CN107719633A - The wing and collapsible suspension formula aircraft of collapsible suspension formula aircraft - Google Patents

The wing and collapsible suspension formula aircraft of collapsible suspension formula aircraft Download PDF

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Publication number
CN107719633A
CN107719633A CN201710799616.3A CN201710799616A CN107719633A CN 107719633 A CN107719633 A CN 107719633A CN 201710799616 A CN201710799616 A CN 201710799616A CN 107719633 A CN107719633 A CN 107719633A
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CN
China
Prior art keywords
wing
connecting rod
cloth support
group
support component
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Granted
Application number
CN201710799616.3A
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Chinese (zh)
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CN107719633B (en
Inventor
徐国祥
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Individual
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Individual
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Priority to CN201710799616.3A priority Critical patent/CN107719633B/en
Publication of CN107719633A publication Critical patent/CN107719633A/en
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Publication of CN107719633B publication Critical patent/CN107719633B/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft

Abstract

The present invention discloses the wing and collapsible suspension formula aircraft of a kind of collapsible suspension formula aircraft, wherein, the wing of collapsible suspension formula aircraft includes the first connecting rod and the 5th connecting rod, the second connecting rod and six-bar linkage being arranged side by side, drive link and shrinking connecting-rod being arranged side by side；One end of the first connecting rod is hinged with frame, and the one end of the first connecting rod, the other end of the 5th connecting rod respectively with second connecting rod and six-bar linkage is hinged；One end of the drive link and the slide assemblies of aircraft are hinged, the other end respectively with first connecting rod, the 5th rod hinge connection；The other end of the one end of the shrinking connecting-rod respectively with second connecting rod and six-bar linkage is hinged.The wing exhibition debit of collapsible suspension formula aircraft of the present invention just, can greatly facilitate the carrying, transport and use of collapsible suspension formula aircraft, to user with extremely satisfied usage experience.

Description

The wing and collapsible suspension formula aircraft of collapsible suspension formula aircraft
Technical field
The present invention relates to aircraft field, the more particularly to a kind of wing and collapsible suspension of collapsible suspension formula aircraft Formula aircraft.
Background technology
Suspension aerobat is a kind of relatively simple, safe aircraft, and it below frame by setting suspension dress Put and reach manned or loading purpose.The wing of existing suspension aerobat is generally triangle, it is not possible to fold or only It could can fold after removal, just the carrying to suspension aerobat, transport and use cause great inconvenience for this.
The content of the invention
The main object of the present invention is to provide a kind of wing of collapsible suspension formula aircraft, it is intended to because existing suspension type flies The wing-folding of row device it is difficult and caused by carry and the technical problem of transport inconvenience.
To achieve the above object, the present invention provides a kind of wing of collapsible suspension formula aircraft, including first connecting rod group Part, the first connecting rod component include：
First connecting rod, one end of the first connecting rod are used to be connected with the frame of collapsible suspension formula aircraft, to be formed First junction；
Second connecting rod, one end of the second connecting rod are articulated with the other end of the first connecting rod；
Drive link, one end of the drive link are used to be connected with the slide assemblies of collapsible suspension formula aircraft, with The second junction is formed, the other end of the drive link is articulated with the first connecting rod, to form the of the first connecting rod Two hinged places；
5th connecting rod, the 5th connecting rod are arranged side by side with the first connecting rod, and one end of the 5th connecting rod is articulated with Between the both ends of the drive link, the other end of the 5th connecting rod is articulated with one end of the second connecting rod；
Six-bar linkage, the six-bar linkage are arranged side by side with the second connecting rod, and one end of the six-bar linkage is articulated with The other end of the other end of the first connecting rod and the 5th connecting rod；And
Shrinking connecting-rod, the shrinking connecting-rod be articulated with the second connecting rod the other end and the six-bar linkage it is another End.
Preferably, the wing of the collapsible suspension formula aircraft also includes：
Second connecting rod component, including third connecting rod and fourth link, one end of the third connecting rod are articulated with described One connecting rod and the 5th connecting rod, the other end of the third connecting rod are articulated with one end of the fourth link, the fourth link The other end be articulated with the second connecting rod and six-bar linkage；
Third connecting rod component, it is arranged between the first connecting rod and the third connecting rod, the third connecting rod component bag Seven-link assembly and the 8th connecting rod are included, one end of the seven-link assembly is articulated with the first connecting rod and the 5th connecting rod, The other end is articulated with one end of the 8th connecting rod, and the other end of the 8th connecting rod is articulated with the third connecting rod；And
Fourth link component, it is arranged between the second connecting rod and the fourth link, the fourth link component bag The 9th connecting rod and the tenth connecting rod are included, one end of the 9th connecting rod is articulated with fourth link, and the other end is articulated with the one of the tenth connecting rod End, the other end of the tenth connecting rod are articulated with the second connecting rod and the six-bar linkage.
Preferably, the wing of the collapsible suspension formula aircraft also includes some wing cloth support components, the wing cloth branch Support component includes：
Fixed cover, the fixed cover are rotatably arranged on the wing, and are set along the length direction of the wing；
Slide rail set, the slide rail set are rotatably arranged on the wing, and are set along the length direction of the wing； And
Wing cloth support frame, the wing cloth support frame carries default radian, and fixation is plugged in the fixed cover, described Wing cloth support frame is also inserted into the slide rail set, and when the wing deploys or collapses, the wing cloth support frame is in the cunning Slided in rail set；
The wing cloth support frame is provided with fixed fixing point in fixed cover, can be combined by the fixing point pre-set, It is fixed, to adapt to different airfoil shapes.
Preferably, the wing cloth support component, including：
First group of wing cloth support component, the fixation of first group of wing cloth support component are set on the seven-link assembly, and first The slide rail of group wing cloth support component is set on the first connecting rod or the 5th connecting rod, the wing of first group of wing cloth support component Cloth support frame is plugged in the fixed cover of first group of wing cloth support component and the slide rail set of first group of wing cloth support component；
Second group of wing cloth support component, the fixation of second group of wing cloth support component are set on the 8th connecting rod, and second The slide rail of group wing cloth support component is set on the first connecting rod or the 5th connecting rod, the wing of second group of wing cloth support component Cloth support frame is plugged in the fixed cover of second group of wing cloth support component and the slide rail set of second group of wing cloth support component；
3rd group of wing cloth support component, the fixation of the 3rd group of wing cloth support component are set on the third connecting rod, and the 3rd The slide rail of group wing cloth support component is set on the first connecting rod or the 5th connecting rod, the wing of the 3rd group of wing cloth support component Cloth support frame is plugged in the fixed cover of the 3rd group of wing cloth support component and the slide rail set of the 3rd group of wing cloth support component；
4th group of wing cloth support component, the fixation of the 4th group of wing cloth support component are set on the fourth link, and the 4th The slide rail of group wing cloth support component is set on the second connecting rod or the six-bar linkage, the wing of the 4th group of wing cloth support component Cloth support frame is plugged in the fixed cover of the 4th group of wing cloth support component and the slide rail set of the 4th group of wing cloth support component；
5th group of wing cloth support component, the fixation of the 5th group of wing cloth support component are set on the 9th connecting rod, and the 5th The slide rail of group wing cloth support component is set on the second connecting rod or the six-bar linkage, the wing of the 5th group of wing cloth support component Cloth support frame is plugged in the fixed cover of the 5th group of wing cloth support component and the slide rail set of the 5th group of wing cloth support component；
6th group of wing cloth support component, the fixation of the 6th group of wing cloth support component are set on the tenth connecting rod, and the 6th The slide rail of group wing cloth support component is set on the second connecting rod or the six-bar linkage, the wing of the 6th group of wing cloth support component Cloth support frame is plugged in the fixed cover of the 6th group of wing cloth support component and the slide rail set of the 6th group of wing cloth support component；And
7th group of wing cloth support component, the fixation of the 7th group of wing cloth support component are set on the second connecting rod, and the 7th The slide rail of group wing cloth support component is set on the six-bar linkage, and the wing cloth support frame of the 7th group of wing cloth support component is plugged in The fixed cover of 7th group of wing cloth support component and the slide rail set of the 7th group of wing cloth support component.
Preferably, the wing of the collapsible suspension formula aircraft also includes wing cloth, and the wing cloth is provided with to be prolonged by front end The inserting passage of rear end is extended, the inserting opening of the inserting passage is arranged on the front end of the wing cloth, the wing cloth support frame It is inserted into the inserting passage of the wing cloth.
The present invention also provides a kind of collapsible suspension formula aircraft, including：
Wing, the wing are wing as described above；
Frame, one end of the first connecting rod of the wing are hinged with the frame, to form the first junction；And
Slide assemblies, it is connected with the housing slide, the slide assemblies and one end of the drive link are hinged, described Slide assemblies have the second pole that the first extreme position for controlling the wing to be fully deployed and the control wing are packed up completely Extreme position, first extreme position is between first junction and second extreme position；
When the slide assemblies slide from first extreme position to the second extreme position direction, the wing Pack up, when the slide assemblies slide from second extreme position to the first extreme position direction, the wing exhibition Open.
