EP0209761B1 - Flugkörper mit ausschwenkbaren Gleitflügeln - Google Patents

Flugkörper mit ausschwenkbaren Gleitflügeln Download PDF

Info

Publication number
EP0209761B1
EP0209761B1 EP86108860A EP86108860A EP0209761B1 EP 0209761 B1 EP0209761 B1 EP 0209761B1 EP 86108860 A EP86108860 A EP 86108860A EP 86108860 A EP86108860 A EP 86108860A EP 0209761 B1 EP0209761 B1 EP 0209761B1
Authority
EP
European Patent Office
Prior art keywords
flying body
wing
fuselage
extensions
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
Application number
EP86108860A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0209761A1 (de
Inventor
Raimar Steuer
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.)
Diehl Verwaltungs Stiftung
Original Assignee
Diehl GmbH and Co
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 Diehl GmbH and Co filed Critical Diehl GmbH and Co
Publication of EP0209761A1 publication Critical patent/EP0209761A1/de
Application granted granted Critical
Publication of EP0209761B1 publication Critical patent/EP0209761B1/de
Expired 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
    • F42B10/146—Fabric fins, i.e. fins comprising at least one spar and a fin cover made of flexible sheet material

Definitions

  • the invention relates to a missile according to the preamble of claim 1.
  • Such a missile is known from GB-A-1 597 098.
  • two partial wing surfaces which are strip-shaped and hinged to one another at the front, can be accommodated, the rear of which is articulated on the missile fuselage and the front is slidably supported along the missile fuselage.
  • the result of this is that when the rear partial wing is unfolded, the front partial wing, overlapping the rear, is also exhibited.
  • This only results in a very small and therefore unsatisfactory gliding wing area.
  • Their rear pivoting is structurally disadvantageous in relation to the position of the center of gravity of a conventional missile of the generic type and also in relation to the rudder regularly arranged behind the sliding wings.
  • the invention relates in particular to a submunition missile of the type known from the DEFENSE ELECTRONICS magazine, issue June 1984, caption on page 102, as a projectile which can be steered by the final phase and is ejected from a carrier rocket which is involved in ballistic flight Supersonic speed has approached a target area.
  • a submunition missile of the type known from the DEFENSE ELECTRONICS magazine, issue June 1984, caption on page 102
  • the respective submunition missile is launched into an elongated slideway approximately parallel to the earth's surface by means of a built-in preprogrammed control after the launching of the carrier.
  • stabilizing wings which essentially only need to have wing effect, in particular not for maneuvering purposes relative to the longitudinal axis of the missile or must be pivoted in some other way.
  • these wings have to be folded towards the submunition fuselage during the submunition shipment in the carrier, as is basically known as such from GB-A-1 597 098, already cited. This is because recording within the periphery of the missile fuselage is not possible because the interior of the fuselage has already been optimally used by the electronic units and the warhead.
  • the aim is to have sliding wings which, due to their large area and their positioning on the fuselage, provide high aerodynamic performance.
  • Textile wings as are known from GB-A-2 059 023, can therefore be provided as large-area sliding wings.
  • it is more favorable in terms of flight dynamics to give such stretchable textile wings with the largest possible cross-sectional area an aerodynamically optimized cross-sectional shape, as is described in more detail in GB-A-2 149 481.
  • foldable wings can also be provided, which are designed, for example, in accordance with US Pat. No. 4,364,531;
  • the object of the invention is to provide a missile of the generic type with deployable wings for more favorable flight characteristics.
  • This surface is largely determined in its cross-sectional geometry in a foldable covering in the form of a flexible cover by the cross section of a profiled front spar which is articulated to the respective wing attachments and which is mechanically stably received in a groove in the folded-up position on the fuselage , which extends outside the submunition hull, namely in the extensions.
  • the attachments can be moved almost arbitrarily in the longitudinal direction of the submunition fuselage to ensure a favorable position of the aerodynamically effective point of attack of the wing exhibited with respect to the position of the center of gravity of the missile, that is to say To be able to optimize flight characteristics. It is only necessary to ensure that the rear edges of the wing and the extensions are at a sufficient distance along the fuselage to the front edge of the rudder in the rear area of the fuselage, so that regular inflow conditions are guaranteed.
  • a submunition carrier 2 preferably an artillery rocket
