CN205221095U - Flexible wing and adopt VTOL aircraft of this wing - Google Patents
Flexible wing and adopt VTOL aircraft of this wing Download PDFInfo
- Publication number
- CN205221095U CN205221095U CN201521006961.XU CN201521006961U CN205221095U CN 205221095 U CN205221095 U CN 205221095U CN 201521006961 U CN201521006961 U CN 201521006961U CN 205221095 U CN205221095 U CN 205221095U
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- wing
- leading edge
- trailing edge
- support beam
- slide
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Abstract
The utility model relates to an aircraft wing specifically is a flexible wing and adopt VTOL aircraft of this wing. The problem of present VTOL aircraft span area receive the unstable technique of windage gesture greatly easily under the VTOL state is solved. A VTOL aircraft, adopts the flexible wing as the integral type fuselage, the flexible wing includes leading edge and wing trailing edge, realize expanding and contract through the slip subassembly between leading edge and the wing trailing edge, be connected with folding covering between leading edge and the wing trailing edge. The utility model discloses a deformation wing chord length can be stretched out and drawn back and changed the size, changes wing area, fused fixed -wing aircraft and many gyroplane's advantage simultaneously, realized that two kinds of flight modes in the same aircraft switch the function of flight wantonly.
Description
Technical field
The utility model relates to a kind of aircraft wing, is specially a kind of deformable wing and adopts the vertically taking off and landing flyer of this wing.
Background technology
" ProjectWing " prototype of Google is the single-blade unmanned plane of 1.5 meters wide, can take off vertically, transfer level to during flight.But when this aircraft flies with plumbness, roomy wing area is subject to windage, and make the stability when plumbness is flown, operability is bad.
In prior art, there is the method being changed wing area by inflation.Conventional inflatable wing has the shortcomings such as rigidity of structure strength character difference: when wing adopts high aspect ratio configuration, in large wing load situation, due to inflatable wing poor rigidity, wing is caused to be out of shape serious, greatly reduce pneumatic efficiency and operator perforniance, and in order to pursue the good rigidity of structure, adopting again the method increasing profile thickness, this brings again extra resistance; During inflation, expansion direction is spanwise simultaneously, and development rate is slow.
Summary of the invention
The utility model be solve current vertically taking off and landing flyer span area greatly under vertical takeoff and landing state easy by wind affect the technical matters causing unsteady attitude, a kind of deformable wing is provided and adopts the vertically taking off and landing flyer of this wing.
Deformable wing described in the utility model realizes by the following technical solutions: a kind of deformable wing, comprises the leading edge of a wing and trailing edge; Realize launching and shrinking by slide assemblies between the described leading edge of a wing and trailing edge; Folding covering is connected with between the described leading edge of a wing and trailing edge.
Deformable wing described in the utility model can change the size of wing quickly and easily.After the leading edge of a wing is separated with trailing edge, covering can be opened; When needs reduce wing area, covering is just folded, and is similar to the folding of fan.
Further, described slide assemblies comprise be located at wing before the slide bar of (afterwards) edge inside and slide rail combine, described slide rail has multiple and arranged in parallel, each slide rail is equipped with a slide bar; The other end of all slide bars is all connected with (front) edge front end after wing; A slide bar is had at least to be provided with tooth bar and to be furnished with the gear be meshed with tooth bar; Described slide assemblies also comprise be located at wing before the miniature motor of (afterwards) edge inside; Described miniature motor is by gear driving rack and then drive all slide bars to slide along respective slide rail, realizes expansion and the contraction of the leading edge of a wing and trailing edge; Between multiple slide bar, movable sleeve is provided with multiple support beam perpendicular with slide bar, and the support beam being positioned at forefront is connected by rope with leading edge of a wing rear end, and the front end of the support beam and trailing edge that are positioned at rearmost is connected by rope; Be connected by rope between adjacent supports beam; The described front end of folding covering is connected with the rear end of the leading edge of a wing, and the rear end of folding covering is connected with the front end of trailing edge, and the centre portion of folding covering is all connected with support beam top.