Preferably, the frame includes two parallel arrangement of slide bars, the first pedestal, the second pedestal, the first positioning seat and use In the first connector for positioning first positioning seat, first pedestal and the second pedestal are respectively arranged at two slide bars Both ends；
The slide assemblies are slidably disposed on two slide bars, and the slide assemblies are located at first pedestal And second between pedestal；
First positioning seat is slidably disposed on the slide bar and positioned at the slide assemblies and second base Between seat, on first positioning seat, first connector is fixedly connected with first positioning for first junction Seat and the slide bar.
Preferably, the collapsible suspension formula aircraft also includes being used for the first power for driving the slide assemblies to slide Device, first power set are between two slide bars；
First power set include the first motor, with the screw rod of the output axis connection of first motor and with it is described The nut of screw rod adaptation, first motor are arranged on first pedestal, and the nut is arranged on the slide assemblies, The screw rod coordinates with the nut, and the avoiding space connected with the screwed hole of the nut is offered on the slide assemblies, Passed through with for the screw rod.
Preferably, the collapsible suspension formula aircraft also includes suspension arrangement, and the suspension arrangement includes suspension arm, held Weight bar and the second positioning seat, second positioning seat are sheathed on two slide bars, and second positioning seat, which has, presses preset angle The first suspension rotating shaft of the setting that is inclined upwardly with the plane where two slide bars is spent, one end of the suspension arm is rotatably pacified Loaded in the described first suspension rotating shaft, one end of the bearing bar is rotatably installed on the other end of the suspension arm.
Preferably, the slide assemblies include：
First sliding part, slideably it is sheathed on two slide bars and fixed with described second positioned at first positioning seat Between the seat of position, first sliding part and one end of the drive link are hinged；
Second sliding part, be slideably sheathed on two slide bars and positioned at second positioning seat and the first pedestal it Between, the nut is arranged at second sliding part, offers on second sliding part and is connected with the screwed hole of the nut The first avoid holes, second sliding part have and described first suspension rotating shaft it is identical second suspension rotating shaft；And
Gangbar, is arranged in second positioning seat, and the both ends of the gangbar respectively with first sliding part and Second sliding part is connected, and the second avoid holes connected with first avoid holes are offered in the gangbar；
The suspension arrangement also includes transmission arm, and one end of the transmission arm is rotatably arranged on the described second suspension and turned On axle, the other end is hinged with the suspension arm.
According to above-mentioned technical proposal, in use, when needing wing to deploy, slide assemblies drive driving to connect to wing One end of bar to first to extreme position move so that drive link rotates relative to first connecting rod so that the second junction with The distance of first junction reduces, and is embodied in the drive link and reduces with first connecting rod in the angle close to frame side. The drive link driving first connecting rod and the 5th connecting rod rotate relative to first junction to the direction away from frame；Together When pass through the drive connection between drive link and first connecting rod, the 5th connecting rod, second connecting rod and six-bar linkage, it is described driving connect Bar drives second connecting rod and six-bar linkage relative to its hinged place to the direction away from frame by first connecting rod and the 5th connecting rod Rotate；Drive connection by second connecting rod, the between six-bar linkage and shrinking connecting-rod simultaneously, the drive link pass through first and connected Bar, the 5th connecting rod, second connecting rod and six-bar linkage driving shrinking connecting-rod turn relative to its hinged place to the direction away from frame It is dynamic；The expansion for being embodied in wing of above-mentioned transmission.
Similarly, when needing wing to collapse, slide assemblies drive one end of drive link to be moved to the second extreme position, make Obtain drive link to rotate relative to first connecting rod so that the distance of the second junction and the first junction increases, and is embodied in The drive link increases with first connecting rod in the angle close to frame side.The drive link driving first connecting rod and the 5th connects Bar rotates relative to first junction to close to the direction of frame；The drive link passes through first connecting rod and the 5th connecting rod Second connecting rod and six-bar linkage is driven to be rotated relative to its hinged place to close to the direction of frame；The drive link passes through first Connecting rod, the 5th connecting rod, second connecting rod and six-bar linkage driving shrinking connecting-rod are relative to its hinged place to close to the direction of frame Rotate；The gathering for being embodied in wing of above-mentioned transmission.
The wing of collapsible suspension formula aircraft of the present invention, one end of drive link is driven relative to the by slide assemblies One junction is moved, and the exhibition that wing can be achieved is received, simple in construction, easy to use.
The wing exhibition debit of collapsible suspension formula aircraft of the present invention just, can greatly facilitate collapsible suspension formula aircraft Carry, transport and use, give user with extremely satisfied usage experience.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing There is the required accompanying drawing used in technology description to be briefly described, it should be apparent that, drawings in the following description are only this Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, can be with Structure according to these accompanying drawings obtains other accompanying drawings.
Fig. 1 is the structural representation of the embodiment of collapsible suspension formula aircraft one of the present invention, wherein, wing is in expansion shape State；
Fig. 2 is another structural representation of collapsible suspension formula aircraft in Fig. 1, wherein, wing is in collapsed state；
Fig. 3 is that the wing of collapsible suspension formula aircraft in Fig. 1 is in the structural representation of deployed condition；
Fig. 4 is the structural representation of another embodiment of wing of collapsible suspension formula aircraft of the present invention, wherein, at wing In deployed condition；
Fig. 5 is the structural representation of fixed cover in Fig. 1；
Fig. 6 is the structural representation of Fig. 1 wing centre section cloth support frames；
Fig. 7 is the structural representation of Fig. 1 wing centre section cloth；
Fig. 8 is the structural representation of frame in Fig. 1, wherein, suspension arrangement is in deployed condition；
Fig. 9 is the structural representation of frame in Fig. 1, wherein, suspension arrangement is not installed；
Figure 10 is the structural representation of the first sliding part in Fig. 1；
Figure 11 is the structural representation of the first positioning seat in Fig. 1；
Figure 12 is the structural representation of the second positioning seat in Fig. 1；
Figure 13 is the structural representation of body cradle in Fig. 1；
Figure 14 is the structural representation of coiling runner in Fig. 1；
Figure 15 is the structural representation of another embodiment wing centre section cloth support frame of collapsible suspension formula aircraft of the present invention.
Drawing reference numeral explanation：
The realization, functional characteristics and advantage of the object of the invention will be described further referring to the drawings in conjunction with the embodiments.
Embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete Site preparation describes, it is clear that described embodiment is only the part of the embodiment of the present invention, rather than whole embodiments.Base Embodiment in the present invention, those of ordinary skill in the art obtained under the premise of creative work is not made it is all its His embodiment, belongs to the scope of protection of the invention.
If it is to be appreciated that related in the embodiment of the present invention directionality instruction (such as up, down, left, right, before and after ...), Then directionality instruction be only used for explaining relative position relation under a certain particular pose (as shown in drawings) between each part, Motion conditions etc., if the particular pose changes, directionality instruction also correspondingly changes therewith.
If in addition, relating to the description of " first ", " second " etc. in the embodiment of the present invention, " first ", " second " etc. are somebody's turn to do Description be only used for describing purpose, and it is not intended that instruction or implying its relative importance or implicit indicating indicated skill The quantity of art feature.Thus, " first " is defined, the feature of " second " can be expressed or implicitly includes at least one spy Sign.
Figure to figure show collapsible suspension formula aircraft of the present invention wing and collapsible suspension formula aircraft it is preferred Embodiment and variant embodiment, in these embodiments with multiple improvement；In specific descriptions, each change for therein Enter and be described as an embodiment, in the case of no constructive interference and conflict, the technical characteristic between following each embodiments can With independent assortment.The combination of this technical scheme is will be understood that when the combination appearance of technical scheme is conflicting or can not realize It is not present, also not within the protection domain of application claims.
The present invention provides a kind of wing of collapsible suspension formula aircraft.
In embodiments of the present invention, Fig. 1 to Fig. 4 is referred to, a kind of wing 29 of collapsible suspension formula aircraft, including One link assembly 1, the first connecting rod component 1 include：
First connecting rod 2, one end of the first connecting rod 2 are used to be connected with the frame 30 of collapsible suspension formula aircraft 100, To form the first junction 5；
Second connecting rod 3, one end of the second connecting rod 3 are articulated with the other end of the first connecting rod 2；
Drive link 10, one end of the drive link 10 are used for the slide assemblies 4 with collapsible suspension formula aircraft 100 Connection, to form the second junction 85, the other end of the drive link 10 is articulated with the first connecting rod 2, with described in formation Second hinged place 12 of first connecting rod 2；
5th connecting rod 13, the 5th connecting rod 13 are arranged side by side with the first connecting rod 2, one end of the 5th connecting rod 13 It is articulated between the both ends of the drive link 10, the other end of the 5th connecting rod 13 is articulated with the one of the second connecting rod 3 End；
Six-bar linkage 14, the six-bar linkage 14 are arranged side by side with the second connecting rod 3, one end of the six-bar linkage 14 It is articulated with the other end of the first connecting rod 2 and the other end of the 5th connecting rod 13；And
Shrinking connecting-rod 15, the shrinking connecting-rod 15 are articulated with the other end of the second connecting rod 3 and the six-bar linkage 14 other end.
