaining rings 28 and 29, respectively.
  • the assembled position with the wings in the operative or unfurled state is apparent from Fig. 5. In this position the pins 30-33 abut against the outer edges in each respective oval aperture 34 and 35 respectively.
  • the wing In the unfurled position, the wing is held in place partly by the ends of the journal pins 30-33 in the apertures of the retaining rings 28-29 and partly by the fact that the semi­ circular portion of the anchorage fitting 19 abuts against the inside of a cooperating similarly semicircular groove 36 in the ring 27 at the same time as the anchorage fitting 20 fits, with its locking bead 26, into a specifically adapted locking groove 37 which is also disposed in the ring 27.
  • the groove 36 and the locking groove 37 are disposed in register with one another in a recess or bottom groove 38 in the periphery of the ring 27.
  • the groove runs axially in relation to the main direction of the projectile.
  • a callipered leaf spring 39 which originally is compressed against the bottom of the recess but, as soon as the wing is completely unfurled, will snap in between the plates 15 and 16 and prevent these from being pressed together by aerodynamic forces.
  • the width of the leaf spring 39 corresponds to the inner space between the flat portions of the plates 15 and 16.
  • the leaf spring 39 also prevents the anchorage fittings 19 and 20 from being displaced out from theri respective recesses in the ring 27.
  • the wing is held in the furled state by a device which is not shown on the Drawings.
  • the device may consist of an outer casing which is removed when the wing is to be unfurled or when th wings are held furled by the discharge barrel.
  • Figs. 12 and 13 shown one alternative of the reversible journalling of the wing according to Figs. 5-11.
  • the main principle is, however, the same. The difference lies in the fact that, in this case, the wing is anchored to a rotary shaft 40.
  • This shaft is provided with an axially directed rectangular bottom groove 47.
  • the one plate of the wing, here designated 41 is joined, with its flat or straight portion, with the one longitudinal edge of the shaft groove along the joint 43.
  • the second plate, here designated 42 has a fitting 44 with a locking edge 45 which, when the wing is unfurled, engages with a corresponding recess 46 in the opposing longitudinal edge of the groove 47 in the shaft 40.
  • a bulging leaf spring 48 is disposed in the bottom of the recess, this spring being capable, as previously described, of snapping in between the plates in the wing as soon as the wing has reached the completely unfurled position.
  • the leaf spring 48 effectively prevents compression between the plates of the wing.

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)
EP19890850054 1988-03-16 1989-02-17 Aile ou ailette déployable pour missiles ou autres projectiles Withdrawn EP0333681A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE8800932 1988-03-16
SE8800932A SE460738B (sv) 1988-03-16 1988-03-16 Foer missiler och andra projektiler avsedd utfaellbar vinge

Publications (1)

Publication Number Publication Date
EP0333681A1 true EP0333681A1 (fr) 1989-09-20

Family

ID=20371699

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19890850054 Withdrawn EP0333681A1 (fr) 1988-03-16 1989-02-17 Aile ou ailette déployable pour missiles ou autres projectiles

Country Status (2)

Country Link
EP (1) EP0333681A1 (fr)
SE (1) SE460738B (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3927798A1 (de) * 1989-08-23 1991-03-14 Rheinmetall Gmbh Fluegelstabilisiertes geschoss
DE4025515A1 (de) * 1990-08-11 1992-02-13 Messerschmitt Boelkow Blohm Tragfluegel fuer aus einem rohr startende flugkoerper
US5368255A (en) * 1992-06-04 1994-11-29 Hughes Aircraft Company Aerotumbling missile
FR2738908A1 (fr) * 1995-09-15 1997-03-21 Giat Ind Sa Dispositif de freinage aerodynamique d'une sous-munition ejectee d'un obus cargo en etant animee d'un mouvement de rotation
DE3916690C1 (de) * 1989-05-23 1998-10-01 Bodenseewerk Geraetetech Ausklappbare Flügelanordnung für Flugkörper
EP1818646A1 (fr) * 2006-02-10 2007-08-15 LFK-Lenkflugkörpersysteme GmbH Ailes déployables flexibles pour missile
DE102006044945A1 (de) * 2006-09-22 2008-04-03 Lfk-Lenkflugkörpersysteme Gmbh Lagerung und Verriegelung für einen Wickelflügel
FR2911954A1 (fr) 2007-01-31 2008-08-01 Nexter Munitions Sa Dispositif de pilotage d'une munition a gouvernes deployables
DE202006020972U1 (de) 2006-09-22 2011-06-01 LFK-Lenkflugkörpersysteme GmbH, 86529 Lagerung und Verriegelung für einen Wickelflügel
DE102019131443A1 (de) * 2019-11-21 2021-05-27 Schunk Kohlenstofftechnik Gmbh Flügel

