EP0675334A1 - Aerodynamische Stabilisier- und Bremsvorrichtung für Abwurfkörper - Google Patents

Aerodynamische Stabilisier- und Bremsvorrichtung für Abwurfkörper Download PDF

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Publication number
EP0675334A1
EP0675334A1 EP95400414A EP95400414A EP0675334A1 EP 0675334 A1 EP0675334 A1 EP 0675334A1 EP 95400414 A EP95400414 A EP 95400414A EP 95400414 A EP95400414 A EP 95400414A EP 0675334 A1 EP0675334 A1 EP 0675334A1
Authority
EP
European Patent Office
Prior art keywords
flaps
machine according
machine
dynamic pressure
flap
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.)
Granted
Application number
EP95400414A
Other languages
English (en)
French (fr)
Other versions
EP0675334B1 (de
Inventor
Naîri Elmayan
Manuel Henri Seco
Hugues Beslier
Jean-Pierre Audouin
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.)
MATRA BAE DYNAMICS FRANCE
Original Assignee
MATRA DEFENSE
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 MATRA DEFENSE filed Critical MATRA DEFENSE
Publication of EP0675334A1 publication Critical patent/EP0675334A1/de
Application granted granted Critical
Publication of EP0675334B1 publication Critical patent/EP0675334B1/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
    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/50—Brake flaps, e.g. inflatable

Definitions

  • the present invention relates to devices which can be released from an aircraft, of the type provided with passive aerodynamic stabilization means, such as fins, intended to take an initial trajectory after dropping substantially parallel to the speed of the aircraft.
  • passive aerodynamic stabilization means such as fins
  • aircraft should be interpreted as covering both rotary and fixed-wing aircraft.
  • the invention finds an important application in the field of infrared or electromagnetic decoys which, to be effective, begin to play their role near the aircraft to cause the attachment of a self-steering or a radar. a hostile, then must move away in a sufficiently progressive way so that the auto-director or the radar remains hung on them, but sufficiently fast so that a missile auto-director or a radar cannot, after extinction of the lure , hang on the aircraft again.
  • a non-propelled, aerodynamically stabilized lure is given a drag coefficient Cx such that it gives the machine a satisfactory separation from the plane at high speed and low altitude, this coefficient cannot provide sufficient separation for ejection at lower speed or higher altitude, due to the drop in dynamic pressure.
  • the machine further comprises flaps which can be deployed automatically after release.
  • each of these flaps 17, four in number is constituted by a spring steel plate, the front part of which is held pressed against the body by fixing means, such as screws 18.
  • the flaps 17 are kept applied against the body of the machine, under the fins 14, and are therefore compact. They are preformed in the deployed position, so that they are then under tension and that in the absence of stress they take a free position making a determined angle a with the axis of the machine ( a ⁇ 45 ° for example).
  • the elasticity of the flaps is such that the dynamic pressure exerted on them in flight gives them an angle relative to the axis of the body which depends directly on the dynamic pressure and which is less than a .
  • the length of the flaps 17 and the fins 14 is such that they do not project beyond the rear of the body.
  • each flap 16 is reinforced by shorter elastic strips 20 whose presence modifies the law of deformation. These additional blades will be present or not according to the law of variation of the drag to be given to the machine. They are fixed flat on the flaps, for example by rivets 22.
  • the shape of the fins 14 and that of the flaps 17, as well as the nature of the means for fixing the flaps, depend on the envisaged application. It may be indicated by way of example that, in the case of a device constituted by a decoy having a caliber of 30 mm and about twenty centimeters in length, four flaps devoid of reinforcing blades, of 0.6 mm thick spring, fixed to the body by a few solder points.
  • each flap 17a is constituted by an elastic metal blade (spring steel in general), articulated on the body to the back of the skates.
  • each flap 17a can be welded to one of the elements of a hinge 24 placed immediately behind the rear sockets 16.
  • the hinges have a limited clearance, so that the flap in the free state, once turned towards the rear , make an angle b of about 45 ° with the axis of the body, near the hinge.
  • the flap 17a is designed to be folded towards the nose of the vehicle when it is stored and to be kept in abutment against the body by a fin 14 (FIG. 4).
  • the flap can be preformed so as to take the form shown in solid lines in FIG. 5 as soon as the machine is ejected and the fins 14 deployed.
  • the flaps 17a have a raised beak 26, their deployment is caused by the action of the wind on the spout.
  • the wind action can be replaced or supplemented by that of other means, for example by a pincer spring mounted on the hinge 24, a spring intended to slightly detach the flap from the body when it is released, or a wire of traction connected to the corresponding fin.