According to above-mentioned technical proposal, in use, when needing wing 29 to deploy, slide assemblies 4 drive wing 29 One end movement of drive link 10 so that drive link 10 rotates relative to first connecting rod 2 so that the second junction 85 and first The distance of junction 5 reduces, and is embodied in the drive link 10 and subtracts with first connecting rod 2 in the angle close to the side of frame 30 It is small.The drive link 10 drives the connecting rod 13 of first connecting rod 2 and the 5th relative to first junction 5 to away from frame 30 Direction rotates；Simultaneously by between drive link 10 and first connecting rod 2, the 5th connecting rod 13, second connecting rod 3 and six-bar linkage 14 Drive connection, the drive link 10 drive second connecting rod 3 and six-bar linkage 14 relative by the connecting rod 13 of first connecting rod 2 and the 5th Rotated in its hinged place to the direction away from frame 30；Simultaneously by between second connecting rod 3, six-bar linkage 14 and shrinking connecting-rod 15 Drive connection, the drive link 10 are stretched by the driving of first connecting rod 2, the 5th connecting rod 13, second connecting rod 3 and six-bar linkage 14 Contracting connecting rod 15 rotates relative to its hinged place to the direction away from frame 30；The exhibition for being embodied in wing 29 of above-mentioned transmission Open.
Similarly, when needing wing 29 to collapse, slide assemblies 4 drive one end movement of drive link 10 so that driving connects Bar 10 rotates relative to first connecting rod 2 so that the distance of the second junction 85 and the first junction 5 increases, and is embodied in institute Drive link 10 is stated with first connecting rod 2 in the angle close to the side of frame 30 to increase.The drive link 10 drives the He of first connecting rod 2 5th connecting rod 13 rotates relative to first junction 5 to close to the direction of frame 30；The drive link 10 passes through first The connecting rod 13 of connecting rod 2 and the 5th drives second connecting rod 3 and six-bar linkage 14 to turn relative to its hinged place to close to the direction of frame 30 It is dynamic；The drive link 10 drives shrinking connecting-rod by first connecting rod 2, the 5th connecting rod 13, second connecting rod 3 and six-bar linkage 14 15 rotate relative to its hinged place to close to the direction of frame 30；The gathering for being embodied in wing 29 of above-mentioned transmission.
In summary, above-mentioned structure setting is passed through so that the wing 29 of folded suspension type aircraft is compact-sized, can hold Carry bigger weight flight；And closer to the wing of birds.
The wing 29 of collapsible suspension formula aircraft of the present invention, one end phase of drive link 10 is driven by slide assemblies 4 Slided for the first junction 5, the exhibition that wing 29 can be achieved is received, simple in construction, easy to use.
The wing 29 of collapsible suspension formula aircraft of the present invention opens up debit just, can greatly facilitate collapsible suspension formula aircraft 100 carrying, transport and use, to user with extremely satisfied usage experience.
Secondly, by the way that the connecting rod 13 of first connecting rod 2 and the 5th is arranged side by side, and by second connecting rod 3 and six-bar linkage 14 simultaneously Row is set, and not only can preferably transmit the driving force of drive link 10 so that wing 29 can smoothly open up receipts；But also can To strengthen the structural strength of wing 29.
In addition, the setting of shrinking connecting-rod 15, while the structure of wing 29 is run well with the skeleton of birds wing more To be alike, and beneficial to the support to wing cloth 16.
Further, the shrinking connecting-rod 15 is expansion link.When the shrinking connecting-rod 15 extends, place wing, area becomes Greatly, span increase, lift increase, when the shrinking connecting-rod 15 shortens, place wing, area reduction, span reduction, lift subtract It is small.
Further, in order to reduce the coasting distance of slide assemblies 4 and reduce drive link 10 size, the driving Connecting rod 10 is arranged on one end of the close frame 30 of the first connecting rod 2.
In a particular embodiment, the drive link 10 can be arranged between first connecting rod 2 and the both ends of the 5th connecting rod 13 Any position, but the hinged place of the drive link 10 and first connecting rod 2 is from more remote, the driving with a distance from the frame 30 Length dimension needed for connecting rod 10 is bigger；For wing 29 during completing expansion and collapsing, the slide assemblies 4 need to drive drive The stroke of the dynamic one end of connecting rod 10 movement is bigger, thus it requires the length of the frame 30 is bigger, and then folded suspension type is flown The carrying of device 100 is unfavorable.In the present embodiment, the drive link 10 is arranged on the close frame 30 of the first connecting rod 2 One end.
So the wing 29 of collapsible suspension formula aircraft of the present invention, by the way that drive link 10 is arranged on into described first One end of the close frame 30 of connecting rod 2 so that the size of the drive link 10 is smaller, default needed for the slide assemblies 4 Driving trip is smaller, so as to may be such that the frame 30 be sized to it is smaller, and then may be such that collapsible suspension formula fly The volume of device 100 is smaller, realizes lightweight, the Miniaturization Design of collapsible suspension formula aircraft 100；And reduce frame 30 flight resistance and the weight for reducing complete machine, beneficial to the flight of aircraft 100.
Further, in order that wing, which is realized, preferably opens up fruit of producing effects, Fig. 3 and Fig. 4, the He of first connecting rod 2 are referred to 5th connecting rod 13 be arranged in parallel, and accordingly, the second connecting rod 3 and six-bar linkage 14 be arranged in parallel, the He of drive link 15 Second connecting rod 3 be arranged in parallel, and the shrinking connecting-rod 15 be arranged in parallel with the first connecting rod 2.
The wing 29 of collapsible suspension formula aircraft of the present invention, set by the way that the first connecting rod 2 is parallel with the 5th connecting rod 13 Put, the second connecting rod 3 and six-bar linkage 14 be arranged in parallel, and the other end of the first connecting rod 2 connects with described second respectively The other end of bar 3 and be hinged, described 5th connecting rod of six-bar linkage 14 is be hinged with second connecting rod 3 and six-bar linkage 14 respectively so that The first connecting rod 2, second connecting rod 3, the 5th connecting rod 13 and six-bar linkage 14 form a parallelogram drive mechanism；Together Reason, the drive link 10, first connecting rod 2, the connecting rod 13 of second connecting rod 3 and the 5th also form parallelogram transmission knot Structure；Similarly, the first connecting rod 2, second connecting rod 3, six-bar linkage 14 and shrinking connecting-rod 15 also form parallelogram biography Dynamic structure.The drive link 10 is be hinged with the connecting rod 13 of first connecting rod 2 and the 5th respectively, the shrinking connecting-rod 15 respectively with The second connecting rod 3 and six-bar linkage 14 are be hinged, so, drive the drive link 10 to may be such that drive link 10, first connects Bar 2, second connecting rod 3, the 5th connecting rod 13, six-bar linkage 14 and shrinking connecting-rod 15 deploy or collapsed.
According to above-mentioned technical proposal, in use, when needing wing to deploy, slide assemblies 4 drive driving to wing One end movement of connecting rod 10 so that the distance of the second junction 85 and the first junction 5 reduces, and is embodied in the driving and connects Bar 10 reduces with first connecting rod 2 in the angle close to the side of frame 30.Drive link 10 drives first connecting rod 2 and the phase of the 5th connecting rod 13 Rotated for first junction 5 to the direction away from frame 30；Connected simultaneously according to drive link 10, first connecting rod 2, second The connecting rod 13 of bar 3 and the 5th form parallelogram drive mechanism and drive link 10, first connecting rod 2, second connecting rod 3 with And the 5th parallelogram drive mechanism for forming of connecting rod 13, the drive link 10 passes through the connecting rod 13 of first connecting rod 2 and the 5th Second connecting rod 3 and six-bar linkage 14 is driven to be rotated relative to its hinged place to the direction away from frame 30；Meanwhile connected according to driving The parallelogram drive mechanism and first connecting rod that bar 10, first connecting rod 2, the connecting rod 13 of second connecting rod 3 and the 5th are also formed 2nd, the parallelogram drive mechanism that second connecting rod 3, six-bar linkage 14 and shrinking connecting-rod 15 are formed, the drive link 10 are logical Cross first connecting rod 2, the 5th connecting rod 13, second connecting rod 3 and six-bar linkage 14 drive shrinking connecting-rod 15 relative to its hinged place to Direction away from frame 30 rotates；The expansion for being embodied in wing 29 of above-mentioned transmission.