Described slide assemblies comprise be located at wing before the multiple pneumatic or hydraulic push rod of (afterwards) edge inside, movable end that is pneumatic or hydraulic push rod is arranged in parallel and be all connected with (front) edge front end after wing; Pneumatic or hydraulic push rod passes through the flexible expansion and the contraction that realize the leading edge of a wing and trailing edge; Between the movable end of multiple pneumatic or hydraulic push rod, movable sleeve is provided with multiple support beam vertical with movable end; The support beam being positioned at forefront is connected by rope with leading edge of a wing rear end, and the front end of the support beam and trailing edge that are positioned at rearmost is connected by rope; Be connected by rope between adjacent supports beam; The described front end of folding covering is connected with the rear end of the leading edge of a wing, and the rear end of folding covering is connected with the front end of trailing edge, and the centre portion of folding covering is all connected with support beam top.
By slide bar and slide rail or pneumatic, that hydraulic push rod can realize the leading edge of a wing and trailing edge expansion and contraction, achieve the quick adjusting of wing area.Mulit-point Connection between covering and support beam and wing front and rear edge, when wing shrinks, progressively launch under the drive (passing through rope) of support beam (afterwards) edge before wing, the covering be connected with wing front and rear edge and support beam is then similar to fan and is folded like that; Covering is all connected with support beam by one side, to strengthen the intensity after expansion.In like manner pneumatic or hydraulic push rod and covering are also similar connection modes.
Vertically taking off and landing flyer described in the utility model adopts following technical scheme to realize: a kind of vertically taking off and landing flyer, described aircraft adopts deformable wing as integral type fuselage, front fuselage is provided with a pair screw propeller, and afterbody is provided with empennage and yaw rudder.
The Variable Geometry Wing of novel changable shape wing vertical landing aircraft described in the utility model adopts the anatomical connectivity of similar telescopic atenna between the leading edge of a wing and trailing edge, covering is laid on these telescopic beams, stretchs out rear intensity height and can meet large load requirements.
Variable Geometry Wing chord length designed by the utility model can telescopic variation size, changes wing area; Merge the advantage of fixed wing aircraft and many autogiros simultaneously, achieve the function of same aircraft two kinds of offline mode any switching laws flights.
The utility model can also make up many autogiros in speed, voyage, the shortcoming on load carrying ability, makes aircraft power transmission structure greatly simplify simultaneously, improve stability and safety compared with tiltrotor.The transport of U.S. army V-22 osprey is exactly a kind of tiltrotor, and media repeatedly report that it has an accident, and reason appears at power aspect mostly.To sum up, the application has aly merged the course of new aircraft of many rotors and Fixed Wing AirVehicle advantage, gathers around and have great advantage on power-line patrolling etc.
The utility model application prospect:
(1) electric inspection process is widely used in: substitute original manpower unfolding hauling rope stringing mode and staff scene tour electric power circuit, these work novel unmanned plane one frame can complete;
(2) Post disaster relief: after earthquake, disaster area can be limited for the place of fixed wing aircraft landing, and goods and materials can not be transported to the place nearest from front, is transported to periphery airport often and delivers to destination by transport vehicle or other method of shipment again; But although helicopter can vertical landing flying speed be not high have impact on travelling speed.Newly-designed aircraft takeoff landing is not high to site requirements, then can land near a line rescue group and save the intermediate transition time thus rapid delivery goods and materials; Can with the mode flight of fixed-wing after taking off, flying speed can reach very high;
(3) anti-terrorism and warlike operation is applied to.
Accompanying drawing explanation
Plan structure schematic diagram after Fig. 1 changeability wing described in the utility model launches.
Side-looking structural representation after Fig. 2 changeability wing described in the utility model launches.
Perspective view after Fig. 3 changeability wing described in the utility model launches.
Plan structure schematic diagram after Fig. 4 changeability wing described in the utility model shrinks.
Side-looking structural representation after Fig. 5 changeability wing described in the utility model shrinks.
Perspective view after Fig. 6 changeability wing described in the utility model shrinks.
The connection partial schematic diagram of Fig. 7 slide bar described in the utility model and slide track component and wing.
The connection diagram of Fig. 8 rope described in the utility model and support beam and wing front and rear edge.
The 1-leading edge of a wing, 2-trailing edge, 3-slide assemblies, the folding covering of 4-, 5-screw propeller, 6-empennage, 7-yaw rudder, the pneumatic or hydraulic push rod of 8-, 9-support beam, 10-slide bar, 11-rope.
Detailed description of the invention
A kind of deformable wing, comprises the leading edge of a wing 1 and trailing edge 2; Realize launching and shrinking by slide assemblies 3 between the described leading edge of a wing 1 and trailing edge 2; Folding covering 4 is connected with between the described leading edge of a wing 1 and trailing edge 2.