  • a plurality of submunition missiles 3 are arranged peripherally adjacent to one another along the inner circumferential surface of the shell 1 in a longitudinal sectional plane, said targets flying over a target area to combat armored targets identified or expected there the sleeve 1 are expelled radially.
  • the individual submunition missiles 3 are steered into a slideway that extends approximately parallel to the surface of the earth, periodically with a search detonator seeker head across the flight direction along a strip extending parallel to the direction of flight for a target object to be fought to search, which is then attacked while leaving the gliding trajectory - as described in DE-A-3 303 763 in the steepest possible approach approach.
  • the missile 3 is equipped with extendable sliding wings 4. To save space, they are folded towards the fuselage 5 of the missile 3 during the transfer in the carrier 2, and they are only extended into the functional position shown in FIG. 2 after they have been ejected from the transfer carrier 2.
  • the maneuvering is provided by the control rudders 7 which are pivotably articulated in the tail area 6 and which can be folded out about grooves 9 in the structure of the fuselage 5 about folding axes 8 when the carrier 2 has ejected its submunition missiles 3.
  • the space required for accommodating, for example, retractable wings 4 is available, which have a much larger surface area than the rudder 7 and whose root area 10 extends substantially over that part of the fuselage 5 which is proven by the search detonator signal processing and control auxiliary devices and in particular also by the armor-piercing submunition active charge.
  • the wings 4 are diametrically opposed to each other approximately along a generatrix of the lateral surface of the fuselage 5, and thus approximately parallel to its longitudinal axis 11, two.
  • these attachments 12 lie precisely in a plane in which on both sides of the missile fuselage 5 there is a free space 13 from the adjacent inner surface area of the carrier shell 1 is given (as is evident from the description of a small circle in a much larger circle geometrically).
  • the radial width 14 can make up almost half the diameter of the missile fuselage 5.
  • the axially parallel length 15 depends on aerodynamic conditions with regard to the geometry of the missile fuselage 5 and according to the geometry of the flared wings 4 which are tied to the fuselage 5 at or shortly behind the rear end of the attachments 12.
  • the attachments 12 must allow sufficient clearance 16 for sufficient undisturbed flow against the rudder 7 along the missile fuselage 5; otherwise, they can be selected along the missile fuselage 5 in the aerodynamically most favorable position (in which the aerodynamically effective wing application point lies axially at least slightly behind the center of gravity of the missile 3). Also for fluidic reasons, the front end 17 of the attachments 12 runs beveled into the outer contour of the missile fuselage 5.
  • the attachments 12 thus serve the pivotable mounting of folding wings 4, which are folded into grooves 18 in the applied position and which do not extend from the attachments 12 into the interior of the fuselage 5.
  • the folding wings 4 are each preferably an aerodynamically profiled front spar 19, around which a flexible sheath 20, for example canvas, is guided, which is stretched backwards by a rear spar 21 or a rope 22 when the front spar 19 is pivoted out; as described in DE-A3 340 501 for a similar fabric folding wing.
  • a knee joint lever or, according to DE-A-3 403 573.7, a swivel rod articulated in the region of the front spar pivot axis 24 (not considered in the drawing) may be provided; if the sheath 20 is not tightened by means of a tension cable 22.
  • the width of the front spar 19 is chosen as large as possible in the interest of the greatest possible profiling specification for the curvature of the casing 20 and thus approximately as large as the radial width 14 of the attachments 12, which in its groove 18 next to the front spar 19 also any rear spar 21 (and possibly also the folded-in cover 20) of the respective wing 4.
  • the length of the front spar 19, which is aerodynamically profiled in cross section, is not limited to the axial length 15 of the attachments 12. Because during the stowage of the submunition missile 3 in its carrier 2, it is not a problem if the front spar 19 folded towards the fuselage 5 - as shown in dashed lines in FIG. 2 - protrudes rearward from the attachments 12 and extends into the area of the stern. Rudder 7 extends - if sufficient clearance 16 along fuselage 5 is ensured only when wing 4 is folded out.
  • the folding wing 4 can also be designed according to DE-A-3 417 082.0, i.e. have the design of flat box-shaped, telescopically slidable slats, which are moved apart when the front spar 19 is unfolded about its pivot axis 24 so as to be aerodynamic to assemble the shaped wing surface from the cross-sectional shapes of the successive slats.

