EP0013096B1 - Deployable wing mechanism - Google Patents

Deployable wing mechanism Download PDF

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Publication number
EP0013096B1
EP0013096B1 EP79302854A EP79302854A EP0013096B1 EP 0013096 B1 EP0013096 B1 EP 0013096B1 EP 79302854 A EP79302854 A EP 79302854A EP 79302854 A EP79302854 A EP 79302854A EP 0013096 B1 EP0013096 B1 EP 0013096B1
Authority
EP
European Patent Office
Prior art keywords
wing
segment
segments
hinge
deployable
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
EP79302854A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0013096A1 (en
Inventor
Keith Donald Thomson
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.)
Commonwealth of Australia
Original Assignee
Commonwealth of Australia
Commonwealth of Australia Department of Defence
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 Commonwealth of Australia, Commonwealth of Australia Department of Defence filed Critical Commonwealth of Australia
Publication of EP0013096A1 publication Critical patent/EP0013096A1/en
Application granted granted Critical
Publication of EP0013096B1 publication Critical patent/EP0013096B1/en
Expired 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

  • No. 1,485,163 Braun which is a relatively early Patent, dated 1924, and has a stub wing mounted on the fuselage by means of a hinge arranged longitudinally on the fuselage, and has an outer wing section joined to it by a vertical pivot pin, the object being stated to be to provide wings which can be folded similarly to the wings of birds.
  • the earlier specification includes bracing means to cause both wings to be positioned similarly.
  • the specification also refers to increasing possible wing spread.
  • the hinging both of the stub wing to the fuselage and the outer wing post to the stub wing is by single hinge means not suitable in modern missiles and high speed aircraft and wings are not shaped to facilitate folding against the body nor to follow body contours, and use a special construction which simulates feathers as without these the folding would not generally be possible.
  • DE-A-1,199,664, Dynamit Nobel Aktiengeselschaft relates to a rocket having spring ejected fins each comprising an inner part hinged along a longitudinal axis to fold into a cavity of the body with the outer part of the fin being housed within a cavity in the inner part of the fin so that it can be retracted into the inner part of the fin but projected to increase the area of the fin if the rocket leaves its firing tube.
  • a further object is to arrange the wing assembly that when in a stowed position there is minimal projection from the shell of the missile or fuselage to which the wing structure is attached.
  • a still further object is to provide the necessary rigidity in flight and the abaility to control the rate of deployment and to achieve a balanced operation and simultaneous positioning and to provide effective locking both when the wings are stowed or deployed.
  • each wing of an airborne missile, air craft or marine device arranged to have an inner and an outer wing segment connected together to be generally co-extensive when deployed and arranged to be stowed against the body, inner hinge means connecting an inner edge portion of the inner wing segment to the body along a generally longitudinally disposed axis on the body, and outer hinge means connecting the outer wing segment to an edge portion of the inner segment remote from the inner hinge means, the outer hinge means being disposed generally at right angles to the surface of the said inner and outer wing segments at the outer hinge means, means to move and hold the inner wing segment angularly about the inner hinge means in relation to the body, and means to move and hold the outer wing segment angularly about the outer hinge means in relation to the first wing segment, whereby both wing segments can lie adjacent to the body or can be deployed outwards to selected positions, characterised in that the outer wing segment has substantial extension behind the inner wing segment, both when deployed and stowed, whereby
  • the invention allows highly manoeuvrable ground or air-launched cruise missiles to be produced which can be launched from either tubes or aircraft bomb racks or bomb bays, the invention applying also to torpedoes or other marine devices.
  • the body 1 of a missile has a centre body section 2 on which the wings are mounted and has the usual tail fins 3 and control system 4.
  • the inner wing segments 5 are joined to the centre section 2 of the body on a longitudinal axis 6 and, as will be seen, the inner wing segments 5 are shaped to fit to the body when their free ends are swung inward about the axis 6.
  • the outer wing segment 7 is hinged to the outer part of the inner wing segment 5 on an axis 8 which is perpendicular to the surface of the inner wing segment, any suitable mechanism being used to move the segments from a folded to a deployed position.