Similarly, slide assemblies 4 can drive drive link 10 to collapse wing 29.And because the first connecting rod 2 and the Five connecting rods 13 be arranged in parallel, the second connecting rod 3 and six-bar linkage 14 be arranged in parallel and the drive link 15 and second connects Bar 3 be arranged in parallel, the gathering that the wing 29 can be more neat.
Further, Fig. 3 and Fig. 4 are referred to, the wing 100 of the collapsible suspension formula aircraft also includes second connecting rod Component 6, the second connecting rod component 6 include third connecting rod 7 and fourth link 8, and one end of the third connecting rod 7 is articulated with One connecting rod 2 and the 5th connecting rod 13, the other end of the third connecting rod 7 are articulated with one end of fourth link 8, the fourth link 8 other end is articulated with second connecting rod 3 and six-bar linkage 14.
During the wing 100 exhibition is received, under the driving effect of drive link 10, first connecting rod 2 and second connects Bar 3 and the 3rd connect 7 bars relatively rotate, third connecting rod 7 also relatively rotates with fourth link 8, fourth link 8 also with Second connecting rod 3 relatively rotates.
The wing 29 of collapsible suspension formula aircraft of the present invention, by setting second connecting rod component 6, wing 29 can be strengthened Structural strength provide condition for follow-up link assembly installation so that the fixed cover 24 being mounted above is moved by default direction It is dynamic.
Further, third connecting rod component 17, third connecting rod component are additionally provided between first connecting rod 2 and third connecting rod 7 17 include the connecting rod 19 of seven-link assembly 18 and the 8th, and one end of seven-link assembly 18 is articulated with the connecting rod 13 of first connecting rod 2 and the 5th, The other end is articulated with one end of the 8th connecting rod 19, and the other end of the 8th connecting rod 19 is articulated with the middle part of third connecting rod 7.
During wing 29 deploys or collapsed, seven-link assembly 18 connects with first connecting rod 2, the 5th connecting rod 13 and the 8th Bar 19 relatively rotates, and the 8th connecting rod 19 also relatively rotates with third connecting rod 7.
Further, fourth link component 20, fourth link component are additionally provided between second connecting rod 3 and fourth link 8 20 include the 9th connecting rod 21 and the tenth connecting rod 22, and one end of the 9th connecting rod 21 is articulated with the middle part of fourth link 8, other end hinge One end of the tenth connecting rod 22 is connected to, the other end of the tenth connecting rod 22 is articulated with second connecting rod 3 and six-bar linkage 14.
During wing 29 deploys or collapsed, with the connecting rod 22 of fourth link 8 and the tenth phase occurs for the 9th connecting rod 21 To rotating, the tenth connecting rod 22 also relatively rotates with second connecting rod 3 and six-bar linkage 14.
Wherein, first connecting rod 2, fourth link 8, the 5th connecting rod 13, the 8th connecting rod 19 and the tenth connecting rod 22 are two It is arranged in parallel and the space passed through for other connecting rods is left in centre, in order to is hinged between each connecting rod, and enhancing machine The structural strength of the wing 29.
Wherein, because second connecting rod 3 and six-bar linkage 14 are single setting, in order to strengthen the connection with shrinking connecting-rod 15 Intensity, the other end of the second connecting rod 3 and six-bar linkage 14, which offers, supplies the breach of the grafting of shrinking connecting-rod 15 (to scheme not Show), the shrinking connecting-rod 15 is plugged in the breach, so that two relative side wall clamping shrinking connecting-rods 15 of the breach, so as to Strengthen the bonding strength of shrinking connecting-rod 15.
In the present embodiment, the third connecting rod 7, the connecting rod 21 of seven-link assembly 18 and the 9th is parallel with second connecting rod 3 sets Put, and seven-link assembly 18 is collinearly set with drive link；The fourth link 8, the 8th connecting rod 19 and the tenth connecting rod 22 with First connecting rod 2 be arranged in parallel.To ensure that wing 29 can more smoothly open up receipts.
In the present embodiment, the third connecting rod 7 is be hinged be hinged to form the first of the first connecting rod 2 with first connecting rod 2 Place 9, second hinged place 12 is between the hinged place 9 of the first junction 5 and first.So that the size of drive link 10 It is shorter.
In the present embodiment, above-mentioned each connecting rod is carbon fiber hollow stem, it is ensured that while wing 29 has sufficient intensity, The weight of wing 29 can also be made light as much as possible, beneficial to the flight of wing 29.Moreover, each carbon fiber hollow stem is preferably using circle Bar；Certainly, connecting rod can also use the connecting rod of the shapes such as square bar.
Similarly, in the structure of wing 29, link assembly can also be increased to meet the installation requirements of wing cloth support component, The structural strength of wing 29 can also further be increased simultaneously, this is no longer going to repeat them.
Further, Fig. 1, Fig. 3 are referred to Fig. 6, the wing 29 of the collapsible suspension formula aircraft is also including some Wing cloth support component 23, the wing cloth support component 23 include：
Fixed cover 24, the fixed cover 24 are rotatably arranged in the wing (it should be pointed out that wing refers to structure herein Into each link assembly of wing skeleton) on, and set along the length direction of the wing 29.In a particular embodiment, it is described solid Surely set 24 is rotatably arranged in the second connecting rod component 6 and/or third connecting rod component 17 and/or fourth link component 20 On.
Slide rail set 25, the slide rail set 25 are rotatably arranged in the wing (it should be pointed out that wing refers to structure herein Into each link assembly of wing skeleton) on, and set along the length direction of the wing 29.In a particular embodiment, the cunning Rail set 25 is rotatably arranged on the first connecting rod component 1.
Wing cloth support frame 26, the wing cloth support frame 26 carries default radian, and fixation is plugged in fixed cover 24, institute State wing cloth support frame 26 and be also inserted into the slide rail set 25, when the wing 29 deploys or collapsed, the wing cloth support frame 26 Slided in slide rail set 25.
The wing cloth support frame 26 is provided with fixed fixing point in fixed cover 24 (figure is not marked), can be by pre-setting Fixing point combines, and is fixed, to adapt to different airfoil shapes.In a particular embodiment, reference picture 3 and Fig. 4, the present invention provide Two kinds of preferable assembled schemes.It is of course also possible to adjustment and movement according to demand, to adapt to different wing shapes requirements.
In the present embodiment, the fixed cover 24 is rotatably arranged in the second connecting rod component 6, third connecting rod component 17 and fourth link component 20 on.
Further, reference picture 7, the wing 29 of collapsible suspension formula aircraft also include wing cloth 16, pass through above-mentioned knot Structure is designed, and the wing cloth 16 of wing 29 can be set on wing cloth support frame 26；Specifically, the front end of wing cloth 26 to postmedian thickness Degree is gradually reduced, and wing cloth 16 is more met aerodynamic design after deploying, beneficial to the flight of wing 29.
Further, the inserting passage 27 that rear end is extended to by front end is provided with wing cloth 16, inserts the inserting of passage 27 Opening 28 is arranged on the front end of wing cloth 16；During installation, wing cloth support frame 26 is inserted into front end and the inserting passage 27 of wing cloth 16, It is simple in construction to realize that wing cloth 16 is set on wing cloth support frame 26, it is easy for installation, and it is easy to the folding and expansion of wing 29.
During wing 29 deploys or collapsed, first connecting rod component 1 and second connecting rod component 6, third connecting rod component 17 and fourth link component 20 can relatively rotate, second connecting rod component 6, third connecting rod component 17 and fourth link Component 20 drives wing cloth support frame 26 to be slided along slide rail set 25 by fixed cover 24；In the process, slide rail set 25 can also be with the One link assembly 1 relatively rotates, and fixed cover 24 can also connect with second connecting rod component 6, third connecting rod component 17 and the 4th Bar assembly 20 relatively rotates, in order to first connecting rod component 1 and second connecting rod component 6, third connecting rod component 17 and the Relative rotation between double leval jib component 20.Because fixed cover 24 is fixedly connected with wing cloth support frame 26, and fixed cover 24 is in Position on two link assemblies 6, third connecting rod component 17 and fourth link component 20 will not change, and fixed cover 24 is visual For the fixed point of wing cloth support frame 26；I.e. during wing 29 deploys or collapsed, different wing cloth support frames 26 and second connects Be respectively provided with fixed point on bar assembly 6, third connecting rod component 17 and fourth link component 20, realize different wing cloth support frames 26 it Between with the relative position on the length and width direction of wing 29 by preset direction move, avoid wing cloth support frame 26 and wing cloth 16 mutually pull, uniform force fully tensioned in the expansion rear wing cloth 16 of wing 29, and whole aerofoil surface smoothly causes air-flow Resistance is smaller when flowing through aerofoil surface, while wing cloth 16 is formd and is effectively protected, and makes the structure of wing 29 more reliable.
