EP0013096A1 - Deployable wing mechanism - Google Patents
Deployable wing mechanism Download PDFInfo
- Publication number
- EP0013096A1 EP0013096A1 EP79302854A EP79302854A EP0013096A1 EP 0013096 A1 EP0013096 A1 EP 0013096A1 EP 79302854 A EP79302854 A EP 79302854A EP 79302854 A EP79302854 A EP 79302854A EP 0013096 A1 EP0013096 A1 EP 0013096A1
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- European Patent Office
- Prior art keywords
- wing
- segments
- segment
- 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.)
- Granted
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- 230000007246 mechanism Effects 0.000 title description 10
- 239000012530 fluid Substances 0.000 claims description 9
- 230000008878 coupling Effects 0.000 claims 2
- 238000010168 coupling process Methods 0.000 claims 2
- 238000005859 coupling reaction Methods 0.000 claims 2
- 238000010276 construction Methods 0.000 description 2
- 241001415771 Torpedinidae Species 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 210000003746 feather Anatomy 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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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
- This invention relates to a deployable wing mechanism.
- Typical examples of movable wings are shown in the following United States natents:
- 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. Reference is also made to the folding facility being useful in transporting of flying machines and to give improving storage.
- 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 the 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.
- a further object is to so 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 ability 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, aircraft 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 said body, first hinge means connecting an inner edge portion of the inner wing segment to the body along a generally longitudinally disposed axis on the body, second hinge means connecting the outer wing segment to an edge portion of the inner segment remote from the first hinge means, the second hinge means being disposed generally at right angles to the surface of the said inner and outer wing segments at the second hinge means, means to move and hold the inner wing segment angularly about the first hinge means in relation to the body, and means to move and hold the outer wing segment angularly about the second 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.
- the invention allows highly manouvrable 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 torpedos 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 missile 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.
- 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 hudraulic 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 pivotted 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.
- the 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)
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aerials With Secondary Devices (AREA)
- Details Of Aerials (AREA)
Abstract
Description
- This invention relates to a deployable wing mechanism.
- It is already known to have on missiles, aircraft and similar mechanisms, wings which can be moved from a stowed to an active position or from a trailing to an extended position, the purpose generally being to allow the wings to be positioned according to requirements, such as in the case of navy planes where it is necessary to fold the wings or in the case of high speed aircraft where it is necessary to use swing wings. It is thus known to so mount the wings on the fuselage or body of a missile that they can be variously positioned according to requirements.
- Typical examples of movable wings are shown in the following United States natents:
- No. 2,572,421 Abel, which shows an aircraft with a fixed stub wing supporting a main wing section through pivoting means which allow the wing to be rotated through 90° and then swing back to lie parallel to the fuselage. This folding is not possible in flight.
- No. 4,022,403 Chiquet, which uses a wing hinged directly to the fuselage about a vertical pivot and provided with hydraulic means to allow the wing to be extended or folded back along the fuselage, the purpose however being to reduce overall width when the aircraft moves along a narrow path when not airborne.
- It is also known in modern high speed aircraft to use such an arrangement to allow the wings to be swept back in flight for greater aerodynamic efficiency at high speeds yet, when extended, to allow reasonably low landing speeds.
- 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. Reference is also made to the folding facility being useful in transporting of flying machines and to give improving storage.
- 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 the 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.
- It is an object of the present invention to provide certain improvements to deployable wing assemblies, the principal object being to allow the wings to fold in an effective manner but to allow the wings to extend when required so that for instance a missile can be ejected from a tube or barrel and when airborne can have the wings deployed.
- A further object is to so 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 ability 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.
- The objects of the present invention are achieved by having each wing of an airborne missile, aircraft 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 said body, first hinge means connecting an inner edge portion of the inner wing segment to the body along a generally longitudinally disposed axis on the body, second hinge means connecting the outer wing segment to an edge portion of the inner segment remote from the first hinge means, the second hinge means being disposed generally at right angles to the surface of the said inner and outer wing segments at the second hinge means, means to move and hold the inner wing segment angularly about the first hinge means in relation to the body, and means to move and hold the outer wing segment angularly about the second 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.
