US2924175A - Foldable fin arrangement for a projectile - Google Patents

Foldable fin arrangement for a projectile Download PDF

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Publication number
US2924175A
US2924175A US616496A US61649656A US2924175A US 2924175 A US2924175 A US 2924175A US 616496 A US616496 A US 616496A US 61649656 A US61649656 A US 61649656A US 2924175 A US2924175 A US 2924175A
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US
United States
Prior art keywords
fin
projectile
fin arrangement
arrangement
members
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.)
Expired - Lifetime
Application number
US616496A
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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 BRANDT Ste
BRANDT SOC NOUV ETS
Original Assignee
BRANDT SOC NOUV ETS
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.)
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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 US2924175A publication Critical patent/US2924175A/en
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

Definitions

  • the present invention relates to foldable fin arrangements for projectiles and in particular fin arrangements for stabilizing self-propelled projectiles or rockets on their trajectory.
  • the object of the invention is to provide a. fin arrangement which is simple, particularly convenient to use and very effective in use.
  • each of the fins which is mounted along one of its longitudinal edges on the central body of the fin arragement for pivotal movement about a longitudinal axis parallel to the axis of the fin arrangement, comprises at least two members connected together for pivotal movement about an axis parallel to said axes.
  • Fig. 1 is a rear end view of a fin arrangement, embodying the invention, in the unfolded or open position of the arrangement;
  • Fig. 2 is a partial side elevational view with a part of the body of the rocket, on which the fin arrangement is mounted, shown in section, and
  • Figs. 3 and 4 are similar views, the fin arrangement being in its folded or closed position.
  • the fin arrangement is adapted to be fixed to the rear end of the hollow body R of a rocket or other projectile, this body being tapped at a for receiving the screw-threaded forward end 1 of the central body 2 of the fin arrangement.
  • This body 2 is a body of revolution about a longitudinal axis XX (Fig. 2) which, after the body 2 has been screwed into the body R, coincides with the longitudinal axis of the projectile.
  • the body 2 which is hollow so as to form a nozzle 3 for ejection of the propelling gases, comprises a flange 4 and terminates at its rear end in a flange 5.
  • Pivoted to the body 2 are a number of fins--three in the presently-described embodiment-which are capable of being unfolded or opened in their operative positions A, B, C shown in Figs. 1 and 2, or folded or closed in their inoperative positions A, B C shown in Figs. 3 and 4.
  • Each fin comprises two members 6 and 7 which, in the unfolded fin position, are disposed adjacent one another substantially in a longitudinal radial plane containing the axis XX, whereas in the closed fin position they are closed one on top of the other and assume the positions 60 and 7a shown in Figs. 3 and 4.
  • each fin is pivoted to the body 2 by a pin 8 which is parallel to the axis XX, extends through the flange 4 of the body 2 and is engaged at its 2,924,175 Patented 9, 1960 forward end 9 in a blind hole formed in the forward part of the body 2, and at the rear end in a boss 10 provided on the flange 5 of said body. 1 r
  • the member 6 of the fin is pivotably mounted on the pin 8 by two eyes 11.
  • a coil spring 12 encompassing the pin 8 is arranged to work'under torsion so as to open or unfold the member 6 of the fin by pivoting it about the pin 8 in the direction of arrow f (Fig. 1) up to an extreme position shown in Fig. 1, one of the ends 13 of this spring bearing against the body 2 and its other end 14 bearing against the member 6.
  • the spring 12 is arranged to work under compression since at one end it abutsthe flange 4 and at its other end it abuts the forward face 15 of the rear eye 11 of the member6ofthefin.
  • the spring 12 urges the fin rearwardly relative to the projectile in the direction of arrow 1' (Fig. 2) and tends to engage thisfin inits unfolded position in a locked position resulting from the engagement of a recess 16 formed in the rear face of the eye 11, on a knifeedged part or like projection -17 formed on the forward face of the boss 10 (or vice-verse).
  • the recess 16 and the projection 17 are so oriented that when the projection enters the recess, the member 6 of the fin lies in a substantially radial plane relative to the body 2.
  • the other member 7 of the fin is pivoted to the member 6 in a similar manner, that is, by means of a pin 18 which is also parallel to the axis XX.
  • This pin 18 extends through conjugate eyes 19 and 20 formed on the members 6 and 7.
  • a spring 21 encompasses the pin 18 and also works, firstly, under torsion so as to unfold the member 7 of the fin by pivotal movement in the direction of arrow f relative to the member 6 (Fig. 1), the ends 22 and 23 of this spring bearing laterally against the members 6 and 7, and, secondly, under compression, since it bears against two of the eyes 19 and 20 and thus locks the member 7 to the member 6 in the unfolded position by engagement of a knife-edged part or like projection 24, formed on one of the eyes 20 of the member 7, in a recess 25 formed in the adjacent face of the adjoining eye 19 of the member 6 (or vice versa).
  • one of the eyes 19, for example the rear eye 19 (Fig. 2), comprises an abutment 26 adapted to serve as a bearing face in the folded position 7a (see Fig. 3) of the member 7.
  • the fin arrangement Before the projectile is launched, the fin arrangement is in the folded or closed position shown in Figs. 3 and 4.
  • the two members of each fin are in their forward position, relative to the projectile, on their pivot pins 8 and 18 and their recesses 16 and 25 are disengaged from the locking means formed by the projections 17 and 24.
  • the fins are held in the folded position 6a, 7a in opposition to the actions of the springs 12 and 21 by a detachable ring 27 which is slipped over the folded fin arrangement in the forward direction relative to the projectile.
  • the projectile R provided with the fin arrangement in its folded position, is engaged in the launching barrel and the ring 27 is automatically slipped off when it abuts the rear end of the launching barrel.
  • the fins are temporarily held in their folded position while they are in side this barrel, but as soon as they issue therefrom they are automatically unfolded by the actions of the springs 12 and 21, each of which causes both the rotation of 3 16 and 25. Each fin 6-7 is thus locked in the unfolded or open position.
  • the folded fin arrangement takes up a very small amount of space.
  • the fin arrangement dees not protrudefrom the Outer contour of the projectile (Fig. 3-) and thus does not interfere with the proper launching thereof.
  • the automatic unfolding and locking of the fins by the action of the springs 12 and 21 rendersthe fin arrangement absolutely sure in operation.
  • each fin may consist of more than two members pivoted together in the above-described manner.
  • a projectile comprising a central body defining a longitudinal axis, fins symmetrically distributed around said body, each fin including at least first and second planar members and hinge devices coupling the planar members and spaced longitudinally of each other, further hinge devices coupling the first planar members to said body, the hinge devices providing for a displacement of the parts whereby the first and second planar members can be flattened against each other and against said body, locking means on the hinge devices between associated planar members.
  • the locking means between the associated planar members and between said one of the latter and said body being on longitudinally spaced hinge devices; said locking means providing for locking the associated planar members in coplanar radial positions, and springs associated with each hinge device and acting with compressive and torsional forces respectively to actuate the locking means and to bring the planar members into radial position whereat the locking means are actuatable.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
US616496A 1955-10-20 1956-10-17 Foldable fin arrangement for a projectile Expired - Lifetime US2924175A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1038951X 1955-10-20

