CN101065291A - Lift augmentation system - Google Patents
Lift augmentation system Download PDFInfo
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- CN101065291A CN101065291A CN 200580016913 CN200580016913A CN101065291A CN 101065291 A CN101065291 A CN 101065291A CN 200580016913 CN200580016913 CN 200580016913 CN 200580016913 A CN200580016913 A CN 200580016913A CN 101065291 A CN101065291 A CN 101065291A
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- leading edge
- flexible surface
- hoisting force
- aggrandizement apparatus
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Abstract
This invention relates generally to a lift augmentation system for an airframe. More particularly, the invention concerns the combination of extendable/retractable wing tips with an airframe for lift augmentation as well as wings that can pivot into a deployed position. Flexible surface elements may be rolled for storage and unrolled for deployment with at least one being on the suction surface of the wing and at least one being on the pressure surface of the wing.
Description
Background of invention
This invention relates generally to a kind of device that is used to increase aircraft body design-calculated hoisting force ability, this device or as one of this aircraft body optional new installation or as one the repacking parts.More particularly, the present invention relates to a kind of device that additional hoisting capacity is provided by the light flexible sheet of working weight as required.
The invention brief introduction
Hoisting force aggrandizement apparatus of the present invention can comprise an extensible leading edge supporting member.This developing power can make this hoisting force aggrandizement apparatus produce longitudinal extension along existing wing.This developing power can also make this hoisting force aggrandizement apparatus rotate between a favorite places and an expanded position.This hoisting force aggrandizement apparatus also comprises at least one pair of flexible surface's part, and this flexible surface's part partly is contained on the leading edge supporting member, and they play a part the aerodynamic force surface of hoisting force aggrandizement apparatus.Flexible surface's part in this flexible surface's part defines the suction face of hoisting force aggrandizement apparatus at least in part.Another flexible surface's part in this flexible surface's part defines the pressure surface of hoisting force aggrandizement apparatus at least in part.Increase area in order to change hoisting force, an expanding unit of hoisting force aggrandizement apparatus can be used to launch and pack up leading edge supporting member and flexible surface's part.
Flexible surface's part can be made by one or more materials.Suitable material comprises, fabric substrate material for example, composite material, carbon fiber reinforcement material, synthetic polymer sheet, cloth textile material and have the material etc. of laminating surface layer.In some use occasion, can use stay to strengthen flexible surface's part partly.
Expanding unit can comprise that the fabric that a sub-device of spar that is used for launching and pack up the leading edge supporting member and are used for launching and pack up flexible surface's part controls sub-device.Suitable fabric is controlled sub-device can comprise a spool that is wound with flexible surface's part on it.A suitable common electric machine can be used for controlling the expansion of flexible surface's part when the hoisting force aggrandizement apparatus launches, then can be used for making flexible surface's part to restore to the original state when the hoisting force aggrandizement apparatus is packed up.Use the occasion of a plurality of flexible surface's parts at the hoisting force aggrandizement apparatus, can advantageously use a plurality of spools.For flexible surface's part being fixed on the framing member of hoisting force aggrandizement apparatus, several skate apparatus can be arranged on certain position on the framing member, skate apparatus is packed up the respective edges of flexible surface's part slidably on this position.In some use occasion, a hawser pulley gear can be used for fabric and launch sub-device.
Suitable spar launches sub-device can comprise various mechanicals device.For example, one or more rack-and-pinion device can be set, rack member be fixed on the spar, and pinion drive is fixed on the fixing supporting member.Perhaps, can use a helicoidal gear.In helicoidal gear, a rotating helical member can be fixed on the spar, and a fixing related parts is fixed on the fixing supporting member.Perhaps, a fixing helical member that is installed on the spar can be cooperated mutually with a rotating related parts that is installed on the fixing supporting member.Irrelevant with mechanical device, spar launches sub-device and preferably can handle the leading edge supporting member and move between the primary importance and the second place, wherein this primary importance can be a position of collecting fully or packing up, and the second place then can be a position of launching or partly launching fully.Under the situation of the end that the hoisting force aggrandizement apparatus is positioned at existing aerodynamic force surface, spar launches sub-device can make the motion of spar telescopically.Comprise at the hoisting force aggrandizement apparatus under the situation of a pivoted device that this primary importance is generally the position of collection fully, and this second place is generally the position of launching fully.
Hoisting force aggrandizement apparatus of the present invention can be used as parts of original equipment, perhaps as parts of reequiping purposes.In both cases, it can use with multiple aircraft body.Preferably, under the situation that is used for the wing tip expansion, the hoisting force aggrandizement apparatus makes specified wing area be increased in about 15% to about 35% scope.In the use occasion of wing tip expansion, the cross sectional shape that the hoisting force aggrandizement apparatus has is consistent with the cross sectional shape of existing wing tip.In addition, preferably the profile of leading edge part is consistent with the profile of existing leading edge, and when launching or packing up with convenient hoisting force aggrandizement apparatus, the leading edge part longitudinally moves with respect to the leading edge of wing slidably, and can not cause injurious effects to existing wing.
If desired, the aircraft body can manual operation (or unattended) and remote manipulation.In addition, the aircraft body can comprise any in the various propelling units, comprise as an example: jet engine, the pusher propeller actuating device, tractor propellar actuating device, diesel motor, rotary engine, ducted fan engine, Sabath'e-cycle engine, perhaps a kind of fuel piston formula driving engine of a for example anterior installation and the small-sized turbojet of a rear portion installation or the hybrid combining of gas turbine engine.