- It will be realised that the invention, among other things, allows highly manouvrable 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 torpedos or other marine devices.
-
- FIGS. 1, 2 and 3 are schematic views of the invention as applied to an airborne missile, FIG. 1 showing the wing structure folded against the body of the missile, FIG. 2 showing the inner wing segments deployed but with the outer wing segments trailing in the position they occupy when folded and FIG. 3 showing the missile with both the inner and outer wing segments deployed.
- FIG. 4 is a somewhat schematic-part sectional view of a typical wing structure with both the outer and inner wing segments deployed.
- FIG. 5 is a schematic detailed view showing how the inner wing segment is locked when in the deployed position.
- FIG. 6 is a side elevation of a wing with both segments in the deployed position.
- FIG. 7 is a similar view but with the wing segments sectioned on the plane of the pivot between the inner wing segment and the outer wing segment.
- FIG. 8 is a schematic plan showing how the inner wing segment can be deployed by means of a torsion bar in the hinge shaft and showing how the outer wing segment is deployed by a hydraulic mechanism.
- FIG. 9 is a view similar to FIG. 4 but showing how cable mechanisms can be used for deploying both the inner and outer wing segments.
- FIG. 10 is a detailed view showing how the outer wing segment can be locked in its folded position prior to it being unlocked and deployed by a cable.
- FIG. 11 is a schematic front elevation of a missile showing how the inner and outer wing segments can be located on pods on two sides of the missile body.
- FIG. 12 is a similar view but showing how the wing segments can be mounted on adjacent hinging means.
- FIG. 13 is a similar view but showing the wing segments mounted on a single hinging axis.
- FIG. 14 shows how the wing segments of FIG. 12 can be geared together for similar movement, and
- FIG. 15 shows how the wing segments of FIG. 13 can be geared together to move synchronously.
- Referring first to FIGS. 1, 2 and 3 it will be seen that the
body 1 of a missile has acentre body section 2 on which the wings are mounted and has theusual tail fins 3 andcontrol system 4. - The
inner wing segments 5 are joined to thecentre section 2 of the body on alongitudinal axis 6 and, as will be seen, theinner wing segments 5 are shaped to fit to the body when their free ends are swung inward about theaxis 6. - The
outer wing segment 7 is hinged to the outer part of theinner wing segment 5 on anaxis 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. - In the following description, similar members will be referred to by similar identification members.
- FIG. 4 is a typical example of how the
inner wing segment 5 and theouter wing segment 7 can be mounted in relation to thebody 2 of the missile and in relation to each other,pods 10 being secured to thebody 2 of themissile 1, one on either side of the body, and these pods carry ahollow shaft 11 about which theinner segments 5 of the wing are orientated, the wing segment including extendinghinge members 12 which encircle theshaft 11 and by co-acting with the pod align the wing longitudinally in respect to the pods and thebody 1. - 6 The
hollow shaft 11 has in it atorsion bar 13 which is fixed at theend 14 to the pod and at theend 15 to theinner wing segment 5 and this torsion rod is so arranged that when thewing segment 5 is released from a folded position, the torsion member will orientate theinner wing segment 5 about theshaft 11 to bring it out to its fully deployed position. - The
outer wing segment 7 has near its inner end an aperture which engages apivot pin 17, the inner end of thisouter wing segment 7 fitting into arecess 18 in theinner wing segment 5 so that it can lie along the body of the missile in the position indicated by thedotted lines 19 in FIG. 4 but can be deployed outwardly about thepivot pin 17 when this is required, the deploying force being supplied by means of acable 20 connected to any suitable mechanism which passes over aguide pulley 21 secured in therecess 18 of theinner segment 5 of the wing and having its end rigidly fixed at 22 to theouter 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 thepod 10 and is loaded by means of a spring so that as the wing is outwardly deployed by thetorsion bar 13 the free end of thedetent 23 is positioned behind theshoulder 24 at the root of theinner wing segment 5 to then firmly hold the wing segment in its deployed position. - From the foregoing it will be realised that a device is provided in which the inner wing segment is supported from the
