EP0186903A1 - Empennage déployant des roquettes à ailettes stabilisatrices - Google Patents

Empennage déployant des roquettes à ailettes stabilisatrices Download PDF

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Publication number
EP0186903A1
EP0186903A1 EP85116566A EP85116566A EP0186903A1 EP 0186903 A1 EP0186903 A1 EP 0186903A1 EP 85116566 A EP85116566 A EP 85116566A EP 85116566 A EP85116566 A EP 85116566A EP 0186903 A1 EP0186903 A1 EP 0186903A1
Authority
EP
European Patent Office
Prior art keywords
unit according
tail unit
bearing
wings
base body
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
EP85116566A
Other languages
German (de)
English (en)
Other versions
EP0186903B1 (fr
Inventor
Marion Heide
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.)
JOSEF LUBIG GMBH
Original Assignee
Josef Lubig GmbH
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 Josef Lubig GmbH filed Critical Josef Lubig GmbH
Publication of EP0186903A1 publication Critical patent/EP0186903A1/fr
Application granted granted Critical
Publication of EP0186903B1 publication Critical patent/EP0186903B1/fr
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

Definitions

  • the invention relates to a folding tail unit for wing-stabilized missile projectiles with an essentially rotationally symmetrical base body, in which shafts are arranged in an annular groove around the wings under the action of springs that are supported against the base body and wing.
  • the known folding tail units have several, for example twelve, wings.
  • a spring is assigned to each of the wings, which is located together with the wing on the shaft about which the wing can be pivoted.
  • the shaft is designed as a circular ring or half a circular ring and the insertion of the sets of parts consisting of shafts, springs and wings into the annular groove of the base body has proven to be extremely time-consuming. This process requires the cooperation of two workers who, if they are well trained and very skillful, take more than 10 minutes to complete this process. This results in unbearably high labor costs, since the folding tail unit is a mass-produced item.
  • the invention has for its object to provide a retractable tail so designed that the assembly of the wings and springs is carried out with significantly reduced workload and can even be automated if necessary.
  • the invention relates to a folding stabilizer for wing-stabilized missile projectiles with an essentially rotationally symmetrical base body in which shafts are arranged in an annular groove around the wings under the action of springs supporting themselves against the base body and wings, and which is characterized in that each wing is assigned to individual journal serving as a shaft.
  • the bearing journals have a cylindrical middle part to which truncated cones adjoin on both sides towards the ends of the bearing journals.
  • the bearing pins are adapted to the shape of the annular groove, so that they always remain in a precisely tangential position in this and the cylindrical central part forms a perfect guide for the wing or its bore, with which it engages around the central part.
  • the largest diameters of the truncated cones are smaller than the diameter of the cylindrical middle part. This creates at both ends of the cylindrical middle part of the bearing pin an annular surface which rests in the annular groove of the base body against edges which result in radial incisions in the base body which are necessary there anyway to accommodate the spring legs. As a result, movement of the bearing journals in their longitudinal direction is excluded in the annular groove, so that the bearing journals remain in their predetermined position in any case.
  • Collars can also be arranged on the trunnion in the region of the ends of the central part, one of which is arranged on a collar sleeve to enable the wing and possibly also the spring to be slid on, which can be pushed onto a tapered section of the trunnion. This considerably simplifies the assembly of the sets of parts consisting of the journal, wing and spring.
  • the bearing pin can be designed at one end as a stepped bolt, on which a bolt cap is attached.
  • This bolt cap complements the bearing journal to its original shape and the length of its sleeve part can be dimensioned such that its free circular ring surface together with the circular ring surface resulting from a gradation of the stepped bolt serves to guide the wing.
  • the annular groove running radially to the longitudinal axis of the base body can follow the shape of a polygon, the number of sides of which corresponds to the number of wings, and the bearing pins can be cylindrical in this case.
