CN207060405U - The more flapping flight devices of lap siding and flapping-wing aircraft - Google Patents

Abstract

Vehicle technology field is the utility model is related to, more particularly, to a kind of more flapping flight devices of lap siding and flapping-wing aircraft.The more flapping flight devices of the lap siding include aircraft ring frames, driving mechanism for flapping wing and multiple wing groups of fluttering, and the direction interval of multiple rear ends of front end of the wing group along aircraft ring frames to aircraft ring frames of fluttering is laid；Wing group of fluttering includes two flapping-wing aircraft wings being arranged symmetrically；Driving mechanism for flapping wing is used to make flapping-wing aircraft wing be fluttered；Flapping-wing aircraft wing includes flapping wing covering of the fan, and flapping wing covering of the fan includes end truss, support bar and covering, and the quantity of support bar is more, and more support bars are fixed on the truss of end, and more support bars are used to support fixed covering.The more flapping flight devices of lap siding that the flapping-wing aircraft includes.The utility model adds the thrust of flapping-wing aircraft, is advantageous to increase the flying quality of flapping-wing aircraft.

Description

The more flapping flight devices of lap siding and flapping-wing aircraft

Technical field

Vehicle technology field is the utility model is related to, more particularly, to a kind of more flapping flight devices of lap siding and flapping wing Machine.

Background technology

Flapping-wing aircraft is also known as ornithopter, refers to the aviation for overweighting air that wing can flutter up and down as bird and insect wing Device, the wing fluttered not only produce lift, also produce motive force forward.Modern flapping wing aircraft is divided into imitative bird from principle and flutterred The wing and imitative insect flapping wing, based on the unmanned flapping wing of microminiature.The frequency of fluttering of imitative bird flapping wing is low, and wing area is big, and similar birds fly OK, manufacture is relatively easy；Imitative insect flapping wing is fluttered, and frequency is high, and wing area is small, and manufacture difficulty is high, but can easily realize outstanding Stop.Bionic ornithopter has having great advantage in military and civilian, turns into the focus of development.But existing flapping-wing aircraft is adopted Flapping-wing aircraft wing is that its caused thrust is smaller, limits the flying quality of flapping-wing aircraft.

Utility model content

The purpose of this utility model is to provide a kind of more flapping flight devices of lap siding and flapping-wing aircraft, existing to solve Have that thrust caused by used flapping-wing aircraft wing present in technology is smaller, and the technology for limiting the flying quality of flapping-wing aircraft is asked Topic.

The utility model provides a kind of more flapping flight devices of lap siding, including aircraft ring frames, driving mechanism for flapping wing and Multiple wing groups of fluttering, between the direction of multiple rear ends of front end of the wing machine along the aircraft ring frames to the aircraft ring frames of fluttering Every laying；The wing group of fluttering includes two flapping-wing aircraft wings being arranged symmetrically；The driving mechanism for flapping wing is described for making Flapping-wing aircraft wing is fluttered；The flapping-wing aircraft wing includes flapping wing covering of the fan, and the flapping wing covering of the fan includes end truss, support bar And covering, the quantity of the support bar is more, and the more support bars are fixed on the end truss, and the more branch Strut is used to support the fixed covering.

The utility model additionally provides a kind of flapping-wing aircraft, including the more flapping flight devices of described lap siding.

Compared with prior art, the beneficial effects of the utility model are：

After the utility model on the wing-body of flapping-wing aircraft wing by increasing flapping wing covering of the fan, it can moderately increase flapping wing The flexibility of machine wing；In addition, being postponed by cloth that two adjacent support bars misplace up and down, covering just can be made perpendicular to branch Being shaped as the section of the axis of strut is in shape of taking out stitches, and can so play guide functions, and in flapping-wing aircraft wing motion, It can make the exhibition of gas to flowing by rectification, air-flow is guided into the rear of flapping-wing aircraft wing, flapping-wing aircraft wing is pushed away toward rear Tolerance becomes big, therefore adds the thrust of flapping-wing aircraft, is advantageous to increase the flying quality of flapping-wing aircraft.

Brief description of the drawings

, below will be right in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art The required accompanying drawing used is briefly described in embodiment or description of the prior art, it should be apparent that, describe below In accompanying drawing be some embodiments of the present utility model, for those of ordinary skill in the art, do not paying creativeness On the premise of work, other accompanying drawings can also be obtained according to these accompanying drawings.

Fig. 1 is the structural representation for the aircraft ring frames that the utility model embodiment one provides；

Fig. 2 is Fig. 1 side view；

Fig. 3 is Fig. 2 top view；

Fig. 4 is the dimensional structure diagram for the aircraft ring frames that the utility model embodiment one provides；

Fig. 5 is the partial enlarged drawing at A in Fig. 4；

Fig. 6 is the structural representation for the flapping wing covering of the fan that the utility model embodiment one provides；

Fig. 7 is the front view for the flapping wing covering of the fan that the utility model embodiment one provides；

Fig. 8 is the top view for the flapping wing covering of the fan that the utility model embodiment one provides；

Fig. 9 is the close-up schematic view at B in Fig. 8；

Figure 10 is the structural representation of support bar in the utility model embodiment one；

Figure 11 is the structural representation of the flapping-wing aircraft wing provided in the utility model embodiment one；

Figure 12 is the close-up schematic view at K in Figure 11；

Figure 13 is structural representation of the driving mechanism for flapping wing at the first visual angle of the offer of the utility model embodiment one；

Figure 14 is the close-up schematic view at L in Figure 13；

Figure 15 is structural representation of the driving mechanism for flapping wing at the second visual angle of the offer of the utility model embodiment one；

Figure 16 is the partial enlarged drawing at C in Figure 15；

Figure 17 is structural representation of the driving mechanism for flapping wing at the 3rd visual angle of the offer of the utility model embodiment one；

Figure 18 is the partial enlarged drawing at D in Figure 17；

Figure 19 is the structural representation for the flapping-wing aircraft fixed-wing that the utility model embodiment two provides；

Figure 20 does not install structural representation during fixed-wing covering for flapping-wing aircraft fixed-wing in the utility model embodiment two；

Figure 21 is the close-up schematic view at E in Figure 20；

Figure 22 is the close-up schematic view at F in Figure 20；

Figure 23 is the close-up schematic view at G in Figure 20；

Figure 24 is the structural representation of rib in the utility model embodiment two；

Figure 25 is the schematic diagram at another visual angle of rib in the utility model embodiment two；

Figure 26 is the structural representation of the flapping-wing aircraft provided in the utility model embodiment two.

Figure 27 is the close-up schematic view at H in Figure 26；

Figure 28 is the structural representation for the flapping-wing aircraft empennage that the utility model embodiment two provides；

Figure 29 is the schematic diagram at another visual angle for the flapping-wing aircraft empennage that the utility model embodiment two provides；

Figure 30 is the schematic diagram at the another visual angle for the flapping-wing aircraft empennage that the utility model embodiment two provides；

Figure 31 is the structural representation (elevator covering is not shown) of elevator in the utility model embodiment two；

Figure 32 is the structural representation at another visual angle of elevator in the utility model embodiment two；

Figure 33 is the close-up schematic view at I in Figure 32；

Figure 34 is the structural representation (stabilization covering is not shown) of horizontal stabilizer in the utility model embodiment two；

Figure 35 is the close-up schematic view at J in Figure 34；

Figure 36 is the structural representation of stabilization rib in the utility model embodiment two；

Figure 37 is the schematic diagram at another visual angle of stabilization rib in the utility model embodiment two；

Figure 38 is the axonometric drawing of flapping-wing aircraft in the utility model embodiment two；

Figure 39 is flapping-wing aircraft front view in the utility model embodiment two；

Figure 40 is flapping-wing aircraft top view in the utility model embodiment two；

Figure 41 is the structure that flapping wing power set are connected with multiple driving mechanism for flapping wing in the utility model embodiment one Schematic diagram；

Figure 42 is the structural representation of the more flapping flight devices of lap siding in the utility model embodiment one.