Brief description
For those skilled in the art, many purposes of the present invention and advantage are by reading this specification sheets, and with perfectly clear, identical label is used for identical part among the figure together with reference to the accompanying drawings, wherein:
Fig. 1 is the transparent view of signal with aircraft body of hoisting force aggrandizement apparatus of the present invention;
Fig. 2 is the top view of this hoisting force aggrandizement apparatus when being in complete expanded position;
Fig. 3 is the front elevation of this hoisting force aggrandizement apparatus when being in complete expanded position;
Fig. 4 is the top view of this hoisting force aggrandizement apparatus cut-away section when being in complete expanded position;
Fig. 5 is the partial section of an amplification being intercepted of the 5-5 line along Fig. 4;
Fig. 6 is the partial section of an amplification being intercepted of the 6-6 line along Fig. 4;
Fig. 7 is the partial section of an amplification being intercepted of the 7-7 line along Fig. 4;
Fig. 8 is the partial section of an amplification being intercepted of the 8-8 line along Fig. 4;
Fig. 9 is the top view of signal that is configured to the hoisting force aggrandizement apparatus of pivoted deployed condition;
Figure 10 is the section drawing of a part being intercepted of the 10-10 line along Fig. 9;
Figure 11 is the section drawing of a part being intercepted of the 11-11 line along Fig. 9;
Figure 12 be one with the similar view of Fig. 9, there is shown the collection and the expanded position of leading edge spar;
Figure 13 is the top view of signal with hoisting force aggrandizement apparatus of a pair of wing components;
Figure 14 is the front elevation of the signal of the embodiment among Figure 13; And
Figure 15 is a transparent view of installing and using a signal of the hoisting force aggrandizement apparatus on unpiloted unpowered vehicle body.
Detailed Description Of The Invention
Concerning this specification sheets, term " aircraft body " is the common name that is used to refer to the means of delivery of a kind of any kind that can move in gas medium such as air.For example, the aircraft body can comprise (illustrating and unrestricted in the mode of example) aircraft body, and aerodone produces the object of hoisting force, the space vehicle when returning, helicopter and similar aircraft etc.The aircraft body can be driven by engine installation, perhaps also can be motorless.Equally, the aircraft body can be manned or unmanned, or is subjected to remote operation.
Referring to Fig. 1, the aircraft body 20 that constitutes a suitable common aircraft body comprises a high wing components 22 of fixing and being bearing on the fuselage 24.This wing components 22 has a left side and starboard wing 22a and 22b usually.Each wing is designed to have specified wing area usually.As shown in the figure, aircraft body 20 also has two shoe fin assemblies 26 of fixing and being bearing on the high wing components 22.
For engine-on flight is provided, aircraft body 20 also comprises a pair of propelling unit 28,30.Each propelling unit 28,30 can lean on any suitable conventional fuel to come work, comprising (but not limited) gasoline, diesel oil and synthetic engine fuel.And each propelling unit can be worked under any desired heat power circulation.In addition, each propelling unit can be by an explosive motor, a jet engine, and a rotary engine, a Sabath'e-cycle engine or a ducted fan engine constitute.Each propelling unit can also be operationally be connected with a screw propeller or with any proper device by this aircraft body of air driven.For example, an anterior screw propeller 32 of installing is just driven by a propelling unit 28 herein, and the ducted fan engine 34 that is arranged between two shoes of fin assembly 26 is then driven by another propelling unit 30. Propelling unit 28,30 can be worked or next device work simultaneously.Therefore, ducted fan engine 34 plays a pusher propeller, and it can be arranged on the rear portion of fuselage 24, more quietly moves than the anterior tractor propellar of installing 32 so that obtain.
Each wing 22a, the outer end of 22b comprises an extensible/retractable wing tip hoisting force aggrandizement apparatus 40.This wing tip hoisting force aggrandizement apparatus 40 is mirror image each other.Therefore, it is just enough to describe one of them device 40, because people understand fully, the another one device will have same feature, but carry out work in the mode of contrast.Each wing tip device 40 can be independently basically.Therefore, wing tip device 40 can be used as a repacking annex that is used for existing aircraft body provides.Perhaps, wing tip device 40 can be used as an optional equipment is provided by original equipment manufacturers.
Each wing tip device 40 can move between the primary importance 40 of packing up fully ' (being shown in broken lines in Fig. 2) and the second place (illustrating with solid line in Fig. 2).The second place can be the position of launching fully that is shown among Fig. 1, or at an expanded position and a midway location between the stowed position fully fully.Like this, when wing tip device 40 launches, relevant wing 22a, the area of 22b just increases, thereby the available hoisting force of aircraft body 20 also just increases.Wing tip device 40 can make the increase of nominal area of relevant wing up to about 100%.It is about 50% that this increase area preferentially is adopted as, and preferably this area increase is in about 15% to about 35% scope.In addition, the wing tip device has increased the aspect ratio of original wing and device 40 combinations, has increased the hoisting force and the aerodynamic efficiency of this combination thus.
As wing 22a shown in Figure 1, when the 22b chord length is a constant, wing tip device 40 just can with use together along the tapered wing of direction from fuselage guide vane point.Whether be tapered irrelevantly with wing, the leading edge of wing tip device should be basically and the leading edge conllinear of relevant wing.In addition, the trailing edge of wing tip device 40 should parallel with its leading edge basically, and the wing chord length that makes wing tip device 40 substantially with the wing chord equal in length of relevant wing tip.
For the hoisting force that further improves wing tip device 40 increases characteristic, a upwardly extending wing fence 42 and a wing fence 44 that extends can be set downwards.As required, the wing fence on opposed wing tip 42 can have a dihedral angle between them.Equally, the wing fence on opposed wing tip 44 also can have a dihedral angle between them.It is actv. that these wing fences 42,44 circulate for the secondary air of minimizing between the end face (or suction face) of bottom surface of wing (or pressure surface) and wing.The minimizing of the secondary flow of this three-dimensional can also improve originally the hoisting force that can obtain from wing 22.As following will be more fully as described in, the wing fence 42,44 on these wing tips can also play rectifying device (it be used for hidden hoisting force aggrandizement apparatus 40 with launch and pack up relevant device).