  • the wing can also be fastened to the bearing journal in that notches are arranged on the bearing journal on both sides of the wing.
  • Embodiments of tail units according to the invention are shown below with reference to the drawing.
  • the folding tail unit is shown in FIG. 1 in a side view with the wings attached and in FIG. 2 in section with the wings opened.
  • the base body is designated in its entirety by 1, the wings by 2.
  • In the base body 1 there is an annular groove 3 in which a bearing pin 4 is arranged for each wing 2.
  • the annular groove 3 there are also the circular parts of the leg spring 5, the legs of which rest on the one hand against the wings 2 and on the other hand against the base body 1 and by the action of which.
  • Wing 2 can be opened from the position shown in Fig. 1 after the projectile has left the launcher.
  • the annular groove 3 arranged in the base body 1 can run axially parallel to the longitudinal axis 8 of the base body 1, as shown in FIG. 3, also at an acute angle to the longitudinal axis 8, as shown in FIG. 4, and also at right angles to the longitudinal axis 8, as in FIGS. 5 and 6.
  • the mounting pins 4 are fastened in the annular groove 3 as shown in FIGS. 7 to 10 by deforming or bending one or both parts of the base body surrounding the annular groove 3
  • Fig. 11 is shown in its entirety with 4 bearing pin, which consists of a cylindrical central part 9 and two truncated cones 1o adjoining its ends. The free ends of the truncated cones can be supplemented by spherical sections or blunt cones.
  • the arrangement of the bearing pin 4 in the annular groove 3 results from: Fig. 12.
  • the cylindrical part of the bearing pin 4 is located within that part 3a of the annular groove 3, in which the wing 2, not shown in the drawing, and which is through the cylindrical Part of the journal 4 is guided properly.
  • the conical parts of the bearing pin 4 adapt to the curvature of the annular groove 3 and facilitate the positioning of the bearing pin-4 within the ring groove 3. This contributes to the fact that the ends of the bearing pin 4 are frustoconically shaped in a spherical section or in a similar manner.
  • the bearing journal designated in its entirety by 4
  • the bearing journal is designed in such a way that it has a cylindrical middle part 9, to which frusto-conical members 10o connect, the largest diameter of which is smaller than the diameter of the middle part 9.
  • bearing journals according to FIGS. 14 and 15 can be used, the ends of which, as can be seen from the figures, are designed differently in FIG. 14 by the fact that rounded endings are attached to the end faces of the cylindrical part or, as in FIG Fig. 15 can be seen, to which truncated cones are connected ring collars.
  • the bearing pins 4 can also have ring collars 11 at the ends of their center pieces 9, as can be seen in FIG. 16.
  • One of the ring collars 11 can be part of a sleeve 12 which is pushed onto a correspondingly tapered section of the journal 4.
  • the bearing pin 4 shown in FIG. 17, it is formed at one end as a stepped bolt 12 onto which a bolt cap 13 is attached.
  • the bolt cap 13 supplements the stepped bolt 12 to form the bearing pin 4 and it can be fastened to the stepped bolt 12 by a deformation 14.
  • the length of the bolt cap 13 can be dimensioned such that the wing 2 is mounted between it and the original part of the bearing journal 4.
  • tail unit according to the Er 18 results from the fact that the deepest of the annular groove 3 is given a polygonal shape which differs from the immediate circular shape, as can be seen in FIG. 15 and the number of pages corresponds to the number of wings 2.
  • bearing journals 4 can be used which have an essentially cylindrical shape and can therefore be manufactured particularly cost-effectively, but on the other hand it must be accepted that the annular groove 3 of the base body 1 cannot be produced by turning it round.
  • the ends of the pivot 4 can, in particular to ensure the distances spherical cap, also be formed stum p fzylindrisch or beveled, as can be seen from FIGS. 19 and 2o.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Pivots And Pivotal Connections (AREA)
  • Toys (AREA)
  • Support Of The Bearing (AREA)
EP19850116566 1984-12-31 1985-12-24 Empennage déployant des roquettes à ailettes stabilisatrices Expired - Lifetime EP0186903B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19843447852 DE3447852A1 (de) 1984-12-31 1984-12-31 Klappleitwerk fuer fluegelstabilisierte raketengeschosse
DE3447852 1984-12-31

