EP0327680A1 - Ailes stabilisatrices pivotantes - Google Patents

Ailes stabilisatrices pivotantes Download PDF

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Publication number
EP0327680A1
EP0327680A1 EP88117795A EP88117795A EP0327680A1 EP 0327680 A1 EP0327680 A1 EP 0327680A1 EP 88117795 A EP88117795 A EP 88117795A EP 88117795 A EP88117795 A EP 88117795A EP 0327680 A1 EP0327680 A1 EP 0327680A1
Authority
EP
European Patent Office
Prior art keywords
tail
wall
bearing
wing
tail unit
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.)
Withdrawn
Application number
EP88117795A
Other languages
German (de)
English (en)
Inventor
Klaus Dietmark Karius
Armin Eskam
Rolf Hellwig
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall 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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0327680A1 publication Critical patent/EP0327680A1/fr
Withdrawn legal-status Critical Current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 swing tail for a cargo floor according to the preamble of claim 1.
  • Such swing tails for example known from US Pat. No. 3,177,809, however, each have free spaces in the pivoted-in position of the tail wings between the respective inner sides of the tail wings and the outer wall of the storey, as a result of which, in a disadvantageous manner, only a reduced payload space is available within a circular storey wall enclosed by the tail unit .
  • the free spaces essentially arise from the fact that bearing blocks for the wings of such pivoting stabilizers are arranged on a circular outer wall of the storey.
  • the tail fins can be destroyed in a further disadvantageous manner after the passage of the pipe, for example in the case of a drawn pipe, by sudden expansion of the propellant charge gases flowing into the free spaces by an opening blow.
  • the tail fins In the swiveled-in position, the tail fins initially rest with their outer contour on an inner surface of a propellant charge sleeve and, when a tube passes through, on the inner surface of a gun.
  • This arrangement does not allow an overlapping of one empennage wing by another in the swiveled-in position of the empennage wing, which is why on the one hand a large number of short empennage wings have to be arranged on the floor circumference, on the other hand, due to the short wing spans, only small empennage surfaces are available for flight stabilization, so that ballistic scattering of scattered images can occur.
  • the invention advantageously makes it possible, on the one hand, to enlarge the existing payload space by, for example, four partial payload spaces, by means of a segment-like structure of the storey wall between two empennage axes, as a result of which, in particular, an enlarged base-bleed set can be installed.
  • a gap-free contact of the empennage wings on this segment-like storey wall prevents disadvantageous effects on the empennage wings by the fact that an overpressure, possibly destroying the empennage wings, by the propellant charge gases cannot become effective when the wing is swung open after the pipe has been passed through.
  • the storey wall in the respective area of an empennage bearing forms a stop adapted to the outer contour of the empennage wing, as a result of which a wing position with a particularly large opening angle is ensured without additional means.
  • the contours of the interior of the tail unit and the outer side of the storey wall are coordinated with one another in such a way that a joint curve shape results in a decrease in the wing thickness (s) to the extent that in the wing position applied, a wing outer contour adapted to the caliber diameter and in the pivoted wing position in each longitudinal section of the wing are guaranteed under the same bending stresses.
  • a sub-calibrated design of each empennage bearing also allows an overlapping of the bearing area by an adjacent wing in the wing position, which means that especially empennage wings with a larger span, in particular also with caliber diameters with greater curvature, can be arranged on the floor in a space-saving manner.
  • Such a large-area wing arrangement achieves high flight stability, for example in the case of wing-stabilized projectiles, as a result of which particularly little ballistic scattering of scattered images can occur particularly advantageously.
  • the tailplane is explained with reference to an embodiment shown in the drawing.
  • the cargo floor 2 shown in Figure 1 essentially illustrates the outer contours of the cargo floor body 4, which forms a hollow and ogival-shaped tip 9 in the front area, provides space for the payload in the middle floor area and a base-bleed inside in the rear area Set 18 ( Figure 2) and outside a tailplane 1 receives.
  • a guide ring 19 corresponding to the caliber diameter (d) is arranged in the front area and a "slipping" sealing ring 20 is arranged on the projectile rear, the latter being held in the axial direction via a flange 21 fastened to the projectile body 4 with screws 22.
  • the pivoting tail 1 preferably comprises four tail fins 6 which can be pivoted about the tail axis 3 parallel to the projectile axis 3 and connected to the projectile body 4.
  • At least 1, preferably 3, tail arm bearings 7 encompassing the tail axis 5 are arranged on each tail wing 6, each with a bearing 7 in the front, in the middle and is arranged in the rear region of the tail axis 5.
  • the storey wall 8 has radial recesses or constrictions 23 between the bearing points 24 of the tail unit axes 5 (FIG. 2).
  • the tail axles 5 are held in position on the storey wall 8 by securing means, for example pins provided in the area of the bearing points 24.
  • Each empennage wing 6 assumes a rear position defined in the axial direction by a torsion spring 26 which is wound around the empennage axis 5 and which is supported on the one hand on the projectile wall 8 and on the other hand on the middle empennage bearing 7, for example.
  • each tail unit wing 6 is held in its pivoted-out position 12.2 (FIG. 3) by a bevel 27 arranged on the front empennage wing 6 under the influence of the air flow.
  • FIGS. 2 and 3 illustrate on the one hand the wing positions 12.1, 12.2 applied to the storey wall 8 and the pivoted out positions. It can be seen from FIG. 2 that the outer contours 10.1 of the empennage wing 6 in the applied position 12.1 assume a shape adapted to the caliber diameter (d). FIG. 2 also illustrates that the tail wings 6 rest against the outer contour 15 (FIG. 3) of the storey wall 8 without gaps. Such a gap-free installation of the empennage wings 6 is possible because the storey wall 8 between two adjacent empennage axes 5 is segment-like and the outer contour 15 of the segment wall 11 and the contour 16 (FIG. 3) of the inner surface of an applied empennage wing 6 have the same curve.
  • a segment wall inner side 13 which runs parallel to the segment wall outer contour 15, forms a partial payload space 14, which is the previously usually available space of a known cylindrical and dash-dotted bullet wall 28, as is also known from the US-PS 3,177,809 emerges, significantly enlarged.
  • FIG. 4 shows that the contour of the constriction in the outer radius r of an empennage bearing 7 is adapted.
  • the storey wall 8 is designed in the respective area of an empennage bearing 7 as a stop 29 (FIG. 4) adapted to the outer contour 10.2 of the empennage wing 6.
  • This stop 29 consists of an approximately tangential outward side of the constriction 23 and thereby guarantees a stable contact of the outside Contour 10.2 of the empennage wing 6 in a widely pivoted position 10.2 ( Figure 3).
  • the contour 16 of the interior of the empennage wing extends in such a way that a decrease in the wing wall thickness (s) of approximately twice the radius (r) of the empennage bearing 7 up to one at the opposite end of the empennage bearing 7 Wing tip 17 takes place to the extent that the same bending stresses are ensured in each longitudinal cross section of the wing between the tailplane bearing 7 and the wing tip 17 and the load.
  • FIG. 4 shows that the empennage wings 6 are designed in a calibrated position 12.1 in the outer region of the empennage bearings 7 by the caliper of a tail fin tip 17. As a result, each bearing area can be overlapped by an adjacent tailplane wing 6 in order to achieve a large wing span.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Earth Drilling (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP88117795A 1988-02-11 1988-10-26 Ailes stabilisatrices pivotantes Withdrawn EP0327680A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19883804131 DE3804131A1 (de) 1988-02-11 1988-02-11 Schwenkleitwerk
DE3804131 1988-02-11

