US2793591A - Fin arrangement for a projectile - Google Patents

Fin arrangement for a projectile Download PDF

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Publication number
US2793591A
US2793591A US475973A US47597354A US2793591A US 2793591 A US2793591 A US 2793591A US 475973 A US475973 A US 475973A US 47597354 A US47597354 A US 47597354A US 2793591 A US2793591 A US 2793591A
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US
United States
Prior art keywords
fin
projectile
fins
support
fin arrangement
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Expired - Lifetime
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US475973A
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English (en)
Inventor
Jasse Joseph Raymond
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.)
NOUVELLE des Ets BRAUDT Ste
BRANDT SOC NOUV ETS
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BRANDT SOC NOUV ETS
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Publication date
Application filed by BRANDT SOC NOUV ETS filed Critical BRANDT SOC NOUV ETS
Application granted granted Critical
Publication of US2793591A publication Critical patent/US2793591A/en
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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

Definitions

  • the present invention relates to the guidance of projectiles and in particular self-propelled projectiles or rockets.
  • Another object of the invention is to provide a fin arrangement which is of the type having fins that are opened by a pivotal movement on their common support about axes parallel to the longitudinal axis of the fin arrangement and which is characterized in that said fins have a generally cylindrical shape and such cross-section that when they are folded or closed against their support the fin arrangement forms a unit having a cylindrical outer shape and a circular cross-section.
  • Another object of the invention is to provide a projectile in which this fin arrangement is incorporated, the latter having such dimensions that in the position thereof in which the fins are closed the cylinder formed by these fins has substantially the same outer diameter as the cylindrical part of the body of the projectile.
  • Fig. 1 is a rear end view of a fin arrangement which is in its open or deployed position and is combined with a self-propelled projectile, the body of the fin arrangement constituting the ejection nozzle for the propelling gases;
  • Fig. 2 is a plan view thereof, the fin arrangement and the projectile being shown disposed horizontally;
  • Fig. 3 is a view similar to that shown in Fig. 1 but in which the fins are closed or folded back;
  • Fig. 4 is a corresponding plan view
  • Fig. 5 is a sectional view on line 55 of Fig. 3, and
  • Fig. 6 is a diagrammatic view on a very small scale of the projectile which has its fin arrangement closed or folded back and is in place in the launching tube.
  • the fin arrangement is adapted to be fixed to the rear end of the cylindro-ogival body 1 of a self-propelled projectile or rocket.
  • This fin arrangement comprises the combination of a support S and three fins A pivoted tothesupport for pivotal movement about axes parallel to the longitudinal common axis XX of the fin arrangement and the projectile itself.
  • the support S is a body of revolution about the axis XX; it comprises at the forward end, relative to the direction of flight, a screw-threaded portion 2 for the purpose of its attachment to the rear end of the body 1.
  • the shoulder 3 adjacent the screw thread has a diameter d (Fig. 2) whichis very slightly less than the outer diameter of the body 1.
  • The'support S is provided with an axial throughway aperture which forms a passageway 4 for the ejection of the propelling gases.
  • the rear part of this 2,793,591 Patented May 28, 1957 sit passageway is divergent and is followed by a short cylindrical or parallel portion 5 in which is secured a ring 6 provided with inclined fins 7. The latter are adapted to cause the projectile to rotate in the direction of arrow f (Fig. 1) about its longitudinal axis.
  • the support S comprises near the front end behind the shoulder 3 a recess or rebate forming a cylindrical support surface 8. From this support surface the support decreases rapidly in diameter down to a cylindrical surface 9 which is connected by a flared portion 10 to a rear flange 11 which comprises as many bosses 12 as there are fins A; these bosses are angularly equispaced.
  • each boss 12 Fitted in each boss 12 is a spindle or pin 13 which ex- -tends in a direction parallel to the axis XX and is adapted to serve as a pivot pin for the corresponding fin A.
  • This --pin extends through a lug 14 integral with the support S and its forward end is also engaged in a blind hole 15 formed in the support (Fig. 5).
  • Each pin 13 is held in position in the longitudinal direction relative to the support by for example giving a blow with a centre punch "between the rear part of the pin 13 and the boss 12.
  • One fin A is pivotably mounted on each rod 13.
  • Each fin is identical and are of metal or light alloy such as Duralumin.
  • Each fin comprises a thin wall having the general shape of a segment of a cylinder and an armate cross-section the concave side of which faces the direction of rotation of the projectile (Fig. 1). It com prises, starting from the pivot pin, two portions 16 and lTconnected by a rib 18.
  • the portion 16 has an outer radius equal to the inner :radius of the portion 17. These radii being equal to where e is the thickness of the portion 17 (Fig. 1).
  • portion 16 is provided with two eyes 19 and 20 pivotably mounted on the pin 13. These eyes and the portion 16 are reinforced by inner ribs 21. The latter also perform another function to be explained hereinunder.
  • the rear eye 19 includes a notch 22 (Figs. 2 and 5) .whioh isso positioned and oriented with respect to the corresponding fin as to engage, in the open position of the latter (Figs. 1 and 2), a locking projection 23 constituting an abutment of prismatic or like shape and carried by the forward face of the boss 12.
  • the other eye 20 is so disposed relative to the lug 14 and the recess 8, as to per- .mit such longitudinal displacement of the fin as to enable the notch 22 to engage with (Fig. 2) or disengage from (Fig. 5) the abutment 23.