In figure：100- flapping wing power set；110- bottoms support frame；120- top supporting frames；130- side stand components；131- First side stand component；The side stand components of 132- second；The side stand components of 133- the 3rd；140- rib support frames；200- bearings；201- heads Framework；202- head fix bars；203- handpiece support bars；204- tail frameworks；205- tail links；206- wing frameworks； 207- blowing devices；208- blower fan support bars；210- fixed seats；220- support bases；The transmission mechanisms of 300- first；301- ends purlin Frame；302- support bars；303- coverings；304- ribs；The stringers of 305- first；The stringers of 306- second；The stringers of 307- the 3rd；308- Four stringers；The stringers of 309- the 5th；310- driving wheels；320- driven pulleys；330- driving members；The transmission mechanisms of 400- second；401- consolidates Determine wing covering；402- spars；403- ribs；The upper edge strips of 404-；Edge strip under 405-；406- inclined struts；407- leading edge supporting members； 408- leading edge arc tips；The stable necks of 409-；410- link rod parts；The kinematic links of 411- first；The kinematic links of 412- second；415- Rear edge support component；416- stringers；420- connecting portions；421- sliding shoes；422- contiguous blocks；500- flapping-wing aircraft wings；501- machines Wing body；510- wing links；The wings of 520- first divide framework；The wings of 530- second divide framework；600- limiting sections；601- water Flat stabilization；602- vertical tails；603- elevators；604- stabilization spars；605- stabilization ribs；606- stabilizations are grown Purlin；Edge strip on 607- stabilizations；Edge strip under 608- stabilizations；The oblique pillars of 609-；610- stopper slots；611- elevator spars； 612- elevator ribs；613- motors；614- first connecting rods；615- second connecting rods；616- empennage frameworks；The horizontal tails of 617- The wing；618- straight struts；Edge strip among 619- stabilizations；620- blower fan set casings；630- blower fan apparatus；700- aircraft ring frames； 701- fuselage rings；702- shaft couplings；703- hinge axis；704- flapping-wing aircrafts wing, 705- flapping-wing aircrafts fixed-wing, 706- flapping wing tails The wing；707- the 1st is fluttered wing group；709- the 3rd is fluttered wing group.

Embodiment

The technical solution of the utility model is clearly and completely described below in conjunction with accompanying drawing, it is clear that described Embodiment is the utility model part of the embodiment, rather than whole embodiments., it is necessary to say in description of the present utility model It is bright, term " " center ", " on ", " under ", "left", "right", " vertical ", " level ", " interior ", the orientation or position of the instruction such as " outer " It is based on orientation shown in the drawings or position relationship to put relation, is for only for ease of description the utility model and simplifies description, and It is not instruction or implies signified device or element there must be specific orientation, with specific azimuth configuration and operation, therefore It is not intended that to limitation of the present utility model.In addition, term " first ", " second ", " the 3rd " are only used for describing purpose, without It is understood that to indicate or implying relative importance., it is necessary to illustrate, unless otherwise clear and definite in description of the present utility model Regulation and limit, term " installation ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or It is detachably connected, or is integrally connected；Can mechanically connect or be joined directly together, can also be by between intermediary Connect connected, can be the connection of two element internals.For the ordinary skill in the art, can be understood with concrete condition Concrete meaning of the above-mentioned term in the utility model.

Embodiment one

Referring to shown in Figure 41 to Figure 42, the utility model embodiment provides a kind of more flapping flight devices of lap siding, bag Include aircraft ring frames, driving mechanism for flapping wing and multiple wing groups of fluttering；Multiple front ends of the wing group along aircraft ring frames of fluttering are to aircraft Lay at the direction interval of the rear end of framework；Wing group of fluttering includes two flapping-wing aircraft wings 704 being arranged symmetrically, that is to say, that Axisymmetrical of two flapping-wing aircraft wings 704 on the length direction of aircraft ring frames in each wing group of fluttering.It is two neighboring Spacing between wing group of fluttering is equal.

It refer to shown in Fig. 1 and Fig. 2；In the present embodiment, aircraft ring frames include fuselage ring 701, machine head frame 201, machine Tail framework 204, tail link 205, wing framework 206 and blowing device 207；The machine head frame 201 and fuselage ring 701 Anterior connection；Machine head frame 201 is supporting head；The afterbody of the tail link 205 and the fuselage ring 701 connects Connect；Tail framework 204 is connected with tail link 205, and tail framework 204 is supporting flapping-wing aircraft empennage；Positioned at fuselage frame The both sides of frame 701 are connected to wing framework 206, and wing framework 206 is installing flapping-wing aircraft wing；Blowing device 207 is set Put in the machine head frame 201, blowing device 207 can provide the air-flow motive force towards the lower section of machine head frame 201.Flapping wing Machine fixed-wing is installed on the top of fuselage ring, and flapping-wing aircraft fixed-wing is close to the front portion of fuselage ring；Driving mechanism for flapping wing is used Fluttered in making flapping-wing aircraft wing.

Aircraft ring frames provided by the utility model, it is divided into fuselage ring 701, machine head frame 201, tail framework 204 and machine Wing framework 206；Wherein, each framework can be individually processed, and transported and assembled, because each part can individually add Frock is matched somebody with somebody so that the overall assembling of flapping-wing aircraft is relatively simple and conveniently.

Meanwhile blowing device 207 is set in machine head frame 201, blowing device 207 can be provided towards machine head frame The air-flow motive force of 201 lower sections.In aircraft landing, blowing device 200 starts running, and the heading of flapping-wing aircraft is leaned forward, The part of the close tail of fuselage ring is first landed, and then gradually contacted by tail direction to heading with ground, ensured The stationarity and security of flapping-wing aircraft landing.In addition, in ornithopter flight, because blowing device 207 can be provided towards machine The air-flow motive force of the lower section of head framework 201, therefore, it can play a part of providing auxiliary lifting.

It refer to shown in Fig. 5, as a preferred embodiment of the present utility model, the blowing device 207 includes wind Machine support bar 208, blower fan set casing 620 and blower fan apparatus 630, blower fan support bar 208 are connected with machine head frame 201, the wind The both ends of machine support bar 208 connect the blower fan set casing 620 respectively, and the blower fan apparatus 630 is fixed installed in the blower fan In shell 620, the blower fan apparatus 630 can be provided towards the lower section air-flow motive force of machine head frame 201, to ensure the flapping-wing aircraft During landing, the position of the close tail of the fuselage ring is first landed.

As a preferred embodiment of the present utility model, the both ends of the blower fan set casing 620 are respectively arranged with For accommodating the spill mouth of blower fan apparatus 630.During concrete application, blower fan set casing 620 is with blower fan support frame 610 using detachable Connected mode, there is the characteristics of being conveniently replaceable, the spill mouth at the both ends of blower fan set casing 620 can respectively install a blower fan apparatus 630, play a part of lifting air-flow motive force.