body 2 of the missile bypods 10 which carry ashaft 11 which in turn engages the root part of theinner 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 thecable 20 theouter wing segment 7 will be deployed by swinging about thepivot pin 17 and can then be held by tension maintained on thecable 20 or can be locked by other means as will be understood from a description of other embodiments of this device. - In FIG. 6 is shown how the wings in their deployed position project from the
pods 10, theinner wing segment 5 having therecess 18 formed in it, this view showing how both theinner wing segment 5 and theouter wing segment 7 can be given an air-foil shape. - In FIG. 7 is shown particularly how the inner part of the
outer wing segment 7 fits into therecess 18 in theinner wing segment 5 and is held by thepivot pin 17 so that it can orientate within the cavity to move from a folded to a deployed position, thecable 20 being shown by means of which theouter wing segment 7 is deployed. - Referring now to FIG. 8 this shows a further method of deploying the
outer wing segment 7, theinner wing segment 5 being again supported on thehollow shaft 11 which has in it thetorsion bar 13 fixed at theend 14 to thepod 10 and fixed at theend 15 to theinner 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 bytoothed rack 26 on a cylinder 27 which fits over ahollow piston 28 to which pressure fluid can be supplied by means of aline 29 to move the cylinder 27 outwardly to deploy the wing through the engagement of therack 26 with thetoothed segment 25 on the wing, thefluid line 29 in this case being arranged to form acontrol valve 30 which is so arranged that pressure fluid from theline 31 enters the cavity of thepart 32 of the hollow shaft which registers with theline 29 only when the inner segment of thewing 5 is fully extended to allow a flow of pressure fluid to the cylinder 27 to then deploy the outer segment of thewing 7. - Referring now to FIG. 9 where a different form of mechanism is shown for deploying the
wing segments pods 10 again carry thehollow shaft 11 by means of which theinner segments 5 of the wing are orientatable about the pods, but in this case thewing segments 5 are provided with thecylindrical portions 35 which are inter-connected by acable 36 which passes around thecylindrical section 35 in a "crossed-belt" relationship, thecable 36 being locked to thecylindrical sections 35 at an appropriate position so that no slip occurs so that by this mechanism the twoinner 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 ofcables 38 which also pass around thecylindrical sections 35 of eachinner wing segment 5 and again are locked to ensure that there is no movement of thecables 38 in relation to thecylindrical sections 35, these twocables 38 passing aroundguide rollers 39 and being joined to the outer end of apiston 40 of ahydraulic ram cylinder 41. - The
piston 40 is in the extended position when theinner segments 5 of the wings are in their folded or stowed position against the body, but when hudraulic fluid is supplied by any suitable means to thecylinder 41, thepiston 40 is retracted to move theinner wing segments 5 into their deployed position. - By maintaining the pressure in the
cylinder 41 the segments are then locked in their deployed position. - Each
outer wing segment 5 is similarly moved about itspivot pin 17 by acable 44 attached to the wing segment at 45 and extending around apulley 46 into thehollow shaft 11 and extending down that shaft to pass around apulley 47 to be joined to thepiston 48 of acylinder 49, the arrangement being such that when the wings are folded thepiston 48 is in its inward position. When it is desired to deploy thewing segments 7, pressure fluid is applied to thecylinder 49 to force thepiston 48 outwardly to pull on thecables 44 to orientate thewing segment 7 about thepivot.pin 17 into the deployed position. - In FIG. 10 is shown how by using a detent 50 pivotted at 51 to the
inner wing segment 5 and loaded into action by means of aspring 52, the end of thedetent 50 is positioned in anotch 53 to lock the wing segment in its folded position, but by having thecable 44 passing beneath the free end of the detent 50 as shown in FIG. 10, the first pull on thecable 44 by thepiston 48 dislodges the detent from thenotch 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. - It will be realised that the form of control described in the preceding figures can be varied according to requirements.