  • the portion 16 of the fin has such length that in the .two positions thereof its rear edge 24 is disposed slightly beyond the end of the support S whereas its front edge 25 is at the level of the front end of the eye 20.
  • the other portion 17 of the fin has the following characteristics:
  • d. :It comprises two apertures 28 which are in line with ".the eyes 19 and 20- in the closed position of the fin.
  • the fin arrangement is completed by a-spring 29 for each fin.
  • This spring is adapted to open the-fin by causing it to pivot about the pivot pin 13 in the direction of arrow f (Fig. 3) and, furthermore, to displace the fin in the longitudinal direction in the direction of arrow f (Fig. 5) so that it engages the abutment 23.
  • This spring 29 is of the helical type and encompasses the pin 13 between the lug I4 and the eye 19. It Works under torsion in the direction of the pivotal movement of the fin, since a branch 30 and two ends 31 and 32 formed thereon bear against the support S and the fin respectively. Furthermore, it works under compression in the longitudinal direction between the lug 14 and the eye 19.
  • a removable strap 33 is provided for maintaining the fins in their closed, folded position in opposition to the action of the springs 2? (Figs. 3 to 6). V v
  • the fins A bear against the recess 8 and the portion 17 of each fin overlaps the portion 16 of the adjacent fin situated in front thereof relative to the direction of rotation of the projectile.
  • the fin arrangement forms, therefore, a cylindrical unit having substantially the same outer diameter d as the body 1 of the projectile. Only the strap 33 projects from this body.
  • the strap 33 abuts the rear end of this tube and as soon as the projectile is launched this strap is wrenched off and the fins are freed. These fins remain temporarily closed while they are still inside the tube T and they are therefore effective in guiding the projectile.
  • the fins When the fins are completely open the notches 22 engage the abutments 23 which, on account of their prismatic or like shape, automatically take up any play.
  • the fins A are thencefo'rth securely locked in. position and, owing to their stiffening ribs, they are not subject to any vibration capable of disturbing the projectile. They behave exactly as though they were integral with their'support S.
  • these fins present as large a stabilizing surface to the surrounding air as would be prlnssible with a folding fin for a given calibre of projecti e.
  • the inner ribs 21 cause an increase in the air resistance and a thinning of the boundary layer, which results in a steeper slope of the aerodynamic moment curve as a function of the incidence, which is a favorable phenomenon as concerns the stability of the machine.
  • a fin arrangement for a projectile comprising at least one outer support surface; a plurality of parallel pivot pins carried externally by said support; locking means on said support at one end of each of said pivot pins; fins each of which is mounted -'on one of said pivot pins in such manner that each fin is capable of pivoting about its corresponding'pivot pin between an operative open position and an inoperative closed position in which latter position it is closed onto said support surface and furthermore capable of slid ing along said pivot pin between a locked position in which said fin is engaged by its corresponding locking means and an unlocked position in which it is disengaged from said locking means, the locked position corresponding to the operative position and the unlocked position to the inoperative position; and as many single elastically yieldable means as there are fins, each of said yieldable means being adapted constantly to urge its corresponding fin to pivot about the pivot pin in a direction which tends to bring it into said said open operative position and to furthermore urge the fin along its pivot pin in a
  • a support comprising at least one outer support surface; a plurality of parallel pivot pins carried externally by said support; locking means on said support at one end of each of said pivot pins; fins each of which is mounted on one of said pivot pins in such manner that each fin is capable of pivoting about its corresponding pivot pin between an operative open position and an inoperative closed position in which latter position it is closed onto said support surface and furthermore capable of sliding along said pivot pin between a locked position in which said fin is engaged by its corresponding locking means and an unlocked position in which it is disengaged from said locking means, the locked position corresponding to the operative position and the unlocked position to the inoperative position and as many helical springs as there are fins, each of said helical springs being interposed in the longitudinal direction between its corresponding fin and the support so that this spring is under compression and urges the fin in axial translation toward said locked position, this spring being provided with at least two radial branches one of which bears against the support and the other
  • a projectile having a body at least the rear part of which has an outer surface having an axis coinciding with the longitudinal axis of said body and a fin arrangement fixed at the rear of said body and comprising a support fixed to the latter and fins pivotably mounted on said support for pivotal movement about pivot pins parallel to the axis of said body, each of said fins having a thickness which is at least substantially constant and having a general shape of a segment of a cylinder the generatrices of the latter being parallel to said axes and the cross-section of each fin subtending an.
  • each fin comprising in the circumferential direction of the projectile two portions of a cylinder whose arcuate cross-sections have different radii, one of these portions, by which the fin-is pivotably mounted on the support bcing reinforced 011 its inner face by ribs and having an outer radius which corresponds to the inner radius of the other portion, the outer radius of the latter corresponding to half the outer diameter of said rear part of the projectile, whereby when the fins are closed against.
  • said support the fin arrangement assemblage References Cited in the file of this patent I V UNITED STATES PATENTS 1,890,175