  • FIG. 4 is a typical example of how the inner wing segment 5 and the outer wing segment 7 can be mounted in relation to the body 2 of the missile and in relation to each other, pods 10 being secured to the body 2 of the missile 1, one on either side of the body, and these pods carry a hollow shaft 11 about which the inner segments 5 of the wing are orientated, the wing segment including extending hinge members 12 which encircle the shaft 11 and by co-acting with the pod align the wing longitudinally in respect to the pods and the body 1.
  • the hollow shaft 11 has in it a torsion bar 13 which is fixed at the end 14 to the pod and at the end 15 to the inner wing segment 5 and this torsion rod is so arranged that when the wing segment 5 is released from a folded position, the torsion member will orientate the inner wing segment 5 about the shaft 11 to bring it out to its fully deployed position.
  • the outer wing segment 7 has near its inner end an aperture which engages a pivot pin 17, the inner end of this outer wing segment 7 fitting into a recess 18 in the inner wing segment 5 so that it can lie along the body of the misile in the position indicated by the dotted lines 19 in FIG. 4 but can be deployed outwardly about the pivot pin 17 when this is required, the deploying force being supplied by means of a cable 20 connected to any suitable mechanism which passes over a guide pulley 21 secured in the recess 18 of the inner segment 5 of the wing and having its end rigidly fixed at 22 to the outer wing segment 7.
  • the inner wing segment 5 is locked in its deployed position by means of a detent 23 (see FIG. 5) secured to pivot in the pod 10 and is loaded by means of a spring so that as the wing is outwardly deployed by the torsion bar 13 the free end of the detent 23 is positioned behind the shoulder 24 at the root of the inner wing segment 5 to then firmly hold the wing segment in its deployed position.
  • a detent 23 see FIG. 5
  • a device in which the inner wing segment is supported from the body 2 of the missile by pods 10 which carry a shaft 11 which in turn engages the root part of the inner wing segment 5 to allow this segment to swing from a position where it lies against the body of the missile to a position where it is extended as shown for instance in FIG. 3 of the drawings and it will be realised also that when tension is applied to the cable 20 the outer wing segment 7 will be deployed by swinging about the pivot pin 17 and can then be held by tension maintained on the cable 20 or can be locked by other means as will be understood from a description of other embodiments of this device.
  • Fig. 6 is shown how the wings in their deployed position project from the pods 10, the inner wing segment 5 having the recess 18 formed in it, this view showing how both the inner wing segment 5 and the outer wing segment 7 can be given an air-foil shape.
  • FIG. 7 is shown particularly how the inner part of the outer wing segment 7 fits into the recess 18 in the inner wing segment 5 and is held by the pivot pin 17 so that it can orientate within the cavity to move from a folded to a deployed position, the cable 20 being shown by means of which the outer wing segment 7 is deployed.
  • FIG. 8 this shows a further method of deploying the outer wing segment 7, the inner wing segment 5 being again supported on the hollow shaft 11 which has in it the torsion bar 13 fixed at the end 14 to the pod 10 and fixed at the end 15 to the inner segment 5 of the wing so that again the inner segment of the wing can be swung outwardly into the deployed position, using if necessary the locking means of FIG. 5 to hold it in that position, although it may be sufficient to hold it against a stop by means of the torsion spring.
  • the outer wing segment however in this form of the device has a toothed segment 25 which is engaged by toothed rack 26 on a cylinder 27 which fits over a hollow piston 28 to which pressure fluid can be supplied by means of a line 29 to move the cylinder 27 outwardly to deploy the wing through the engagement of the rack 26 with the toothed segment 25 on the wing, the fluid line 29 in this case being arranged to form a control valve 30 which is so arranged that pressure fluid from the line 31 enters the cavity of the part 32 of the hollow shaft which registers with the line 29 only when the inner segment of the wing 5 is fully extended to allow a flow of pressure fluid to the cylinder 27 to then deploy the outer segment of the wing 7.
  • the pods 10 again carry the hollow shaft 11 by means of which the inner segments 5 of the wing are orientatable about the pods, but in this case the wing segments 5 are provided with the cylindrical portions 35 which are inter-connected by a cable 36 which passes around the cylindrical section 35 in a "crossed-belt" relationship, the cable 36 being locked to the cylindrical sections 35 at an appropriate position so that no slip occurs so that by this mechanism the two inner wing sections 5 are caused to move similarly so that the wings are simultaneously folded or simultaneously deployed to ensure symmetry during deployment operation.