Specifically, wing cloth support frame 26 is plugged in fixed cover 24, the side wall of screw through fixed cover 24 supports wing cloth Frame 26 is locked, and to realize the fixation between wing cloth support frame 26 and fixed cover 24, also realizes wing cloth support frame 26 and fixed cover 24 Between fixed position can adjust；Installation linear bearing in slide rail set 25.The wing cloth support frame 26 carries default radian, Wing cloth 16 is set more to meet aerodynamic design after deploying, beneficial to the flight of wing 29.
In another embodiment, Figure 15 is referred to, it is preferable that the structure of the wing cloth support frame 26, it is similar from the side Long drop shape, leading edge 261 are small-radius arc, and top edge 262 is large radius arc, lower edge 263 be it is straight, three Wing cloth support frame 26 is formed while being connected smoothly；The wing cloth support frame 26 also includes bracing piece 264, the bracing piece 264 One end is connected with leading edge 261, and the other end is connected with top edge 262, and bracing piece 264 is arranged on fixed cover 24 and slide rail set 25 It is interior.Because wing cloth support frame 26 is inserted into the inserting passage 27 of wing cloth 16, the radian of wing cloth support frame 26 is exactly The radian of wing cloth 26, can by adjusting the radian of large radius arc and small-radius arc, to adjust the amplitude of the aerofoil of wing 29, Obtain optimal aeroperformance.Moreover, support effect to wing cloth 16 can be strengthened by setting up bracing piece 264.
Specifically, the wing cloth support component 23, including：
First group of wing cloth support component, the fixation of first group of wing cloth support component are set on the seven-link assembly 18, the The slide rail of one group of wing cloth support component is set on the 5th connecting rod 13 or first connecting rod 2, first group of wing cloth support component Wing cloth support frame is plugged in the fixed cover of first group of wing cloth support component and the slide rail set of first group of wing cloth support component；
Second group of wing cloth support component, the fixation of second group of wing cloth support component are set on the 8th connecting rod 19, the The slide rail of two groups of wing cloth support components is set on the 5th connecting rod 13 or first connecting rod 2, second group of wing cloth support component Wing cloth support frame is plugged in the fixed cover of second group of wing cloth support component and the slide rail set of second group of wing cloth support component；
3rd group of wing cloth support component, the fixation of the 3rd group of wing cloth support component are set on the third connecting rod 7, and the 3rd The slide rail of group wing cloth support component is set on the 5th connecting rod 13 or first connecting rod 2, the wing of the 3rd group of wing cloth support component Cloth support frame is plugged in the fixed cover of the 3rd group of wing cloth support component and the slide rail set of the 3rd group of wing cloth support component；
4th group of wing cloth support component, the fixation of the 4th group of wing cloth support component are set on the fourth link 8, and the 4th The slide rail of group wing cloth support component is set on the second connecting rod 3 or six-bar linkage 14, the wing of the 4th group of wing cloth support component Cloth support frame is plugged in the fixed cover of the 4th group of wing cloth support component and the slide rail set of the 4th group of wing cloth support component；
5th group of wing cloth support component, the fixation of the 5th group of wing cloth support component are set on the 9th connecting rod 21, the The slide rail of five groups of wing cloth support components is set on the second connecting rod 3 or six-bar linkage 14, the 5th group of wing cloth support component Wing cloth support frame is plugged in the fixed cover of the 5th group of wing cloth support component and the slide rail set of the 5th group of wing cloth support component；
6th group of wing cloth support component, the fixation of the 6th group of wing cloth support component are set on the tenth connecting rod 22, the The slide rail of six groups of wing cloth support components is set on the second connecting rod 3 or six-bar linkage 14, the 6th group of wing cloth support component Wing cloth support frame is plugged in the fixed cover of the 6th group of wing cloth support component and the slide rail set of the 6th group of wing cloth support component；
7th group of wing cloth support component, the fixation of the 7th group of wing cloth support component are set on the second connecting rod 3, and the 7th The slide rail of group wing cloth support component is set on the six-bar linkage 14, the wing cloth support frame inserting of the 7th group of wing cloth support component In the fixed cover of the 7th group of wing cloth support component and the slide rail set of the 7th group of wing cloth support component.
It is readily conceivable that, wing cloth support component 23 can also be increased or decreased on wing 29, to meet wing to various The demand of intensity, 25 installation site on link assembly is covered by adjusting fixed cover 24 and slide rail, and wing cloth support frame 26 exists Position in fixed cover 24, make wing that there is different expansion shapes, this is no longer going to repeat them.
Specifically, the fixed cover 24 of wing cloth support component is second on the outside of the one end of inboard first connecting rod 2 and wing The one end of connecting rod 3 is respectively filled outside one, on the connecting rod of remaining wave wire formed mounted in connecting rod of the leading edge of a wing.
The present invention also provides a kind of collapsible suspension formula aircraft.
Referring to Fig. 1 includes to Fig. 4, Fig. 8 and Fig. 9, the collapsible suspension formula aircraft 100：
Wing 29, the wing 29 are wing as described above；
Frame 30, one end of the first connecting rod 2 of the wing 29 and frame 30 are be hinged, to form the first junction 5；And
Slide assemblies 4, it is slidably connected with frame 30, the slide assemblies 4 and one end of drive link 10 are hinged, the cunning Dynamic component 4 has the first extreme position that control wing 29 is fully deployed and the second limit position for controlling wing 29 to pack up completely Put, first extreme position is between the first junction 5 and the second extreme position；
When the slide assemblies 4 slide from the first extreme position to the second extreme position direction, the wing 29 is packed up, When the slide assemblies 4 slide from the second extreme position to the first extreme position direction, the wing 29 deploys.
Specifically, in the present embodiment, when needing to use 100 flight of aircraft, slide assemblies 4 are from the second extreme position Slided to the first extreme position, driving wing 29 deploys, and when slide assemblies 4 slide into the first extreme position, wing 29 is complete Deploy, now can uses aircraft 100 to fly.Likewise, when needing to pack up in aircraft 100, slide assemblies 4 from First extreme position slides to the second extreme position, and driving wing 29 packs up (gathering), when slide assemblies 4 slide into second limit During position, wing 29 is packed up completely, now, is easily carried, transporter aircraft 100.
According to the present embodiment, those skilled in the art can be with it is readily conceivable that can be according to actual conditions in first limit Multiple expanded positions are set between position and the second extreme position, to allow slide assemblies 4 to drive wing 29 to deploy difference Angle, so as to meet different actual demands.
Collapsible suspension formula aircraft 100 of the present invention, by the way that one end of first connecting rod 2 and the first positioning seat 11 are hinged, And by setting the slide assemblies 4 with the first extreme position and the second extreme position in frame 30, and by drive link 10 One end be hinged with slide assemblies so that slide assemblies 4 can drive drive link 10 drive wing 29 deploy or pack up.Institute So that collapsible suspension formula aircraft 100 of the present invention is simple in construction, foldable, takes small volume, easy to operate；It is also easy to carry.
Be additionally, since collapsible suspension formula aircraft 100 of the present invention employ above-mentioned wing 29 all embodiments it is complete Portion's technical scheme, therefore all beneficial effects at least caused by the technical scheme with above-described embodiment, herein no longer one by one Repeat.
Further, refer to Fig. 8 and Fig. 9, the frame 30 include two parallel arrangement of slide bars 31, the first pedestal 32, Second pedestal 33, the first positioning seat 11 and the first connector 34 for positioning the first positioning seat 11, the He of the first pedestal 32 Second pedestal 33 is respectively arranged at the both ends of slide bar 31.The slide assemblies 4 are slidably disposed on two slide bars 31, and are slided Component 4 is between the first pedestal 32 and the second pedestal 33.First positioning seat 11 be slidably disposed on slide bar 31 and Between the pedestal 33 of slide assemblies 4 and second, on the first positioning seat 11, i.e., described first connects for first junction 5 The positioning seat 11 of bar 2 and first is be hinged, and first connector 34 is fixedly connected with the first positioning seat 11 and slide bar 31.
In the present embodiment, Figure 11 is referred to, first connector 34 is alignment pin, is opened on first positioning seat 11 Provided with two parallel arrangement of first slide openings 111, first positioning seat 11 is sheathed on two slide bars 31 by two first slide opening 111 On, the first positioning hole 112 with the insertion of wherein one first slide opening 111 is additionally provided with first positioning seat 11, described first connects Fitting 34 is inserted in the first positioning hole 112, and when the first positioning seat 11 slides into correct position, the first connector 34 is by first Positioning seat 11 is fixed.
In the present embodiment, the slide bar 31 is pipe, or the pipe or bar of other shapes, its quantity are two.Root According to the present embodiment, it is easy to expect, in other specific embodiments, the quantity of the slide bar 31 can also be one or three, Or other numerical value.
