US3580529A - Rocket with spreadable empennage - Google Patents

Rocket with spreadable empennage Download PDF

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Publication number
US3580529A
US3580529A US759364A US3580529DA US3580529A US 3580529 A US3580529 A US 3580529A US 759364 A US759364 A US 759364A US 3580529D A US3580529D A US 3580529DA US 3580529 A US3580529 A US 3580529A
Authority
US
United States
Prior art keywords
nozzle body
holding
fin
fins
rocket
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
US759364A
Other languages
English (en)
Inventor
Xaver Suter
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 US3580529A publication Critical patent/US3580529A/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 invention relates to a rocket with spreadable empennage arranged around a nozzle body and consisting of individual fins which are held firm in their folded-in position by a holding device which can be released by the gas pressure.
  • the rocket according to the invention is characterized in this, that the holding device for each fin has a holding member supported in the nozzle body, but adapted to be removed therefrom,,and which is assembled with a locking member holding the fin and said locking member releases the fin when the holding member is removed and the holding member extends inside the external surface of the nozzle body behind the fin.
  • FIG. I is a diagrammatic perspective view of the rear end of a rocket partly in cross section and partly in elevation with the fins folded in and held by the holding device;
  • FIG. 2 shows a cross section at the narrowest part of the nozzle.
  • a nozzle body 5 has in front a flange 6, a second flange 9 in the middle and a flange 10 at the rear end. There are supported in the two'flanges 6 and 9 of the nozzle body 5 four axes 22 (FIG. 2) on which hub portions 18 of the fins 19 are pivoted.
  • the fins 19 have a flat portion 20 and a cylindrical portion 21.
  • the hubs 19 are fixed on the flat part 20 ofthe fins 19.
  • the trailing edge of the fin 19 is situated in the region of the narrowest cross section of the nozzle, the trailing edge 36 of the cylindrical part 21 being further behind than the edge 37 of the flat part 20, so that an offset 33 is formed.
  • the nozzle is closed by a disc 26, which protects the propellant charge (not shown) from atmospheric influences.
  • the disc 26 is inserted and firmly stuck in a groove 23 on the rear end of the nozzle body 5.
  • Four acicular holding members 27, parallel to the axis of the nozzle are fixed to the disc 26, and the holding members project forwardly through boreholes 28 in the nozzle body 5 into the space between the nozzle body 5 and the fins l9.
  • Locking members 29 with their lugs 30 are put on these holding members 27.
  • the members consist of rectangularly bent-back strips.
  • the back 31 of each hook-shaped locking member 29 is supported on a projection 16 of the nozzle body 5 and the trailing edge rests on the leading edge of flange 9.
  • each locking member 29 is supported by the leading edge on the edge 37 of the fin, and by its hooked part 32 on the offset 33 of a fin 19.
  • the hooked parts 32 of the locking members 29 are substantially the same width as the offsets 33 on the trailing edge of each fin 19.
  • Spiral springs 34 are arranged around the axes 22 of the fins 19, and said springs endeavor to swing up the fins 19.
  • the device described operates in the following manner:
  • the disc 26 is flung away by the pressure (forming in the combustion chamber) of the combustion gases.
  • the holding members 27 fixed to the disc 26 are thereupon withdrawn from the lugs 30 of the locking members 29 and release the latter.
  • the fins can be swung up under the force of the s rin s 34, so that they are substantially to the nozzle body T e locking members 29, since they are no longer held by the holding members 27, are thereupon drawn out from the fins l9 and blown away rearwardly by the airflow.
  • Rocket with spreadable empennage comprising a nozzle body, a plurality of pivots arranged parallel to the rocket axis, a plurality of fins mounted on said pivots located around said nozzle body, holding means releasable by propellant gas pressure holding said fins in their folded-in position, said holding means for each fin comprising a holding member extending inside the external surface of said nozzle body behind said fin, said holding member supported in said nozzle body removable from said nozzle body by said propellant gas pressure, a locking member holding said fin cooperating with said holding member, said locking member, when said holding member is removed, releasing said fin.
  • each of said locking members is formed from a strip bent back in the shape of a hook having a lug placed on said holding member.
  • Rocket according to claim 1 wherein a disc is located on the end of said nozzle body to which said holding members are fixed and said nozzle body has boreholes parallel to the axis of said noule body through which said holding members project in the space between said nozzle body and fins.
  • Rocket according to claim 2 wherein a flange is provided on said body and said strip forming the locking member has two edges and one rear side, one of said edges being supported on said flange and the other edge being supported on the trailing edge of each fin an? said rear side being supported on a stationary surface of sai nozzle body.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
US759364A 1967-09-21 1968-09-12 Rocket with spreadable empennage Expired - Lifetime US3580529A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1322567A CH481364A (de) 1967-09-21 1967-09-21 Rakete mit aufklappbarem Leitwerk