Described slide assemblies 3 comprises the slide bar 10 being located at the leading edge of a wing 1 inside and combines with slide rail, and described slide rail has multiple and arranged in parallel, each slide rail is equipped with a slide bar 10; The other end of all slide bars 10 is all connected with trailing edge 2 front end; (0 is provided with tooth bar and is furnished with the gear be meshed with tooth bar to have a slide bar at least; Described slide assemblies also comprises the miniature motor being located at the leading edge of a wing 1 inside; Described miniature motor is by gear driving rack and then drive all slide bars 10 to slide along respective slide rail, realizes expansion and the contraction of the leading edge of a wing and trailing edge; Between multiple slide bar 10, movable sleeve is provided with multiple support beam 9 perpendicular with slide bar 10, and the support beam 9 being positioned at forefront is connected by rope 11 with the leading edge of a wing 1 rear end, and the front end of the support beam 9 and trailing edge 2 that are positioned at rearmost is connected by rope 11; Be connected by rope 11 between adjacent supports beam 9; The front end of described folding covering 4 is connected with the rear end of the leading edge of a wing 1, and the rear end of folding covering 4 is connected with the front end of trailing edge 2, and the centre portion of folding covering 4 is all connected with support beam 9 top.
Described slide assemblies comprises and is located at the multiple pneumatic of the leading edge of a wing 1 inside or hydraulic push rod 8, and movable end that is pneumatic or hydraulic push rod 8 is arranged in parallel and be all connected with trailing edge 2 front end; Pneumatic or hydraulic push rod 8 passes through the flexible expansion and the contraction that realize the leading edge of a wing and trailing edge; Between the movable end of multiple pneumatic or hydraulic push rod 8, movable sleeve is provided with multiple support beam 9 vertical with movable end; The support beam 9 being positioned at forefront is connected by rope 11 with the leading edge of a wing 1 rear end, and the front end of the support beam 9 and trailing edge 2 that are positioned at rearmost is connected by rope 11; Be connected by rope 11 between adjacent supports beam 9; The front end of described folding covering 4 is connected with the rear end of the leading edge of a wing 1, and the rear end of folding covering 4 is connected with the front end of trailing edge 2, and the centre portion of folding covering 4 is all connected with support beam 9 top.
Described slide assemblies comprises the slide bar 10 being located at trailing edge 2 inside and combines with slide rail, and described slide rail has multiple and arranged in parallel, each slide rail is equipped with a slide bar 10; The other end of all slide bars 10 is all connected with the leading edge of a wing 1 rear end; A slide bar 10 is had at least to be provided with tooth bar and to be furnished with the gear be meshed with tooth bar; Described slide assemblies also comprises the miniature motor being located at trailing edge 2 inside; Described miniature motor is by gear driving rack and then drive all slide bars 10 to slide along respective slide rail, realizes expansion and the contraction of the leading edge of a wing and trailing edge; Between multiple slide bar 10, movable sleeve is provided with multiple support beam 9 perpendicular with slide bar 10, and the support beam 9 being positioned at forefront is connected by rope 11 with the leading edge of a wing 1 rear end, and the front end of the support beam 9 and trailing edge 2 that are positioned at rearmost is connected by rope 11; Be connected by rope 11 between adjacent supports beam 9; The front end of described folding covering 4 is connected with the rear end of the leading edge of a wing 1, and the rear end of folding covering 4 is connected with the front end of trailing edge 2, and the centre portion of folding covering 4 is all connected with support beam 9 top.
Described slide assemblies comprises and is located at the multiple pneumatic of trailing edge 2 inside or hydraulic push rod 8, and movable end that is pneumatic or hydraulic push rod 8 is arranged in parallel and be all connected with the leading edge of a wing 1 rear end; Pneumatic or hydraulic push rod 8 passes through the flexible expansion and the contraction that realize the leading edge of a wing and trailing edge; Between the movable end of multiple pneumatic or hydraulic push rod 8, movable sleeve is provided with multiple support beam 9 vertical with movable end; The support beam 9 being positioned at forefront is connected by rope 11 with the leading edge of a wing 1 rear end, and the front end of the support beam 9 and trailing edge 2 that are positioned at rearmost is connected by rope 11; Be connected by rope 11 between adjacent supports beam 9; The front end of described folding covering 4 is connected with the rear end of the leading edge of a wing 1, and the rear end of folding covering 4 is connected with the front end of trailing edge 2, and the centre portion of folding covering 4 is all connected with support beam 9.