In the present embodiment, Fig. 1, Fig. 8 and Figure 13 are referred to, it is strong in order to strengthen first connecting rod 2 and the connection of frame 30 Degree, the frame 30 also include being used to connect first connecting rod 2 and the body cradle 35 of frame 30, and the body cradle 35 is pacified including rotating shaft Dress portion 36 and the inserting rod 37 being convexly equipped on rotating shaft installation portion 36, the rotating shaft installation portion 36 are rotatable by rotating shaft (figure is not marked) Be arranged on the first positioning seat 11, the inserting rod 37 fixes the one end for being inserted in first connecting rod 2, so that first connecting rod 2 can What is rotated is connected with the first positioning seat 11.
Collapsible suspension formula aircraft 100 of the present invention, by setting the first positioning seat 11 and the first connector 34 the Position of the one end of one connecting rod 2 in frame 30 becomes adjustable, so as to widen the scope of application of aircraft 100, to fly Row device 100 can adapt to different flying scenes according to the fixed position of actual conditions adjustment first connecting rod 2.
Further, Fig. 1, Fig. 2, Fig. 8 and Fig. 9 are referred to, the collapsible suspension formula aircraft 100 also includes being used for The first power set 38 for driving slide assemblies 4 to slide, first power set 38 are between two slide bars 31；Described first Power set 38 include the first motor 39, the screw rod 40 being connected with the output shaft (figure is not marked) of the first motor 39 and fitted with screw rod 40 The nut 41 matched somebody with somebody, first motor 39 are arranged on the first pedestal 32, and the nut 41 is arranged on slide assemblies 4, described Output shaft and screw rod 40 for the first motor 39 are offered on first pedestal 32 by through hole (figure is not marked), the screw rod 40 passes through It is connected after the through hole with nut 41；Offered on the slide assemblies 4 with the screwed hole of the nut 41 (figure is not marked) even Logical avoiding space, passed through with for screw rod 40.
In this embodiment, it is preferred that the nut 41 is ball nut, the screw rod 40 collectively forms rolling with nut 41 Ballscrew drive mechanism, the convert rotational motion that the first motor 39 is exported is linear motion, to realize slide assemblies 4 in slide bar Slided on 31.
Specifically, after the transmitter span is opened or packs up signal, the drive screw 40 of the first motor 39 rotates, the nut 41 are arranged on slide assemblies 4, are coordinated by screw rod 40 and nut 41, are driving Slide Group by the convert rotational motion of screw rod 40 Part 4 slide linear motion, and by opened up on slide assemblies 4 avoiding space connected with the screwed hole of the nut 41 with Pass through for screw rod 40 so that the conversion process is achieved, so as to realize the expansion of wing 29 or pack up.
Collapsible suspension formula aircraft 100 of the present invention, by setting the first power set 38 in frame 30, it is possible to achieve Wing 29 is packed up in automation expansion so that the expansion of wing 29 or pack up it is more convenient, to user comfortably to use Experience at family.And the present invention realizes the slip of slide assemblies 4 by the cooperation of screw rod 40 and nut 41 so that the knot of aircraft 100 Structure is simple, easy to operate.
Further, the collapsible suspension formula aircraft 100 also includes suspension arrangement 42, and the suspension arrangement 42 includes Suspension arm 43, the positioning seat 45 of bearing bar 44 and second, second positioning seat 45 are sheathed on two slide bars 31, second positioning Seat 45 has the first suspension rotating shaft 50 of the setting that is inclined upwardly by the plane where predetermined angle and two slide bar 31, the suspension arm 43 one end is rotatably installed in the first suspension rotating shaft 50, and one end of the bearing bar 44 is rotatably installed on suspension arm 43 other end.
In the present embodiment, Fig. 8 and Figure 12 are referred to, based on the identical principle of the first positioning seat 11, second positioning Seat 45 offers two parallel arrangement of second slide openings 48, and second positioning seat 45 is sheathed on two cunnings by two second slide opening 48 On bar 31, the second positioning hole 49 with the insertion of wherein one second slide opening 48 is additionally provided with second positioning seat 45, by certain Position pin is inserted in the second positioning hole 49 to realize the positioning to the second positioning seat 45.
In the present embodiment, the first suspension that second positioning seat 45 has the setting that is with respect to the horizontal plane inclined upwardly turns Axle 50 and the first mounting surface 46 for tilting down setting, first mounting surface 46 are described outstanding perpendicular to the first suspension rotating shaft 50 The one end of upper arm 43 is correspondingly arranged on the first suspension turn hole (figure is not marked), and the suspension arm 43 is rotatable by the first suspension turn hole Be arranged on first suspension rotating shaft 50 on.By said structure set can the suspension arm 43 rotate down when, can be with Expansion is opened；It should be pointed out that for above-mentioned purpose, it is also possible that setting：Second positioning seat have by predetermined angle with Plane where two slide bars be inclined upwardly setting first suspension turn hole, described suspension arm one end be correspondingly arranged on the first suspension turn Axle.
Referring to Fig. 8, when needing to use suspension arrangement 42, driving suspension arm 43 rotates around the first suspension rotating shaft 50, and To the opening position perpendicular to slide bar 31, the other end for being embodied in suspension arm 43 rotates down for rotation, because of the first suspension rotating shaft 50 are obliquely installed, so expanding exhibition to the direction away from slide bar 31 while the other end of suspension arm 43 shows as rotating down Open, then rotate bearing bar 44 and turn to horizontal level, now hang wall 43 and form an inclined L-shaped structure with bearing bar 44, So that user grasps in flight.
Referring to Fig. 2, when that need not use suspension arrangement 42, driving bearing bar 44 turns to flat with intimate suspension arm 43 Capable opening position, then drive suspension arm 43 to be rotated around the first suspension rotating shaft 50, and rotate to the position for being approximately parallel to slide bar 31 Place is put, the other end for being embodied in suspension arm 43 is rotated up, because the first suspension rotating shaft 50 is obliquely installed, so suspension arm 43 The other end show as drawing close and packing up to the direction close to slide bar 31, now the suspension arrangement is packed up, to facilitate aircraft 100 Carrying and transport.
Collapsible suspension formula aircraft 100 of the present invention, by setting the relative place of two slide bar 31 on the second positioning seat 45 Plane be inclined upwardly the first suspension rotating shaft 50 of setting, and suspension arm 43 is rotatably arranged in the first suspension rotating shaft 50 On so that when suspension arm 43 collapses, the other end of suspension arm 43 is drawn close to slide bar 31, is accounted for so as to reduce when suspension arm 43 collapses Space, consequently facilitating the carrying and transport of aircraft 100.
In a particular embodiment, the quantity of the suspension arm 43 can be one, or two, accordingly, described The quantity that bearing bar 44 and first hangs rotating shaft 50 is adapted with suspension arm.In the present embodiment, the quantity of the suspension arm 43 For two, the quantity that the bearing bar 44 and first hangs rotating shaft 50 is also two.
In the present embodiment, the suspension arrangement 42 also includes the second connector 47, and second connector 47 is used for will The other end of two bearing bars 44 is detachably connected.Specifically, second connector 47 is an adapter sleeve, when suspension arrangement 42 is opened up When opening, the other end that second connector 47 is set in two bearing bars 44 links together two bearing bars 44.It is outstanding when needing When hang device 42 is packed up, the second connector 47 is moved to wherein on a bearing bar 44 so that two bearing bars 44 separate.
Further, Fig. 8 to Figure 10 is referred to, the slide assemblies 4 include：
First sliding part 51, slideably it is sheathed on two slide bars 31 and is located at the first positioning seat 11 and the second positioning seat 45 Between, first sliding part 51 and one end of drive link 10 are hinged；
Second sliding part 52, be slideably sheathed on two slide bars 31 and positioned at the second positioning seat 45 and the first pedestal 32 it Between, the nut 41 is arranged on the second sliding part 52, is offered on second sliding part 52 and is connected with the screwed hole of nut 41 Logical the first avoid holes (figure is not marked), second sliding part 52 have and the described first suspension rotating shaft 50 identical second Hang rotating shaft 521；And
Gangbar 54, is arranged in the second positioning seat 45, and the both ends of the gangbar 54 respectively with the first sliding part 51 and Second sliding part 52 is fixedly connected, and to realize the linkage of the first sliding part 51 and the second sliding part 52, is opened in the gangbar 54 Provided with the second avoid holes connected with the first avoid holes (figure is not marked)；
The suspension arrangement 42 also includes transmission arm 55, and one end of the transmission arm 55 is rotatably arranged on the second suspension In rotating shaft 521, the other end is be hinged with suspension arm 43.
In the present embodiment, based on the identical principle of the first positioning seat 11, two are offered simultaneously on first sliding part 51 The 3rd slide opening 56 that row is set, first sliding part 51 is sheathed on two slide bars 31 by two the 3rd slide opening 56, and described the The 3rd positioning hole 57 with the insertion of wherein one the 3rd slide opening 56 is additionally provided with one sliding part 51, the 3rd is inserted in by an alignment pin To realize the positioning to the first sliding part 51 in positioning hole 57, so as to position with realizing the sliding position to slide assemblies 4, so as to Realize the control of the expansion degree to wing 29.