Referring to Fig. 2, wing tip hoisting force aggrandizement apparatus 40 comprises an extendible leading edge supporting member 50, the length of this supporting member surpass stowed position 40 ' and expanded position between distance.Like this, leading edge supporting member 50 just can provide an additional cantilever support part for the hoisting force aggrandizement apparatus.Leading edge supporting member 50 preferably includes a leading edge root cover 52, and this root cover can be made by the epoxy resin-base material that carbon fiber is strengthened, and is perhaps made by other equivalent material (comprising laminated material).Leading edge root cover 52 is consistent with the leading edge shape of relevant wing 22b, and this root cover has one is enough to make leading edge to have successional length when wing tip hoisting force aggrandizement apparatus 40 launches fully.Power for support edge root cover 52 and its slip of minimizing obstruction, polytetrafluoroethylene (Teflon ) the liner (not shown) of suitable shape can be set between the upper and lower surface of the leading edge root cover 52 and the leading edge of a wing, perhaps have other suitable materials of similar characteristic.Liner can be placed on the inboard of leading edge root cover 52, perhaps is placed on the outside face of wing.Liner preferably is placed on the inside face of leading edge root cover 52, so that reduce contingent burble above wing when normally moving.These liners can also make the structure of leading edge root cover 52 bear some stretching and flexural load, and these load act on when launching the hoisting force aggrandizement apparatus on the relevant wing 22b.
Hoisting force aggrandizement apparatus 40 also comprises at least two flexible surface's parts, and a face component 54 is positioned at the end face or the suction face of hoisting force aggrandizement apparatus, and another face component then is positioned at the bottom surface or the pressure surface of hoisting force aggrandizement apparatus.In addition, can expect that two or more face component 54,56 can be used for the suction face and the pressure surface of hoisting force aggrandizement apparatus 40.
Flexible surface's part is preferably made by having the abundant elastomeric sheet material that can reel.This material can be braiding or non-woven.Flexible surface's part can also be made by the synthetic material of the dimensionally stable of any suitable routine, such as aramid fibre (for example Kevlar ), and poly-ester fibres (for example Dacron ), ultrahigh molecular weight polyethylene fiber (Spectra for example
TM), high strength liquid crystal polymer fibre (Vectran for example
TM), nylon or other are material roughly the same.In addition, the material of flexible surface's part should be selected like this, and it should be enough firm, and the aerodynamic pressure that the hoisting force aggrandizement apparatus will bear in the time of can bearing flight can not lose efficacy with other various power.Material with carbon fiber stiffener also is suitable for these flexible surface's parts.This based carbon fiber stiffener can be used as a kind of component of fabric substrate material.This material can comprise the film of one deck synthetic polymer sheeting or a kind of composite material.For example; this composite material for example can comprise a kind of cloth fabric; this cloth fabric and aramid fibre, poly-ester fibres and/or carbon fiber are made into and comprise the superficial layer (such as mylar that is used for intensity and tensile strength such as Mylar ) of several laminations and the skin of PVF film (for example Tedlar) that is used for UV protection or PVDR (for example Kynar) together.
An expanding unit is set, and this device is used for launching and packing up the hoisting force aggrandizement apparatus and be used for launching and packing up flexible surface's part with respect to wing tip, can change the area that hoisting force increases thus.Expanding unit comprises that the fabric that a sub-device of spar that is used for launching and pack up one or more spars and are used for launching and pack up flexible surface's part controls sub-device.
For with respect to wing or aircraft body supporting hoisting force aggrandizement apparatus 40, leading edge spar 60 (see figure 4)s can be fixed on the dividing plate 62 at wing wing tip place.Leading edge spar 60 is preferably fixing like this, makes that this spar can be with respect to the itself longitudinal movement when hoisting force aggrandizement apparatus 40 moves between its primary importance and the second place.For needed structure support is provided, leading edge spar 60 can also be supported by other structures in existing wing.The spar 64 that a wing chord mid point can also be set supports the hoisting force aggrandizement apparatus.When hoisting force aggrandizement apparatus 40 moved between its first and second position, the spar 64 of wing chord mid point can also longitudinally slide with respect to itself.A suitable common actuator 66 (for example DC machine) can be set at least one spar in the spar 60,64.Be preferably in and all be provided with an actuator 66 on each spar, so that when launching or packing up, reduce constraint.
The hoisting force that acts on the wing tip device with the method for machinery can come counteraction by suitable common frictionless bearing (not shown), this bearing launch with pack up during will guide relevant spar 60,64.In the antagonistic force that direction of inboard bearing generation makes progress, outer bearing just produces an antagonistic force that is directed downwards, these bearing reaction produce a couple, and this couple antagonism is acted at least a portion moment on the end of corresponding wing 22 by hoisting force.