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Emergency Lowering Means (AREA)
US475973A 1953-12-21 1954-12-17 Fin arrangement for a projectile Expired - Lifetime US2793591A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1096579T 1953-12-21

Publications (1)

Publication Number Publication Date
US2793591A true US2793591A (en) 1957-05-28

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ID=9618185

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Application Number Title Priority Date Filing Date
US475973A Expired - Lifetime US2793591A (en) 1953-12-21 1954-12-17 Fin arrangement for a projectile

Country Status (6)

Country Link
US (1) US2793591A (fr)
BE (1) BE533456A (fr)
CH (1) CH321152A (fr)
FR (1) FR1096579A (fr)
GB (1) GB753838A (fr)
NL (2) NL100549C (fr)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2858765A (en) * 1956-08-07 1958-11-04 Dale E Startzell Spring-loaded, locking hinge fin assembly
US3185097A (en) * 1956-08-02 1965-05-25 Vincent J Cushing Missile stabilizing means
US3598345A (en) * 1967-09-06 1971-08-10 Oerlikon Buehrle Ag Rocket with folding fins and braking device
US4004514A (en) * 1976-01-20 1977-01-25 The United States Of America As Represented By The Secretary Of The Navy Roll rate stabilized wrap around missile fins
DE2728388A1 (de) * 1976-06-25 1978-01-05 Europ Propulsion Leitwerk fuer ein projektil
US4113204A (en) * 1976-02-26 1978-09-12 Hawker Siddeley Dynamics Limited Auxiliary control of vehicle direction
US6310335B1 (en) * 1998-11-30 2001-10-30 Giat Industries Translational braking device for a projectile during its trajectory
US20040217227A1 (en) * 2001-05-08 2004-11-04 Michael Alculumbre Cartridge with fin deployment mechanism
US20050145750A1 (en) * 2002-02-07 2005-07-07 Shinichi Okada Flying body for firing from a tube with over-calibre stabilisers
EP1855076A1 (fr) * 2006-05-12 2007-11-14 LFK-Lenkflugkörpersysteme GmbH Ailes déployables flexibles pour missile
US20080111020A1 (en) * 2006-11-14 2008-05-15 Raytheon Company Delayed tail fin deployment mechanism and method
US20110315812A1 (en) * 2010-06-25 2011-12-29 Shin Sang-Hun Wing device and flight vehicle having the same
WO2012011980A1 (fr) * 2010-07-20 2012-01-26 Raytheon Company Procédé de modification de projectile
US9593922B2 (en) * 2013-03-14 2017-03-14 Bae Systems Land & Armaments L.P. Fin deployment system
US11428515B2 (en) * 2017-10-04 2022-08-30 Nexter Munitions Fin blocking device and projectile having such a device

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL211396A (fr) * 1955-10-20 Brandt Soc Nouv Ets
DE1083155B (de) * 1957-12-07 1960-06-09 Ilyana Von Thyssen Bornemisza Granatwerfergeschoss
DE1134316B (de) * 1958-04-04 1962-08-02 Bombrini Parodi Delfino Societ Raketengeschoss mit Klappenleitwerk
DE1159314B (de) * 1962-07-11 1963-12-12 Werner Gohlke Dr Ing Elastisches Klappleitwerk, insbesondere fuer Flugkoerper
FR2655720A1 (fr) * 1989-12-08 1991-06-14 Thomson Brandt Armements Aile galbee deployable pour engin volant.