Described movable end that is pneumatic or hydraulic push rod 8 adopts the nested stretching structure of Antenna Type multistage.
A kind of vertically taking off and landing flyer, described aircraft adopts deformable wing as integral type fuselage, and the front end of the leading edge of a wing 1 is provided with a pair screw propeller 5, and the afterbody of trailing edge 2 is provided with empennage 6 and yaw rudder 7.
As Fig. 1 ~ 3 are depicted as the structural representation after wing described in the utility model expansion.Then illustrate concrete Antenna Type stretching structure in visible slide assemblies 3, Fig. 2,3 in Fig. 1, its power comes from pneumatic or hydraulic push rod; Wherein in Fig. 2, collapsible covering launches; Fig. 4 ~ 6 item are the structural representations after wing described in the application shrinks.Fig. 7 is slide assemblies described in the utility model employing slide bar 10 and partial schematic diagram during slide track component, does not draw rope in Fig. 1 ~ 7 in order to not affect agent structure; Fig. 8 display be connection diagram between rope 11 and support beam 9 and wing front and rear edge, eliminate covering for ease of observing.Support beam 9 is movably set on the movable end of slide bar or startup or hydraulic push rod, substantially parallel between multiple support beam 9.
Claims (8)
1. a deformable wing, is characterized in that, comprises the leading edge of a wing (1) and trailing edge (2); Realize launching and shrinking by slide assemblies (3) between the described leading edge of a wing (1) and trailing edge (2); Folding covering (4) is connected with between the described leading edge of a wing (1) and trailing edge (2).
2. deformable wing as claimed in claim 1, it is characterized in that, described slide assemblies (3) comprises and is located at the inner slide bar (10) of the leading edge of a wing (1) and combines with slide rail, and described slide rail has multiple and arranged in parallel, each slide rail is equipped with a slide bar (10); The other end of all slide bars (10) is all connected with trailing edge (2) front end; A slide bar (10) is had at least to be provided with tooth bar and to be furnished with the gear be meshed with tooth bar; Described slide assemblies also comprises the miniature motor being located at the leading edge of a wing (1) inside; Described miniature motor is by gear driving rack and then drive all slide bars (10) to slide along respective slide rail, realizes expansion and the contraction of the leading edge of a wing and trailing edge; Between multiple slide bar (10), movable sleeve is provided with multiple support beam (9) perpendicular with slide bar (10), the support beam (9) being positioned at forefront is connected by rope (11) with the leading edge of a wing (1) rear end, is positioned at the support beam (9) of rearmost and is connected by rope (11) with the front end of trailing edge (2); Be connected by rope (11) between adjacent supports beam (9); The front end of described folding covering (4) is connected with the rear end of the leading edge of a wing (1), the rear end of folding covering (4) is connected with the front end of trailing edge (2), and the centre portion of folding covering (4) is all connected with support beam (9) top.
3. deformable wing as claimed in claim 1, it is characterized in that, described slide assemblies (3) comprises and is located at the inner multiple pneumatic or hydraulic push rod (8) of the leading edge of a wing (1), and movable end that is pneumatic or hydraulic push rod (8) is arranged in parallel and be all connected with trailing edge (2) front end; Pneumatic or hydraulic push rod (8) passes through the flexible expansion and the contraction that realize the leading edge of a wing and trailing edge; Between the movable end of multiple pneumatic or hydraulic push rod (8), movable sleeve is provided with multiple support beam vertical with movable end (9); The support beam (9) being positioned at forefront is connected by rope (11) with the leading edge of a wing (1) rear end, is positioned at the support beam (9) of rearmost and is connected by rope (11) with the front end of trailing edge (2); Be connected by rope (11) between adjacent supports beam (9); The front end of described folding covering (4) is connected with the rear end of the leading edge of a wing (1), the rear end of folding covering (4) is connected with the front end of trailing edge (2), and the centre portion of folding covering (4) is all connected with support beam (9) top.
