EP0802389B1 - Flugkörper mit entfaltbarem Flügel - Google Patents

Flugkörper mit entfaltbarem Flügel Download PDF

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Publication number
EP0802389B1
EP0802389B1 EP19970400838 EP97400838A EP0802389B1 EP 0802389 B1 EP0802389 B1 EP 0802389B1 EP 19970400838 EP19970400838 EP 19970400838 EP 97400838 A EP97400838 A EP 97400838A EP 0802389 B1 EP0802389 B1 EP 0802389B1
Authority
EP
European Patent Office
Prior art keywords
wing
fuselage
fact
state
body according
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 - Lifetime
Application number
EP19970400838
Other languages
English (en)
French (fr)
Other versions
EP0802389A1 (de
Inventor
Bernard Paysant
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.)
Aerospatiale Matra
Original Assignee
Aerospatiale Matra
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Filing date
Publication date
Application filed by Aerospatiale Matra filed Critical Aerospatiale Matra
Publication of EP0802389A1 publication Critical patent/EP0802389A1/de
Application granted granted Critical
Publication of EP0802389B1 publication Critical patent/EP0802389B1/de
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
    • F42B10/16—Wrap-around fins

Definitions

  • the invention relates to a flying object such that a missile equipped with a deployable wing authorizing its storage and transport under an aircraft, when the wing occupies a folded or retracted state.
  • the wing When the flying object is stored or loaded under an aircraft, the wing is in a state folded, in which it is wrapped around the fuselage. Keeping the wing in this folded position is ensured by a retention mechanism whose release is automatically controlled when the machine is dropped. The intrinsic elasticity of the plate in which the wing is formed then brings this one automatically in a deployed state. The wing is then spread of the fuselage of the craft to present in section a substantially semi-circular shape.
  • the plate forming the deployable wing has a profile thin rectangular which remains unchanged when the wing goes from its folded state to its deployed state, and vice versa. Furthermore, that the wing must have a low modulus of elasticity associated with a low thickness so to be able to be wound on the fuselage. The wing deployed therefore has a transverse bending rigidity and in relatively low torsion. That risks create mechanical and aerodynamic malfunctions at extreme speeds and load factors.
  • the main object of the invention is a flying machine equipped with a deployable wing operating according to the principle described in document EP-A-0 622 604, but designed so that the wing has significantly improved rigidity and profile in its deployed state, without maintaining wing in its folded state is more difficult to achieve.
  • this result is obtained by means of a flying object comprising a fuselage and a deployable wing connected to the fuselage by arms articulated so as to be able to occupy a folded state, in which the wing is wrapped around the fuselage, and a deployed state, in which the wing is moved away from the fuselage, characterized in that the profile of the wing along the cross section passing through the longitudinal axis of the craft has a higher moment of inertia in its deployed state than in its folded state.
  • the wing has a curved profile relatively thick in its deployed state and profile relatively thin rectangular in its folded state.
  • the wing preferably comprises at least one strip whose natural state corresponds to relatively thick curved profile and a flattened state, obtained by winding the strip on the fuselage, corresponds to the relatively thin rectangular profile.
  • the wing can then be formed of two bands connected at a leading edge and along a trailing edge of the wing, so that a naturally concave face of each of the bands either turned to the other band.
  • the inertia of the wing in its deployed state is increased in both bending and torsion, so that only the inertia in bending is increased when the wing is formed of a single band.
  • the wing can then be formed either two strips of metallic foil, welded edges to edges, either of two strips of composite material, glued edges to edges.
  • the latter advantageously comprises at least two deployable wings connected to the fuselage independently of each other, by arms articulated, these wings being offset one with respect to the other in a longitudinal direction and forming a substantially complete ring when observed in this longitudinal direction.
  • reference 10 designates part of the fuselage of a flying object such than a missile according to the invention. More precisely, the part shown is a central part of the fuselage, of circular section, which is located between a tapered front end (not shown) and a rear end generally equipped with a device propulsion, ailerons and control surfaces (not shown).
  • the flying machine further comprises two deployable wings 12a and 12b.
  • Each of these wings 12a and 12 is connected to the fuselage 10 by three articulated arms 13a, 14a, 15a and 13b, 14b, .15b, respectively.
  • the two deployable wings 12a and 12b are designed to be able to occupy a folded state, allowing their storage and their transport under an aircraft, as well that a deployed state, serving to increase the range of the craft during its flight.
  • the folded state of the wings 12a and 12b is such that each of the wings is rolled up around the fuselage 10 so as to be pressed against this latest.