In the present embodiment, constructed based on the identical of the second positioning seat 45, second sliding part 52 has and the first peace The second coplanar mounting surface 53 of dress face 46, second mounting surface 53 hang rotating shaft 521 perpendicular to second, the transmission arm 55 One end is correspondingly arranged on the second suspension turn hole (figure is not marked), and the transmission arm 55 is rotatably installed by the second suspension turn hole In the second suspension rotating shaft 521.
In the present embodiment, second positioning seat 45 is described between the first sliding part 51 and the second sliding part 52 The 3rd avoid holes 58 are additionally provided with second positioning seat 45, the gangbar 54 is arranged in the 3rd avoid holes 58, so that Slide Group Part 4 is slided.
In the present embodiment, second sliding part 52 and the structure of the second positioning seat 45 are same or similar, the gangbar 54 be a hollow stem, and first avoid holes and the second avoid holes are the avoiding space on the slide assemblies 4.
The operation principle of collapsible suspension formula aircraft 100 of the present invention is：The drive screw 40 of first motor 39 rotates, described Screw rod 40 drives the second sliding part 52 to be slided along slide bar 31 to close to or to the direction away from the first positioning seat 11 by nut 41, Second sliding part 52 drives the first sliding part 51 to realize linkage, the second sliding part 52 driving drive link therewith by gangbar 54 10 one end is moved to close to or to the direction away from the first positioning seat 11, so as to realize the expansion of wing 29 or pack up.Meanwhile The screw rod 40 relatively moves in the first avoid holes and the second avoid holes.Second sliding part 52 passes through transmission arm 55 simultaneously Driving suspension arm 43 deploys or packed up；Moreover, the reasons why identical with actuating arm 43 is based on, and when the transmission arm 55 is packed up, transmission The other end of arm 55 is drawn close to slide bar 31, so as to reduce the space taken when transmission arm 55 collapses, consequently facilitating aircraft 100 Carrying and transport.
Set by said structure so that collapsible suspension formula aircraft 100 of the present invention, it is simple in construction, it is easy to operate, account for Small with space, carrying is also convenient for.
Further, the nut 41 is detachably mounted on the second sliding part 52.Specifically, when selection motorized motions When wing 29 deploys or collapsed, nut 41 is fixed on the second sliding part 52；When motor out of power, or during other situations, also may be used To select manual actuation wing 29 to deploy or collapse, fixed by the sliding part 52 of nut 41 and second releases, then toward the first base 32 directions of seat rotate suspension arm 43 manually, are coordinated by suspension arm 43 with transmission arm 55 to drive wing 29 to deploy or collapse.
Further, Fig. 1 and Fig. 8 are referred to, the collapsible suspension formula aircraft 100 also includes being used to further enhance The line fixation kit 59 of the stability of aircraft 100, the line fixation kit 59 include fixing line (not shown) and coiling runner 60； Steel wire etc. typically can be selected in the fixing line；The coiling runner 60 is from middle part to the gradual thickening in both ends, to form fixation Line wound portion 61, the fixing hole 62 for being fixed for fixing line one end, the coiling runner 60 are offered in the wound portion 61 On be additionally provided with wind spring (not shown) for automatic takeup；The coiling runner 60 is rotatably arranged at the another of suspension arm 43 End；The fixing line other end is detachably mounted on wing 29.
Specifically, when wing deploys, the fixing line other end is fixed on one end of the remote frame 30 of wing 29, because Pulling force when wing deploys between suspension arm 43 and wing 29 is more than the torsion of wind spring, so the concomitant rotation of coiling runner 60, puts Go out to be wound on the fixing line on coiling runner 60, the length of the fixing line is pre-set so that fixing line discharge after just Wing 29 is tensed, so as to strengthen the strength and stability of wing 29, and then strengthens the security of aircraft 100.When wing is packed up When, coiling runner 60 rotates under the drive of wind spring to preset direction, and fixing line is wound into coiling runner 60 by pilot hole 67 On.
Further, the line fixation kit 59 also includes prerotation vane 66, and the prerotation vane 66 is annularly set, described to lead It is connected respectively with two butt ends of coiling runner 60 to the both ends of piece 66, to be formed fixing line winding with the fixing line wound portion 61 Space.The middle part of the prerotation vane 66 offers pilot hole 67, and the pilot hole 67 is relative with fixing hole 62, the fixing line One end is fixed through the pilot hole 67 with fixing hole 62.The pilot hole 67 is used to be oriented to fixing line, and pine is received to facilitate Fixing line.
Further, Fig. 1, Fig. 2, Fig. 8 and Fig. 9, Figure 14 are referred to, the collapsible suspension formula aircraft 100 also wraps Rotor assemblies 63 are included, the rotor assemblies 63 are installed on the head of aircraft 100.
The second motor 64 that the rotor assemblies 63 include rotor 65 and drive rotor 65 to rotate, second motor 64 Positioned in the side away from the first pedestal 32 of the second pedestal 33.
Collapsible suspension formula aircraft 100 of the present invention, by setting rotor assemblies 63, when can be 100 flight of aircraft, carry For power.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the scope of the invention, it is every at this Under the inventive concept of invention, the equivalent structure transformation made using description of the invention and accompanying drawing content, or directly/use indirectly It is included in other related technical areas in the scope of patent protection of the present invention.

Claims (10)

  1. A kind of 1. wing of collapsible suspension formula aircraft, it is characterised in that including first connecting rod component, the first connecting rod group Part includes：
    First connecting rod, one end of the first connecting rod is used to be connected with the frame of collapsible suspension formula aircraft, to form first Junction；
    Second connecting rod, one end of the second connecting rod are articulated with the other end of the first connecting rod；
    Drive link, one end of the drive link are used to be connected with the slide assemblies of collapsible suspension formula aircraft, to be formed Second junction, the other end of the drive link are articulated with the first connecting rod, to form the second of the first connecting rod the hinge Meet place；
    5th connecting rod, the 5th connecting rod are arranged side by side with the first connecting rod, and one end of the 5th connecting rod is articulated with described Between the both ends of drive link, the other end of the 5th connecting rod is articulated with one end of the second connecting rod；
    Six-bar linkage, the six-bar linkage are arranged side by side with the second connecting rod, and one end of the six-bar linkage is articulated with described The other end of the other end of first connecting rod and the 5th connecting rod；And
    Shrinking connecting-rod, the shrinking connecting-rod are articulated with the other end of the second connecting rod and the other end of the six-bar linkage.
  2. 2. the wing of collapsible suspension formula aircraft as claimed in claim 1, it is characterised in that the collapsible suspension formula flies The wing of row device also includes：
    Second connecting rod component, including third connecting rod and fourth link, one end of the third connecting rod are articulated with described first and connected Bar and the 5th connecting rod, the other end of the third connecting rod are articulated with one end of the fourth link, the fourth link it is another One end is articulated with the second connecting rod and six-bar linkage；
    Third connecting rod component, it is arranged between the first connecting rod and the third connecting rod, the third connecting rod component includes the Seven-link assembly and the 8th connecting rod, one end of the seven-link assembly is articulated with the first connecting rod and the 5th connecting rod, another End is articulated with one end of the 8th connecting rod, and the other end of the 8th connecting rod is articulated with the third connecting rod；And
    Fourth link component, it is arranged between the second connecting rod and the fourth link, the fourth link component includes the Nine connecting rods and the tenth connecting rod, one end of the 9th connecting rod are articulated with fourth link, and the other end is articulated with one end of the tenth connecting rod, institute The other end for stating the tenth connecting rod is articulated with the second connecting rod and the six-bar linkage.
  3. 3. the wing of collapsible suspension formula aircraft as claimed in claim 2, it is characterised in that the collapsible suspension formula flies The wing of row device also includes some wing cloth support components, and the wing cloth support component includes：
    Fixed cover, the fixed cover are rotatably arranged on the wing, and are set along the length direction of the wing；
    Slide rail set, the slide rail set are rotatably arranged on the wing, and are set along the length direction of the wing；And
    Wing cloth support frame, the wing cloth support frame carries default radian, and fixation is plugged in the fixed cover, the wing cloth Support frame is also inserted into the slide rail set, and when the wing deploys or collapses, the wing cloth support frame is in the slide rail set Interior slip；
    The wing cloth support frame is provided with fixed fixing point in fixed cover, can combine, carry out by the fixing point pre-set It is fixed, to adapt to different airfoil shapes.