  • Movement of the inner wing segments 5 is achieved by means of a pair of cables 38 which also pass around the cylindrical sections 35 of each inner wing segment 5 and again are locked to ensure that there is no movement of the cables 38 in relation to the cylindrical sections 35, these two cables 38 passing around guide rollers 39 and being joined to the outer end of a piston 40 of a hydraulic ram cylinder 41.
  • the piston 40 is in the extended position when the inner segments 5 of the wings are in their folded or stowed position against the body, but when hydraulic fluid is supplied by any suitable means to the cylinder 41, the piston 40 is retracted to move the inner wing segments 5 into their deployed position.
  • Each outer wing segment 5 is similarly moved about its pivot pin 17 by a cable 44 attached to the wing segment at 45 and extending around a pulley 46 into the hollow shaft 11 and extending down that shaft to pass around a pulley 47 to be joined to the piston 48 of a cylinder 49, the arrangement being such that when the wings are folded the piston 48 is in its inward position.
  • pressure fluid is applied to the cylinder 49 to force the piston 48 outwardly to pull on the cables 44 to orientate the wing segment 7 about the pivot pin 17 into the deployed position.
  • FIG. 10 is shown how by using a detent 50 pivoted at 51 to the inner wing segment 5 and loaded into action by means of a spring 52, the end of the detent 50 is positioned in a notch 53 to lock the wing segment in its folded position, but by having the cable 44 passing beneath the free end of the detent 50 as shown in FIG. 10, the first pull on the cable 44 by the piston 48 dislodges the detent from the notch 53 and continued pull then holds the detent 50 in the position shown in FIG. 9 and allows the wing to be deployed to its maximum position.
  • Fig. 11 is shown diagramatically how the inner wing segments 5 are connected to pods 10 disposed on either side of the body 2 of the missile, and by the dotted line is indicated how the inner wing segment 5 folds against the body 2, the outer wing segment 7 being shown deployed. When not deployed, the outer wing segment projects back, or it may project forwardly, to be along the body of the missile.
  • the attachment can be otherwise arranged as is shown in FIG. 12 where a single pod 55 is used at the top of the body to support a pair of shafts 11 which again carry the inner segments 5 of the wings which in turn carry the outer segment 7.
  • the mechanism for operating the inner wing segments 5 to move in unison in the forms shown in FIGS. 12 and 13 can be as shown in FIGS. 14 and 15, the inner wing segments 5 in the case of Fig. 14 having toothed segments 58 and 59 which interengage so that both wing segments 5 must move together when being deployed from the folded position or when folding.
  • wing segment on one side is connected to a bevel pinion 61 while the wing section on the other side is connected to the bevel pinion 62 and these two pinions are interconnected by a bevel wheel 63 disposed as shown so that when the bevel wheel 63 is rotated, the two toothed segments 61 and 62 move in opposite direction to cause the inner wing segments 5 to similarly move oppositely.
  • a missile or craft constructed in this way can have the inner wing segments 5 folded to lie along the body but hinged to either extend upwardly or downwardly from the longitudinal fore and aft axis of the body according to the position of the bearing mounts, and when the inner wing segment on each side is folded in, the outer wing segment, which extends generally in the same plane as the inner wing segment will also lie along the body, either forwardly or rearwardly, so that in a frontal view the deployable wing structure fits to the body to give little increase in frontal area, making it possible to mount the missile in a tube from which it can be discharged by known means and thus making it possible to have a device which can be fired from a tube or barrel and will then deploy the wings at the required time.
  • the dimensions of the wings will be dependent on the weight to be carried and the fluid medium in which the device is used, and it will be realised that particularly the inner wing segments can be given a curvature so that they lie neatly along the body of the device, and as the outer wing segments are a swing wing which projects out from the inner wing segment and does not have to be retracted into the inner wing segment, much greater latitude in shape and operation results.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aerials With Secondary Devices (AREA)
  • Details Of Aerials (AREA)
EP79302854A 1978-12-29 1979-12-11 Deployable wing mechanism Expired EP0013096B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AUPD723878 1978-12-29
AU7238/78 1978-12-29