As a preferred embodiment of the present utility model, the blower fan apparatus uses electric ducted fan.Duct wind The isolated fan of the more same diameter of fan can produce bigger lift, and fan ring is included in duct, can both stop that fan is pneumatic Sound is outwards propagated, and compact-sized, safe.

It refer to shown in Fig. 1-Fig. 4, as a preferred embodiment of the present utility model, the fuselage ring 701 wraps Bottom support frame 110, top supporting frame 120 and side stand component 130 are included, top supporting frame 120 is located on bottom support frame 110 Side, side stand component 130 set two, and top supporting frame 120 and the both sides of bottom support frame 110 are respectively arranged a side stand component 130, and the side stand component 130 is connected with top supporting frame 120 and bottom support frame 110 respectively.

As a preferred embodiment of the present utility model, what the bottom support frame 110 be arranged in parallel including two Sub-stent, similarly, top supporting frame 120 also include two sub-stents be arrangeding in parallel, also, form bottom support frame 110 Two sub-stents and composition top supporting frame 120 Liang Gen branches support between parallel setting.

It refer to shown in Fig. 2-Fig. 4, as a preferred embodiment of the present utility model, the side stand component 130 is in Triangular structure, triangular structure have the characteristics of stabilized structure, using the teaching of the invention it is possible to provide stable support.When it is implemented, collateral support Frame 130 sets two, respectively positioned at bottom support frame 110 and the both sides of top supporting frame 120.The side stand component 130 includes the One side stand component 131, the second side stand component 132 and the 3rd side stand component 133, wherein, the first side stand component 131 is located remotely from institute The position of bottom support frame 110 and top supporting frame 120 is stated, the one end of the second side stand component 132 connects with the first side stand component 131 Connect, the other end of the second side stand component 132 is connected with the sub-stent in top supporting frame 120.3rd side stand component 133 and first Side stand component 131 connects, and the other end of the 3rd side stand component 133 is connected with the sub-stent in bottom support frame 110.First is collateral Support 131, the second side stand component 132 and the 3rd side stand component 133 can form gusseted, make structure more firm.

In addition, in the present embodiment, the second side stand component 132 and the 3rd side stand component 133 be provided with it is multiple, multiple second The side stand component 133 of side stand component 132 and the 3rd extends along fuselage length direction, and sets at equal intervals, and then is grown in fuselage Spend direction and even support power is provided.

As a preferred embodiment of the present utility model, the sub-stent of two top supporting frames 120 is smaller than two The sub-stent spacing of individual bottom support frame 110.In addition, also including rib support frame 140, more rib support frames 140 are arranged on top Between support frame 120 and bottom support frame 110, two bottom support frames 110 are smaller than due to two top supporting frames 120 Spacing, the rib support frame 140, top supporting frame 120 and bottom support frame 110 can form triangular structure, strengthen wall The support strength of cloth support frame and bottom support frame 110.Meanwhile more rib support frames 140 are also disposed at two bottom links Sub-stent between, and two top link sub-stent between；Equally play increase by two bottom links and two The effect of individual top link bonding strength.In the present embodiment, it is contemplated that between the sub-stent of two top supporting frames 120 Away from smaller, can also be increased using devices such as some fasteners or locking members between the sub-stent of two top supporting frames 120 Intensity.

Multiple rib support frames 140 are along top supporting frame 120 and length direction (the i.e. fuselage length of bottom support frame 110 Direction) it is uniformly arranged, and then provide uniform support strength to top supporting frame 120 and bottom support frame 110.

As a preferred embodiment of the present utility model, the machine head frame 201 includes tapered structure, and it has Point and connecting portion, the connecting portion are connected with the fuselage ring 701.Machine head frame 201 is arranged to pyramidal structure, more Using water conservancy diversion, reduce air drag in flight course.

More specifically, the machine head frame 201 includes head fix bar 202, the quantity of head fix bar 202 is preferably provided with 5 Root, one end of 5 head fix bars 202 link together, and the other end of 5 head fix bars 202 respectively self-deploys, with respective phase The sub-stent of corresponding top supporting frame 120, the sub-stent of bottom support frame 110 and side stand component 130 are connected, Jin Ercheng Pyramidal structure.

In addition, in order to increase the support strength of each head fix bar 202, the machine head frame 201 also includes more heads Support bar 203, more handpiece support bars 203 are arranged between each head fix bar, and the support of increase head fix bar 202 is strong Degree.

As a preferred embodiment of the present utility model, wing framework 206 sets two, the wing framework 206 Structure triangular in shape, the wing framework 206 connect the side stand component 130 positioned at the same side in the fuselage ring 701 respectively With top supporting frame 120.Triangular structure has the characteristics of stabilized structure, using the teaching of the invention it is possible to provide stable support.

As a preferred embodiment of the present utility model, the wing framework 206 include wing link 510 and First wing divides the wing of framework 520 and second to divide framework 530, and the first wing divides the wing of framework 520 and second to divide framework 530 to distinguish Set it is multiple, also, multiple first wings divide the wing of framework 520 and second divide framework 530 using be arranged at intervals.

Wing link 510 is located at the side of bottom support frame 110 and top supporting frame 120, wing link 510 and bottom Portion's support frame 110 and top supporting frame 120 are parallel, and, the height of wing link 510 is higher than the height of top supporting frame 120 Degree.Wherein, first wing divides the both ends of framework 520 to connect wing link 510 and side stand component 130 respectively, specifically connects The first side stand component 131 to pick in wing link 510 and side stand component 130.Second wing divides the both ends of framework 530 point The wing link 510 and top supporting frame 120 are not connected.Specifically connect wing link 510 and top supporting frame Sub-stent in 120.After installation, the wing of wing link 510 and first divides the wing of framework 520 and second to divide framework 530 form triangular support structure, and the structural stability is strong, and stable support can be provided for fixed-wing.

In addition, in the present embodiment, multiple first wings divide the wing of framework 520 and second to divide framework 530 along fuselage length Direction extends, and sets at equal intervals, and then provides even support power in fuselage length direction.

As a preferred embodiment of the present utility model, tail link 205 sets two, respectively with the fuselage The afterbody connection of framework 701；Specifically two tail links 205 respectively with two sub-stent phases in bottom support frame 110 Connection, tail framework 204 set two, are connected respectively with two tail links 205, tail framework 204 is flutterred to support The wing tail wing.

In flapping flight framework provided by the utility model, wherein, it will integrally be split as fuselage ring 701, machine head frame 201st, tail framework 204, tail link 205 and the part of wing framework more than 206, each several part can individually produce assembling, finally Assembly shop is transported to again and carries out overall package, welding manner can be used to connect between each framework and link, can also one A little connectors are detachably connected, wherein, each framework can be individually processed, and transported and assembled, due to each composition Part can independent process and assemble so that the overall assembling of flapping-wing aircraft is relatively simple and conveniently.

In addition, fuselage ring 701 is using bottom support frame 110, top supporting frame 120 is connected with side stand component 130 and Into；

Machine head frame 201 is connected using head fix bar 202 and handpiece support bar 203 to be formed；

Wing framework 206 divides framework 520 to divide framework 530 to be connected with the second wing using wing link 510, the first wing Connect and form；

, weight big the problem of complex compared to airframe structure in the prior art, this several part is adopted in the utility model Structure is simple, and support strength is high, in light weight, and then reduces the weight of flapping-wing aircraft.