Publications (1)

Publication Number Publication Date
US3580529A true US3580529A (en) 1971-05-25

Family

ID=4390493

Family Applications (1)

Application Number Title Priority Date Filing Date
US759364A Expired - Lifetime US3580529A (en) 1967-09-21 1968-09-12 Rocket with spreadable empennage

Country Status (8)

Country Link
US (1) US3580529A (da)
AT (1) AT285250B (da)
BE (1) BE720313A (da)
CH (1) CH481364A (da)
FR (1) FR1596572A (da)
GB (1) GB1213228A (da)
NL (1) NL150224B (da)
SE (1) SE357822B (da)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2227104A1 (de) * 1972-06-03 1973-12-13 Dynamit Nobel Ag Geschoss oder rakete mit aufklappbarem leitwerk
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
US20040144887A1 (en) * 2001-04-12 2004-07-29 Michael Alculumbre Small arms projectile
US20040217227A1 (en) * 2001-05-08 2004-11-04 Michael Alculumbre Cartridge with fin deployment mechanism
US20100276534A1 (en) * 2008-10-02 2010-11-04 Earle Matthew S Canard-centric missile support
CN104977168A (zh) * 2015-07-15 2015-10-14 江西洪都航空工业集团有限责任公司 一种堵盖释放装置

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE433261B (sv) * 1980-03-31 1984-05-14 Andersson Kurt Goeran En inledningsvis rotationsstabiliserad ballistisk artilleriprojektil forsedd med utfellbara fenor
DE3507677A1 (de) * 1985-03-05 1986-09-11 Diehl GmbH & Co, 8500 Nürnberg Flugkoerper mit ueberkalibrigem leitwerk
RU2176066C1 (ru) * 2001-03-20 2001-11-20 Государственное унитарное предприятие "Государственное научно-производственное предприятие "Сплав" Стабилизатор сверхзвукового реактивного снаряда
RU2244245C1 (ru) * 2003-11-27 2005-01-10 Федеральное Государственное унитарное предприятие "Государственное научно-производственное предприятие "Сплав" Реактивный снаряд

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2784669A (en) * 1953-04-23 1957-03-12 Mach Tool Works Oerlikon Admin Rocket projectile with stabilizer fins
US3196793A (en) * 1963-01-16 1965-07-27 Milenkovic Veljko Folded fin rocket

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2784669A (en) * 1953-04-23 1957-03-12 Mach Tool Works Oerlikon Admin Rocket projectile with stabilizer fins
US3196793A (en) * 1963-01-16 1965-07-27 Milenkovic Veljko Folded fin rocket

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2227104A1 (de) * 1972-06-03 1973-12-13 Dynamit Nobel Ag Geschoss oder rakete mit aufklappbarem leitwerk
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
US20040144887A1 (en) * 2001-04-12 2004-07-29 Michael Alculumbre Small arms projectile
US7089866B2 (en) * 2001-04-12 2006-08-15 Olympic Technologies Limited Small arms projectile
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
US20100276534A1 (en) * 2008-10-02 2010-11-04 Earle Matthew S Canard-centric missile support
US8158915B2 (en) * 2008-10-02 2012-04-17 Raytheon Company Canard-centric missile support
CN104977168A (zh) * 2015-07-15 2015-10-14 江西洪都航空工业集团有限责任公司 一种堵盖释放装置

Also Published As

Publication number Publication date
CH481364A (de) 1969-11-15
DE1776006A1 (de) 1971-07-01
FR1596572A (da) 1970-06-22
NL150224B (nl) 1976-07-15
BE720313A (da) 1969-02-17
SE357822B (da) 1973-07-09
GB1213228A (en) 1970-11-25
AT285250B (de) 1970-10-27
NL6813181A (da) 1969-03-25

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