US2784669A - Rocket projectile with stabilizer fins - Google Patents

Rocket projectile with stabilizer fins Download PDF

Info

Publication number
US2784669A
US2784669A US422633A US42263354A US2784669A US 2784669 A US2784669 A US 2784669A US 422633 A US422633 A US 422633A US 42263354 A US42263354 A US 42263354A US 2784669 A US2784669 A US 2784669A
Authority
US
United States
Prior art keywords
projectile
fins
rocket
rocket projectile
unfolded
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
US422633A
Other languages
English (en)
Inventor
Apotheloz Robert
Niederer Wilhelm
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 Air Defence AG
Original Assignee
Werkzeugmaschinenfabrik Oerlikon Buhrle AG
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 Werkzeugmaschinenfabrik Oerlikon Buhrle AG filed Critical Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Application granted granted Critical
Publication of US2784669A publication Critical patent/US2784669A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • A—HUMAN NECESSITIES
    • A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
    • A61F—FILTERS IMPLANTABLE INTO BLOOD VESSELS; PROSTHESES; DEVICES PROVIDING PATENCY TO, OR PREVENTING COLLAPSING OF, TUBULAR STRUCTURES OF THE BODY, e.g. STENTS; ORTHOPAEDIC, NURSING OR CONTRACEPTIVE DEVICES; FOMENTATION; TREATMENT OR PROTECTION OF EYES OR EARS; BANDAGES, DRESSINGS OR ABSORBENT PADS; FIRST-AID KITS
    • A61F13/00—Bandages or dressings; Absorbent pads
    • A61F13/15—Absorbent pads, e.g. sanitary towels, swabs or tampons for external or internal application to the body; Supporting or fastening means therefor; Tampon applicators
    • A61F13/53—Absorbent pads, e.g. sanitary towels, swabs or tampons for external or internal application to the body; Supporting or fastening means therefor; Tampon applicators characterised by the absorbing medium
    • A61F13/534—Absorbent pads, e.g. sanitary towels, swabs or tampons for external or internal application to the body; Supporting or fastening means therefor; Tampon applicators characterised by the absorbing medium having an inhomogeneous composition through the thickness of the pad
    • A—HUMAN NECESSITIES
    • A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
    • A61F—FILTERS IMPLANTABLE INTO BLOOD VESSELS; PROSTHESES; DEVICES PROVIDING PATENCY TO, OR PREVENTING COLLAPSING OF, TUBULAR STRUCTURES OF THE BODY, e.g. STENTS; ORTHOPAEDIC, NURSING OR CONTRACEPTIVE DEVICES; FOMENTATION; TREATMENT OR PROTECTION OF EYES OR EARS; BANDAGES, DRESSINGS OR ABSORBENT PADS; FIRST-AID KITS
    • A61F13/00—Bandages or dressings; Absorbent pads
    • A61F13/15—Absorbent pads, e.g. sanitary towels, swabs or tampons for external or internal application to the body; Supporting or fastening means therefor; Tampon applicators
    • A61F13/53—Absorbent pads, e.g. sanitary towels, swabs or tampons for external or internal application to the body; Supporting or fastening means therefor; Tampon applicators characterised by the absorbing medium
    • A61F13/539—Absorbent pads, e.g. sanitary towels, swabs or tampons for external or internal application to the body; Supporting or fastening means therefor; Tampon applicators characterised by the absorbing medium characterised by the connection of the absorbent layers with each other or with the outer layers
    • A—HUMAN NECESSITIES
    • A61—MEDICAL OR VETERINARY SCIENCE; HYGIENE
    • A61F—FILTERS IMPLANTABLE INTO BLOOD VESSELS; PROSTHESES; DEVICES PROVIDING PATENCY TO, OR PREVENTING COLLAPSING OF, TUBULAR STRUCTURES OF THE BODY, e.g. STENTS; ORTHOPAEDIC, NURSING OR CONTRACEPTIVE DEVICES; FOMENTATION; TREATMENT OR PROTECTION OF EYES OR EARS; BANDAGES, DRESSINGS OR ABSORBENT PADS; FIRST-AID KITS
    • A61F13/00—Bandages or dressings; Absorbent pads
    • A61F13/15—Absorbent pads, e.g. sanitary towels, swabs or tampons for external or internal application to the body; Supporting or fastening means therefor; Tampon applicators
    • A61F13/53—Absorbent pads, e.g. sanitary towels, swabs or tampons for external or internal application to the body; Supporting or fastening means therefor; Tampon applicators characterised by the absorbing medium
    • A61F13/534—Absorbent pads, e.g. sanitary towels, swabs or tampons for external or internal application to the body; Supporting or fastening means therefor; Tampon applicators characterised by the absorbing medium having an inhomogeneous composition through the thickness of the pad
    • A61F2013/53445—Absorbent pads, e.g. sanitary towels, swabs or tampons for external or internal application to the body; Supporting or fastening means therefor; Tampon applicators characterised by the absorbing medium having an inhomogeneous composition through the thickness of the pad from several sheets