In the embodiment, flapping-wing aircraft wing includes wing-body 501 and flapping wing covering of the fan.Referring to shown in Fig. 6 to Figure 12, flapping wing Covering of the fan includes end truss 301, support bar 302 and covering 303, and the quantity of support bar 302 is more, and more support bars 302 are solid Due on end truss 301, and more support bars 302 are used to support fixed covering 303；More support bars 302 are along end truss 301 length direction parallel interval distribution, and in the short transverse of end truss 301, adjacent two support bars are wrong about 302 Position arrangement.Specifically, along the length direction of end truss 301, the more spaced sets of support bar 302, that is to say, that phase The distance between adjacent two support bars 302 are equal；The axis direction of more support bars 302 is parallel.The length of end truss 301 The exhibition of direction and the wing-body 501 of flapping wing wing is to parallel.The width of end truss 301 and the wing sheet of flapping wing wing Body 501 it is tangential parallel.

The flapping wing covering of the fan that the utility model embodiment provides, when in use, by the wing-body 501 of flapping-wing aircraft wing After increasing flapping wing covering of the fan, it can moderately increase the flexibility of flapping-wing aircraft wing；In addition, by by two adjacent support bars 302 Lower dislocation cloth postpones, and covering 303 can just be shaped as in shape of taking out stitches in the section of the axis perpendicular to support bar 302, this Sample can play guide functions, and in flapping-wing aircraft wing motion, can make the exhibition of gas to flowing by rectification, by air-flow Guide the rear of flapping-wing aircraft wing into, the tolerance that flapping-wing aircraft wing is pushed away toward rear becomes big, therefore adds the thrust of flapping-wing aircraft, favorably In the flying quality of increase flapping-wing aircraft.

In the optional scheme of the embodiment, the quantity of support bar 302 is 3~6.Specifically, in the embodiment, support The quantity of bar 302 is 5.It should be noted that the quantity of support bar 302 is not only limited to above-described number in the embodiment Amount, can also determine particular number, such as 7 according to actual condition.

In the optional scheme of the embodiment, the projection of the axis of three support bars 302 of continuous adjacent on the reference plane Three points are formed, length direction of three points along the end truss 301 bending angle that sequentially line is formed is not less than 136 °, and bending Angle is less than 180 °, axis of the reference planes perpendicular to support bar 302.Covering 303 is successively around excessive root support bar 302, for making Covering 303 can deploy, and form bending angle.Specifically, the projection in the section of covering 303 on the reference plane is in and taken out stitches Shape, the angle C formed in fold-line-shaped between two adjacent root lines is bending angle.It is isosceles that three points, which connect the closed figure to be formed, Triangle.It should be noted that because in Fig. 8, covering tilts down, therefore in Fig. 3, the top of support bar has two Line.

During flapping-wing aircraft wing is fluttered, there is plastic deformation in flapping-wing aircraft wing, and the plastic deformation of flapping-wing aircraft wing produces Also resistance is produced while thrust, with the reduction at bending angle, the area of flapping-wing aircraft wing increases, and causes the type of aerofoil profile to hinder and increases Greatly.When flapping wing bending angle is equal to 156 °, thrust increment caused by the increased guide functions at flapping wing bending angle is more than aerofoil profile The increment of type resistance, and now, flapping wing thrust is maximum.

In the optional scheme of the embodiment, support bar 302 is plugged on end truss 301.Specifically, support bar 302 It is installed on end truss 301, and is had by the way of gluing by way of inserting, realizes support bar 302 and end truss 301 are fixedly connected, and are so advantageous to mitigate the weight of flapping wing covering of the fan.

In the optional scheme of the embodiment, end truss 301 includes outline frame and is arranged at the inside of outline frame More ribs 304.Specifically, outline frame is convex pentagon frame structure, more ribs 304 and convex pentagon frame structure It is fixedly connected, the stability of convex pentagon frame structure is realized by more ribs 304.Convex pentagon frame structure is included successively The first stringer 305, the second stringer 306, the 3rd stringer 307, the 4th stringer 308 and the 5th stringer 309 of connection.Second stringer 306 and the 5th stringer 309 be individually fixed in the both ends of the first stringer 305, and the length direction and the 5th stringer of the second stringer 306 309 length direction is each perpendicular to the length direction of the first stringer 305；One end of 3rd stringer 307 is consolidated with the second stringer 306 Fixed connection, the other end of the 3rd stringer 307 are fixedly connected with one end of the 4th stringer 308, the other end of the 4th stringer 308 and the Five stringers 309 are fixedly connected.The equal length of second stringer 306 and the 5th stringer 309；3rd stringer 307 and the 4th stringer 308 Equal length.The length of first stringer 305 is more than the length of the 3rd stringer 307, and the length of the 3rd stringer 307 is more than the 5th purlin The length of bar 309.

In the optional scheme of the embodiment, convex pentagon frame structure is made of timber.It should be noted that the implementation In example, convex pentagon frame structure is not only limited to be made up of timber, can also use other types of material, convex for mitigating The weight of pentagon frame structure, no longer illustrated one by one for other light-duty material embodiments.

In the optional scheme of the embodiment, covering 303 is nylon cloth.By using nylon cloth, on the one hand for waterproof, separately On the one hand be advantageous to mitigate the weight of flapping wing covering of the fan.

In the optional scheme of the embodiment, support bar 302 is conical pipe.Further be advantageous to mitigate by using conical pipe The weight of flapping wing covering of the fan.No longer it is specifically described it should be noted that conical pipe is prior art.

Specifically, conical pipe is tapered tubes of carbon fibre；That is the material of conical pipe is carbon fiber, and conical pipe is sky Heart pipe.Tapered tubes of carbon fibre has that density is small, in light weight, intensity is high, the characteristic of long lifespan, so as to be advantageous to extend flapping wing covering of the fan Service life.Carbon fiber (Carbon Fiber, abbreviation CF), it is a kind of high intensity of phosphorus content more than 95%, high-modulus The new fiber materials of fiber.It is to be piled up to form along fiber axial direction by organic fibers such as flake graphites, through carbonization And microcrystalline graphite material obtained from graphitization processing.Carbon fiber " soft outside but hard inside ", quality is lighter than metallic aluminium, but intensity is higher than Steel, and there is corrosion-resistant, high-modulus characteristic, all it is important materials in defence and military and civilian aspect.

It should be noted that in the embodiment, conical pipe is not only limited to tapered tubes of carbon fibre, can also use other classes The conical pipe of type, for other types of conical pipe, the embodiment no longer illustrates one by one.

In the optional scheme of the embodiment, the front end of covering 303 is close to the first stringer 305 of end truss 301.Covering 303 rear end is spliced by the arc of multiple indents.

In the embodiment, the quantity of the flapping wing covering of the fan on each flapping-wing aircraft wing is multiple, and multiple flapping wing covering of the fans are along wing Body 501 is opened up to equidistantly distributed, and multiple flapping wing covering of the fans are close to the wingtip of wing-body 501, and away from wing-body 501 Wing root.Flapping wing covering of the fan is fixedly connected with trailing edge.For whole wing-body structure in swing process, flapping wing covering of the fan can be with Wing-body is swung together, there is provided thrust and lift, flapping-wing aircraft wing resistance in upper flutter is small, be advantageous to flapping-wing aircraft take off with Flight.

It refer to shown in Figure 13 and Figure 14；The more flapping flight devices of lap siding also include flapping wing power set 100；Flapping wing drives Motivation structure includes bearing 200, the first transmission mechanism 300 and the second transmission mechanism 400；

First transmission mechanism 300 is installed on the rest 200, the first transmission mechanism 300 and the phase of flapping wing power set 100 Connection, the first transmission mechanism 300 are driven by flapping wing power set 100.