- In FIG. 11 is shown diagramatically how the
inner wing segments 5 are connected topods 10 disposed on either side of thebody 2 of the missile, and by the dotted line is indicated how theinner wing segment 5 folds against thebody 2, theouter 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. - Generally that is the position of the pods as described in the foregoing embodiments but it will be realised that 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 ofshafts 11 which again carry theinner segments 5 of the wings which in turn carry theouter segment 7. - Instead of using two pods with a
shaft 11 in each, or using a single pod as 55 with twoshafts 11 disposed therein, it is possible to use asingle shaft 11 engaging a single pod 56 and in this case again theinner wing segments 5 engage theshaft 11 and again folding of theinner sections 5 of the wing takes place against thebody 2 of the missile, as shown in dotted lines, the roots of the inner wing sections being appropriately designed to form hinge members which engage theshaft 11 in an interleaved relationship. This can be achieved by appropriately reducing the width of the hinge members shown in FIG. 4 so that they can be interleaved. - 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, theinner wing segments 5 in the case of FIG. 14 having toothedsegments wing segments 5 must move together when being deployed from the folded position or when folding. - In the case of FIG. 15 the wing segment on one side is connected to a
bevel pinion 61 while the wing section on the other side is connected to thebevel 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 twotoothed segments inner wing segments 5 to similarly move oppositely. - It will be realised of course that variation in the structures for moving the wing segments is possible within the spirit of this invention and it will be realised also that electrical control of the wing segments is possible but such variations of a construction will lie within the spirit of the present invention.
- From the foregoing description it will be realised that 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.
- While in the foregoing description inner and outer wing segments are referred to, it will be appreciated that a further wing segment could be pivoted to the first outer wing segment, and so on, and also more than two sets of wings could be used.
Claims (17)
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 true EP0013096A1 (en) | 1980-07-09 |
EP0013096B1 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 (en) |
JP (1) | JPS5592900A (en) |
AU (1) | AU524255B2 (en) |
CA (1) | CA1113070A (en) |
DE (1) | DE2965231D1 (en) |
Cited By (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0038310A1 (en) * | 1980-03-31 | 1981-10-21 | Kurt Göran Andersson | Ballistic projectile with extendable fins |
FR2600618A1 (en) * | 1986-06-27 | 1987-12-31 | Thomson Brandt Armements | WING WITH MULTIPLE DEPLOYMENT AND ITS APPLICATION TO A FLYING DEVICE |
GB2205798A (en) * | 1983-08-11 | 1988-12-21 | Secr Defence | Unmanned aircraft |
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 |
US4869442A (en) * | 1988-09-02 | 1989-09-26 | Aerojet-General Corporation | Self-deploying airfoil |
FR2655722A1 (en) * | 1989-12-12 | 1991-06-14 | Aerospatiale | SUPERSONIC MISSILE WITH TORQUE DRIVING BY SPOUILERS. |
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US4460137A (en) * | 1980-03-31 | 1984-07-17 | Andersson Kurt G | Ballistic artillery projectile, that is initially spin-stabilized |
EP0038310A1 (en) * | 1980-03-31 | 1981-10-21 | Kurt Göran Andersson | Ballistic projectile with extendable fins |
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 |
GB2205798A (en) * | 1983-08-11 | 1988-12-21 | Secr Defence | Unmanned aircraft |
GB2205798B (en) * | 1983-08-11 | 1989-06-01 | Secr Defence | Improvements in or relating to unmanned aircraft. |