Publications (2)

Publication Number Publication Date
EP0186903A1 true EP0186903A1 (fr) 1986-07-09
EP0186903B1 EP0186903B1 (fr) 1993-07-21

Family

ID=6254146

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19850116566 Expired - Lifetime EP0186903B1 (fr) 1984-12-31 1985-12-24 Empennage déployant des roquettes à ailettes stabilisatrices

Country Status (2)

Country Link
EP (1) EP0186903B1 (fr)
DE (2) DE3447852A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU589730B2 (en) * 1985-11-14 1989-10-19 Grumman Aerospace Corporation Torsion spring powered missile wing deployment system
FR2790079A1 (fr) * 1999-02-19 2000-08-25 Rheinmetall W & M Gmbh Projectile stabilise par un empennage et pouvant etre lance a partir d'un tube d'arme
US7919740B2 (en) 2007-01-19 2011-04-05 Diehl Bgt Defence Gmbh & Co. Kg Wing-unfolding apparatus, folding wing assembly, and vehicle with folding wing assemblies
CN114322677A (zh) * 2021-12-29 2022-04-12 西安现代控制技术研究所 一种适应舱体的弹翼、滑块精准安装结构

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3937743A1 (de) * 1989-11-13 1991-05-16 Deutsch Franz Forsch Inst Flugkoerper

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE224404C (fr) * 1909-04-20 1910-07-19
US2430896A (en) * 1944-01-08 1947-11-18 Edward G Uhl Rocket stabilizing fins
FR1351422A (fr) * 1962-10-05 1964-02-07 Soc Tech De Rech Ind Perfectionnements aux roquettes
FR2070389A5 (fr) * 1969-12-03 1971-09-10 Serat

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL266892A (fr) * 1960-07-11
DE1578222A1 (de) * 1966-02-04 1972-02-10 Ind & Mecaniques S T R I M Sich entfaltendes Leitwerk,insbesondere fuer Raketen Societe Technique de Recherches
BE759788A (fr) * 1969-12-05 1971-06-03 Sarmac Sa Projectile autopropulse empenne
DE2342783C2 (de) * 1973-08-24 1983-12-22 Rheinmetall GmbH, 4000 Düsseldorf Mit einem Leitwerk versehenes Geschoß

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE224404C (fr) * 1909-04-20 1910-07-19
US2430896A (en) * 1944-01-08 1947-11-18 Edward G Uhl Rocket stabilizing fins
FR1351422A (fr) * 1962-10-05 1964-02-07 Soc Tech De Rech Ind Perfectionnements aux roquettes
FR2070389A5 (fr) * 1969-12-03 1971-09-10 Serat

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU589730B2 (en) * 1985-11-14 1989-10-19 Grumman Aerospace Corporation Torsion spring powered missile wing deployment system
FR2790079A1 (fr) * 1999-02-19 2000-08-25 Rheinmetall W & M Gmbh Projectile stabilise par un empennage et pouvant etre lance a partir d'un tube d'arme
US6314886B1 (en) 1999-02-19 2001-11-13 Rheinmetall W & M Gmbh Projectile to be fired from a weapon barrel and stabilized by a guide assembly
US7919740B2 (en) 2007-01-19 2011-04-05 Diehl Bgt Defence Gmbh & Co. Kg Wing-unfolding apparatus, folding wing assembly, and vehicle with folding wing assemblies
CN114322677A (zh) * 2021-12-29 2022-04-12 西安现代控制技术研究所 一种适应舱体的弹翼、滑块精准安装结构
CN114322677B (zh) * 2021-12-29 2024-05-28 西安现代控制技术研究所 一种适应舱体的弹翼、滑块精准安装结构

Also Published As

Publication number Publication date
DE3447852C2 (fr) 1991-02-28
EP0186903B1 (fr) 1993-07-21
DE3587471D1 (de) 1993-08-26
DE3447852A1 (de) 1986-08-28

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