Second transmission mechanism 400 has link rod part 410 and connecting portion 420, one end and first of the link rod part 410 Transmission mechanism 300 is flexibly connected by axis connection, the other end of the link rod part 410 with connecting portion 420, and connecting portion 420 slides Installation is on the rest 200.Flapping wing power set 100 drive the first transmission mechanism 300 to operate, and the first transmission mechanism 300 passes through the Link rod part 410 in two transmission mechanisms 400 drives the connecting portion 420 to be moved back and forth along the short transverse of bearing 200；

The both ends of the connecting portion 420 are connected to the flapping-wing aircraft wing 500 being arranged symmetrically, the edge of connecting portion 420 The short transverse of bearing 200 moves back and forth, and then drives two flapping-wing aircraft wings 500 to be fluttered, to produce enough liters Power, and then ensure aircraft stabilized flight.The flapping wing power set of flapping-wing aircraft are powered by battery；Battery is installed on fuselage ring On.

As shown in figure 17, master is included as a preferred embodiment of the present utility model, first transmission mechanism 300 Driving wheel 310, driven pulley 320 and driving member 330, the driving member 330 are used to connect driving wheel 310 and driven pulley 320, also, The driving wheel 310 and driven pulley 320 are flexibly connected with bearing 200 respectively.Need to illustrate makes, and is flexibly connected what is referred to here It is that by being connected between axle and bearing 200, driven pulley 320 is connected driving wheel 310 again by between axle and bearing 200, So that driving wheel 310 and driven pulley 320 can be rotated around corresponding axle respectively.When it is implemented, driving wheel 310 passes through Flapping wing power set 100 are driven, and driving wheel 310 is connected with driven pulley 320 by driving member 330, therefore, driving wheel 310 can drive driven pulley 320 synchronously to be rotated by driving member 330.

Above-mentioned flapping wing power set 100 preferably use motor.Motor is installed on the rest 200, and motor passes through Axle driving driving wheel 310 is rotated.

As a preferred embodiment of the present utility model, driving wheel 310 and driven pulley 320 are in arrangement, driving wheel 310 are arranged on the top of bearing 200, and driven pulley 320 is arranged on the lower section of bearing 200, and the position of driving wheel 310 is located at driven pulley Directly over 320, to ensure the stability of transmission.

As a preferred embodiment of the present utility model, the driving member 330 uses chain or belt.The present embodiment Middle that driving wheel 310 and driven pulley 320 are driven using chain, the driving member 330 is using the advantages of chain drive, no The situation of skidding can be produced, and then has ensured the stability of transmission.

As a preferred embodiment of the present utility model, the bearing 200 includes fixed seat 210 and support base 220, Support base 220 is vertically arranged in fixed seat 210, and the fixed seat 210 is propped up to be rotatablely connected with driven pulley 320 by axle Support seat 220 is used to be flexibly connected by axle with the driving wheel 310, meanwhile, support base 220 is additionally operable to slide with connecting portion 420 Connection, so that connecting portion 420 slides up and down along the short transverse of support base 220, above-mentioned fixed seat 210 and support base 220 are led Play a supporting role and the connection function to connecting portion 420.

As shown in figure 14, as a preferred embodiment of the present utility model, the link rod part 410 includes the first transmission The kinematic link 412 of connecting rod 411 and second, the first kinematic link 411 are used to be flexibly connected by axle with driven pulley 320, and second passes One end of dynamic connecting rod 412 is flexibly connected with the first kinematic link 411 by axle, the other end of the second kinematic link 412 with it is described Connecting portion 420 is flexibly connected.

When driven pulley 320 in first transmission mechanism 300 rotates, the first kinematic link 411 is driven to rotate by axle, first Kinematic link 411 drives the second kinematic link 412 to move by axle, due to the support base 220 in connecting portion 420 and bearing 200 It is slidably connected, therefore the second kinematic link 412 can back and forth be moved with short transverse of the rotation connection 420 in support base 220 It is dynamic.

As a preferred embodiment of the present utility model, the connecting portion 420 includes sliding shoe 421 and contiguous block 422, the sliding shoe 421 is slidably connected with the support base 220 in bearing 200, and contiguous block 422 is fixed on sliding shoe 421, institute Contiguous block 422 is stated to connect the second kinematic link 412 and flapping-wing aircraft wing 500.Second kinematic link 412 can drive connection Block 422 and sliding shoe 421 are moved back and forth in the short transverse of support base 220.Due to two flapping-wing aircraft wings 500 respectively with Contiguous block 422 is connected, reciprocating in sliding shoe 421 meanwhile, it is capable to drive two flapping-wing aircraft wings 500 synchronously to be fluttered Action, provided safeguard for the Movement consistency of two flapping-wing aircraft wings 500, and then enough lift is provided flapping-wing aircraft, ensured The stability of ornithopter flight.

As a preferred embodiment of the present utility model, the sliding shoe 421 is close to the end of bearing 200 and bearing Support base 220 in 200 coordinates slide rail mode to connect by neck.When it is implemented, can be in sliding shoe 421 close to bearing 200 end set neck, slide rail is set on support base 220, neck can be connected with slide rail, wherein, slide rail along The short transverse of support base 220 extends, to ensure that sliding shoe 421 can move back and forth along the short transverse of support base 220.Certainly, Opposite arrangement can also be used, i.e. the end set slide rail in sliding shoe 421 close to bearing 200, in support base 220 Upper setting neck, wherein, neck extends along the short transverse of support base 220, to ensure that sliding shoe 421 can be along support base 220 short transverses move back and forth.

Need exist for explanation, support base 220 of the sliding shoe 421 in the end of bearing 200 and bearing 200 It can also be connected by other conventional modes.For example, pilot hole can be set on sliding shoe 421, set on the rest 200 The axis of guide, the axis of guide arrange in fixed seat 210 that sliding shoe 421 can be socketed on the axis of guide by pilot hole vertically, above-mentioned company Binding structure can equally reach and make sliding shoe 421 vertically (i.e. the short transverse of support base 220) be moved back and forth.

As shown in Figure 17 and Figure 18, as a preferred embodiment of the present utility model, what is provided in the present embodiment flutters In wing drive mechanism, in addition to limiting section 600, the limiting section 600 are set on the rest 200, and limiting section 600 is used for transmission Part 330 is spacing.

When it is implemented, limiting section 600 sets two, two limiting sections 600 are arranged in the support base in bearing 200 220 both sides, two limiting sections 600 can carry out spacing respectively to the both sides of driving member 330, make driving member 330 as requested Track operation, ensure that driving member 330 will not produce the situation for deviateing running track, ensure the security of transmission.It is meanwhile spacing Portion 600 is connected by screw bolts mode and is connected with support base 220, can be arranged on support base 220 multiple for installing bolt Hole, so, by changing upper installation site of the limiting section 600 in support base 220, and then to the tensioner of driving member 330 Power is adjusted.

As a preferred embodiment of the present utility model, the limiting section 600 has a stopper slot 610, the limit Position groove 610 is used to accommodate the driving member 330.When it is implemented, the width of the width of stopper slot 610 and driving member 330 is mutually fitted Match somebody with somebody, it is therefore an objective to it is spacing using movement locus progress of the stopper slot 610 to driving member 330 (particularly chain), reduce because outside is dry Relate to or the self reason of driving member 330 is deformed, transmission is impacted, it is impossible to ensure what flapping-wing aircraft wing 500 was stablized Motion.

