US3880383A - Control flap unit for projectiles or rockets - Google Patents

Control flap unit for projectiles or rockets Download PDF

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Publication number
US3880383A
US3880383A US366519A US36651973A US3880383A US 3880383 A US3880383 A US 3880383A US 366519 A US366519 A US 366519A US 36651973 A US36651973 A US 36651973A US 3880383 A US3880383 A US 3880383A
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US
United States
Prior art keywords
pivot lever
fin
rudder carrier
guide slot
pivot
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
US366519A
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English (en)
Inventor
Alfred Voss
Heinz-Wilhelm Kreutz
Heinz Kroschel
Manfred Strunk
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Dynamit Nobel AG
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Dynamit Nobel AG
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Filing date
Publication date
Application filed by Dynamit Nobel AG filed Critical Dynamit Nobel AG
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Publication of US3880383A publication Critical patent/US3880383A/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

Definitions

  • a sliding sleeve is disposed internall of the rudder carrier for engagement with pivot levers mounted eccentrically with respect to the fin pivot HYES so as to move the fins from a folded condition ex tending longitudinall along the outside of the rudder carrier to an in-flight position extending radiallv with respect to the rudder carrier.
  • Lateral guide slots are provided in the rudder carrier for guiding the mounting end portions of the fins.
  • Curved pi ⁇ ot le ⁇ er guide slots are prmided in the rudder carrier all for guiding the pivot levers to effect the pivotal movement of the fins in response to longitudinal movement of the pivot le ⁇ ers resulting from engagement with the mo ⁇ ahlt: sliding sleeve.
  • pivot lever guide slots are constructed with an extension forwardly of the lateral slots so as to accommodate attachment and detachmerit of the fins with fixedly attached pivot levers onto the rudder carrier by merely inserting the pi ⁇ ot levers through the most forward portions of the pi ⁇ ot leier guide slot and then moving the fin into position in the lateral slots where the fins are pivotall connected to the rudder carrier h to oifurther connecting mean through aligned apertures in the fins and the rudder carrier.
  • This invention relates to a control flap unit for projectiles or rockets of the type having control fins guided in lateral slots in the tail of a rudder carrier of the projectile or rocket. which fins can be unfolded about axes arranged at transverse and preferably right angles to the longitudinal axis of the projectile or rocket. tangentially to the rudder or control unit carrier.
  • a control flap unit for projectiles or rockets which can be fired from the barrel ofa gun.
  • the rudder carrier has a longitudinal bore wherein a sliding sleeve is disposed which can be moved axially by means of a spring force. This sliding sleeve presses. with its rear end. against pivot levers arranged at the rudders or tins and thus unfolds. after the projectile or rocket has left the gun barrel. the fins about axes extending at right angles to the longitudinal axis of the projectile or rocket. tangentially to the rudder carrier. into the flying position.
  • the pivot levers extend from the outside through the rudder carrier in circular-arc-shaped slots.
  • the fins are additionally guided in the zone of their mounting end in lateral slots in the rear or tail por tion of the rudder carrier.
  • the tail of the rudder carrier is provided with a correspondingly larger outer diameter as compared to the remaining portion of the rudder carrier to accommodate these lateral slots.
  • the tail or rear portion is made integral with the remaining portion of the rudder carrier. then it is necessary. in order to mount the fins. to insert the latter without the pivot levers in the lateral slots with their mounting end. and thereafter to attach the pivot levers.
  • the reason therefor is that the circular-arc-shaped slots for the pivot levers are effectively entirely covered by rudder carrier tail portion structure which accommodates the lateral slots.
  • the subsequent mounting of the pivot levers. however. is extremely cumbersome. since corresponding bolts must be inserted from the inside of the rudder carrier through the circular-arc slots to the mounting end of the fins and then must be threadedly joined to the latter. for example.
  • This invention is based on the problem of avoiding the above-mentioned disadvantages. i.e.. to simplify. on the one hand. the assembly of the tail unit and. on the other hand. to increase the operational safety thereof.
  • the ahove-described arrangement of the present invention considerably reduces the complications previously encountered as discussed above in the assembly of the rudder or tail unit on a projectile with foldahle fins.
  • the operational safety of the projectile is also improved by the above-described arrangement of the present invention. since the pivot levers can be fixedly connected to the fins hy fashioning the pivot levers. for example. as integral bolts or pins which. prior to the assembly of the fins on the rudder carrier. are reliably joined thereto in the manner of a rivet connection. so that even very large lateral forces can be flawlessly absorbed.
  • FIG. I is a longitudinal partially sectional view illustrating a projectile or rocket with a control flap unit constructed in accordance with the present invention:
  • FIG. 2 is an enlarged longitudinal view of the rear of the rudder carrier which shows a part of the control flap unit of FIG. I with the fins removed;
  • FIGS. 30 and 311 show a fin in two different views. likewise on an enlarged scale.
  • the projectile or rocket with a nose 1 and a one-piece intergral rudder carrier 2 is provided. at the tail 3 shown in a longitudinal sectional view. with fins 4 shown in the unfolded condition. e.e.. in the flying position.