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR494610A (fr) * 1917-04-21 1919-09-13 Michel Cappella Obus à ailettes et à pointes de diamant
US1890175A (en) * 1930-05-22 1932-12-06 Brandt Edgar William Projectile having guide tails
GB514085A (en) * 1939-02-18 1939-10-30 Leslie Ernest Shilston Improvements in dart flights
US2421752A (en) * 1943-02-22 1947-06-10 Eureka Williams Corp Rocket projectile
US2465401A (en) * 1943-09-23 1949-03-29 Leslie A Skinner Rocket fin assembly
DE914933C (de) * 1953-04-23 1954-07-12 Oerlikon Buehrle Ag Raketengeschoss mit aufklappbaren Stabilisierungsfluegeln

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR494610A (fr) * 1917-04-21 1919-09-13 Michel Cappella Obus à ailettes et à pointes de diamant
US1890175A (en) * 1930-05-22 1932-12-06 Brandt Edgar William Projectile having guide tails
GB514085A (en) * 1939-02-18 1939-10-30 Leslie Ernest Shilston Improvements in dart flights
US2421752A (en) * 1943-02-22 1947-06-10 Eureka Williams Corp Rocket projectile
US2465401A (en) * 1943-09-23 1949-03-29 Leslie A Skinner Rocket fin assembly
DE914933C (de) * 1953-04-23 1954-07-12 Oerlikon Buehrle Ag Raketengeschoss mit aufklappbaren Stabilisierungsfluegeln

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3185097A (en) * 1956-08-02 1965-05-25 Vincent J Cushing Missile stabilizing means
US2858765A (en) * 1956-08-07 1958-11-04 Dale E Startzell Spring-loaded, locking hinge fin assembly
US3598345A (en) * 1967-09-06 1971-08-10 Oerlikon Buehrle Ag Rocket with folding fins and braking device
US4004514A (en) * 1976-01-20 1977-01-25 The United States Of America As Represented By The Secretary Of The Navy Roll rate stabilized wrap around missile fins
US4113204A (en) * 1976-02-26 1978-09-12 Hawker Siddeley Dynamics Limited Auxiliary control of vehicle direction
DE2728388A1 (de) * 1976-06-25 1978-01-05 Europ Propulsion Leitwerk fuer ein projektil
US6310335B1 (en) * 1998-11-30 2001-10-30 Giat Industries Translational braking device for a projectile during its trajectory
US7207518B2 (en) * 2001-05-08 2007-04-24 Olympic Technologies Limited Cartridge with fin deployment mechanism
US20040217227A1 (en) * 2001-05-08 2004-11-04 Michael Alculumbre Cartridge with fin deployment mechanism
US20050145750A1 (en) * 2002-02-07 2005-07-07 Shinichi Okada Flying body for firing from a tube with over-calibre stabilisers
US7004425B2 (en) * 2002-02-07 2006-02-28 Diehl Munitionssysteme Gmbh & Co. Kg Flying body for firing from a tube with over-caliber stabilizers
EP1855076A1 (fr) * 2006-05-12 2007-11-14 LFK-Lenkflugkörpersysteme GmbH Ailes déployables flexibles pour missile
US7628353B2 (en) 2006-11-14 2009-12-08 Raytheon Company Delayed tail fin deployment mechanism and method
WO2008147453A3 (fr) * 2006-11-14 2009-01-15 Raytheon Co Mécanisme et procédé de déploiement d'empennage retardé vertical
US20080111020A1 (en) * 2006-11-14 2008-05-15 Raytheon Company Delayed tail fin deployment mechanism and method
US20110315812A1 (en) * 2010-06-25 2011-12-29 Shin Sang-Hun Wing device and flight vehicle having the same
US8525089B2 (en) * 2010-06-25 2013-09-03 Agency For Defense Development Wing device and flight vehicle having the same
WO2012011980A1 (fr) * 2010-07-20 2012-01-26 Raytheon Company Procédé de modification de projectile
US8640589B2 (en) 2010-07-20 2014-02-04 Raytheon Company Projectile modification method
US9593922B2 (en) * 2013-03-14 2017-03-14 Bae Systems Land & Armaments L.P. Fin deployment system
US11428515B2 (en) * 2017-10-04 2022-08-30 Nexter Munitions Fin blocking device and projectile having such a device

Also Published As

Publication number Publication date
NL236992A (fr)
FR1096579A (fr) 1955-06-22
CH321152A (fr) 1957-04-30
GB753838A (en) 1956-08-01
BE533456A (fr)
NL100549C (fr)

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