Definitions

  • the invention relates to a rocket projectile having stabilizer fins hinged at its rear end which are folded within the outline of the projectile for storage and transport, and are unfolded after launching the projectile in order to stabilize the same in flight.
  • a rocket projectile of the kind referred to comprising in combination: a rear portion, retractable fins pivoted on the said rear portion parallel to the axis of the projectile, a coupling member and a coiled spring both arranged concentrically around the said rear portion and both being common to all of the said fins, the said spring being in torque connection with the said rear portion at one end and with the said coupling member at the other end, and after launching unfolding all the said fins simultaneously.
  • the said rocket projectile comprises a rear throat portion, a helical spring coiled round and at one end attached to the said throat portion, a toothed crown journalled on the outside of the said rear throat portion, and connected to the other end of the said helical spring, pivots arranged parallel to the projectile axis and rotatably journalled in the said rear throat portion, gear pinions and fins xed for rotation on each of the said pivots, respectively, the said gear pinions meshing with the said toothed crown, which when rotated by the said helical spring expanding about the projectile axis after launching rotates the said pivots about their respective axes and thereby simultaneously unfolds the said ns.
  • the said rocket may comprise in addition: a ange arranged on the said rear throat portion forming a bearing block for all the said pivots, a collar arranged on each of the said pivots behind said flange, a compression spring arranged on each of the said pivots between said flange and the said collar biassing the said pivot rearward in the axial direction, a cam arranged on each pivot and an associated cam on the said flange, the said cams and associated cams interengaging in the unfolded position of the said fins.
  • i Y v Figl l shows the rear portion of a rocket projectile, namely in the upper half a longitudinal section through the folded empennage, and in the lower half an elevation of the unfolded empennage.
  • Fig. 2 shows in the lower half a section along the line 2-2 of Fig. l, and in the upper half a rear end view of the rocket with the empennage unfolded.
  • a nozzle 2 On the rear part of the rocket body 1 (Fig. l) a nozzle 2 is arranged, on which a aring extension piece 3, is mounted.
  • a cylindrical bush 4 with a toothed crown 5 is journalled rotatably.
  • a helical torsion spring 6 is mounted which at one end is held in a recess 7 of the nozzle 2, while its other end engages into a bore 8 of the toothed crown 5.
  • Each stabilizer n 9 is mounted on a pivot 10 which is rotatably journalled in a bearing block 11 of the extension piece 3.
  • a gear pinion 12 On the pivot 10 moreover a gear pinion 12 is mounted which is in mesh with the toothed crown 5.
  • the pivot 10, gear pinion 12 and stabilizer n 9 are fixedly connected with one another, for example by means of a dowcl pin.
  • the pivot 10 carries at its rear end a ange 13.
  • a prestressed compression spring 14 is arranged which constantly pulls thepivot, and with it the gear pinion 12 and the stabiliser fin, in the rearward direction.
  • the gear pinion and the bearing block have recesses 11a and 12a, respectively, which mutually interengage when the stabiliser iin is completely unfolded, and which secure the latter, as illustrated in the lower half of Fig. 1, in the unfolded position.
  • the manner of operation of the device is as follows: During storage and transport the stabiliser fins 9, which are under the action of the pre-loaded helical torsion spring 6, are held in their folded position by means of cap (not shown in the drawing). When pushing the projectile into the launching tube, the cap is removed, and the stabiliser fins bear on the inner wall surface of When the projectile has left the launching tube after tiring, the stabiliser fins 9 are simultaneously unfolded Vabout the pivots 10 by the helical torsion spring 6 which acts on the gear pinions 12 through the toothed crown 5. Under the action of the compression spring 13 the two recesses 11a and 12a thereafter mutually interengage, and retain the stabiliser tins 9 in the unfolded position.
  • a rocket projectile comprising in combination: a rear throat portion, a helical spring coiled round and at one end attached to the said throat portion, a toothed crown journalled on the outside of the said rear throat portion, and connected to the other end of the said helical spring, pivots arranged parallel to the projectile axis and rotatably journalled in the said rear throat portion, gear pinions and ns xed for rotation on each of the said pivots, respectively, the said gear pinions meshing with the said toothed crown, which when rotated by the said helical spring expanding about the, projectile axis after launching rotates the said pivots about their respective axes and thereby simultaneously unfolds the said fins.
  • a rocket projectile as claimed in claim 1 comprising in addition: a flange arranged on the said rear throat in the unfolded position of the said ns and being retained interengaged by the said compression springs.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)
  • Toys (AREA)
US422633A 1953-04-23 1954-04-12 Rocket projectile with stabilizer fins Expired - Lifetime US2784669A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH740059X 1953-04-23