  • a sliding sleeve 5 is shown with a compression spring 6 disposed in front thereof.
  • the annular collar 7 of the sliding sleeve 5 contacts pivot levers 8 guided in slots 9 of the rudder carrier 2.
  • the fins 4, in turn. are guided in the lateral slots 10.
  • each ofthe circulanarc-shaped slots 9 have an extension ll extending forwardly of front end 12 of the lateral slots [2 toward the nose I.
  • These extensions 1] are preferably provided in the direction of the longitudinal axis of the projectile or rocket so as to simplify the manufacture thereof.
  • these extensions 11 can basically also be ofany desired curved shape within the intendment ofthe present invention.
  • the tail 3 is furthermore provided with bores l3 of which likewise only one is illlustrated wherein the fins 4 are attached with a conventional means to be pivotable tangentially with respect to the rudder carrier 2 about respective pivot axes extending perpendicular to the longitudinal axis or centerline of the projectile.
  • the fin 4 shown in a lateral view in FIG. 3a is fixedly joined to the pivot lever at its mounting end 14 by riveting as shown in a sectional view the upper portion ofthe pivot lever into the head [5.
  • FIG. 3b the same fin 4 is shown in a plan or top view. with the illustration of mounting bore 16 which is associated with the bore 13 in the rudder carrier 2 for accommodating a screw or the like through bores l3 and I6 to pivotally mount the tin to the rudder carrier.
  • a control flap unit for a projectile comprising:
  • a one piece integral rudder carrier extending in the direction ofa longitudinal axis of the projectile and having a rear portion of larger cross-sectional di mensions than a more forward portion immediately adjacent thereto.
  • At least one guiding fin means attached to said rudder carrier for pivotal movement about respective pivot axes extending transverse to said longitudinal axis pivot lever means mounted on each of said fin means eccentrically with respect to respective ones of said fin pivot axes.
  • lateral fin guide slot means in said rear portion for accommodating pivotal movement of radially inward portions of said fin means
  • pivot lever guide slot means in said carrier engageable with said pivot lever means for effecting pivotal movement of said fin means about said respective pivot axes in response to longitudinal movement of said pivot lever means.
  • said pivot lever guide slot means extending from said rear portion forwardly into said more forward portion to ac commodate attachment and detachment of said fin means viith said pivot lever means fixedly mounted thereto;
  • a control flap unit according to claim 1, wherein said pivot lever guide slot means are of circulanarcshaped configuration over the portion thereof in said rear portion of the rudder carrier and are of longitudinally extending straight configuration over the portion thereof in said more forward portion of the rudder car rier.
  • a control flap unit wherein said fin means are movable between a storage position extending tangential to said rudder carrier along said more forward portion and an in-use flight position extending radially with respect to said rear portion.
  • a control flap unit according to claim 3. wherein said longitudinally movable abutment means is a sliding sleeve disposed inside said rudder carrier. and wherein said sliding sleeve abuts radially inward end portions of said pivot lever means.
  • a control flap unit according to claim 5. wherein radially outward end portions of said pivot lever means engage said pivot lever guide slot means in said rear portion.
  • each lateral fin guide slot means in said rear portion is defined by opposing faces.
  • each respective pivot lever guide slot means in said rear portion being formed in both faces of respective lateral fin guide slot means.
  • each respective pivot lever means engaging respective pivot lever guide slot means on both faces of each respective lateral fin guide slot means.
  • each pivot lever guide slot means radially communicating between said channel and the outer surface of said rudder carrier.
  • a control flap according to claim I wherein a plurality of fin means are provided.
  • a control flap unit according to claim 9. wherein said upper portion is essentially polygonal in crosssection. each side of the polygon corresponding with one of said fin means.
  • a control flap unit according to claim I wherein said pivot lever guide slot means forwardly extends in said forward portion by a distance sufficient so that said fin means can clear the forwardmost part of said rear portion of said rudder carrier when the pivot lever means engages the forwardmost part of said pivot lever guide slot means.
  • a process for assembling a control flap unit useful for a projectile including:
  • a one-piece integral rudder carrier extending in the direction ofa longitudinal axis of the projectile and having a rear portion of larger cross-sectional dimensions than a more forward portion immediately adjacent thereto,
  • At least one guiding fin means attached to said rudder carrier for pivotal movement about respective pivot axes extending transverse to said longitudinal axis,
  • pivot lever means mounted on each of said fin means eccentrically with respect to respective ones of said fin pivot axes
  • lateral fin guide slot means in said rear portion for accommodating pivotal movement of radially inward portions of said fin means
  • pivot lever guide slot means in said carrier engageable with said pivot lever means for effecting pivotal movement of said fin means about said respective pivot axes in response to longitudinal movement of said pivot lever means, said pivot lever guide slot means extending from said rear portion forwardly into said more forward portion to accommodate attachment and detachment of said fin means with said pivot lever means fixedly mounted thereto, and

