WO1988005898A1 - Projectile ou missile empenne - Google Patents

Projectile ou missile empenne Download PDF

Info

Publication number
WO1988005898A1
WO1988005898A1 PCT/EP1988/000069 EP8800069W WO8805898A1 WO 1988005898 A1 WO1988005898 A1 WO 1988005898A1 EP 8800069 W EP8800069 W EP 8800069W WO 8805898 A1 WO8805898 A1 WO 8805898A1
Authority
WO
WIPO (PCT)
Prior art keywords
wing
housing
bore
axis
angle
Prior art date
Application number
PCT/EP1988/000069
Other languages
German (de)
English (en)
Inventor
Gmbh Rheinmetall
Original Assignee
Eskam, Armin
Grosswendt, Werner
Glotz, Gerhard
Peller, Helmut
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 Eskam, Armin, Grosswendt, Werner, Glotz, Gerhard, Peller, Helmut filed Critical Eskam, Armin
Publication of WO1988005898A1 publication Critical patent/WO1988005898A1/fr

Links

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

Definitions

  • the invention relates to a wing stable it projectile or missile according to the preamble of claim 1.
  • a wing-stabilized projectile is known from US Pat. No. 4,568,040, in which the respective wing base is movably received in a slot arranged obliquely to the circumferential direction and to the longitudinal axis and is held by means of a pin which extends transversely to the slot.
  • the object of the invention is therefore to provide a wing-stabilized projectile or missile of the type mentioned, in which with the aid of a simple device it is achieved that the wings are arranged adjacent to the projectile in the retracted position and perpendicular to the longitudinal axis in the extended position e of the projectiles and thus act like knife blades.
  • Fig. 1 shows a perspective and detail of a housing of a projectile or missile with wings folded or unfolded
  • Fig. 2 shows an articulated connection between the housing and wing as a detail of Fig. 1;
  • Fig. 3 show a wing in side view and in and plan view
  • Fig. 5 shows schematically a section through part of the housing, perpendicular to the longitudinal axis of the housing
  • Fig. 6 shows a section through part of the
  • a tubular, partially partially prismatic housing section 1 which has a ring section 2, in the area of which wings 3 are articulated, to which the prismatic area 4 adjoins the tip of the wing body or projectile, on the flattened side of which surfaces 5 extending in the axial direction rest the wings 3 in the folded state, d. H. that the wings 3 then take up a position that takes up little space.
  • the wings 3 have a hinge pin 6 on the foot side, which is inclined to the wing longitudinal axis 30 (cf. also FIG. 4) and is rotatably received in a bore 7 in the housing 1 so that it cannot fall out.
  • the bore 7 is also suitable for the radial plane 33 (cf. also FIG. 5) of the housing 1.
  • the pivot pins are secured by locking rings 8.
  • the ring section 2 also has on the outside in the region of each bore 7 a recess 9 which is delimited on one side by a connecting element 10.
  • the recess 9 is formed in the present embodiment such that the wing 3 can rotate 90 ° by rotation about the pivot pin 6, so that it then stands as a knife wing perpendicular to the longitudinal axis of the missile or projectile (the angle ⁇ between the wing and the longitudinal axis of the housing is in in this case 90 °) and rests against the stop shoulder 10.
  • each wing 3 being biased in the direction of rotation 12 by a helical spring 11, the helical spring 11 being fixed at one end 13 to the pivot pin 6 and with the other end 14 to the ring section 2 under appropriate pretension, the helical spring 11 being secured by a Screw 15 is held, which is screwed into a corresponding threaded bore 16 at the free end of the pivot pin 6.
  • the ends 13, 14 of the helical spring 11 are expediently inserted into corresponding bores 17 in the pivot pin 6 or recesses 18 in the ring 2.
  • the threaded bore 16 is also advantageously stepped so that it essentially receives the helical spring windings. As a result, little interior space is taken up by the wing linkage.
  • FIGS. 5 and 6 show how the bore 7 is to be arranged in the housing wall so that the respective wing 3 can be folded into the desired positions.
  • the axis 31 of the bore 7 projected onto the housing longitudinal plane 32 - which is defined by the extension of the wing surface 25 of the unfolded wing 3 - includes the angle ⁇ with the radial plane 33 going through the bore 7.
  • the axis 31 projected onto a radial plane 33 passing through the bore 7 includes the angle ⁇ with the longitudinal plane 32.
  • the angles ⁇ and ⁇ in turn correspond to the angles indicated in FIGS. 3 and 4.
  • angles ⁇ and ⁇ are each approximately 45 °.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