The more flapping flight devices of the lap siding include at least one above-mentioned driving mechanism for flapping wing.Due to driving mechanism for flapping wing Detailed description has been made above, therefore, repeats no more here.

When using multiple driving mechanism for flapping wing, multiple driving mechanism for flapping wing are spaced cloth successively by the direction of head to tail Put, in each driving mechanism for flapping wing, only retain flapping wing power set 100 in one of driving mechanism for flapping wing, preferably protect The flapping wing power set 100 in a driving mechanism for flapping wing of head end or machine tail end are stayed, also, each flapping wing drives By axis connection between driving wheel 310 in mechanism, ensure that each driving wheel 310 can be rotated synchronously；Similarly, it is each Also by axis connection between driven pulley 320, ensureing can synchronously be rotated between each driven pulley 320, due to driven pulley 320 It is connected with the second transmission mechanism 400, drives each flapping-wing aircraft wing 500 to synchronize by each second transmission mechanism 400 and flutter It is dynamic, uniformity of fluttering is ensured, stable lift is provided for flapping-wing aircraft, ensures flapping-wing aircraft stabilized flight.

In the embodiment, the quantity for wing group of fluttering is 3, that is to say, that the quantity of flapping-wing aircraft wing is 6.From fly To the rear extreme direction of aircraft ring frames, 3 wing groups of fluttering are followed successively by the 1st wing group the 707, the 2nd of fluttering and flutter for the front end of machine frame Wing group and the 3rd is fluttered wing group 709.

The mode that 3 wing groups of fluttering are fluttered can be that the 1st wing group of fluttering is fluttered downwards, while the 2nd flutters wing group Flutter upwards, and the 3rd wing group of fluttering is fluttered downwards.Using it is this flutter mode when, flutter for 33 and pushed away caused by wing group Power is larger.

Referring to shown in Figure 41, in the embodiment, the quantity of driving mechanism for flapping wing is 3, and 3 wing groups of fluttering are flutterred with 3 Wing drive mechanism corresponds, that is to say, that 1 driving mechanism for flapping wing drives two flapping-wing aircraft machine machines of 1 wing group of fluttering The wing is synchronously fluttered.3 driving mechanism for flapping wing are driven by same flapping wing power set.Flapping wing power set pass through shaft coupling 702 The driving wheel of 3 driving mechanism for flapping wing of driving rotates simultaneously.Wing-body 501 and wing frame articulation, work as driving mechanism for flapping wing When the wing-body is fluttered, this physical efficiency of flapping wing rotates around with hinge axis 703.

It should be noted that the difference of 3 wing groups of fluttering flutter to realize situation (flutter by i.e. 3 wing groups of fluttering Flowing mode), the sliding shoe 421 in each driving mechanism for flapping wing corresponding to wing group of fluttering can be made in the height of support base 220 The initial position in direction is different.

The lap siding flapping flight device that the embodiment provides, by setting multiple wing groups of fluttering to solve wavy fly Row problem, make flight course more steady, solve fitful wind damping problem, anti-side wind energy power is strong.

Embodiment two

The utility model embodiment two provides a kind of flapping-wing aircraft, including the more flapping flight dresses of file that embodiment one provides Put；The flapping-wing aircraft also includes flapping-wing aircraft fixed-wing 705 and flapping-wing aircraft empennage 706.

Referring to shown in Figure 19 to Figure 25, in the embodiment, flapping-wing aircraft fixed-wing includes fixed-wing covering 401, the and of spar 402 Rib 403；The quantity of spar 402 is more, and the more parallel intervals of spar 402 are set；The quantity of rib 403 is multiple, and Multiple parallel intervals of rib 403 are set；Spar 402 passes through rib 403, and spar 402 is fixedly connected with rib 403；Spar 402 For hollow pipe, chordwise, it is gradually reduced by fixed nose of wing to fixed-wing trailing edge, the caliber of more spars 402, that is, Say, the caliber of more spars 402 differs, and the caliber of the spar 402 positioned at the leading edge of flapping-wing aircraft fixed-wing is maximum, and is located at The caliber of the spar 402 of the leading edge of flapping-wing aircraft fixed-wing is minimum.It should be noted that caliber refers to pipe external diameter.Specifically, Fixed-wing covering is supported jointly by spar and rib, and fixed-wing covering is fixedly connected with spar and rib respectively；The more wings Tangential parallel interval arrangement of the beam 402 along flapping-wing aircraft fixed-wing, that is to say, that the length direction of spar 402 is fixed with flapping-wing aircraft The exhibition of the wing is to parallel；Exhibition of multiple ribs 403 along flapping-wing aircraft fixed-wing is set to parallel interval, that is to say, that the length of rib 403 It is tangential parallel with flapping-wing aircraft fixed-wing to spend direction.In the embodiment, the quantity of spar is 3.

Flapping-wing aircraft fixed-wing provided by the utility model, by carrying out rearranging simplification to the structure of fixed-wing, use Hollow pipe is used as spar 402 to mitigate weight, and in the chordwise of fixed-wing, the caliber of more spars 402 is gradually reduced, To optimize the distribution situation of more spars 402 of fixed-wing, and preferably highly it can mitigate weight using wing structure, The moment of flexure for bearing wing and the performance of shearing are also assures that, so that fixed-wing is advantageous to the take-off and landing of flapping-wing aircraft The raising of flying quality.

In the optional scheme of the embodiment, rib 403 includes upper edge strip 404, lower edge strip 405 and corbeling；Upper edge strip 404 are located at the top of lower edge strip 405, and upper edge strip 404 is fixedly connected with lower edge strip 405, and corbeling is installed on edge strip 404 Between lower edge strip 405.Specifically, the aerofoil profile of flapping-wing aircraft fixed-wing is plano-convex aerofoil profile；That is, upper edge strip 404 is in arc Shape, and lower edge strip 405 is linear；One end of upper edge strip 404 is fixedly connected with one end of lower edge strip 405, upper edge strip 404 it is another One end is fixedly connected with the other end of lower edge strip.The space that corbeling is formed between upper edge strip 404 and upper edge strip 404 In.

In the optional scheme of the embodiment, upper edge strip 404 is structure as a whole with lower edge strip 405.Specifically, upper edge strip 404 are made with lower edge strip 405 of integrally formed technique, are so advantageous to improve the steadiness of rib 403.

In the optional scheme of the embodiment, corbeling includes more inclined struts 406, and inclined strut 406 is fixed with flapping-wing aircraft The chordwise of the wing is set in angle, and one end of inclined strut 406 is fixedly connected with upper edge strip 404, the other end of inclined strut 406 It is fixedly connected with lower edge strip 405.Specifically, more inclined struts 406 are so advantageous to upper edge strip 404 in the distribution of line shape is torn open With the supporting role of lower edge strip 405, the steadiness of rib 403 is enhanced.

In the optional scheme of the embodiment, flapping-wing aircraft fixed-wing also includes leading edge supporting member 407, for supporting fixed-wing Covering 401；Leading edge supporting member 407 is installed on the spar 402 of fixed nose of wing, is also leading edge supporting member with regard to saying 407 are fixed on the spar 402 of caliber maximum of the leading edge of flapping-wing aircraft fixed-wing.Specifically, the number of leading edge supporting member 407 Measure to be multiple, length direction uniform intervals of multiple leading edge supporting members 407 along spar 402 are set.Leading edge supporting member 407 It is identical with the shape of the leading edge of flapping-wing aircraft fixed-wing with leading edge arc tips 408, the leading edge arc tips 408.