One end of each flexible surface's part 54,56 is fixed on the dividing plate 62, thereby this face component fixed and provides a continuous basically aerodynamic force surface for relevant wing.The other end of each flexible surface's part 54,56 preferably is fixed on fabric and controls on the sub-device, so that regulate the expansion of flexible surface's part and/or pack up.Fabric is controlled sub-device can comprise for example one or several corresponding spool, this scroll binding at the end of hoisting force aggrandizement apparatus in the rectifying device that hoisting force stiffening device 42,44 is provided.The expansion of flexible surface's part/pack up spool can be contained on the axle and can be handled by a suitable common actuator 68 (for example DC machine), and this actuator also can be arranged in the rectifying device that is provided by hoisting force stiffening device 42,44.For example, this actuator 68 can comprise the gear 70 mating gear (see figure 5)s with the end of spool.Therefore, when actuator 68 work, it just can control the expansion of flexible surface's part 54,56 or the speed of packing up.In addition, actuator 68 provides the drg of a machinery, packs up/launch spool so that fix this rotationally, thereby can control the degree that the flexible surface launches.Flexible surface's part is packed up and launched to the reel assembly (see figure 4) that is contained in the outer end of wing wing tip device 40.Specifically, flexible surface's part 54 (see figure 7)s can be packed up on preceding reel assembly 72, and flexible surface's part 56 at rear portion can be packed up on the reel assembly (not shown) of corresponding back.In order to simplify the operation, the top of upper surface spare 54 at corresponding lower surface spare 54 ' can be set.Upper and lower face component 54,54 ' can be when packing up by rolling them around reel assembly 72 simultaneously, and upon deployment by emitting them and side by side launch and pack up from reel assembly 72 simultaneously.
Various actuating devices can be used as the sub-device that spar launches, so that launch wing tip hoisting force aggrandizement apparatus 40 with respect to existing wing.For example, a kind of suitable actuating device can comprise being fixed on the leading edge spar 60 or with this spar and makes common tooth bar 70 (see figure 6)s that single-piece is suitable.Tooth bar 70 and corresponding actuating device 66 (see figure 4) cooperatings are so that realize launching and pack up device 40 with respect to wing by the leading edge spar 60 that is along the longitudinal movement.Another kind of suitable actuating device can be a rotating screw bar and a threaded collar that matches.Herein, screw rod can be fixed on the leading edge spar or on the existing wing structure, the threaded collar that matches can be fixed on the opposing party of leading edge spar or existing wing structure.The screw rod or the axle collar that matches can rotate, thereby the leading edge spar is advanced with respect to existing wing or return.
Though leading edge spar shown in the drawings is a single part, can expect that this leading edge spar also can be a sectioning, wherein short part telescopically is placed in other parts, thereby the whole length of leading edge spar is reduced.In this structure, spar launch sub-device can be between foregoing first and second position telescopically motion leading edge.In addition, leading edge spar telescopically is placed in the compatible sleeve, this sleeve can be installed on the existing aircraft housing construction, thereby has simplified the repacking construction.
For the ease of face component correct on same track, moving when packing up and launch, each flexible surface's part can comprise preceding and rearward projection portion, for example 80,82 (seeing Fig. 6 and 8), the spar 60 of before these juts are placed in respectively and are arranged on and back wing chord mid point, in the corresponding formed channels in 64 (for example 84,86).Specifically, last flexible surface's part 54 has one and is bearing near jut 80 (see figure 6)s at the upper limb place of leading edge spar 60 and another and is bearing in jut 82 (see figure 8)s near the upper limb place of spar 64.Equally, following flexible face component has one and is bearing near the jut 80 ' (see figure 6) of the lower edge of leading edge spar 60 and another and is bearing in jut 82 ' near the lower edge of spar 64.Another flexible surface's part 56,56 ' is in leading edge (along the air flow line of hoisting force aggrandizement apparatus top) rather than have a jut 83,83 ' on trailing edge respectively.The jut 83 of last flexible surface's part 54 is positioned at the upper limb place of spar 64, and the jut 83 ' of flexible surface's part 56 ' then is positioned at the lower edge of spar 64.The trailing edge (see figure 4) of back flexible surface's part 56,56 ' is connected to each other so that in use they are kept together.In some use occasion, preferably can also make these trailing edges be configured as the concave curvature of direction for the downstream, so that Flutter Control or compensation.
These juts 80,80 ', 82,82 ', 83,83 ' and relevant passage are with the bolt rope that uses in aerodone and the corresponding spar passage that is used for laying them is similar.As shown in Figure 7, the end 90 of each passage 84,84 ', 90 ' is made into stream line pattern or smooth shape, thereby, reduced the possibility that flexible surface's part 54,54 ' is caused damage owing to sharp keen edge thus for the edge of flexible element provides a mild inlet.Utilize this structure, flexible surface's part just can be fixedly mounted at least one spar by this way, i.e. air-flow that can held stationary above spar face component border.
Another embodiment of the hoisting force aggrandizement apparatus of this specification sheets is shown in Figure 9.In this embodiment, expanding unit comprises that a spar launches sub-device, and this device can be controlled sub-device when the leading edge spar launches and pack up flexible surface's part at fabric, this leading edge spar pivotally is launched and packs up.For example, in this embodiment, hoisting force aggrandizement apparatus 40 comprises an extensible leading edge spar, and this spar can be around the vertical axis motion passing through pivot 100 in the aircraft body.The leading edge place of this extensible leading edge spar 102 at hoisting force aggrandizement apparatus 40 is set.Wing tip device 104 pivotally is connected with the outer end of leading edge spar 102, and defines the outer end of hoisting force aggrandizement apparatus 40.
For hoisting force is increased, flexible surface's part 106 launches backward from leading edge spar 102.After launching fully, flexible surface's part 106 is also controlled sub-device from fabric and is launched, and this fabric is controlled sub-device can comprise a reel assembly 108, and this reel assembly is fixed on the aircraft body of wing tip device 104 in the end of spar 102.The flexible surface can be made by the relevant above-mentioned same material of the embodiment that installs with the wing tip of hoisting force aggrandizement apparatus.The lifting area that this embodiment of hoisting force aggrandizement apparatus can increase the aircraft body surpasses 100%.In some application scenario, this embodiment of hoisting force aggrandizement apparatus can be whole liftings surface of aircraft body.