Publications (1)

Publication Number Publication Date
US2784669A true US2784669A (en) 1957-03-12

Family

ID=4533080

Family Applications (1)

Application Number Title Priority Date Filing Date
US422633A Expired - Lifetime US2784669A (en) 1953-04-23 1954-04-12 Rocket projectile with stabilizer fins

Country Status (6)

Country Link
US (1) US2784669A (en(2012))
BE (1) BE527578A (en(2012))
CH (1) CH313397A (en(2012))
FR (1) FR1097883A (en(2012))
GB (1) GB740059A (en(2012))
NL (2) NL186136B (en(2012))

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2924175A (en) * 1955-10-20 1960-02-09 Brandt Soc Nouv Ets Foldable fin arrangement for a projectile
US3085511A (en) * 1959-04-22 1963-04-16 Hans O Donner Tail of mortar projectile
US3185097A (en) * 1956-08-02 1965-05-25 Vincent J Cushing Missile stabilizing means
US3378216A (en) * 1966-04-29 1968-04-16 Susquehama Corp Integral fin canister-nozzle exit cone
US3580529A (en) * 1967-09-21 1971-05-25 Oerlikon Buehrle Ag Rocket with spreadable empennage
US3756602A (en) * 1972-11-24 1973-09-04 R Carella Archery arrow vane
US5282422A (en) * 1991-04-08 1994-02-01 Bofors Ab Sub-combat unit
WO2002079716A1 (en) 2001-03-20 2002-10-10 Bofors Defence Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
WO2019093939A1 (en) * 2017-11-10 2019-05-16 Bae Systems Bofors Ab Tail portion
US11428515B2 (en) * 2017-10-04 2022-08-30 Nexter Munitions Fin blocking device and projectile having such a device

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
DE1206760B (de) * 1963-08-10 1965-12-09 Karlsruhe Augsburg Iweka Synchronisierungsvorrichtung fuer Spreizleitwerke

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR896502A (fr) * 1940-09-23 1945-02-23 Commerciale Caproni Comp Dispositif de commande des ailettes d'un projectile muni d'un empennage

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR896502A (fr) * 1940-09-23 1945-02-23 Commerciale Caproni Comp Dispositif de commande des ailettes d'un projectile muni d'un empennage

