US3058422A - Wing assembly for missiles - Google Patents

Wing assembly for missiles Download PDF

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Publication number
US3058422A
US3058422A US21285A US2128560A US3058422A US 3058422 A US3058422 A US 3058422A US 21285 A US21285 A US 21285A US 2128560 A US2128560 A US 2128560A US 3058422 A US3058422 A US 3058422A
Authority
US
United States
Prior art keywords
flap
bolt
wing
wing part
extended position
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
US21285A
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English (en)
Inventor
Olsson Olof Bertil
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.)
Saab Bofors AB
Original Assignee
Bofors AB
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 Bofors AB filed Critical Bofors AB
Application granted granted Critical
Publication of US3058422A publication Critical patent/US3058422A/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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/02—Mounting or supporting thereof
    • 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

  • This invention relates to projectiles and rockets and, more particularly, to a wing therefor having a fixed wing part and a folding flap which is spring actuated into the position in which it forms an extension of the fixed wing part.
  • the size of the spring must be minimized, making it important that the locking device for securing the folding flap in the spring actuated position be extremely reliable so as to secure positively .the flap immediately after it has assumed its extended position. Wherever the locking device does not secure the flap in its extended position, air and side pressures acting upon the flap will prevent the main spring from returning the flap into the desired position at any time after the initial firing of the projectile or rocket. It is therefore an object of :the present invention to provide a wing for projectiles or rockets in which the flap is securely locked in proper position immediately after assuming such position as an extension of the fixed wing part, in'an eflicient, effective, and reliable manner.
  • Another object of the present invention is to provide an operating assembly for moving the folding flap of a projectile or rocket wing into an extended position relative to the first wing part and which includes self-actuating locking means for retaining such flap in an extended position, in a reliable and fool-proof manner.
  • a spring actuated bolt is arranged upon the fixed wing part for movement between an initial position in which it permits the flap to be rotated from an initial to an extended position, following which it engages with a cooperating part of the flap to secure such flap in the extended position.
  • the locking device normally retains the locking bolt in a retracted position and is responsive to the movement of the flap to the completely extended position to release such locking bolt for movement immediately before or upon the movement of the flap to the extended position so as to lock the flap in such extended position.
  • FIGURE 1 is a fragmentary perspective view, with parts broken away, of a wing assembly made in accordance with the present invention showing the flap in a position in which it forms an extension of the wing;
  • FIGURE 2 is a view similar to FIGURE 1 but showing the wing assembly with the flap in a tilted position;
  • FIGURE 3 is an enlarged fragmentary cross sectional view of certain parts of the present invention with the flap in an initial position out of an extended position relative to the fixed wing part;
  • FIGURE 4 is a view similar to FIGURE 3, showing the pants in response to movement of the flap to the extended position relative to the wing.
  • a wing assembly made in accordance with the present invention is shown to include a plastic fixed wing part 1 and a plastic wing flap part 2,
  • a torsion spring 3 is mounted in the folding flap part and is secured at one end to the flap part (not shown) and at the opposite end to a support 5 of a light alloy part 4 cast into wing part 2.
  • Flap 2 is rotatably supported on wing 1 by means of a support stud 5 extending from casting 4 into a corresponding bore in wing 1.
  • the turning force for the flap is supplied by torsion spring 3 which is twisted when the fiap is in the position of FIG. 3.
  • Casting 4 is further provided with a lower lug having an oblique cam surface 6 and an upper locking lug 7.
  • An oblique surface 7a of the upper lug 7 faces a corresponding oblique surface 8a of a locking bolt 8 that is slidably carried by the fixed wing part 1.
  • a catch pin 10 slidably supported within a transversely extending opening in the bolt 8 is urged by a leaf spring 11, mounted within an axial bore 11a in the bolt 8, toward an outwardly extended locking position in engagement with a shoulder 1a of the fixed wing part 1, thus preventing an upward movement of the locking bolt 8 by the spring 9.
  • the outermost end of the catch pin 10 is in the path of movement of the cam surface 6 of the lower lug on the casting 4, so that upon movement of the flap with the casting 4 toward the extended position, the cam surface 6 will urge the catch pin 10 inwardly against the action of the leaf spring 11, to release the locking bolt 8 for movement upwardly toward locking engagement with the upper lock lug 7 of the casting 4.
  • the oblique surface 8a of the locking bolt 8 will slidably engage with the corresponding surface 7a of the lock lug 7, to draw the flap into alignment with the fixed part 1.
  • the flap 2 is prevented from passing its centered position in alignment with the fixed part 1 by a stop member 12 integral with the fixed wing part 1 and a facing lug 13 of the casting 4, thus assuring the proper alignment of the flap with the fixed part of the wing and the positive locking together of the parts by the lock bolt 8 and the lock lug 7.
  • the spring 9 can be made comparatively strong as it does not obstruct the movement of the flap toward the centered position shown in FIGURES l and 3, such spring 9 acting upon the locking bolt 8 only after the flap has been put into proper alignment with the fixed wing part 1.
  • a wing assembly for projectiles and rockets comprising, in combination, a fixed wing part, a folding flap part, a stud extending from one part and journalled in the other for rotatably supporting the flap on the wing part, torsion spring means yieldably acting between said fixed part and said folding flap for effecting rotation of said folding flap from an initial toward an adjusted position relative to said fixed part, said flap in said adjusted position forming an aligned extension of said fixed wing part, a bolt slidably carried in said fixed wing part for longitudinal movement transversely to the axis of rotation of the flap from a retracted position into an extended position engaging said flap to secure the same in said adjusted position, a spring in said fixed wing part yieldably urging said bolt toward said extended position for engagement with said flap, a releasable locking device securing said bolt in said retracted position, and a lug carried by said flap actuating said locking device toward a released position in response to rotation of said flap into said adjusted position in which it forms an extension of