  • Each of the wings then presents practically the shape of a circle surrounding almost all of the fuselage in section along a plane perpendicular to the longitudinal axis X-X of the machine.
  • a retention mechanism such as a fastener interposed between the two then adjacent ends of the wing. This mechanism is automatically released when dropping or launching the flying object.
  • each of the wings 12a and 12b is moved away from the fuselage 10 while being maintained at a substantially uniform distance from it by the articulated arms 13a, 14a, 15a and 13b, 14b, .15b.
  • Each wings 12a and 12b therefore present in section the shape of an arc close to a Semi circle.
  • the mounting of the wings 12a and 12b on the fuselage 10 is produced symmetrically with respect to a plane passing through the longitudinal axis X-X of this fuselage, so that the wings 12a and 12b form a substantially complete ring when they are observed in a parallel longitudinal direction to this axis.
  • the wings deployed 12a and 12b then behave like a wing single forming a continuous ring around the fuselage of the craft.
  • the behavior of the set constituted by the wings 12a and 12b is therefore practically independent possible changes in direction of the craft during his flight.
  • the wings 12a and 12b have a different inertia, depending on whether they occupy their deployed state or their folded state. More specifically, this inertia is significantly more high when the wings occupy their extended state than when they occupy their folded state.
  • This characteristic provides relatively easy maintenance wings in their folded state while giving them a much higher rigidity, especially in transverse bending and preferably in torsion, in their state deployed. We are thus guaranteed not to create a malfunction mechanical or aerodynamic in extreme speed and load factor conditions.
  • the wing 12a is constituted by a strip 16a, flexible and elastic which naturally presents in cross section, that is to say along a plane passing through the axis longitudinal XX, approximately the shape of a hanger whose concave side faces the fuselage 10.
  • the band 16a tends to take back when its retention mechanism is released, and which corresponds to the deployed state of wing 12a, the latter has a relatively thick curved profile. Consequently, the inertia of the wing 12a is then relatively high. This therefore prevents it from being subjected to detrimental deformations under conditions extremes of theft.
  • the relatively convex profile wing 12a thick in its extended state also improves the aerodynamic behavior of this during the flight of the flying object.
  • each of the wings 12a and 12b is connected to the fuselage 10 by three articulated arms 13a, 14a, 15a and 13b, 14b, .15b.
  • the arms 13a, 14a and 13b, 14b are in the form of arcs of a circle complementary to the form presented in section by the fuselage 10.
  • these arms 13a, 14a and 13b, 14b are interposed between the two ends of the corresponding wing 12a, 12b and the fuselage, and they're hinged on these parts by hinges 18a, 19a, 20a, 21a (figure 2).
  • the third articulated arm 15a is placed at equal distance of the first two arms 13a, 14a between the fuselage 10 and wing 12a and it appears under the form of two sections of arms 22a, 23a, articulated between them by a hinge 24a and articulated respectively on the fuselage 10 and on the wing 12a in pairs other hinges 25a and 26a.
  • Each of the two sections 22a, 23a of this third arm 15a has a complementary shape of the shape presented in section by the fuselage 10, so that these sections fold back one on the other against the fuselage, when the wing 16a is folded over the latter ( Figure 2).
  • the hinges 18a, 19a, 20a, 21a, 24a, 25a and 26a are for example formed by legs fixed to the fuselage 10 or wing 12a by rivets or by means an adhesive.
  • the articulations themselves are ensured by wicks of "Kevlar” (registered trademark) coated with flexible resin.
  • the wing 12a is constituted by the assembly of two bands 16a and 17a, flexible and elastic, connected to each other according to the leading edge and along the trailing edge of the wing. More specifically, this connection is made in such a way so that the strips 16a and 17a have faces naturally turned towards each other.
  • the behavior of the wing 12a thus produced is comparable to that described above, that is to say that the wing has a curved profile relatively thick when in a deployed state and a relatively thin rectangular profile when occupies its folded state. By the way, the wing naturally regains its deployed form and relatively thick, as soon as the means of retention are released.
  • this embodiment has the advantage, compared in case only one strip is used to form the wing, to increase both torsional rigidity and bending stiffness, when passing to the state deployed.
  • the strip (s) 16a and 17a constituting the deployable wing 12a can be metallic foil tapes or material tapes composite.
  • two bands are associated to form the wing, they are welded edges to edges when made by tinsel and they are glued edge to edge when made made of composite material.
  • the flying object according to the invention can also be equipped with a single deployable wing presenting a profile which varies when the wing passes from its folded state to its deployed state and vice versa.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Aerials With Secondary Devices (AREA)

Claims (7)