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)
EP86108860A 1985-07-03 1986-06-30 Flugkörper mit ausschwenkbaren Gleitflügeln Expired EP0209761B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3523769 1985-07-03
DE19853523769 DE3523769A1 (de) 1985-07-03 1985-07-03 Submunitions-flugkoerper mit ausstellbaren gleitfluegeln

Publications (2)

Publication Number Publication Date
EP0209761A1 EP0209761A1 (de) 1987-01-28
EP0209761B1 true EP0209761B1 (de) 1989-04-19

Family

ID=6274843

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86108860A Expired EP0209761B1 (de) 1985-07-03 1986-06-30 Flugkörper mit ausschwenkbaren Gleitflügeln

Country Status (3)

Country Link
US (1) US4869441A (enrdf_load_stackoverflow)
EP (1) EP0209761B1 (enrdf_load_stackoverflow)
DE (2) DE3523769A1 (enrdf_load_stackoverflow)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2812936A1 (fr) * 1986-08-12 2002-02-15 Aerospatiale Missile a voilure variable
SE461750B (sv) * 1987-03-20 1990-03-19 Lars Johan Schleimann Jensen Foerfarande foer styrning av ett flygande objekt, saasom en projektil, mot ett maal och projektil foer foerfarandets genomfoerande
DE3730019C1 (de) * 1987-09-08 1988-12-22 Diehl Gmbh & Co Submunitions-Flugkoerper
DE3838735C2 (de) * 1988-11-15 1997-12-18 Diehl Gmbh & Co Klapp-Flügel, insbes. für ein Geschoss
DE3914308C2 (de) * 1989-04-29 1994-04-14 Diehl Gmbh & Co Ruder für ein Projektil
DE3918244A1 (de) * 1989-06-05 1990-12-06 Diehl Gmbh & Co Von einem flugkoerper wegklappbarer fluegel
US5106034A (en) * 1991-02-28 1992-04-21 The United States Of America As Represented By The Secretary Of The Navy Device and process for attachment of parts to rocket motors
US5312070A (en) * 1992-04-02 1994-05-17 Grumman Aerospace Corporation Segmented variable sweep wing aircraft
US5537909A (en) * 1995-04-17 1996-07-23 Hughes Missile System Company All-aspect bomb damage assessment system
US6119976A (en) * 1997-01-31 2000-09-19 Rogers; Michael E. Shoulder launched unmanned reconnaissance system
DE19827278A1 (de) * 1998-06-19 1999-12-23 Diehl Stiftung & Co Lenkbarer Flugkörper
US6073882A (en) * 1998-09-21 2000-06-13 Zieger; N. Henning Flying vehicle with retractable wing assembly
DE19906969B4 (de) * 1999-02-19 2004-10-14 Rheinmetall W & M Gmbh Aus einem Waffenrohr verschießbares leitwerkstabilisiertes Geschoß
DE102004007311A1 (de) * 2004-02-14 2005-09-01 Diehl Bgt Defence Gmbh & Co. Kg Geschoss mit vom Geschoss-Rumpf wegklappbaren Flügeln
WO2010064945A1 (ru) * 2008-12-01 2010-06-10 Afanasyev Sergey Nikolaevich Летательный аппарат
DE102013006812B4 (de) * 2013-04-19 2015-01-15 Mbda Deutschland Gmbh Lenkflugkörper sowie Wirksystem, umfassend den Lenkflugkörper
DE102019002705A1 (de) * 2019-04-12 2020-10-15 Mbda Deutschland Gmbh Marschflugkörper und Verfahren zum Steuern eines Marschflugkörpers

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB650322A (en) * 1947-03-11 1951-02-21 Roger Aime Robert Improvements in folding wings for aircraft
US3507150A (en) * 1966-01-24 1970-04-21 Robert F Stengel Wind velocity probing device and method
US3647163A (en) * 1969-11-19 1972-03-07 Thomas E Sweeney Foldable semirigid airfoil for airborne vehicles
GB1597098A (en) * 1971-06-23 1981-09-03 British Aerospace Missiles
US4522356A (en) * 1973-11-12 1985-06-11 General Dynamics, Pomona Division Multiple target seeking clustered munition and system
SE429266B (sv) * 1977-02-09 1983-08-22 Bofors Ab Stjertparti avsett for en i ett eldror utskjutbar fenstabiliserad granat
US4106727A (en) * 1977-05-09 1978-08-15 Teledyne Brown Engineering, A Division Of Teledyne Industries, Inc. Aircraft folding airfoil system
DE2920347C2 (de) * 1979-05-19 1982-11-11 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Gefechtskopf mit ausstoßbaren Wirkkörpern
US4351499A (en) * 1979-09-24 1982-09-28 General Dynamics Double fabric, retractable, self-erecting wing for missle
SE433882B (sv) * 1979-10-09 1984-06-18 Bofors Ab Utfellbar fena for en fenstabiliserad ammunitionsenhet i form av en granat
US4364531A (en) * 1980-10-09 1982-12-21 Knoski Jerry L Attachable airfoil with movable control surface
US4455943A (en) * 1981-08-21 1984-06-26 The Boeing Company Missile deployment apparatus
DE3301873A1 (de) * 1983-01-21 1984-07-26 Rheinmetall GmbH, 4000 Düsseldorf Flugkoerper
DE3403573A1 (de) * 1983-11-09 1985-08-08 Diehl GmbH & Co, 8500 Nürnberg Geschoss mit herausklappbaren fluegeln
DE3417082A1 (de) * 1984-05-09 1985-11-14 Diehl GmbH & Co, 8500 Nürnberg Klapp-fluegel, insbesondere fuer ein geschoss
DE3515326A1 (de) * 1985-04-27 1986-10-30 Rheinmetall GmbH, 4000 Düsseldorf Nutzlastgeschoss