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2226123A1 (de) * 1971-06-24 1973-01-11 Bofors Ab Umdrehungsbremse zur abbremsung einer von einem geschoss, einer rakete od.dgl. trennbaren einheit
DE2609932A1 (de) * 1976-03-10 1977-09-15 Messerschmitt Boelkow Blohm Klappleitwerk fuer flugkoerper
DE3026409A1 (de) * 1979-09-24 1982-03-04 General Dynamics Corp., St. Louis, Mo. Doppelwandiger ein- und selbsttaetig ausklappbarer geschossfluegel
DE3618956C1 (de) * 1986-06-05 1987-11-19 Rheinmetall Gmbh Leitwerk mit entfaltbaren Fluegeln fuer Geschosse und Flugkoerper

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2226123A1 (de) * 1971-06-24 1973-01-11 Bofors Ab Umdrehungsbremse zur abbremsung einer von einem geschoss, einer rakete od.dgl. trennbaren einheit
DE2609932A1 (de) * 1976-03-10 1977-09-15 Messerschmitt Boelkow Blohm Klappleitwerk fuer flugkoerper
DE3026409A1 (de) * 1979-09-24 1982-03-04 General Dynamics Corp., St. Louis, Mo. Doppelwandiger ein- und selbsttaetig ausklappbarer geschossfluegel
DE3618956C1 (de) * 1986-06-05 1987-11-19 Rheinmetall Gmbh Leitwerk mit entfaltbaren Fluegeln fuer Geschosse und Flugkoerper

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3916690C1 (de) * 1989-05-23 1998-10-01 Bodenseewerk Geraetetech Ausklappbare Flügelanordnung für Flugkörper
DE3927798A1 (de) * 1989-08-23 1991-03-14 Rheinmetall Gmbh Fluegelstabilisiertes geschoss
DE4025515A1 (de) * 1990-08-11 1992-02-13 Messerschmitt Boelkow Blohm Tragfluegel fuer aus einem rohr startende flugkoerper
US5368255A (en) * 1992-06-04 1994-11-29 Hughes Aircraft Company Aerotumbling missile
FR2738908A1 (fr) * 1995-09-15 1997-03-21 Giat Ind Sa Dispositif de freinage aerodynamique d'une sous-munition ejectee d'un obus cargo en etant animee d'un mouvement de rotation
NO339906B1 (no) * 2006-02-10 2017-02-13 Lfk Lenkflugkoerpersysteme Gmbh Foldevinge for en flykropp
EP1818646A1 (fr) * 2006-02-10 2007-08-15 LFK-Lenkflugkörpersysteme GmbH Ailes déployables flexibles pour missile
DE102006006160B4 (de) * 2006-02-10 2017-05-24 Mbda Deutschland Gmbh Wickelflügel für einen Flugkörper
DE102006044945A1 (de) * 2006-09-22 2008-04-03 Lfk-Lenkflugkörpersysteme Gmbh Lagerung und Verriegelung für einen Wickelflügel
DE202006020972U1 (de) 2006-09-22 2011-06-01 LFK-Lenkflugkörpersysteme GmbH, 86529 Lagerung und Verriegelung für einen Wickelflügel
EP1953494A1 (fr) 2007-01-31 2008-08-06 NEXTER Munitions Dispositif de pilotage d'une munition à gouvernes déployables
FR2911954A1 (fr) 2007-01-31 2008-08-01 Nexter Munitions Sa Dispositif de pilotage d'une munition a gouvernes deployables
DE102019131443A1 (de) * 2019-11-21 2021-05-27 Schunk Kohlenstofftechnik Gmbh Flügel
DE102019131443B4 (de) 2019-11-21 2022-03-17 Schunk Kohlenstofftechnik Gmbh Flügel, der klapp­ oder verschwenkbar mit einem Körper verbunden ist

Also Published As

Publication number Publication date
SE8800932D0 (sv) 1988-03-16
SE8800932L (sv) 1989-09-17
SE460738B (sv) 1989-11-13

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