In the optional scheme of the embodiment, stable card is also each had on the top of leading edge supporting member 407 and upper edge strip 404 Groove 409；Flapping-wing aircraft fixed-wing also includes the stable beam of leading edge；The stable beam of leading edge is sticked in stable neck 409, and leading edge is supported into structure Part 407 and upper edge strip 404 connect, to ensure the steadiness of leading edge supporting member 407.

In the optional scheme of the embodiment, flapping-wing aircraft fixed-wing also includes rear edge support component 415, for supporting fixed-wing Covering 401；Rear edge support component 415 is installed on the spar 402 of fixed-wing trailing edge, is also with regard to saying, rear edge support component 415 are fixed on the spar 402 of caliber minimum of the trailing edge of flapping-wing aircraft fixed-wing.Specifically, the number of rear edge support component 415 Measure to be multiple, length direction uniform intervals of multiple rear edge support components 415 along spar 402 are set.

It should be noted that in the embodiment, can also be opened up on the top of rear edge support component and upper edge strip steady Determine neck；Flapping-wing aircraft fixed-wing can also include the stable beam of trailing edge；The stable beam of trailing edge is sticked in stable neck, by rear edge support Component and upper edge strip connect, to ensure the steadiness of rear edge support component.

In the optional scheme of the embodiment, flapping-wing aircraft fixed-wing also includes a stringer 416, the length direction of the stringer 416 It is parallel with the length direction of spar, and the stringer is also fixedly connected with rib.Also rear edge support component is fixed with the stringer 415。

In the optional scheme of the embodiment, the material of spar 402 is aluminium alloy.It should be noted that in the embodiment, the wing The material of beam 402 is not only limited to aluminium alloy, and the light-weight metal of other forms can also be freely chosen according to actual condition, to Realize the function of mitigating fixed-wing；No longer specifically repeated one by one for light-weight metal the present embodiment of other forms.

In the optional scheme of the embodiment, the material of rib 403 is aluminium alloy.It should be noted that in the embodiment, the wing The material of rib 403 is not only limited to aluminium alloy, and the light-weight metal of other forms can also be freely chosen according to actual condition, to Realize the function of mitigating fixed-wing；Do not repeated specifically further for light-weight metal the present embodiment of other forms.

In the optional scheme of the embodiment, the material of fixed-wing covering 401 is nylon cloth.It should be noted that the implementation In example, the material of fixed-wing covering 401 is not only limited to nylon cloth, can also freely choose other forms according to actual condition Fixed-wing covering 401, to realize waterproof and mitigate the function of fixed-wing；For 401 realities of fixed-wing covering of other forms Example is applied not repeat specifically further.

Referring to shown in Figure 26 and Figure 27, in the embodiment, the spar 402 of aircraft ring frames 700 and flapping-wing aircraft fixed-wing is fixed Connection.It should be noted that in the embodiment, the aspect ratio of flapping-wing aircraft fixed-wing can be 11.00,7.69 or 6.27.

Referring to shown in Figure 28 to Figure 37, flapping-wing aircraft empennage includes tailplane 617 and vertical tail 602 in the embodiment, Aircraft ring frames 700 are fixedly connected with the tailplane 617 of flapping-wing aircraft empennage.

Tailplane includes horizontal stabilizer 601 and elevator 603, after elevator 603 is installed on horizontal stabilizer 601 Edge；Driving rod drive is installed on horizontal stabilizer 601, for adjusting the angle of pitch of elevator；Horizontal stabilizer 601 includes The more stabilization spars 604 set along tailplane chordwise parallel interval, and it is parallel along tailplane spanwise Spaced multiple stabilization ribs 605；Stabilization spar 604 passes through stabilization rib 605, and stabilization spar 604 with Stabilization rib 605 is fixedly connected；Stabilization spar 604 is hollow pipe, apart from nearest stable of the leading edge of horizontal stabilizer 601 The caliber of face spar 604 is more than the caliber of other stabilization spars 604, that is to say, that in more stabilization spars 604, only The caliber of that the root stabilization spar 604 nearest apart from the leading edge of horizontal stabilizer 601 is maximum, other stabilization spars 604 caliber is both less than the caliber of that the root stabilization spar 604 nearest apart from the leading edge of horizontal stabilizer 601.Need to illustrate , caliber refers to pipe external diameter.Specifically, vertical tail 602 is fixedly connected with tailplane.Horizontal stabilizer 601 is Make the flapping-wing aircraft there is appropriate static stability.The pitching of flapping-wing aircraft can be realized by the elevator of setting.Stabilization spar 604 length direction is consistent with the spanwise of tailplane；The length direction of stabilization rib 605 and the wing of tailplane Chord line is consistent.In the embodiment, the quantity of stabilization spar 604 is three.The quantity of elevator is two.

The flapping-wing aircraft empennage that the embodiment provides, the form by stabilization spar 604 using hollow pipe, in order to mitigate The weight of tailplane, the caliber of the stabilization spar 604 nearest from the leading edge of horizontal stabilizer 601 is more than other stabilizations The caliber of spar 604, it can so optimize the distribution situation of more stabilization spars 604, so as to be advantageous to tailplane Design structure optimizes, to improve the longitudinal stability of flapping-wing aircraft and maneuverability.

In the embodiment in optional scheme, horizontal stabilizer 601 also includes more stabilization stringers 606, and more stable The length direction of face stringer 606 is parallel to each other, and length direction phase one of the length direction of stabilization stringer 606 with determining face spar Cause.

In the embodiment in optional scheme, stabilization rib 605 includes edge strip under edge strip 607, stabilization on stabilization 608 and stabilization corbeling；Edge strip 607 is located at the top of edge strip 608 under stabilization, and edge strip on stabilization on stabilization 607 are fixedly connected with edge strip under stabilization 608, and stabilization corbeling is installed on edge strip 607 and stabilization lower edge on stabilization Between bar 608.Specifically, edge strip 607 is curved on stabilization, and edge strip 608 is linear under stabilization；Stabilization upper limb One end of bar 607 is fixedly connected with one end of edge strip under stabilization 608, on stabilization under the other end and stabilization of edge strip 607 The other end of edge strip 608 is fixedly connected.Stabilization corbeling be located on stabilization on edge strip 607 and stabilization edge strip 607 it Between in the space that is formed.

In the embodiment in optional scheme, edge strip 607 is structure as a whole with stabilization lower edge on stabilization.

In the embodiment in optional scheme, stabilization corbeling includes more oblique pillars 609, oblique pillar 609 Set with chordwise in angle, and one end of oblique pillar 609 is fixedly connected with edge strip on stabilization 607, oblique pillar 609 The other end be fixedly connected with edge strip under stabilization 608.Specifically, more stabilization inclined struts are in the distribution of line shape is torn open, so Be advantageous to the supporting role to edge strip 608 under edge strip on stabilization 607 and stabilization, enhance the firm of stabilization rib 605 Property.

In the embodiment in optional scheme, stabilization rib 605 also includes edge strip 619 among stabilization, in stabilization Between edge strip 619 be located on stabilization under edge strip 607 and stabilization between edge strip 608.Among stabilization on edge strip 619 and stabilization It is connected between edge strip 607 by straight strut 618, passes through allotment between edge strip 608 under stabilization centre edge strip 619 and stabilization Post 618 is connected.