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  • 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)
US366519A 1972-06-03 1973-06-04 Control flap unit for projectiles or rockets Expired - Lifetime US3880383A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2227103A DE2227103A1 (de) 1972-06-03 1972-06-03 Klappleitwerk

Publications (1)

Publication Number Publication Date
US3880383A true US3880383A (en) 1975-04-29

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Application Number Title Priority Date Filing Date
US366519A Expired - Lifetime US3880383A (en) 1972-06-03 1973-06-04 Control flap unit for projectiles or rockets

Country Status (6)

Country Link
US (1) US3880383A (fi)
BE (1) BE800361A (fi)
DE (1) DE2227103A1 (fi)
FR (1) FR2188136B1 (fi)
GB (1) GB1423283A (fi)
IT (1) IT985640B (fi)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5085380A (en) * 1987-09-10 1992-02-04 British Aerospace Public Limited Company Projectile guidance
US5464173A (en) * 1994-12-16 1995-11-07 The United States Of America As Represented By The Secretary Of The Navy Subassembly means
US6398156B2 (en) * 1999-12-16 2002-06-04 Lfk Lenkflugkoerpersysteme Gmbh Mounting for attaching a rudder to a missile
WO2002090870A1 (en) * 2001-05-08 2002-11-14 Olympic Technologies Ltd Projectile with fin deployment mechanism
US6578792B2 (en) * 2001-04-12 2003-06-17 Diehl Munitionssysteme Gmbh & Co. Kg Rudder blade mounting arrangement for a missile
US6695252B1 (en) * 2002-09-18 2004-02-24 Raytheon Company Deployable fin projectile with outflow device
US8415598B1 (en) * 2010-12-20 2013-04-09 The United States Of America As Represented By The Secretary Of The Army Extendable fins for a tube-launched projectile
CN114322677A (zh) * 2021-12-29 2022-04-12 西安现代控制技术研究所 一种适应舱体的弹翼、滑块精准安装结构

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2841773C2 (de) * 1978-09-26 1984-07-12 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Schwenkbare Anordnung des Leitwerks, insbesondere bei Flugkörpern oder Geschossen
FR2539503B1 (fr) * 1983-01-14 1987-01-16 Luchaire Sa Dispositif pour le deploiement automatique des ailettes d'un empennage destine a la stabilisation d'un engin lance par piston

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1198248B (de) * 1963-07-17 1965-08-05 Diehl Fa Klappleitwerk

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1198248B (de) * 1963-07-17 1965-08-05 Diehl Fa Klappleitwerk

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5085380A (en) * 1987-09-10 1992-02-04 British Aerospace Public Limited Company Projectile guidance
US5464173A (en) * 1994-12-16 1995-11-07 The United States Of America As Represented By The Secretary Of The Navy Subassembly means
US6398156B2 (en) * 1999-12-16 2002-06-04 Lfk Lenkflugkoerpersysteme Gmbh Mounting for attaching a rudder to a missile
US6578792B2 (en) * 2001-04-12 2003-06-17 Diehl Munitionssysteme Gmbh & Co. Kg Rudder blade mounting arrangement for a missile
US7207518B2 (en) * 2001-05-08 2007-04-24 Olympic Technologies Limited Cartridge with fin deployment mechanism
GB2391923A (en) * 2001-05-08 2004-02-18 Olympic Technologies Ltd Projectile with fin deployment mechanism
US20040217227A1 (en) * 2001-05-08 2004-11-04 Michael Alculumbre Cartridge with fin deployment mechanism
GB2391923B (en) * 2001-05-08 2005-07-06 Olympic Technologies Ltd Projectile
WO2002090870A1 (en) * 2001-05-08 2002-11-14 Olympic Technologies Ltd Projectile with fin deployment mechanism
US6695252B1 (en) * 2002-09-18 2004-02-24 Raytheon Company Deployable fin projectile with outflow device
US8415598B1 (en) * 2010-12-20 2013-04-09 The United States Of America As Represented By The Secretary Of The Army Extendable fins for a tube-launched projectile
CN114322677A (zh) * 2021-12-29 2022-04-12 西安现代控制技术研究所 一种适应舱体的弹翼、滑块精准安装结构
CN114322677B (zh) * 2021-12-29 2024-05-28 西安现代控制技术研究所 一种适应舱体的弹翼、滑块精准安装结构

Also Published As

Publication number Publication date
BE800361A (fr) 1973-10-01
IT985640B (it) 1974-12-10
DE2227103A1 (de) 1973-12-13
GB1423283A (en) 1976-02-04
FR2188136B1 (fi) 1976-11-12
FR2188136A1 (fi) 1974-01-18

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