Publications (2)

Publication Number Publication Date
EP0013096A1 EP0013096A1 (en) 1980-07-09
EP0013096B1 true EP0013096B1 (en) 1983-04-13

Family

ID=3767901

Family Applications (1)

Application Number Title Priority Date Filing Date
EP79302854A Expired EP0013096B1 (en) 1978-12-29 1979-12-11 Deployable wing mechanism

Country Status (5)

Country Link
EP (1) EP0013096B1 (ja)
JP (1) JPS5592900A (ja)
AU (1) AU524255B2 (ja)
CA (1) CA1113070A (ja)
DE (1) DE2965231D1 (ja)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8352978B2 (en) 1998-05-15 2013-01-08 United Video Properties, Inc. Systems and methods for advertising television networks, channels, and programs
US8949901B2 (en) 2011-06-29 2015-02-03 Rovi Guides, Inc. Methods and systems for customizing viewing environment preferences in a viewing environment control application
US9288521B2 (en) 2014-05-28 2016-03-15 Rovi Guides, Inc. Systems and methods for updating media asset data based on pause point in the media asset
US11644287B2 (en) 2019-06-13 2023-05-09 Raytheon Company Single-actuator rotational deployment mechanism for multiple objects

Families Citing this family (36)

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SE433261B (sv) * 1980-03-31 1984-05-14 Andersson Kurt Goeran En inledningsvis rotationsstabiliserad ballistisk artilleriprojektil forsedd med utfellbara fenor
US4842218A (en) * 1980-08-29 1989-06-27 The United States Of America As Represented By The Secretary Of The Navy Pivotal mono wing cruise missile with wing deployment and fastener mechanism
GB2205798B (en) * 1983-08-11 1989-06-01 Secr Defence Improvements in or relating to unmanned aircraft.
US4691880A (en) * 1985-11-14 1987-09-08 Grumman Aerospace Corporation Torsion spring powered missile wing deployment system
FR2600618A1 (fr) * 1986-06-27 1987-12-31 Thomson Brandt Armements Aile a deploiement multiple, et son application a un engin volant
FR2812936A1 (fr) * 1986-08-12 2002-02-15 Aerospatiale Missile a voilure variable
FR2623898B1 (fr) * 1987-11-26 1990-03-23 France Etat Armement Dispositif de deploiement d'une ailette de projectile
US4869442A (en) * 1988-09-02 1989-09-26 Aerojet-General Corporation Self-deploying airfoil
GB2369177A (en) * 1989-06-02 2002-05-22 British Aerospace Aerofoil deployment system
FR2655722B1 (fr) * 1989-12-12 1992-03-13 Aerospatiale Missile supersonique a pilotage en couple par spouilers.
US5829715A (en) * 1996-04-19 1998-11-03 Lockheed Martin Vought Systems Corp. Multi-axis unfolding mechanism with rate controlled synchronized movement
US6092264A (en) * 1998-11-13 2000-07-25 Lockheed Martin Corporation Single axis fold actuator and lock for member
AU2001234732A1 (en) 2000-02-01 2001-08-14 United Video Properties, Inc. Methods and systems for forced advertising
US6581871B2 (en) * 2001-06-04 2003-06-24 Smiths Aerospace, Inc. Extendable and controllable flight vehicle wing/control surface assembly
DE102004039770A1 (de) * 2004-08-16 2006-03-02 Diehl Bgt Defence Gmbh & Co. Kg Flügelanordnung
RU2501712C1 (ru) * 2012-10-10 2013-12-20 Алексей Александрович Пирогов Винт пирогова махового действия с асимметрично поворотной лопастью
CN105691593B (zh) * 2016-03-11 2018-01-02 国网浙江省电力公司信息通信分公司 一种折叠翼无人机
CN107310729A (zh) * 2016-03-11 2017-11-03 甘丽霞 一种机翼
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CN105947209B (zh) * 2016-05-10 2018-04-17 菁果国际教育科技（广州）有限公司 一种节能环保型建筑市政用无人机
CN105905276B (zh) * 2016-05-10 2018-02-09 吉林省山河艮盛科技有限公司 一种建筑工程用折叠翼无人机
CN105799911B (zh) * 2016-05-10 2017-11-21 哈尔滨讯建科技有限公司 一种节能环保建筑工程用折叠翼无人机
CN105865271B (zh) * 2016-05-27 2017-09-05 中国人民解放军国防科学技术大学 一种采用快速充气弹翼的便携式导弹
CN108548457B (zh) * 2018-03-20 2023-12-05 浙江理工大学 一种导弹用单一动力源同步驱动式二次折叠展开机构
CN109533241B (zh) * 2018-12-14 2023-08-15 南京信息工程大学 一种智能折翼水下机器人
CN109405643A (zh) * 2018-12-17 2019-03-01 江南机电设计研究所 一种高刚度横向折叠式翼面
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CN113665792B (zh) * 2021-08-11 2023-12-05 广东空天科技研究院 一种折叠机翼及适用于折叠机翼高承载状态的锁定机构
CN114056524A (zh) * 2021-12-07 2022-02-18 中国海洋大学 一种水下防旋转尾翼和具有该尾翼的直读式ctd
CN114485288B (zh) * 2021-12-27 2024-05-28 西安现代控制技术研究所 小口径弹体-大翼展空间折叠尾翼的展开、锁紧方法
CN114852314A (zh) * 2022-05-20 2022-08-05 大连海事大学 一种降低折叠翼冲击载荷的空投型水下滑翔机
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US2572421A (en) * 1947-09-20 1951-10-23 Jr Edmund Abel Aircraft folding wing construction
US3197158A (en) * 1963-04-29 1965-07-27 Francis M Rogallo Flexible wing vehicle configurations
US3218005A (en) * 1961-12-06 1965-11-16 Calderon Alberto Alvarez High lift system for high speed aircraft
DE1241268B (de) * 1963-10-03 1967-05-24 Ver Flugtechnische Werke Ges M Flugkoerper, insbesondere Rakete oder Hoehensonde, mit Faltufluegeln zur Rueckfuehrung des Flugkoerpers aus dem Luftraum zur Erde
US3743218A (en) * 1968-06-28 1973-07-03 T Sweeney Semi-rigid airfoil for airborne vehicles
US3788578A (en) * 1971-05-19 1974-01-29 T Sweeney Semi-rigid airfoil for airborne vehicles
US3790104A (en) * 1973-03-12 1974-02-05 Us Navy High/low aspect ratio dual-mode fin design
US4022403A (en) * 1976-01-28 1977-05-10 Louis Francois Chiquet Convertible aircraft