Publications (1)

Publication Number Publication Date
US2924175A true US2924175A (en) 1960-02-09

Family

ID=9587986

Family Applications (1)

Application Number Title Priority Date Filing Date
US616496A Expired - Lifetime US2924175A (en) 1955-10-20 1956-10-17 Foldable fin arrangement for a projectile

Country Status (7)

Country Link
US (1) US2924175A (fr)
BE (1) BE551492A (fr)
CH (1) CH333219A (fr)
DE (1) DE1038951B (fr)
FR (1) FR1134930A (fr)
GB (1) GB795045A (fr)
NL (2) NL104379C (fr)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3058422A (en) * 1959-04-13 1962-10-16 Bofors Ab Wing assembly for missiles
US3103886A (en) * 1960-10-13 1963-09-17 Charles H Popenoe Coiling fin for tube launched missiles
US3165281A (en) * 1962-07-11 1965-01-12 Werner J V Gohlke Elastic folding control surfaces for aerodynes
US3273500A (en) * 1965-01-25 1966-09-20 Kongelbeck Sverre Self-erecting folding fin
US3695556A (en) * 1970-08-03 1972-10-03 Us Navy Hinged stability and control fin assembly
US3952970A (en) * 1974-08-28 1976-04-27 The United States Of America As Represented By The Secretary Of The Navy Means for improving rocket missile accuracy
DE2637461A1 (de) * 1976-08-20 1978-03-09 Messerschmitt Boelkow Blohm Leitwerk fuer flugkoerper
EP0013096A1 (fr) * 1978-12-29 1980-07-09 The Commonwealth Of Australia Mécanisme pour aile repliable
US4336914A (en) * 1978-12-29 1982-06-29 The Commonwealth Of Australia Deployable wing mechanism
US5063849A (en) * 1989-10-20 1991-11-12 Aktiebolaget Bofors Subwarhead
US5085381A (en) * 1991-03-29 1992-02-04 The United States Of America As Represented By The Secretary Of The Air Force Deployable aerodynamic aerosurface
US6092264A (en) * 1998-11-13 2000-07-25 Lockheed Martin Corporation Single axis fold actuator and lock for member
US20040217227A1 (en) * 2001-05-08 2004-11-04 Michael Alculumbre Cartridge with fin deployment mechanism
WO2008071608A1 (fr) * 2006-12-15 2008-06-19 Thales Dispositif d'empennage porteur deployable pour obus
US20110315812A1 (en) * 2010-06-25 2011-12-29 Shin Sang-Hun Wing device and flight vehicle having the same
CN105620722A (zh) * 2014-10-29 2016-06-01 北京临近空间飞行器系统工程研究所 一种基于热敏形状记忆合金的折叠翼舵小型化展开结构
US9593922B2 (en) * 2013-03-14 2017-03-14 Bae Systems Land & Armaments L.P. Fin deployment system
EP3165870A1 (fr) * 2015-11-06 2017-05-10 MBDA Deutschland GmbH Aile repliable pour missile et missile équipé d'au moins une aile repliable
US20180093753A1 (en) * 2016-09-30 2018-04-05 Edward Chow Collapsible and Rapidly-Deployable Unmanned Aerial Vehicle