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2924175A (en) * 1955-10-20 1960-02-09 Brandt Soc Nouv Ets Foldable fin arrangement for a projectile
US3185097A (en) * 1956-08-02 1965-05-25 Vincent J Cushing Missile stabilizing means
US3085511A (en) * 1959-04-22 1963-04-16 Hans O Donner Tail of mortar projectile
US3378216A (en) * 1966-04-29 1968-04-16 Susquehama Corp Integral fin canister-nozzle exit cone
US3580529A (en) * 1967-09-21 1971-05-25 Oerlikon Buehrle Ag Rocket with spreadable empennage
US3756602A (en) * 1972-11-24 1973-09-04 R Carella Archery arrow vane
US5282422A (en) * 1991-04-08 1994-02-01 Bofors Ab Sub-combat unit
US20050229806A1 (en) * 2001-03-20 2005-10-20 Bofors Defence Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
WO2002079716A1 (en) 2001-03-20 2002-10-10 Bofors Defence Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
US7104497B2 (en) * 2001-03-20 2006-09-12 Bae Systems Bofors Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
US20070114323A1 (en) * 2001-03-20 2007-05-24 Bae Systems Bofors Ab Method of Synchronizing Fin Fold-Out on a Fin-Stabilized Artillery Shell, and an Artillery Shell Designed in Accordance Therewith
US7487934B2 (en) 2001-03-20 2009-02-10 Bae Systems Bofors Ab Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith
US11428515B2 (en) * 2017-10-04 2022-08-30 Nexter Munitions Fin blocking device and projectile having such a device
WO2019093939A1 (en) * 2017-11-10 2019-05-16 Bae Systems Bofors Ab Tail portion
KR20200084013A (ko) * 2017-11-10 2020-07-09 비에이이 시스템즈 보포즈 아베 꼬리 부분
JP2021502534A (ja) * 2017-11-10 2021-01-28 ベーアーエー・システムズ・ボフォース・アクチエボラグＢａｅ Ｓｙｓｔｅｍｓ Ｂｏｆｏｒｓ Ａｂ テール部分
US11307004B2 (en) * 2017-11-10 2022-04-19 Bae Systems Bofors Ab Tail portion for fin-stabilized projectile

Also Published As

Publication number Publication date
NL93582C (en(2012))
CH313397A (de) 1956-04-15
BE527578A (en(2012))
GB740059A (en) 1955-11-09
FR1097883A (fr) 1955-07-12
NL186136B (nl)

Similar Documents

Publication Publication Date Title
US2784669A (en) Rocket projectile with stabilizer fins
US2924175A (en) Foldable fin arrangement for a projectile
US2494026A (en) Projectile
DE1168804B (de) Flugkoerperhinterteil mit mehreren Stabilisierungsflossen
DE925213C (de) Zuender fuer nicht rotierende Raketengeschosse
US3031967A (en) Fin arrangement for projectiles
US1611835A (en) Folding pencil compass
US2960036A (en) Hollow-charge warheads of projectiles
US1476107A (en) Fountain pen
DE888066C (de) Rohr- und Vorrohrsicherung fuer Drallgeschosszuender
DE816970C (de) Rakete
US1136480A (en) Projectile.
US3515360A (en) Pivot system for folding control surfaces
US1276892A (en) Projectile.
GB1352118A (en) Rockets
DE3408585A1 (de) Fluegelstabilisiertes geschoss
DE914933C (de) Raketengeschoss mit aufklappbaren Stabilisierungsfluegeln
US1540920A (en) Self-filling pencil
US2330393A (en) Bomb
US3027124A (en) Encapsulated seat stabilizing mechanism
US3015462A (en) Stabilization boom for aircraft encapsulated seat
US3282538A (en) Ejection device
DE3439256C1 (de) Einrichtung zur Korrektur der Fluglage von Munition
US1302008A (en) Shell.
DE1017950B (de) Abschussvorrichtung fuer Raketengeschosse