Un projectile ou missile empenné comporte un logement (1) présentant un axe longitudinal, auquel sont articulées plusieurs ailettes (3) qui, dans leur position déployée, perpendiculaire à l'axe longitudinal, sont précontraintes par des ressorts. En vue d'un encombrement minime des ailettes (3) en position escamotée, mais afin qu'elles assurent une sustentation symétrique, en position déployée, comme avec des ailettes en forme de lame, il est prévu que chaque ailette (3) possède côté base un pivot (6) qui est inclincé par rapport à l'axe longitudinal (30) de l'ailette et monté rotatif sans pouvoir sortir de son logement grâce à un perçage (7) du logement (1), ledit perçage (7) étant incliné en conséquence par rapport au plan radial du logement (1). Sur la face extérieure du logement (1) dans la région de chaque perçage (7) est prévu un évidement permettant un déploiement par pivotement de chaque ailette (3). Ledit évidement est délimité par un épaulement de butée (10) destiné à l'ailette (3), qui maintient cette dernière en position verticale par rapport à l'axe longitudinal.
PCT/EP1988/000069 1987-02-02 1988-02-01 Projectile ou missile empenne WO1988005898A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3702994 1987-02-02
DEP3702994.0870202 1987-02-02

Publications (1)

Publication Number Publication Date
WO1988005898A1 true WO1988005898A1 (fr) 1988-08-11

Family

ID=6320016

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP1988/000069 WO1988005898A1 (fr) 1987-02-02 1988-02-01 Projectile ou missile empenne

Country Status (2)

Country Link
ES (1) ES2006547A6 (fr)
WO (1) WO1988005898A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2238856A (en) * 1989-12-08 1991-06-12 Thomson Brandt Armements Deployable shaped wing for a flying projectile
EP0506536A1 (fr) * 1991-03-26 1992-09-30 Societe D'applications Generales D'electricite Et De Mecanique Sagem Dispositif de déplacement d'une ailette d'un projectile
WO1995031689A1 (fr) * 1994-05-13 1995-11-23 Hughes Aircraft Company Missile a ailettes de guidage deployables
EP0803701A2 (fr) * 1996-04-19 1997-10-29 Lockheed Martin Vought Systems Mécanisme de déploiement multiaxial à mouvement synchronisé contrÔlé
US6092264A (en) * 1998-11-13 2000-07-25 Lockheed Martin Corporation Single axis fold actuator and lock for member
WO2006081226A1 (fr) * 2005-01-26 2006-08-03 Raytheon Company Systeme de deploiement d'ailettes monoaxial
US8378278B2 (en) 2008-02-26 2013-02-19 Elbit Systems Ltd. Foldable and deployable panel
SE2000115A1 (en) * 2020-07-03 2022-01-04 Saab Ab A wing arrangement, a projectile, a method for deploying a wing blade, a use and a method for assembly

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR584999A (fr) * 1924-07-29 1925-02-19 Obus à couteaux
US3063375A (en) * 1960-05-19 1962-11-13 Wilbur W Hawley Folding fin
US3185097A (en) * 1956-08-02 1965-05-25 Vincent J Cushing Missile stabilizing means
FR1485580A (fr) * 1966-03-15 1967-06-23 Hotchkiss Brandt Empennage perfectionné pour roquette
FR1505851A (fr) * 1965-12-20 1967-12-15 United Kingdom Government Ailettes de stabilisation et de guidage repliables pour fusées
US3998407A (en) * 1974-07-30 1976-12-21 The United States Of America As Represented By The Secretary Of The Army Folding tail fins
US4664339A (en) * 1984-10-11 1987-05-12 The Boeing Company Missile appendage deployment mechanism

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR584999A (fr) * 1924-07-29 1925-02-19 Obus à couteaux
US3185097A (en) * 1956-08-02 1965-05-25 Vincent J Cushing Missile stabilizing means
US3063375A (en) * 1960-05-19 1962-11-13 Wilbur W Hawley Folding fin
FR1505851A (fr) * 1965-12-20 1967-12-15 United Kingdom Government Ailettes de stabilisation et de guidage repliables pour fusées
FR1485580A (fr) * 1966-03-15 1967-06-23 Hotchkiss Brandt Empennage perfectionné pour roquette
US3998407A (en) * 1974-07-30 1976-12-21 The United States Of America As Represented By The Secretary Of The Army Folding tail fins
US4664339A (en) * 1984-10-11 1987-05-12 The Boeing Company Missile appendage deployment mechanism