FR2600618A1 (en) * | 1986-06-27 | 1987-12-31 | Thomson Brandt Armements | WING WITH MULTIPLE DEPLOYMENT AND ITS APPLICATION TO A FLYING DEVICE |
EP0251890A1 (en) * | 1986-06-27 | 1988-01-07 | Thomson-Brandt Armements | Multiple unfolding wing, and its use in an aircraft missile |
DE3726735B3 (en) * | 1986-08-12 | 2004-02-05 | Société Nationale Industrielle Aérospatiale | Rocket with a variable structure |
US5108051A (en) * | 1987-11-26 | 1992-04-28 | L'etat Francais Represente Par Le Delegue General Pour L'armement | Deployment mechanism of a projectile fin |
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 |
FR2655722A1 (en) * | 1989-12-12 | 1991-06-14 | Aerospatiale | SUPERSONIC MISSILE WITH TORQUE DRIVING BY SPOUILERS. |
US5143320A (en) * | 1989-12-12 | 1992-09-01 | Societe Nationale Industrielle Et Aerospatiale | Spoiler torque controlled supersonic missile |
EP0433128A1 (en) * | 1989-12-12 | 1991-06-19 | AEROSPATIALE Société Nationale Industrielle | Supersonic missile guided by a coupling action carried out by spoilers |
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 |
US9137491B2 (en) | 2000-02-01 | 2015-09-15 | Rovi Guides, Inc. | Methods and systems for forced advertising |
EP1265050A1 (en) * | 2001-06-04 | 2002-12-11 | Smiths Industries Actuation Systems Inc. | Extendable and controllable flight vehicle wing/control surface assembly |
US6581871B2 (en) | 2001-06-04 | 2003-06-24 | Smiths Aerospace, Inc. | Extendable and controllable flight vehicle wing/control surface assembly |
DE102004039770A1 (en) * | 2004-08-16 | 2006-03-02 | Diehl Bgt Defence Gmbh & Co. Kg | wing assembly |
EP2907746A4 (en) * | 2012-10-10 | 2016-10-12 | Aleksei Aleksandrovich Pirogov | Pirogov flywheel-effect propeller having an asymmetrically rotating blade |
CN105865271A (en) * | 2016-05-27 | 2016-08-17 | 中国人民解放军国防科学技术大学 | Portable missile adopting fast inflatable missile wings |
CN109533241A (en) * | 2018-12-14 | 2019-03-29 | 南京信息工程大学 | A kind of intelligence flap underwater robot |
CN109533241B (en) * | 2018-12-14 | 2023-08-15 | 南京信息工程大学 | Intelligent flap underwater robot |
CN109405643A (en) * | 2018-12-17 | 2019-03-01 | 江南机电设计研究所 | A kind of laterally folded formula aerofoil of high rigidity |
CN112896487A (en) * | 2021-01-28 | 2021-06-04 | 西安电子科技大学 | Unmanned aerial vehicle synchronous unfolding and folding system, method and application |
CN113665792B (en) * | 2021-08-11 | 2023-12-05 | 广东空天科技研究院 | Folding wing and locking mechanism suitable for high bearing state of folding wing |
CN113665792A (en) * | 2021-08-11 | 2021-11-19 | 广东空天科技研究院 | Folding wing and locking mechanism suitable for high bearing state of folding wing |
CN114485288A (en) * | 2021-12-27 | 2022-05-13 | 西安现代控制技术研究所 | Unfolding and locking method of small-caliber projectile body-large wingspan space folding tail wing |
CN114485288B (en) * | 2021-12-27 | 2024-05-28 | 西安现代控制技术研究所 | Unfolding and locking method for small-caliber projectile body-large-span space folding tail wing |
CN114852314A (en) * | 2022-05-20 | 2022-08-05 | 大连海事大学 | Air-drop underwater glider capable of reducing impact load of folding wings |
CN115060124A (en) * | 2022-07-08 | 2022-09-16 | 江西洪都航空工业集团有限责任公司 | Portable missile wing locking device of commonality |
CN115060124B (en) * | 2022-07-08 | 2023-11-03 | 江西洪都航空工业集团有限责任公司 | Portable missile wing locking device of commonality |
CN116513448B (en) * | 2023-07-04 | 2023-10-13 | 西安羚控电子科技有限公司 | Limiting device of folding wing and folding wing |
CN116513448A (en) * | 2023-07-04 | 2023-08-01 | 西安羚控电子科技有限公司 | Limiting device of folding wing and folding wing |
CN118270226A (en) * | 2024-06-04 | 2024-07-02 | 西安羚控电子科技有限公司 | Folding and unfolding device of aircraft |
Also Published As
Publication number | Publication date |
---|---|
AU524255B2 (en) | 1982-09-09 |
AU5387979A (en) | 1980-07-03 |
EP0013096B1 (en) | 1983-04-13 |
JPS5592900A (en) | 1980-07-14 |
CA1113070A (en) | 1981-11-24 |
DE2965231D1 (en) | 1983-05-19 |
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