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  • 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)
EP19950400414 1994-03-02 1995-02-27 Aerodynamische Stabilisier- und Bremsvorrichtung für Abwurfkörper Expired - Lifetime EP0675334B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9402401 1994-03-02
FR9402401A FR2716965B1 (fr) 1994-03-02 1994-03-02 Engin largable à stabilisation et freinage aérodynamique.

Publications (2)

Publication Number Publication Date
EP0675334A1 true EP0675334A1 (de) 1995-10-04
EP0675334B1 EP0675334B1 (de) 2000-04-12

Family

ID=9460594

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19950400414 Expired - Lifetime EP0675334B1 (de) 1994-03-02 1995-02-27 Aerodynamische Stabilisier- und Bremsvorrichtung für Abwurfkörper

Country Status (3)

Country Link
EP (1) EP0675334B1 (de)
DE (1) DE69516200T2 (de)
FR (1) FR2716965B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2564839A2 (de) 2009-01-09 2013-03-06 Forward Pharma A/S Pharmazeutische Formulierung mit einem oder mehreren Fumarsäureestern in einer Erosionsmatrix
RU2814708C1 (ru) * 2023-08-22 2024-03-04 Акционерное общество "Научно-производственное объединение "СПЛАВ" им. А.Н. Ганичева" Головная часть вращающегося реактивного снаряда

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2747464B1 (fr) * 1996-04-16 1999-09-17 Aerospatiale Engin volant a aile deployable
US8278612B2 (en) * 2010-07-27 2012-10-02 Raytheon Company Aerodynamic fin lock for adjustable and deployable fin

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE977742C (de) * 1965-04-14 1969-04-30 Kunststofftechnische Studienge Flugkoerper mit entgegen der Luftrichtung ausklappbaren messerfoermigen Leitwerkfluegeln
DE1553980A1 (de) * 1965-02-18 1969-09-25 Breda Mecc Bresciana Einstellvorrichtung der Schussweite von Raketengeschossen
CH480612A (de) * 1967-09-06 1969-10-31 Oerlikon Buehrle Ag Rakete mit Klappleitwerk und Bremsvorrichtung
DE2154584A1 (de) * 1971-11-03 1973-05-10 Dynamit Nobel Ag Flugkoerper zur bekaempfung von unterwasserzielen
DE2637793A1 (de) * 1976-08-21 1978-02-23 Messerschmitt Boelkow Blohm Vorrichtung zur verminderung der fluggeschwindigkeit und zur stabilisierung der lage einer streumunition

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1553980A1 (de) * 1965-02-18 1969-09-25 Breda Mecc Bresciana Einstellvorrichtung der Schussweite von Raketengeschossen
DE977742C (de) * 1965-04-14 1969-04-30 Kunststofftechnische Studienge Flugkoerper mit entgegen der Luftrichtung ausklappbaren messerfoermigen Leitwerkfluegeln
CH480612A (de) * 1967-09-06 1969-10-31 Oerlikon Buehrle Ag Rakete mit Klappleitwerk und Bremsvorrichtung
DE2154584A1 (de) * 1971-11-03 1973-05-10 Dynamit Nobel Ag Flugkoerper zur bekaempfung von unterwasserzielen
DE2637793A1 (de) * 1976-08-21 1978-02-23 Messerschmitt Boelkow Blohm Vorrichtung zur verminderung der fluggeschwindigkeit und zur stabilisierung der lage einer streumunition

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2564839A2 (de) 2009-01-09 2013-03-06 Forward Pharma A/S Pharmazeutische Formulierung mit einem oder mehreren Fumarsäureestern in einer Erosionsmatrix
RU2814708C1 (ru) * 2023-08-22 2024-03-04 Акционерное общество "Научно-производственное объединение "СПЛАВ" им. А.Н. Ганичева" Головная часть вращающегося реактивного снаряда

Also Published As

Publication number Publication date
DE69516200D1 (de) 2000-05-18
FR2716965B1 (fr) 1996-05-03
EP0675334B1 (de) 2000-04-12
DE69516200T2 (de) 2000-11-23
FR2716965A1 (fr) 1995-09-08

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