  4. 4. the wing of collapsible suspension formula aircraft as claimed in claim 3, it is characterised in that the wing cloth support component, Including：
    First group of wing cloth support component, the fixation of first group of wing cloth support component are set on the seven-link assembly, first group of wing The slide rail of cloth support component is set on the first connecting rod or the 5th connecting rod, the wing cloth branch of first group of wing cloth support component Support is plugged in the fixed cover of first group of wing cloth support component and the slide rail set of first group of wing cloth support component；
    Second group of wing cloth support component, the fixation of second group of wing cloth support component are set on the 8th connecting rod, second group of wing The slide rail of cloth support component is set on the first connecting rod or the 5th connecting rod, the wing cloth branch of second group of wing cloth support component Support is plugged in the fixed cover of second group of wing cloth support component and the slide rail set of second group of wing cloth support component；
    3rd group of wing cloth support component, the fixation of the 3rd group of wing cloth support component are set on the third connecting rod, the 3rd group of wing The slide rail of cloth support component is set on the first connecting rod or the 5th connecting rod, the wing cloth branch of the 3rd group of wing cloth support component Support is plugged in the fixed cover of the 3rd group of wing cloth support component and the slide rail set of the 3rd group of wing cloth support component；
    4th group of wing cloth support component, the fixation of the 4th group of wing cloth support component are set on the fourth link, the 4th group of wing The slide rail of cloth support component is set on the second connecting rod or the six-bar linkage, the wing cloth branch of the 4th group of wing cloth support component Support is plugged in the fixed cover of the 4th group of wing cloth support component and the slide rail set of the 4th group of wing cloth support component；
    5th group of wing cloth support component, the fixation of the 5th group of wing cloth support component are set on the 9th connecting rod, the 5th group of wing The slide rail of cloth support component is set on the second connecting rod or the six-bar linkage, the wing cloth branch of the 5th group of wing cloth support component Support is plugged in the fixed cover of the 5th group of wing cloth support component and the slide rail set of the 5th group of wing cloth support component；
    6th group of wing cloth support component, the fixation of the 6th group of wing cloth support component are set on the tenth connecting rod, the 6th group of wing The slide rail of cloth support component is set on the second connecting rod or the six-bar linkage, the wing cloth branch of the 6th group of wing cloth support component Support is plugged in the fixed cover of the 6th group of wing cloth support component and the slide rail set of the 6th group of wing cloth support component；And
    7th group of wing cloth support component, the fixation of the 7th group of wing cloth support component are set on the second connecting rod, the 7th group of wing The slide rail of cloth support component is set on the six-bar linkage, and the wing cloth support frame of the 7th group of wing cloth support component is plugged in the 7th The fixed cover of group wing cloth support component and the slide rail set of the 7th group of wing cloth support component.
  5. 5. the wing of collapsible suspension formula aircraft as claimed in claim 3, it is characterised in that the collapsible suspension formula flies The wing of row device also includes wing cloth, and the wing cloth is provided with the inserting passage that rear end is extended to by front end, the inserting passage Inserting opening is arranged on the front end of the wing cloth, and the wing cloth support frame is inserted into the inserting passage of the wing cloth.
  6. A kind of 6. collapsible suspension formula aircraft, it is characterised in that including：
    Wing, the wing are the wing as described in any one of claim 1 to 5；
    Frame, one end of the first connecting rod of the wing are hinged with the frame, to form the first junction；And
    Slide assemblies, it is connected with the housing slide, the slide assemblies and one end of the drive link are hinged, the slip Component has the second limit position that the first extreme position for controlling the wing to be fully deployed and the control wing are packed up completely Put, first extreme position is between first junction and second extreme position；
    When the slide assemblies slide from first extreme position to the second extreme position direction, the wing is received Rise, when the slide assemblies slide from second extreme position to the first extreme position direction, the wing expansion.
  7. 7. collapsible suspension formula aircraft as claimed in claim 6, it is characterised in that it is parallel arrangement of that the frame includes two Slide bar, the first pedestal, the second pedestal, the first positioning seat and the first connector for positioning first positioning seat, described One pedestal and the second pedestal are respectively arranged at the both ends of two slide bars；
    The slide assemblies are slidably disposed on two slide bars, and the slide assemblies are located at first pedestal and Between two pedestals；
    First positioning seat be slidably disposed on the slide bar and positioned at the slide assemblies and second pedestal it Between, first junction on first positioning seat, first connector be fixedly connected first positioning seat with The slide bar.
  8. 8. collapsible suspension formula aircraft as claimed in claim 7, it is characterised in that the collapsible suspension formula aircraft is also Including the first power set for driving the slide assemblies to slide, first power set be located at two slide bars it Between；
    First power set include the first motor, with the screw rod of the output axis connection of first motor and with the screw rod The nut of adaptation, first motor are arranged on first pedestal, and the nut is arranged on the slide assemblies, described Screw rod coordinates with the nut, and the avoiding space connected with the screwed hole of the nut is offered on the slide assemblies, to Pass through for the screw rod.
  9. 9. collapsible suspension formula aircraft as claimed in claim 8, it is characterised in that the collapsible suspension formula aircraft is also Including suspension arrangement, the suspension arrangement includes suspension arm, bearing bar and the second positioning seat, and second positioning seat is sheathed on two On the slide bar, there is second positioning seat plane as predetermined angle and where two slide bars to be inclined upwardly the of setting One suspension rotating shaft, one end of the suspension arm are rotatably installed in the first suspension rotating shaft, one end of the bearing bar It is rotatably installed on the other end of the suspension arm.
  10. 10. collapsible suspension formula aircraft as claimed in claim 9, it is characterised in that the slide assemblies include：
    First sliding part, slideably it is sheathed on two slide bars and positioned at first positioning seat and second positioning seat Between, first sliding part and one end of the drive link are hinged；
    Second sliding part, slideably it is sheathed on two slide bars and between second positioning seat and the first pedestal, The nut is arranged at second sliding part, and connected with the screwed hole of the nut is offered on second sliding part One avoid holes, second sliding part have and the identical second suspension rotating shaft of the described first suspension rotating shaft；And
    Gangbar, is arranged in second positioning seat, and the both ends of the gangbar respectively with first sliding part and second Sliding part is connected, and the second avoid holes connected with first avoid holes are offered in the gangbar；
    The suspension arrangement also includes transmission arm, and one end of the transmission arm is rotatably arranged on the described second suspension rotating shaft On, the other end is hinged with the suspension arm.
CN201710799616.3A 2017-09-06 2017-09-06 Wing of foldable suspension type aircraft and foldable suspension type aircraft Active CN107719633B (en)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109760833A (en) * 2019-01-28 2019-05-17 胡高 Can take down the exhibits resilient wing
CN110371282A (en) * 2019-07-24 2019-10-25 安徽工业大学 A kind of telescopic type folding wing
CN115188263A (en) * 2022-06-09 2022-10-14 深圳市华星光电半导体显示技术有限公司 Multi-fold folding assembly and multi-fold display device
CN115675832A (en) * 2022-12-27 2023-02-03 成都航空职业技术学院 Multi-section type space quadrilateral wing framework and bionic aircraft

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US3743218A (en) * 1968-06-28 1973-07-03 T Sweeney Semi-rigid airfoil for airborne vehicles
WO2008125868A2 (en) * 2007-04-16 2008-10-23 Peter Jeremy Dodd Aircraft
DE202011005401U1 (en) * 2011-04-18 2011-06-29 Schiller, Sepp, 81371 Wing skeleton for ornithopter
CN105947179A (en) * 2016-05-20 2016-09-21 天津大学 Folding mechanism for changing wingspan of wings
CN205675229U (en) * 2016-04-05 2016-11-09 及兰平 Folding wing

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Publication number Priority date Publication date Assignee Title
US3743218A (en) * 1968-06-28 1973-07-03 T Sweeney Semi-rigid airfoil for airborne vehicles
WO2008125868A2 (en) * 2007-04-16 2008-10-23 Peter Jeremy Dodd Aircraft
DE202011005401U1 (en) * 2011-04-18 2011-06-29 Schiller, Sepp, 81371 Wing skeleton for ornithopter
CN205675229U (en) * 2016-04-05 2016-11-09 及兰平 Folding wing
CN105947179A (en) * 2016-05-20 2016-09-21 天津大学 Folding mechanism for changing wingspan of wings

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109760833A (en) * 2019-01-28 2019-05-17 胡高 Can take down the exhibits resilient wing
CN109760833B (en) * 2019-01-28 2020-10-09 胡高 Foldable elastic wing
CN110371282A (en) * 2019-07-24 2019-10-25 安徽工业大学 A kind of telescopic type folding wing
CN115188263A (en) * 2022-06-09 2022-10-14 深圳市华星光电半导体显示技术有限公司 Multi-fold folding assembly and multi-fold display device
CN115188263B (en) * 2022-06-09 2023-10-31 深圳市华星光电半导体显示技术有限公司 Multi-fold folding assembly and multi-fold display device
CN115675832A (en) * 2022-12-27 2023-02-03 成都航空职业技术学院 Multi-section type space quadrilateral wing framework and bionic aircraft

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