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
  • Superstructure Of Vehicle (AREA)
US21285A 1959-04-13 1960-04-11 Wing assembly for missiles Expired - Lifetime US3058422A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE350259 1959-04-13

Publications (1)

Publication Number Publication Date
US3058422A true US3058422A (en) 1962-10-16

Family

ID=20262267

Family Applications (1)

Application Number Title Priority Date Filing Date
US21285A Expired - Lifetime US3058422A (en) 1959-04-13 1960-04-11 Wing assembly for missiles

Country Status (6)

Country Link
US (1) US3058422A (en, 2012)
BE (1) BE589608A (en, 2012)
CH (1) CH378734A (en, 2012)
DE (1) DE1147514B (en, 2012)
GB (1) GB869410A (en, 2012)
NL (2) NL250199A (en, 2012)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3650496A (en) * 1969-05-14 1972-03-21 Bofors Ab Folding fins for missiles
US3782668A (en) * 1970-09-25 1974-01-01 Us Army Ramp forward of control fin
US4203569A (en) * 1977-10-17 1980-05-20 Bei Electronics, Inc. Fin and nozzle unit for a free-flight rocket
US4691880A (en) * 1985-11-14 1987-09-08 Grumman Aerospace Corporation Torsion spring powered missile wing deployment system
US4717093A (en) * 1985-08-12 1988-01-05 Grumman Aerospace Corporation Penguin missile folding wing configuration
JPH09159398A (ja) * 1995-12-01 1997-06-20 Komatsu Ltd 飛翔体の翼装置
US6092264A (en) * 1998-11-13 2000-07-25 Lockheed Martin Corporation Single axis fold actuator and lock for member
CN102774494A (zh) * 2012-07-06 2012-11-14 北京林业大学 可自动张开飞行器折叠舵
CN104677199A (zh) * 2015-01-21 2015-06-03 浙江理工大学 一种单驱动多折叠舵面同步展开机构
CN107454882A (zh) * 2016-02-22 2017-12-08 深圳市大疆创新科技有限公司 机架及使用该机架的无人机
US10006748B2 (en) 2014-12-11 2018-06-26 Mbda Deutschland Gmbh Rudder system
CN109253667A (zh) * 2018-08-31 2019-01-22 江西洪都航空工业集团有限责任公司 一种导弹折叠舵面纵向展开机构
CN109405669A (zh) * 2018-08-31 2019-03-01 江西洪都航空工业集团有限责任公司 一种快拆翼面自动锁定机构