4. deformable wing as claimed in claim 1, it is characterized in that, described slide assemblies (3) comprises and is located at the inner slide bar (10) of trailing edge (2) and combines with slide rail, and described slide rail has multiple and arranged in parallel, each slide rail is equipped with a slide bar (10); The other end of all slide bars (10) is all connected with the leading edge of a wing (1) rear end; A slide bar (10) is had at least to be provided with tooth bar and to be furnished with the gear be meshed with tooth bar; Described slide assemblies also comprises the miniature motor being located at trailing edge (2) inside; Described miniature motor is by gear driving rack and then drive all slide bars (10) to slide along respective slide rail, realizes expansion and the contraction of the leading edge of a wing and trailing edge; Between multiple slide bar (10), movable sleeve is provided with multiple support beam (9) perpendicular with slide bar (10), the support beam (9) being positioned at forefront is connected by rope (11) with the leading edge of a wing (1) rear end, is positioned at the support beam (9) of rearmost and is connected by rope (11) with the front end of trailing edge (2); Be connected by rope (11) between adjacent supports beam (9); The front end of described folding covering (4) is connected with the rear end of the leading edge of a wing (1), the rear end of folding covering (4) is connected with the front end of trailing edge (2), and the centre portion of folding covering (4) is all connected with support beam (9) top.
5. deformable wing as claimed in claim 1, it is characterized in that, described slide assemblies (3) comprises and is located at the inner multiple pneumatic or hydraulic push rod (8) of trailing edge (2), and movable end that is pneumatic or hydraulic push rod (8) is arranged in parallel and be all connected with the leading edge of a wing (1) rear end; Pneumatic or hydraulic push rod (8) passes through the flexible expansion and the contraction that realize the leading edge of a wing and trailing edge; Between the movable end of multiple pneumatic or hydraulic push rod (8), movable sleeve is provided with multiple support beam vertical with movable end (9); The support beam (9) being positioned at forefront is connected by rope (11) with the leading edge of a wing (1) rear end, is positioned at the support beam (9) of rearmost and is connected by rope (11) with the front end of trailing edge (2); Be connected by rope (11) between adjacent supports beam (9); The front end of described folding covering (4) is connected with the rear end of the leading edge of a wing (1), and the rear end of folding covering (4) is connected with the front end of trailing edge (2), and the centre portion of folding covering (4) is all connected with support beam (9).
6. the deformable wing as described in claim 3 or 5, is characterized in that, described movable end that is pneumatic or hydraulic push rod (8) adopts the nested stretching structure of Antenna Type multistage.
7. a vertically taking off and landing flyer, it is characterized in that, the deformable wing of described aircraft employing as described in any one of claim 1 ~ 5 is as integral type fuselage, the front end of the leading edge of a wing (1) is provided with a pair screw propeller (5), and the afterbody of trailing edge (2) is provided with empennage (6) and yaw rudder (7).
8. a vertically taking off and landing flyer, it is characterized in that, described aircraft adopts deformable wing as claimed in claim 6 as integral type fuselage, and the front end of the leading edge of a wing (1) is provided with a pair screw propeller (5), and the afterbody of trailing edge (2) is provided with empennage (6) and yaw rudder (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521006961.XU CN205221095U (en) | 2015-12-08 | 2015-12-08 | Flexible wing and adopt VTOL aircraft of this wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521006961.XU CN205221095U (en) | 2015-12-08 | 2015-12-08 | Flexible wing and adopt VTOL aircraft of this wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205221095U true CN205221095U (en) | 2016-05-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521006961.XU Withdrawn - After Issue CN205221095U (en) | 2015-12-08 | 2015-12-08 | Flexible wing and adopt VTOL aircraft of this wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205221095U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105438444A (en) * | 2015-12-08 | 2016-03-30 | 山西大学 | Deformable wings and vertical take-off and landing aircraft using wings |
| CN110510105A (en) * | 2019-08-21 | 2019-11-29 | 深圳飞马机器人科技有限公司 | Automatic deploying and retracting wing, unmanned plane and its control method |
-
2015
- 2015-12-08 CN CN201521006961.XU patent/CN205221095U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105438444A (en) * | 2015-12-08 | 2016-03-30 | 山西大学 | Deformable wings and vertical take-off and landing aircraft using wings |
| CN110510105A (en) * | 2019-08-21 | 2019-11-29 | 深圳飞马机器人科技有限公司 | Automatic deploying and retracting wing, unmanned plane and its control method |
| CN110510105B (en) * | 2019-08-21 | 2024-02-13 | 深圳飞马机器人股份有限公司 | Automatic wing retraction, unmanned aerial vehicle and control method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160511 Effective date of abandoning: 20170811 |
|
| AV01 | Patent right actively abandoned |