GB846069A - Improvements in and relating to a fin arrangement for projectiles - Google Patents

Improvements in and relating to a fin arrangement for projectiles

Info

Publication number
GB846069A
GB846069A GB3167/59A GB316759A GB846069A GB 846069 A GB846069 A GB 846069A GB 3167/59 A GB3167/59 A GB 3167/59A GB 316759 A GB316759 A GB 316759A GB 846069 A GB846069 A GB 846069A
Authority
GB
United Kingdom
Prior art keywords
fins
fin
gases
plug
projectile
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
Application number
GB3167/59A
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.)
Hotchkiss Brandt SA
Original Assignee
Hotchkiss Brandt SA
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 Hotchkiss Brandt SA filed Critical Hotchkiss Brandt SA
Publication of GB846069A publication Critical patent/GB846069A/en
Expired legal-status Critical Current

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
    • F42B10/20—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces
    • 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
    • F42B10/18—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel using a longitudinally slidable support member

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)
  • Automatic Assembly (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Basic Packing Technique (AREA)

Abstract

846,069. Self-propelled missiles and tail units therefor. HOTCHKISS-BRANDT. Jan. 29, 1959 [Feb. 13, 1958], No. 3167/59. Classes 9(1) and 9(2). A tail unit for a missile as described in Specification 768,295 comprises an annular body 1 screwed on to the nozzle e and provided with pairs of bosses 4, 5 between which are pivoted fins 3 held in the folded position by cranked arms 28 mounted on a tube 25 containing a launching charge as in Specification 768,295. The tube 25 is screwed to a plug 22 held in the body 1 by shear pins 23. When the charge 26 is fired the gases enter passages in the plug 22 and through passage 27 may fire a device f as in Specification 768,295. The gases also cause the pins 23 to shear, so that the plug 22 and tube 25 are left behind in the launcher and arms 28 leave the fins 3. The propellent gases also enter cavities 8 between the fins and the body 1 and the outward thrust of the gases forces the fins to the extended position. As the fins rotate a heel portion 14, Fig. 6, stresses a locking spring 17 and when a bearing surface 12 comes to rest against a lug projecting radially from the body 1, the spring becomes wedged against a curved surface 15. The medial plane of each fin is inclined at a small angle to the axis of the projectile, so that in flight each fin has a positive incidence to the relative wind and thus produces a rotation of the projectile. Also the pivotal axis of each fin is inclined at a small angle to the projectile axis, so that when in the closed position each fin has a slight positive incidence to the launching gases on the outer surface. Thus a component of the gas thrust opposes the thrust of the gas in the cavities 8 and slows down the deployment of the fins. When the projectiles are to be used with lowpowered propellants, the locking spring is reduced in size and carries a weight to support the deployed fin.
GB3167/59A 1958-02-13 1959-01-29 Improvements in and relating to a fin arrangement for projectiles Expired GB846069A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR758227A FR1191519A (en) 1958-02-13 1958-02-13 Deploying tail for artillery projectile

Publications (1)

Publication Number Publication Date
GB846069A true GB846069A (en) 1960-08-24

Family

ID=8705741

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3167/59A Expired GB846069A (en) 1958-02-13 1959-01-29 Improvements in and relating to a fin arrangement for projectiles

Country Status (8)

Country Link
US (1) US3031967A (en)
BE (1) BE575185A (en)
CH (1) CH348629A (en)
DE (1) DE1123597B (en)
ES (1) ES247439A1 (en)
FR (1) FR1191519A (en)
GB (1) GB846069A (en)
NL (2) NL111191C (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3125956A (en) * 1964-03-24 Fold able fin
NL101734C (en) * 1959-04-13
US3127838A (en) * 1960-10-12 1964-04-07 Bombrini Parodi Delfino Spa Retractable blade tail unit for projectiles
US3697019A (en) * 1970-05-13 1972-10-10 Us Navy Stabilizing fin assembly
DE2342783C2 (en) * 1973-08-24 1983-12-22 Rheinmetall GmbH, 4000 Düsseldorf Projectile equipped with a tail unit
US4158447A (en) * 1977-11-29 1979-06-19 The United States Of America As Represented By The Secretary Of The Navy Expanding stabilizing fin cup
DE4105142A1 (en) * 1991-02-20 1992-08-27 Diehl Gmbh & Co PROJECTILE WITH FOLD-OUT PAD
DE4119613C2 (en) * 1991-06-14 1997-03-27 Diehl Gmbh & Co Missiles with fold-out guidance devices
FR2895071B1 (en) * 2005-12-19 2008-01-18 Giat Ind Sa ANTI-REBOUND LOCKING DEVICE OF A DEPLOYABLE FIN OF A PROJECTILE.
SE535837C2 (en) * 2011-04-14 2013-01-08 Bae Systems Bofors Ab Fenutfällningsmekanism
US10150556B2 (en) 2016-05-23 2018-12-11 The Boeing Company Low-profile wing hinge mechanism
CN115451757B (en) * 2022-09-13 2024-07-16 北京航星传动科技有限公司 Grid rudder folding and unfolding actuating mechanism and servo system thereof

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE201605C (en) *
US2145508A (en) * 1937-01-04 1939-01-31 Sageb Sa Bladed projectile
AT157500B (en) * 1937-01-04 1939-11-25 Sageb Sa Bullet for mortar with smooth barrel.
US2427217A (en) * 1943-09-23 1947-09-09 Harry J Lebherz Rocket fin assembly
US2465401A (en) * 1943-09-23 1949-03-29 Leslie A Skinner Rocket fin assembly
US2671398A (en) * 1951-05-11 1954-03-09 Allen S Peck Metal pop-out stabilizing tail for small bombs
FR1061242A (en) * 1952-08-05 1954-04-09 Development of rocket projectiles with deployable tail fins
FR1104534A (en) * 1954-05-13 1955-11-21 Soc Tech De Rech Ind Deployable tail
LU33739A1 (en) * 1955-07-21

Also Published As

Publication number Publication date
CH348629A (en) 1960-08-31
US3031967A (en) 1962-05-01
FR1191519A (en) 1959-10-20
ES247439A1 (en) 1959-12-16
NL111191C (en) 1965-05-17
NL295562A (en) 1965-05-10
DE1123597B (en) 1962-02-08
BE575185A (en) 1959-05-15

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