(see figure 9) as shown in the figure, the pivot 100 of the size slave wing root portion of flexible surface's part 106 successively decreases gradually to the plate 104 of wing wing tip.Therefore, reel assembly 108 has the wideest part of enough rolled length flexible surface's parts 106, just whole flexible surface's part 106,107 can be packed up.Upper and lower flexible surface's part 106,107 is preferably in trailing edge 150 places and is connected, and perhaps is connected in about 10% length range of the wing chord length in hoisting force aggrandizement apparatus cross section.This cross section that helps flexible surface's part 106,107 that is connected with keeps aerofoil profile, and the possibility of separating between the suction face that helps to reduce the trailing edge place and the pressure surface.
If desired, upper and lower flexible surface's part 106,107 can have one or more stays 152.Can certain at interval distance between the stay 152 along leading edge spar 102.When using, stay 152 helps to strengthen flexible surface's part, and also helps to keep aerofoil profile.As a replacement scheme, can a vertically extending fabric membrane be set at a certain distance along spar 102, so that be used for being adjusted at the interval between up and down flexible surface's part 106,107.These fabric membranes can be the continuous basically cross sections of required aerofoil profile, or separate and be fixed on material strips on upper and lower flexible surface's part 106,107 along chordwise.
For flexible surface's part 106,107 is extended to expanded position, head board 154 (see figure 9)s are fixed on the outer end of two flexible surface's parts 106,107.Head board 154 is with the end of flexible surface's part 106,107 be clamped together securely (Figure 11).In addition, head board 154 comprises a plurality of and is arranged on the linear bearing that reduces to rub 160,162,164,166,168,170,172,174 that bearing track 132,134,136,138 (see figure 10)s on each supporting member 112,114 match.These bearings can make the less Frictional Slipping of generation between head board 154 (seeing Figure 11) and leading edge spar 102.In addition, these bearings are configured in the head board 154 like this, make the longitudinal axis 180 of head board 154 and the wing chord 182 of hoisting force aggrandizement apparatus form a fixed angle.For this reason, wing chord is taken as one by leading edge spar 102 top point and the straight line of the trailing edge of flexible surface's part 106,107.Because this structure, head board 154 has also determined the angle of attack of the wing tip of hoisting force aggrandizement apparatus.
This embodiment of hoisting force aggrandizement apparatus can also move between the primary importance (seeing Figure 12) and the second place.Herein, primary importance is the position (shown in broken lines among the figure) of packing up fully.On the second place, leading edge spar 102 is launched fully, and substantially perpendicular to the axis of reel assembly 108.For this leading edge spar 102 ' is turned to expanded position from the stowed position, can use a hawser and pulley gear.For example, an end of flexible expansion hawser 190 can be fixed on the leading edge spar 102 of inboard of outer end of spar 102.Between this hawser and the outer end that is preferably disposed on pivot 100 and spar 102 being connected of spar near the middle part of distance.Launch hawser 190 through a pulley 192 that is installed on the frame 194, enter then in the frame 194, and twisted on the suitable common Winder (not shown) at this place.When expansion hawser 190 was involved in, leading edge spar 102 just rotated around pivot 100, shifted to the position of launching fully from primary importance.
This expanding unit also comprises a second hawser, i.e. pitching tensioning hawser 200.One end of pitching tensioning hawser 200 is fixed on the head board 154.Then, this pitching tensioning hawser is through a pulley 202 that is contained in the downstream end of wing tip device 104, and is contained in the pulley 204 of the end of leading edge spar 102 through another.Then, pitching tensioning hawser 200 inwardly enters in the frame 194 that wherein is provided with a suitable common hawser wire coiling machine (not shown) by leading edge spar 102 again.
After leading edge spar 102 launched, pitching tensioning hawser 200 just was involved in.At first, head board 154 is clamped on its favorite places.When the tensioning of pitching tensioning hawser, wing tip device 104 just rotates around its pivot 206, moves on to its expanded position (it extends back from leading edge spar 102) herein from favorite places 104 ' (it and leading edge spar 102 longitudinally substantial registration) herein.Best leading edge perpendicular on complete expanded position of the outside face of wing tip device 104 and leading edge spar 102.
The continuation of pitching tensioning hawser 200 is reeled head board 154 outwards will be drawn out along leading edge spar 102, (see figure 9) till flexible surface's part 106,107 launches fully.When head board 154 when leading edge spar 102 moves, linear bearing is just along supporting member 112,114 (seeing Figure 11) motion, and the edge 120,122 of the expansion of flexible surface's part 106,107 longitudinally is drawn out by corresponding slotted hole 116,118.When last tensioning hawser 200, trailing edge 150 (see figure 10)s of flexible surface's part 106,107 are clamped on the leading edge spar 102 with suitable spatial relationship, have obtained the required aerofoil profile in hoisting force aggrandizement apparatus cross section thus.
Flexible surface's part 106,107 can be packed up with driving spool 108 coiling flexible surface parts 106,107 by the tension force that reduces on the hawser 200.In addition, in order to pack up the leading edge spar, when the tension force on acting on hawser 190 reduces, can use aerodynamic drag that this spar is turned round rapidly around its pivot 100.
Those skilled in the art are appreciated that hydraulic actuator can also be used for spar launches sub-device, thereby the leading edge spar can be packed up by power and control setup.