  1. Flugkörper mit einem Rumpf (10) und einem entfaltbaren Flügel (12a,12b), der mit dem Rumpf durch gelenkige Arme (13a,14a,15a; 13b,14b,15b) derart verbunden ist, daß er einen zusammengelegten Zustand, in welchem der Flügel um den Rumpf herum gelegt ist, und einen ausgefahrenen Zustand, in welchem der Flügel vom Rumpf beabstandet ist, annehmen kann,
       dadurch gekennzeichnet, daß das Profil des Flügels (12a,12b) gemäß dem durch die Längsachse (X-X) des Flugkörpers verlaufenden Querschnitt in dessen ausgeefahrenem Zustand ein höheres Trägheitsmoment aufweist als in dessen zusammengelegtem Zustand.
  2. Flugkörper gemäß Anspruch 1, dadurch gekennzeichnet, daß der Flügel (12a,12b) in seinem ausgefahrenen Zustand ein relativ voluminöses, bauchiges Profil und in seinem zusammengelegten Zustand ein rechteckiges, relativ schmales Profil aufweist.
  3. Flugkörper gemäß Anspruch 2, dadurch gekennzeichnet, daß der Flügel (12a,12b) mindestens ein geschmeidiges und elastisches Band (16a,17a) aufweist, dessen natürlicher Zustand dem relativ voluminösen, bauchigen Profil entspricht, und dessen durch Zusammenlegen des Bandes auf dem Rumpf erhaltener abgeplatteter Zustand dem rechteckigen, relativ schmalen Profil entspricht.
  4. Flugkörper gemäß Anspruch 3, dadurch gekennzeichnet, daß der Flügel (12a,12b) aus zwei Bändern (16a,17a) gebildet ist, die entlang einer Flügelvorderkante bzw. Flügeleintrittskante und entlang einer Flügelhinterkante bzw. Flügelaustrittskante derart miteinander verbunden sind, daß eine im natürlichen Zustand konkave Fläche jedes der Bänder zum anderen Band hin gerichtet ist.
  5. Flugkörper gemäß Anspruch 4, dadurch gekennzeichnet, daß der Flügel (12a,12b) aus zwei am Stoß geschweißten Bändern (16a,17a) aus Metallfolie gebildet ist.
  6. Flugkörper gemäß Anspruch 4, dadurch gekennzeichnet, daß der Flügel (12a,12b) aus zwei am Stoß verklebten Bändern (16a,17a) aus Verbundmaterial gebildet ist.
  7. Flugkörper gemäß einem der vorangehenden Ansprüche, dadurch gekennzeichnet, daß er mindestens zwei entfaltbare Flügel (12a,12b) umfaßt, die unabhängig voneinander durch gelenkige Arme (13a,14a,15a; 13b,14b,15b) mit dem Rumpf verbunden sind, wobei diese Flügel in einer Längsrichtung zueinander versetzt sind und, in dieser Längsrichtung betrachtet, einen im wesentlichen durchgehenden Ring bilden.
EP19970400838 1996-04-16 1997-04-14 Flugkörper mit entfaltbarem Flügel Expired - Lifetime EP0802389B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9604725 1996-04-16
FR9604725A FR2747464B1 (fr) 1996-04-16 1996-04-16 Engin volant a aile deployable

Publications (2)

Publication Number Publication Date
EP0802389A1 EP0802389A1 (de) 1997-10-22
EP0802389B1 true EP0802389B1 (de) 2000-11-15

Family

ID=9491236

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19970400838 Expired - Lifetime EP0802389B1 (de) 1996-04-16 1997-04-14 Flugkörper mit entfaltbarem Flügel

Country Status (4)

Country Link
EP (1) EP0802389B1 (de)
DE (1) DE69703510T2 (de)
ES (1) ES2153638T3 (de)
FR (1) FR2747464B1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE541598C2 (sv) * 2017-11-10 2019-11-12 Bae Systems Bofors Ab Akterparti för en fenstabiliserad projektil

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3188957A (en) * 1962-04-03 1965-06-15 Aerojet General Co Ring stabilizer
US3374969A (en) * 1966-07-28 1968-03-26 Army Usa Stabilized projectile
DE3516367A1 (de) * 1985-05-07 1986-11-13 Diehl GmbH & Co, 8500 Nürnberg Flugkoerper mit klappfluegel
US4752052A (en) * 1986-12-17 1988-06-21 The Marquardt Company Projectile
US5417393A (en) * 1993-04-27 1995-05-23 Hughes Aircraft Company Rotationally mounted flexible band wing
FR2716965B1 (fr) * 1994-03-02 1996-05-03 Matra Defense Engin largable à stabilisation et freinage aérodynamique.

Also Published As

Publication number Publication date
FR2747464B1 (fr) 1999-09-17
FR2747464A1 (fr) 1997-10-17
DE69703510T2 (de) 2001-05-17
DE69703510D1 (de) 2000-12-21
EP0802389A1 (de) 1997-10-22
ES2153638T3 (es) 2001-03-01

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