In the embodiment in optional scheme, horizontal stabilizer 601 also includes stabilization covering, and stabilization covering is by stabilizing Face spar 604 and stabilization rib 605 are supported, that is to say, that stabilization covering is by stabilization spar 604 and stabilization rib 605 common supports, and stabilization covering is fixedly connected with stabilization spar 604 and stabilization rib 605 respectively.

In the embodiment in optional scheme, elevator includes the more elevator spars 611 that parallel interval is set, and The multiple elevator ribs 612 set along the spanwise parallel interval of tailplane；The length direction and water of elevator spar The spanwise of the horizontal tail wing is parallel；Elevator spar passes through elevator rib 612, and elevator spar and elevator rib 612 It is fixedly connected.

In the embodiment in optional scheme, elevator also includes elevator covering, and elevator covering is by elevator spar Supported with elevator rib 612.

In the embodiment in optional scheme, driving rod drive includes motor 613, first connecting rod 614 and second Connecting rod 615, the casing of motor 613 are fixedly connected with horizontal stabilizer 601, and the motor shaft of motor 613 and first connects One end of bar 614 is fixedly connected, and one end of the other end and second connecting rod 615 of first connecting rod 614 is hinged, second connecting rod 615 The other end is hinged with elevator.Specifically, the elevator rib 612 at the both ends of the length direction of elevator is pacified with level respectively Determine face 601 to be hinged, so when the motor 613 of bar flapping wing power set works, just the angle of pitch of elevator can be carried out Regulation.The axial direction of the motor shaft of the length direction of first connecting rod 614 and the motor 613 of driving rod drive is perpendicular；The The axial direction of the motor shaft of the length direction of two connecting rods 615 and the motor 613 of driving rod drive is perpendicular.

In the embodiment in optional scheme, vertical tail 602 includes empennage framework 616, and parcel empennage framework 616 Empennage covering.Empennage framework 616 is aluminium alloy, and the material of empennage covering is waterproof nylon cloth.Empennage framework 616 is by hollow pipe It is made.

In the embodiment in optional scheme, the material of stabilization rib 605 is aluminium alloy.

In the optional scheme of the embodiment, the material of stabilization spar 604 and the material of elevator spar are aluminium alloy. It should be noted that in the embodiment, the material of stabilization spar 604 and the material of elevator spar are not only limited to aluminium conjunction Gold, the light-weight metal of other forms can also be freely chosen according to actual condition, to realize the function of mitigating tailplane；It is right No longer specifically repeated one by one in light-weight metal the present embodiment of other forms.

In the optional scheme of the embodiment, the material of stabilization rib 605 and the material of elevator rib 612 are that aluminium closes Gold.It should be noted that in the embodiment, the material of stabilization rib 605 and the material of elevator rib 612 are not only limited to Aluminium alloy, the light-weight metal of other forms can also be freely chosen according to actual condition, to realize the work(for mitigating tailplane Energy；Do not repeated specifically further for light-weight metal the present embodiment of other forms.

In the optional scheme of the embodiment, the material of stabilization covering and the material in elevator covering face are nylon cloth. It should be noted that in the embodiment, the material of the material of stabilization covering and the material in elevator covering face is not only limited to Nylon cloth, the material of other forms can also be freely chosen according to actual condition, to realize waterproof and mitigate the work(of fixed-wing Energy；Do not repeated specifically further for material the present embodiment of other forms.It should be noted that in the embodiment, the flapping-wing aircraft It can be unmanned flapping-wing aircraft, or manned flapping-wing machine.

Finally it should be noted that：Various embodiments above is only to illustrate the technical solution of the utility model, rather than it is limited System；Although the utility model is described in detail with reference to foregoing embodiments, one of ordinary skill in the art should Understand：It can still modify to the technical scheme described in foregoing embodiments, either to which part or whole Technical characteristic carries out equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from this practicality newly The scope of each embodiment technical scheme of type.

Claims (10)

1. a kind of more flapping flight devices of lap siding, it is characterised in that including aircraft ring frames, driving mechanism for flapping wing and multiple flutter Wing group, the direction interval of multiple rear ends of front end of the wing group along the aircraft ring frames to the aircraft ring frames of fluttering are laid； The wing group of fluttering includes two flapping-wing aircraft wings being arranged symmetrically；The driving mechanism for flapping wing is used to make the flapping-wing aircraft machine The wing is fluttered；The flapping-wing aircraft wing includes flapping wing covering of the fan, and the flapping wing covering of the fan includes end truss, support bar and covering, The quantity of the support bar is more, and the more support bars are fixed on the end truss, and the more support bars are used In the fixed covering of support.

2. the more flapping flight devices of lap siding according to claim 1, it is characterised in that the aircraft ring frames include fuselage Framework and wing framework；Be connected to the wing framework positioned at the both sides of the fuselage ring, the wing framework to The flapping-wing aircraft wing is installed.

3. the more flapping flight devices of lap siding according to claim 1 or 2, it is characterised in that also filled including flapping wing power Put；The driving mechanism for flapping wing includes bearing, the first transmission mechanism and the second transmission mechanism；First transmission mechanism is arranged on On the bearing, first transmission mechanism is driven by the flapping wing power set；Second transmission mechanism has Link rod part and connecting portion, one end of the link rod part and the first transmission mechanism axis connection, the other end of the link rod part with The connecting portion is flexibly connected, and the connecting portion is slidably mounted on the bearing, and first transmission mechanism passes by second Link rod part in motivation structure drives the connecting portion to be moved back and forth along the height of support direction；The both ends difference of the connecting portion Two flapping-wing aircraft wings of connected symmetrical dendrimer arrangement, two flapping-wing aircraft wings are driven to carry out by the mobile link portion Flutter.

4. the more flapping flight devices of lap siding according to claim 1 or 2, it is characterised in that three institutes of continuous adjacent State the projection of the axis of support bar on the reference plane and form three points, length direction of three points along the end truss The bending angle that sequentially line is formed is not less than 136 °, and the bending angle is less than 180 °, and the reference planes are perpendicular to the branch The axis of strut.

5. the more flapping flight devices of lap siding according to claim 3, it is characterised in that first transmission mechanism includes Driving wheel, driven pulley and the driving member being connected with the driving wheel and the driven pulley, the driving wheel and described driven Wheel is flexibly connected with the bearing respectively.

6. the more flapping flight devices of lap siding according to claim 5, it is characterised in that the driving member using chain or Belt.

7. the more flapping flight devices of lap siding according to claim 5, it is characterised in that the bearing include fixed seat and Support base, the support base are vertically arranged in the fixed seat, and the fixed seat with the driven pulley to be flexibly connected, institute Support base is stated to be used to be flexibly connected with the driving wheel.

8. the more flapping flight devices of lap siding according to claim 5, it is characterised in that the link rod part includes first and passed Dynamic connecting rod and the second kinematic link, first kinematic link pass through axis connection, second kinematic link with the driven pulley Both ends are flexibly connected with first kinematic link and the connecting portion respectively.

9. the more flapping flight devices of lap siding according to claim 8, it is characterised in that the connecting portion includes sliding shoe And contiguous block, the sliding shoe are connected with the bearing sliding, the contiguous block is fixed on the sliding shoe, the contiguous block To connect second kinematic link and the flapping wing.

10. a kind of flapping-wing aircraft, it is characterised in that including the more flapping flights of lap siding as claimed in any one of claims 1-9 wherein Device.