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3403508A1 (de) * 1984-02-02 1985-08-08 Dynamit Nobel Ag, 5210 Troisdorf Flugkoerper
DE102017113058B4 (de) 2017-06-14 2023-04-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. Raumtransport-Fluggerät

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1448166A (en) * 1918-05-15 1923-03-13 Edw Fay Wilson Projectile
FR1096579A (fr) * 1953-12-21 1955-06-22 Brandt Soc Nouv Ets Empennage pour projectile
FR1104534A (fr) * 1954-05-13 1955-11-21 Soc Tech De Rech Ind Empennage déployable
US2784669A (en) * 1953-04-23 1957-03-12 Mach Tool Works Oerlikon Admin Rocket projectile with stabilizer fins

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1061242A (fr) * 1952-08-05 1954-04-09 Perfectionnement aux projectiles-fusées à ailettes d'empennage déployables

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1448166A (en) * 1918-05-15 1923-03-13 Edw Fay Wilson Projectile
US2784669A (en) * 1953-04-23 1957-03-12 Mach Tool Works Oerlikon Admin Rocket projectile with stabilizer fins
FR1096579A (fr) * 1953-12-21 1955-06-22 Brandt Soc Nouv Ets Empennage pour projectile
FR1104534A (fr) * 1954-05-13 1955-11-21 Soc Tech De Rech Ind Empennage déployable

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3058422A (en) * 1959-04-13 1962-10-16 Bofors Ab Wing assembly for missiles
US3103886A (en) * 1960-10-13 1963-09-17 Charles H Popenoe Coiling fin for tube launched missiles
US3165281A (en) * 1962-07-11 1965-01-12 Werner J V Gohlke Elastic folding control surfaces for aerodynes
US3273500A (en) * 1965-01-25 1966-09-20 Kongelbeck Sverre Self-erecting folding fin
US3695556A (en) * 1970-08-03 1972-10-03 Us Navy Hinged stability and control fin assembly
US3952970A (en) * 1974-08-28 1976-04-27 The United States Of America As Represented By The Secretary Of The Navy Means for improving rocket missile accuracy
DE2637461A1 (de) * 1976-08-20 1978-03-09 Messerschmitt Boelkow Blohm Leitwerk fuer flugkoerper
EP0013096A1 (fr) * 1978-12-29 1980-07-09 The Commonwealth Of Australia Mécanisme pour aile repliable
JPS5592900A (en) * 1978-12-29 1980-07-14 Commw Of Australia Wing stretching apparatus
US4336914A (en) * 1978-12-29 1982-06-29 The Commonwealth Of Australia Deployable wing mechanism
US5063849A (en) * 1989-10-20 1991-11-12 Aktiebolaget Bofors Subwarhead
US5085381A (en) * 1991-03-29 1992-02-04 The United States Of America As Represented By The Secretary Of The Air Force Deployable aerodynamic aerosurface
US6092264A (en) * 1998-11-13 2000-07-25 Lockheed Martin Corporation Single axis fold actuator and lock for member
US20040217227A1 (en) * 2001-05-08 2004-11-04 Michael Alculumbre Cartridge with fin deployment mechanism
US7207518B2 (en) * 2001-05-08 2007-04-24 Olympic Technologies Limited Cartridge with fin deployment mechanism
AU2007332583B2 (en) * 2006-12-15 2013-09-19 Thales Extendable lifting tail device for shell
FR2910122A1 (fr) * 2006-12-15 2008-06-20 Thales Sa Dispositif d'empennage porteur deployable pour obus
WO2008071608A1 (fr) * 2006-12-15 2008-06-19 Thales Dispositif d'empennage porteur deployable pour obus
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
US9593922B2 (en) * 2013-03-14 2017-03-14 Bae Systems Land & Armaments L.P. Fin deployment system
CN105620722A (zh) * 2014-10-29 2016-06-01 北京临近空间飞行器系统工程研究所 一种基于热敏形状记忆合金的折叠翼舵小型化展开结构
EP3165870A1 (fr) * 2015-11-06 2017-05-10 MBDA Deutschland GmbH Aile repliable pour missile et missile équipé d'au moins une aile repliable
US10429158B2 (en) 2015-11-06 2019-10-01 Mbda Deutschland Gmbh Folding wing for a missile and a missile having at least one folding wing arranged thereon
US20180093753A1 (en) * 2016-09-30 2018-04-05 Edward Chow Collapsible and Rapidly-Deployable Unmanned Aerial Vehicle
US10752334B2 (en) * 2016-09-30 2020-08-25 Edward Chow Collapsible and rapidly-deployable unmanned aerial vehicle

Also Published As

Publication number Publication date
NL211396A (fr)
BE551492A (fr)
DE1038951B (de) 1958-09-11
FR1134930A (fr) 1957-04-19
GB795045A (en) 1958-05-14
CH333219A (fr) 1958-10-15
NL104379C (fr)

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