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106839897B (zh) * 2017-01-03 2019-01-15 北京临近空间飞行器系统工程研究所 一种直线螺旋展开折叠翼机构

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1191519A (fr) * 1958-02-13 1959-10-20 Hotchkiss Brandt Empennage déployant pour projectile d'artillerie
US2923241A (en) * 1957-09-09 1960-02-02 Aerojet General Co Folding stabilizing fins
US2924175A (en) * 1955-10-20 1960-02-09 Brandt Soc Nouv Ets Foldable fin arrangement for a projectile

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
LU31733A1 (en, 2012) * 1951-11-07

Patent Citations (3)

* 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
US2923241A (en) * 1957-09-09 1960-02-02 Aerojet General Co Folding stabilizing fins
FR1191519A (fr) * 1958-02-13 1959-10-20 Hotchkiss Brandt Empennage déployant pour projectile d'artillerie

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3650496A (en) * 1969-05-14 1972-03-21 Bofors Ab Folding fins for missiles
US3782668A (en) * 1970-09-25 1974-01-01 Us Army Ramp forward of control fin
US4203569A (en) * 1977-10-17 1980-05-20 Bei Electronics, Inc. Fin and nozzle unit for a free-flight rocket
US4717093A (en) * 1985-08-12 1988-01-05 Grumman Aerospace Corporation Penguin missile folding wing configuration
US4691880A (en) * 1985-11-14 1987-09-08 Grumman Aerospace Corporation Torsion spring powered missile wing deployment system
JPH09159398A (ja) * 1995-12-01 1997-06-20 Komatsu Ltd 飛翔体の翼装置
US6092264A (en) * 1998-11-13 2000-07-25 Lockheed Martin Corporation Single axis fold actuator and lock for member
CN102774494A (zh) * 2012-07-06 2012-11-14 北京林业大学 可自动张开飞行器折叠舵
US10006748B2 (en) 2014-12-11 2018-06-26 Mbda Deutschland Gmbh Rudder system
CN104677199A (zh) * 2015-01-21 2015-06-03 浙江理工大学 一种单驱动多折叠舵面同步展开机构
CN107454882A (zh) * 2016-02-22 2017-12-08 深圳市大疆创新科技有限公司 机架及使用该机架的无人机
US10625855B2 (en) 2016-02-22 2020-04-21 SZ DJI Technology Co., Ltd. Foldable multi-rotor aerial vehicle
CN107454882B (zh) * 2016-02-22 2021-05-07 深圳市大疆创新科技有限公司 机架及使用该机架的无人机
US11427319B2 (en) 2016-02-22 2022-08-30 SZ DJI Technology Co., Ltd. Foldable multi-rotor aerial vehicle
US12071237B2 (en) 2016-02-22 2024-08-27 SZ DJI Technology Co., Ltd. Foldable multi-rotor aerial vehicle
CN109253667A (zh) * 2018-08-31 2019-01-22 江西洪都航空工业集团有限责任公司 一种导弹折叠舵面纵向展开机构
CN109405669A (zh) * 2018-08-31 2019-03-01 江西洪都航空工业集团有限责任公司 一种快拆翼面自动锁定机构

Also Published As

Publication number Publication date
BE589608A (fr) 1960-08-01
CH378734A (de) 1964-06-15
GB869410A (en) 1961-05-31
NL250199A (en, 2012)
NL101734C (en, 2012)
DE1147514B (de) 1963-04-18

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