The aircraft body that second embodiment of hoisting force aggrandizement apparatus is used to have short and thick wing or do not have wing is particularly suitable.For example, there is not the helicopter of wing that a hoisting force aggrandizement apparatus among this embodiment that pivotally launches can be installed.Each side of this helicopter can be installed a hoisting force aggrandizement apparatus, and makes favorite places with the leading edge spar fuselage against helicopter.When launching, this hoisting force aggrandizement apparatus just launches to the outer side direction from helicopter body or fuselage.A looking-glass symmetry hoisting force aggrandizement apparatus is arranged on the opposite side of helicopter.These hoisting force aggrandizement apparatus weight are lighter, can be used for improving the low noise work of helicopter.Specifically, when wing launched, helicopter can be worked in a kind of mode of automatic rotation, thereby had reduced the noise from main rotor, and flexible wings provides the operability of similar aerodone simultaneously.In this use occasion, except the blade of main rotor, the hoisting force aggrandizement apparatus provides whole lifting areas of helicopter basically.
Second embodiment of hoisting force aggrandizement apparatus can also be used for a kind of wing installation that can independently install, and this device does not have wing for those and needs the structure of some glide ability or aircraft body to use.The example of this class formation has the lifting entity, air-drop container etc.In these use occasions, the hoisting force aggrandizement apparatus provides whole lifting areas for the aircraft body.
In this use occasion, can use the wing installation 220 of the hoisting force aggrandizement apparatus (seeing Figure 13) that includes a pair of balanced configuration each other.The leading edge spar 102,102 of wing installation 220 as mentioned above " respectively stowed position 102 ' between and rotate between 102 .The expansion of flexible surface's part 106,106 ' can link.For example, reel assembly 108,108 ' can have intermeshed gear 210,212 respectively, so that guarantee that the expansion and the tensioning of wing installation 220 both sides are symmetrical.If this use occasion needs the hoisting force aggrandizement apparatus of wing installation 220 to have the swept-back shape, this shape can be passed through reel assembly 108, angle configurations between 108 ' the axis becomes the twice at leading edge spar 102,102 ' the required sweepback angle and realizes easily.
For leading edge spar 102,102 ' is bearing in the shoulder wing position, each hoisting force aggrandizement apparatus has a vertical struts 222,224 that relevant pivot 100,100 ' is housed on it.In addition, spar cramp bar 230,232 can be set extends between the root of relevant leading edge spar 102,102 ' and bar 230,232.By means of this configuration, spar 102,102 ' just is forced in motion in the aircraft body (pivotal axis and it perpendicular).
Referring to Figure 15, the air-drop container 250 shown in the figure has the shape of rectangular prism.But any other suitable common shape also can consider, and is for example cylindrical, has semicircle, trapezoidal or triangular-section prismatic etc.If desired, a rectifying device can be fixed on the front end of container 250.Equally, if desired, a rectifying device or direction control structure 252 can be fixed on the rear end of container 250, so that the stabilising surface of vertical and level is provided.
In order when dropping, to increase the cross track distance of this container, flexible wings hoisting force aggrandizement apparatus 220 can be fixed on the top of container 250.To a certain extent, wing installation 220 can be transformed into container 250 glide vehicle.When container began to throw in, the hoisting force aggrandizement apparatus just was stowed in the gondola 254 and by remote control equipment (RCE) and is deployed into shown position.
Spar cramp bar 230,232 with respect to container 250 along side direction and longitudinal supporting wing 220.For this reason, be provided with several suitable cramp bars and lift arm, some cramp bars wherein and lift arm can be placed in the rectifying device of gondola 254 and vertical extent part thereof.These cramp bars and lift arm can also be used to adjusting the height of the preceding and trailing portion of gondola 254, thereby also can control and/or adjust the angle of attack of wing 220.
Hoisting force aggrandizement apparatus of the present invention provides some great advantages.For example, verified to the test of this hoisting force aggrandizement apparatus, in some use occasion, can obtain the great minimizing (about 40%) of ground taxi distance, takeoff speed has also obtained tangible reduction (about 32%).Flight simulation test also shows not have 50 feet needed take off distances of obstacle and also can reduce (about 40%) significantly.The landing data of this hoisting force aggrandizement apparatus also will be improved some rice compared with flying performance.
The identical controlled descent performance of hoisting force aggrandizement apparatus of installing at the gondola inner top makes it become one to be used for that the space enters again or the competitive candidate of para-cargo operation application facet.The hoisting force aggrandizement apparatus that gondola is installed provides a kind of small-sized, compact device of handling and transporting be convenient to, and provides and promote and the wing area of autonomous landing control, so that accurately throw on the target location.
Other advantages of " wing tip hoisting force aggrandizement apparatus " comprise the great gain that is implemented in the span and aspect ratio aspect, have improved the proportionate relationship of hoisting force to resistance thus effectively.In collapsed state, wing tip hoisting force aggrandizement apparatus provides the section of a short and low aspect ratio and low resistance, and this section makes an aircraft body forming that is used to quicken.On the contrary, when launching, the expansion of wing has increased aspect ratio, thereby makes big hoisting force and low-speed operations optimization under " cruising " state.This expansion structure is favourable for operation of dash road and long-term sustained use.Importantly, for cruise and the high-speed flight running state between transition condition or long-term low speed cruising ability, what this wing tip hoisting force aggrandizement apparatus provided In-Flight Deployment under the situation of depowering may.
Other advantages of this hoisting force aggrandizement apparatus are that this device does not rely on aircraft body platform, and the speed when stowed configuration is greater than the speed of rotor craft body.Aspect military use, this hoisting force aggrandizement apparatus also has near the noiseless running advantage of (it has the tactics potentiality of association).
Obviously, a kind of later-model hoisting force aggrandizement apparatus described above.In addition, it is apparent that for those skilled in the art that various features of the present invention all exist many remodeling, change, substitute and equivalent.Therefore, clearly, all these remodeling change, and substitute and equivalent all belongs within the principle and scope of the present invention by defined in the accompanying Claim book, also all are included in the present invention thus.