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2238856A (en) * 1989-12-08 1991-06-12 Thomson Brandt Armements Deployable shaped wing for a flying projectile
FR2655720A1 (fr) * 1989-12-08 1991-06-14 Thomson Brandt Armements Aile galbee deployable pour engin volant.
GB2238856B (en) * 1989-12-08 1993-12-15 Thomson Brandt Armements Deployable shaped wing for a flying projectile
EP0506536A1 (fr) * 1991-03-26 1992-09-30 Societe D'applications Generales D'electricite Et De Mecanique Sagem Dispositif de déplacement d'une ailette d'un projectile
FR2674619A1 (fr) * 1991-03-26 1992-10-02 Sagem Dispositif de deplacement d'une ailette d'un projectile.
WO1995031689A1 (fr) * 1994-05-13 1995-11-23 Hughes Aircraft Company Missile a ailettes de guidage deployables
EP0803701A2 (fr) * 1996-04-19 1997-10-29 Lockheed Martin Vought Systems Mécanisme de déploiement multiaxial à mouvement synchronisé contrÔlé
EP0803701A3 (fr) * 1996-04-19 1998-11-25 Lockheed Martin Vought Systems Mécanisme de déploiement multiaxial à mouvement synchronisé contrÔlé
US6092264A (en) * 1998-11-13 2000-07-25 Lockheed Martin Corporation Single axis fold actuator and lock for member
WO2006081226A1 (fr) * 2005-01-26 2006-08-03 Raytheon Company Systeme de deploiement d'ailettes monoaxial
US7642492B2 (en) 2005-01-26 2010-01-05 Raytheon Company Single-axis fin deployment system
US8378278B2 (en) 2008-02-26 2013-02-19 Elbit Systems Ltd. Foldable and deployable panel
SE2000115A1 (en) * 2020-07-03 2022-01-04 Saab Ab A wing arrangement, a projectile, a method for deploying a wing blade, a use and a method for assembly
WO2022005363A1 (fr) * 2020-07-03 2022-01-06 Saab Ab Agencement d'aile, projectile, procédé de déploiement d'une pale d'aile, utilisation et procédé d'assemblage
SE544263C2 (en) * 2020-07-03 2022-03-22 Saab Ab A wing arrangement, a projectile, a method for deploying a wing blade, a use and a method for assembly
US11781841B2 (en) 2020-07-03 2023-10-10 Saab Ab Wing arrangement, a projectile, a method for deploying a wing blade, a use and a method for assembly

Also Published As

Publication number Publication date
ES2006547A6 (es) 1989-05-01

Similar Documents

Publication Publication Date Title
DE3543042C2 (fr)
DE3833329C2 (de) Chipartige Mikrosicherung
DE2834296C3 (de) Vorrichtung zum Herstellen von hinterdrehten Nuten in pfannenförmigen Knochen
EP0773007B1 (fr) Capule de hanche endoprothétique
CH681421A5 (fr)
DE2106671C3 (de) Vorrichtung zum Schärfen von Bohrerspitzen, insbesondere von Spiralbohrern
DE1777097C3 (de) Bohrkopf
WO1988005898A1 (fr) Projectile ou missile empenne
CH625602A5 (fr)
DE69024458T2 (de) Subgefechtskopf
DE2261173B2 (de) Vorrichtung zum lösbaren Festlegen von Lasten
DE1119058B (de) Befestigungsvorrichtung
DE4343024C2 (de) Vorrichtung zur veränderbaren Kodierung und diese enthaltende Verbindungsvorrichtung
DE10118216A1 (de) Ruderblatt-Lagereinrichtung für ein Geschoß
DE2609932C2 (de) Klappleitwerk für Flugkörper
DE2811678A1 (de) Laengenverstellbare strebe
EP0183219A1 (fr) Raccord pour au moins trois traverses longeant les axes de coordonnées
DE2711280A1 (de) Verbindungsanordnung
DE69217604T2 (de) Subgefechtskopf
EP0376044B1 (fr) Outil de carottage
DE3712704A1 (de) Flugkoerper mit ausklappbaren fluegeln
CH661347A5 (de) Geschoss mit einem leitwerk aus einer anzahl sich selbst aufrichtenden fluegeln, insbesondere fuer artilleriegeschuetze.
DE3730019C1 (de) Submunitions-Flugkoerper
DE202006003731U1 (de) Einstelleinrichtung eines Montagemittels für Lagergehäuse
DE3149288A1 (de) Schwenkmechanismus fuer stehsegler- und wellenreitbretter

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): US

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): AT BE CH DE FR GB IT LU NL SE

WA Withdrawal of international application