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US1485163A (en) * 1923-01-30 1924-02-26 Braun Frank Flying machine
US2572421A (en) * 1947-09-20 1951-10-23 Jr Edmund Abel Aircraft folding wing construction
US3218005A (en) * 1961-12-06 1965-11-16 Calderon Alberto Alvarez High lift system for high speed aircraft
US3197158A (en) * 1963-04-29 1965-07-27 Francis M Rogallo Flexible wing vehicle configurations
DE1241268B (de) * 1963-10-03 1967-05-24 Ver Flugtechnische Werke Ges M Flugkoerper, insbesondere Rakete oder Hoehensonde, mit Faltufluegeln zur Rueckfuehrung des Flugkoerpers aus dem Luftraum zur Erde
US3743218A (en) * 1968-06-28 1973-07-03 T Sweeney Semi-rigid airfoil for airborne vehicles
US3788578A (en) * 1971-05-19 1974-01-29 T Sweeney Semi-rigid airfoil for airborne vehicles
US3790104A (en) * 1973-03-12 1974-02-05 Us Navy High/low aspect ratio dual-mode fin design
US4022403A (en) * 1976-01-28 1977-05-10 Louis Francois Chiquet Convertible aircraft

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8352978B2 (en) 1998-05-15 2013-01-08 United Video Properties, Inc. Systems and methods for advertising television networks, channels, and programs
US8949901B2 (en) 2011-06-29 2015-02-03 Rovi Guides, Inc. Methods and systems for customizing viewing environment preferences in a viewing environment control application
US9288521B2 (en) 2014-05-28 2016-03-15 Rovi Guides, Inc. Systems and methods for updating media asset data based on pause point in the media asset
US11644287B2 (en) 2019-06-13 2023-05-09 Raytheon Company Single-actuator rotational deployment mechanism for multiple objects

Also Published As

Publication number Publication date
CA1113070A (en) 1981-11-24
AU524255B2 (en) 1982-09-09
AU5387979A (en) 1980-07-03
JPS5592900A (en) 1980-07-14
DE2965231D1 (en) 1983-05-19
EP0013096A1 (en) 1980-07-09

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