Claims (40)
1. hoisting force aggrandizement apparatus that uses for the aircraft body comprises:
One has the extensible wing structure that increases area;
An extensible leading edge supporting member;
A pair of flexible face component, one of them flexible surface's part limit a suction face of this wing structure, and another flexible surface's part limits a pressure surface of this wing structure, and this flexible surface's part is installed on this leading edge supporting member; And
An expanding unit, this device are used for launching and pack up this leading edge supporting member and this flexible surface's part, so that change this increase area.
2. the described hoisting force aggrandizement apparatus of claim 1 is characterized in that, this flexible surface's part is made up of a kind of composite material with carbon fiber reinforcement.
3. the described hoisting force aggrandizement apparatus of claim 1 is characterized in that, this flexible surface's part is made up of a kind of fabric substrate material.
4. the described hoisting force aggrandizement apparatus of claim 3 is characterized in that, also comprises carbon fiber stiffener composition.
5. the described hoisting force aggrandizement apparatus of claim 1 is characterized in that, this flexible surface's part is made up of a kind of synthetic polymer sheet.
6. the described hoisting force aggrandizement apparatus of claim 1 is characterized in that, this flexible surface's part is made up of a kind of composite material, and this composite material comprises cloth fabric that has carbon fiber and the superficial layer with lamination.
7. the described hoisting force aggrandizement apparatus of claim 1 is characterized in that, at least one the flexible surface's part in this flexible surface's part comprises several stays.
8. the described hoisting force aggrandizement apparatus of claim 1 is characterized in that, this expanding unit comprises that a spar that is used for launching and pack up this leading edge supporting member launches sub-device.
9. the described hoisting force aggrandizement apparatus of claim 1 is characterized in that, this expanding unit comprises that a fabric that is used for launching and pack up this flexible surface's part controls sub-device.
10. the described hoisting force aggrandizement apparatus of claim 9 is characterized in that, this fabric is controlled sub-device and comprised the spool that is wound with this flexible surface's part at least one its.
11. the described hoisting force aggrandizement apparatus of claim 9 is characterized in that, this fabric is controlled sub-device and is comprised a plurality of spools that are wound with this flexible surface's part on it.
12. the described hoisting force aggrandizement apparatus of claim 9 is characterized in that this fabric is controlled the slide plate that sub-device comprises that this flexible surface's part is fixed thereon.
13. the described hoisting force aggrandizement apparatus of claim 9 is characterized in that, this fabric is controlled sub-device and is comprised a rack-and-pinion mechanism.
14. the described hoisting force aggrandizement apparatus of claim 9 is characterized in that, this fabric is controlled sub-device and is comprised a screw rod mechanism.
15. the described hoisting force aggrandizement apparatus of claim 9 is characterized in that, this fabric is controlled sub-device and is comprised a hawser and pulley gear.
16. the described hoisting force aggrandizement apparatus of claim 1, it is characterized in that, this leading edge supporting member and this flexible surface's part cooperation define a wing section, and the direction that launch along fabric in this wing section passes through and has a unmodified wing chord length basically.
17. the described hoisting force aggrandizement apparatus of claim 8 is characterized in that, this spar launches sub-device and make this leading edge supporting member telescopically motion between first and second position.
18. the described hoisting force aggrandizement apparatus of claim 8 is characterized in that, this spar launches sub-device and make this leading edge supporting member telescopically motion between a complete stowed position and the second place.
19. the described hoisting force aggrandizement apparatus of claim 8 is characterized in that, this spar launches sub-device and make this leading edge supporting member telescopically motion between a complete stowed position and a complete expanded position.
20. the described hoisting force aggrandizement apparatus of claim 8 is characterized in that, this spar launches sub-device makes this leading edge supporting member pivotally move between first and second position.
21. the described hoisting force aggrandizement apparatus of claim 8 is characterized in that, this spar launches sub-device makes this leading edge supporting member pivotally move between a complete stowed position and the second place.
22. the described hoisting force aggrandizement apparatus of claim 8 is characterized in that, this spar launches sub-device pivotally moves this leading edge supporting member between a complete stowed position and complete expanded position.
23. the described hoisting force aggrandizement apparatus of claim 1 is characterized in that this leading edge supporting member comprises at least one guide rail, this guide rail is equipped with an edge of at least one the flexible surface's part in this flexible surface's part.
24. the aircraft body with a hoisting force aggrandizement apparatus comprises:
Fixed wing with a leading edge and a nominal area;
One is arranged on the exterior extensible wing structure of this fixed wing, and this wing structure has the same big increase area with this nominal area;
An extensible leading edge supporting member, this supporting member is arranged essentially parallel to the leading edge setting of this fixed wing;
A pair of flexible face component, one of them flexible surface's part limit a suction face of this wing structure, and another flexible surface's part limits a pressure surface of this wing structure, and this flexible surface's part is installed on this leading edge supporting member; And
The expanding unit of a partial fixing on this fixed wing, this device are used for launching and pack up this leading edge supporting member and this flexible surface's part, so that change this increase area.
25. the described aircraft body with a hoisting force aggrandizement apparatus of claim 24 is characterized in that, this increases area in about scope of 15% to 35% of this nominal area.
26. the described aircraft body with a hoisting force aggrandizement apparatus of claim 24 is characterized in that the leading edge of this fixed wing has a section shape, and it is characterized in that, this leading edge supporting member has an identical section shape.
27. the described aircraft body of claim 24, it is characterized in that, this fixed wing has a suction face, this suction face has a fixing section shape, and it is characterized in that at least a portion of flexible surface's part in flexible surface's part has a section shape identical with the section shape of this fixed wing.