Publications (1)

Publication Number Publication Date
EP0327680A1 true EP0327680A1 (fr) 1989-08-16

Family

ID=6347119

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88117795A Withdrawn EP0327680A1 (fr) 1988-02-11 1988-10-26 Ailes stabilisatrices pivotantes

Country Status (2)

Country Link
EP (1) EP0327680A1 (fr)
DE (1) DE3804131A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2742220A1 (fr) * 1995-12-09 1997-06-13 Agency Defense Dev Appareil pour deplier et fixer les ailettes d'un engin
WO2002021069A1 (fr) 2000-09-05 2002-03-14 Bofors Defence Ab Procede et systeme d'extension du parcours de tir d'un missile d'artillerie stabilise par ailettes
WO2019093939A1 (fr) * 2017-11-10 2019-05-16 Bae Systems Bofors Ab Portion de queue
CN111189363A (zh) * 2020-01-19 2020-05-22 中北大学 一种直翼飞行稳定器

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB831221A (en) * 1957-03-29 1960-03-23 Vickers Armstrongs Ltd Improvements in or relating to projectiles
US3177809A (en) * 1962-07-24 1965-04-13 Budd Co Semi-fixed artillery round

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB831221A (en) * 1957-03-29 1960-03-23 Vickers Armstrongs Ltd Improvements in or relating to projectiles
US3177809A (en) * 1962-07-24 1965-04-13 Budd Co Semi-fixed artillery round

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2742220A1 (fr) * 1995-12-09 1997-06-13 Agency Defense Dev Appareil pour deplier et fixer les ailettes d'un engin
US5820072A (en) * 1995-12-09 1998-10-13 Agency For Defense Development Apparatus for unfolding and fixing missile fins
WO2002021069A1 (fr) 2000-09-05 2002-03-14 Bofors Defence Ab Procede et systeme d'extension du parcours de tir d'un missile d'artillerie stabilise par ailettes
EP1328768B1 (fr) * 2000-09-05 2011-06-29 BAE Systems Bofors AB Procede et systeme d'extension de la portee d'un missile d'artillerie stabilise par ailettes
WO2019093939A1 (fr) * 2017-11-10 2019-05-16 Bae Systems Bofors Ab Portion de queue
US11307004B2 (en) 2017-11-10 2022-04-19 Bae Systems Bofors Ab Tail portion for fin-stabilized projectile
CN111189363A (zh) * 2020-01-19 2020-05-22 中北大学 一种直翼飞行稳定器

Also Published As

Publication number Publication date
DE3804131A1 (de) 1989-08-24

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