Also Published As

Publication number Publication date
DE3662945D1 (en) 1989-05-24
DE3523769C2 (enrdf_load_stackoverflow) 1988-07-28
DE3523769A1 (de) 1987-01-08
US4869441A (en) 1989-09-26
EP0209761A1 (de) 1987-01-28

Similar Documents

Publication Publication Date Title
EP0209761B1 (de) Flugkörper mit ausschwenkbaren Gleitflügeln
DE2904749C2 (de) Flugkörper nach Art einer Drohne
DE60130470T2 (de) Ultraweit reichendes gelenktes Artilleriegeschoss
EP1674819B1 (de) Drohne
US4336914A (en) Deployable wing mechanism
EP0013096B1 (en) Deployable wing mechanism
DE19740888C2 (de) Verfahren zum autonomen Lenken eines drallstabilisierten Artilleriegeschosses und autonom gelenktes Artilleriegeschoß zur Durchführung des Verfahrens
WO2018099603A1 (de) Flugkörper zum abfangen von fremddrohnen
DE3735426A1 (de) Geschoss mit entfaltbarem element zur bekaempfung freibeweglicher objekte, vorzugsweise flugkoerpern
DE2935044A1 (de) Unbemannter, aus einem transportbehaelter zu startender flugkoerper
DE1954540A1 (de) Spin- und rippenstabilisierte Rakete
EP1399706A1 (de) Artillerie-projektil mit austauschbarer nutzlast
DE2452053A1 (de) Einrichtung zum starten von raketengetriebenen flugkoerpern
DE3437824C2 (enrdf_load_stackoverflow)
DE1958355A1 (de) Flugkoerpersystem
DE69523064T2 (de) Verfahren und vorrichtung zur verwendung eines von einem trägerflugzeug gestarteten gefechtskopfes zur bekämpfung von an der flugbahn des trägerflugzeuges entlang identifizierten zielen
EP1090266B1 (de) Flugkörper zur bekämpfung feststehender und/oder beweglicher ziele
DE3522154C2 (enrdf_load_stackoverflow)
US3724782A (en) Deployable aerodynamic ring stabilizer
DE3618958C1 (de) Leitwerk mit entfaltbaren Fluegeln
DE60302281T2 (de) Waffe, die eine Rakete enthält, und die an einem Tarnkappen-Flugzeug montiert ist, und Waffensystem, das ein Tarnkappen-Flugzeug und eine solche Waffe enthält
DE68917043T2 (de) Flügelanordnung für ein Geschoss.
DE102019109360A1 (de) Inventionssystem zur Abwehr von RAM-Zielen und/oder UAVs sowie Verfahren zur Abwehr von RAM-Zielen und/oder UAVs
DE3874494T2 (de) Abwurfkoerper mit aerodynamischen bremsmitteln.
DE102005042484B4 (de) Unbemannter Gleitflugkörper

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: A1

Designated state(s): DE FR GB IT NL

17P Request for examination filed

Effective date: 19861218

17Q First examination report despatched

Effective date: 19880316

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT NL

REF Corresponds to:

Ref document number: 3662945

Country of ref document: DE

Date of ref document: 19890524

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19890610

Year of fee payment: 4

ITF It: translation for a ep patent filed
ET Fr: translation filed
GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19910301

ITTA It: last paid annual fee
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: NL

Payment date: 19910630

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Effective date: 19930101

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19930428

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19930624

Year of fee payment: 8

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19940630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Effective date: 19950228

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 19940630

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 20050630