28. the described aircraft body of claim 24 is characterized in that this fixed wing has a trailing edge, and it is characterized in that, this flexible surface's part has a trailing edge that parallels with this leading edge basically.
29. the described aircraft body of claim 24 also comprises one second fixed wing, and it is characterized in that each fixed wing comprises:
An exterior extensible wing structure that is arranged on corresponding fixed wing, this wing structure have the same big increase area with this nominal area;
An extensible leading edge supporting member, this supporting member is arranged essentially parallel to the leading edge setting of this corresponding fixed wing;
A pair of flexible face component, one of them flexible surface's part limit a suction face of this wing structure, and another flexible surface's part limits a pressure surface of this wing structure, and this flexible surface's part is installed on this leading edge supporting member; And
The expanding unit of a partial fixing on this fixed wing, this device are used for launching and pack up this leading edge supporting member and this flexible surface's part, so that change this increase area.
30. the described aircraft body of claim 24 comprises a propelling unit.
31. the described aircraft body of claim 30 is characterized in that this propelling unit comprises a jet engine.
32. the described aircraft body of claim 30 is characterized in that this propelling unit comprises a propeller driving device.
33. the described aircraft body of claim 32 is characterized in that this propelling unit comprises the propeller driving device of a push type.
34. the described aircraft body of claim 30 is characterized in that this propelling unit comprises a diesel motor.
35. the described aircraft body of claim 30 is characterized in that this propelling unit comprises a rotary engine.
36. the described aircraft body of claim 30 is characterized in that this propelling unit comprises a ducted fan engine.
37. the described aircraft body of claim 30 is characterized in that this propelling unit comprises a Sabath'e-cycle engine.
38. the described aircraft body of claim 30 is characterized in that this aircraft body is remote operated.
39. the described aircraft body of claim 30 is characterized in that, this propelling unit comprises an anterior driving engine of installing and the driving engine that install at the rear portion.
40. the described aircraft body of claim 39 is characterized in that, the driving engine that install this front portion is a piston engine, and the driving engine that install at this rear portion is a gas turbine engine.
Applications Claiming Priority (7)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US55997004P | 2004-04-07 | 2004-04-07 | |
| US60/559,971 | 2004-04-07 | ||
| US60/559,972 | 2004-04-07 | ||
| US60/559,970 | 2004-04-07 | ||
| US60/560,962 | 2004-04-12 | ||
| US60/575,028 | 2004-05-28 | ||
| US60/616,408 | 2004-10-07 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101065291A true CN101065291A (en) | 2007-10-31 |
Family
ID=38965665
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200580016913 Pending CN101065291A (en) | 2004-04-07 | 2005-04-07 | Lift augmentation system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101065291A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102865993A (en) * | 2012-09-24 | 2013-01-09 | 西北工业大学 | Recyclable airplane model experimental facility capable of changing appearance and parameter |
| CN102975851A (en) * | 2012-07-17 | 2013-03-20 | 江闻杰 | Multifunction wing tip turbine engine having fore-lying impellers |
| US9033282B2 (en) | 2010-07-14 | 2015-05-19 | Airbus Operations Limited | Wing tip device |
| CN108423176A (en) * | 2018-04-18 | 2018-08-21 | 南方科技大学 | A kind of modularization fixed-wing unmanned plane |
| CN109153440A (en) * | 2016-07-06 | 2019-01-04 | 空中客车德国运营有限责任公司 | Aircraft with the wing elements for reducing load |
| CN112124589A (en) * | 2020-10-14 | 2020-12-25 | 李勇霖 | Two rotor vector unmanned aerial vehicle that verts |
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2005
- 2005-04-07 CN CN 200580016913 patent/CN101065291A/en active Pending
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9199727B2 (en) | 2010-07-14 | 2015-12-01 | Airbus Operations Limited | Wing tip device |
| US9033282B2 (en) | 2010-07-14 | 2015-05-19 | Airbus Operations Limited | Wing tip device |
| US9193445B2 (en) | 2010-07-14 | 2015-11-24 | Airbus Operations Limited | Wing tip device |
| US11851164B2 (en) | 2010-07-14 | 2023-12-26 | Airbus Operations Limited | Wing tip device |
| CN102975851A (en) * | 2012-07-17 | 2013-03-20 | 江闻杰 | Multifunction wing tip turbine engine having fore-lying impellers |
| CN102975851B (en) * | 2012-07-17 | 2015-11-25 | 江闻杰 | The high-mobility, multipurpose, wheeled vehicle wing-tip vortex turbine that a kind of impeller is preposition |
| CN102865993B (en) * | 2012-09-24 | 2014-10-15 | 西北工业大学 | Recyclable airplane model experimental facility capable of changing appearance and parameter |
| CN102865993A (en) * | 2012-09-24 | 2013-01-09 | 西北工业大学 | Recyclable airplane model experimental facility capable of changing appearance and parameter |
| CN109153440A (en) * | 2016-07-06 | 2019-01-04 | 空中客车德国运营有限责任公司 | Aircraft with the wing elements for reducing load |
| CN108423176A (en) * | 2018-04-18 | 2018-08-21 | 南方科技大学 | A kind of modularization fixed-wing unmanned plane |
| CN108423176B (en) * | 2018-04-18 | 2024-02-27 | 南方科技大学 | Modularized fixed wing unmanned aerial vehicle |
| CN112124589A (en) * | 2020-10-14 | 2020-12-25 | 李勇霖 | Two rotor vector unmanned aerial vehicle that verts |
| CN112124589B (en) * | 2020-10-14 | 2022-01-25 | 李勇霖 | Two rotor vector unmanned aerial vehicle that verts |
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