CN206537487U - A kind of aircraft of the variable wing of aerofoil profile and the application wing - Google Patents
A kind of aircraft of the variable wing of aerofoil profile and the application wing Download PDFInfo
- Publication number
- CN206537487U CN206537487U CN201720099927.4U CN201720099927U CN206537487U CN 206537487 U CN206537487 U CN 206537487U CN 201720099927 U CN201720099927 U CN 201720099927U CN 206537487 U CN206537487 U CN 206537487U
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- China
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- wing
- rib
- tie
- aerofoil profile
- steering wheel
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Abstract
The utility model provides the aircraft of a kind of variable wing of aerofoil profile and the application wing, central controller and the pitot tube being connected with central controller are provided with fuselage, wing includes rib, tie-beam, bull stick and steering wheel, it is disposed in parallel relation to one another between the rib, and horizontal direction of the rib along wing is set, each rib is laterally spaced is provided with multiple tie points, and the tie point on each rib is in a longitudinal direction in correspondence with each other, tie-beam is vertically connected on the tie point of rib, all tie-beams between adjacent ribs are connected by the same bull stick laterally set, each bull stick is provided with a steering wheel, steering wheel controlled connection central controller, the output shaft of steering wheel connects bull stick by gear drive.Beneficial effect is that aerofoil profile can deform, so as to change the parameters such as the lift-drag ratio of aircraft, is loaded with for the unmanned plane of deformable wing compares fixed aerofoil profile aircraft, the enhancing of its environment-adapting ability, completion multipurpose function that can be outstanding.
Description
Technical field
The utility model belongs to aircraft wing field, more particularly, to a kind of variable wing of aerofoil profile and using the wing
Aircraft.
Background technology
At present, known Fixed Wing AirVehicle, including unmanned plane and model airplane, the aerofoil profile of wing all immobilize
, and the parameter such as fixed its lift-drag ratio of aerofoil profile is changeless, this is unmanned plane major defect, it is impossible to according to environment not
Together, the difference of task is performed, aerofoil profile is deformed, so as to change the parameters such as the lift-drag ratio of aircraft, this causes unmanned plane function
Single, environment-adapting ability is poor, it is impossible to realize multipurpose function.
Utility model content
In view of this, the utility model is directed to the aircraft of a kind of variable wing of aerofoil profile and the application wing, can
Difference, the difference of execution task according to environment, aerofoil profile deforms, so that change the parameters such as the lift-drag ratio of aircraft, while this
Wing deformation uses gear-driven form, and wing deformation accuracy rate is high, which solve unmanned plane because caused by fixed aerofoil profile
Defect, is loaded with for the unmanned plane of deformable wing compares fixed aerofoil profile aircraft, the enhancing of its environment-adapting ability, can be outstanding it is complete
Into multipurpose function.
To reach above-mentioned purpose, what the technical solution of the utility model was realized in：
Central controller and the stream being connected with the central controller are provided with a kind of variable wing of aerofoil profile, fuselage
Speed pipe, wing includes being disposed in parallel relation to one another between multiple ribs, multiple tie-beams, multiple bull sticks and steering wheel, multiple ribs,
And horizontal direction of the rib along wing is set, each the rib is laterally spaced is provided with multiple tie points, and each
In a longitudinal direction in correspondence with each other, the tie-beam is vertically connected on the described of the rib to the tie point on the rib
On tie point, all tie-beams between the adjacent rib are connected by the same bull stick laterally set, Mei Yigen
The bull stick passes through tooth provided with a steering wheel, central controller described in the steering wheel controlled connection, the output shaft of the steering wheel
The wheel drive connection bull stick.
Wing includes four ribs, and each the rib is laterally spaced is provided with eight tie points, each rib
The tie-beam that is respectively connected between a tie-beam, the adjacent rib of eight tie points connected by a bull stick
Connect.
Also include gravity sensor, the gravity sensor is connected to the central controller.
A kind of aircraft of the variable wing of application aerofoil profile.
Relative to prior art, the aircraft of the variable wing of aerofoil profile described in the utility model and the application wing has
Following advantage：
Pitot tube can monitor the size of the front air speed of incoming flow in flight course, and gravity sensor can detect load
Weight information, and the front air speed of incoming flow information and weight information that monitor are transferred to central controller, central controller
Difference, the difference of execution task that can be according to the aircraft environment, control steering wheel, steering wheel output shaft passes through gear drive control
Bar rotation, so as to drive tie-beam to rotate, makes rib rotate, and realizes control wing camber, and aerofoil profile deforms, so that
Change the parameters such as the lift-drag ratio of aircraft, while the deformation of this wing uses gear-driven form, wing deformation accuracy rate is high, this solution
Unmanned plane because defect caused by fixed aerofoil profile, the aircraft for being loaded with deformable wing is compared fixed aerofoil profile aircraft and come
Say, the enhancing of its environment-adapting ability, completion multipurpose function that can be outstanding.
Rib is divided into 4 parts by this wing, and each rib of wing is connected by tie-beam, and adjacent tie-beam is logical
Bull stick connection is crossed, this can make every part wing rigidly big, intensity is big, in flight course, without obvious flutter.
Brief description of the drawings
Constitute a part of accompanying drawing of the present utility model to be used for providing further understanding to of the present utility model, this practicality is new
The schematic description and description of type is used to explain the utility model, does not constitute to improper restriction of the present utility model.
In accompanying drawing：
Fig. 1 is the structural representation of wing described in the utility model.
Fig. 2 is the electric control structure schematic diagram of the utility model embodiment.
Description of reference numerals：
1- ribs；11- tie points；2- tie-beams；3- bull sticks；4- steering wheels；5- gears.
Embodiment
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the utility model can
To be mutually combined.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " on ", " under ",
The orientation or position relationship of the instruction such as "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " are
Based on orientation shown in the drawings or position relationship, it is for only for ease of description the utility model and simplifies description, rather than indicate
Or imply that the device or element of meaning must have specific orientation, with specific azimuth configuration and operation, therefore be not understood that
For to limitation of the present utility model.In description of the present utility model, unless otherwise indicated, " multiple " are meant that two or two
More than individual.
, it is necessary to which explanation, unless otherwise clearly defined and limited, term " are pacified in description of the present utility model
Dress ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integratedly
Connection；Can be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected to by intermediary,
It can be the connection of two element internals.For the ordinary skill in the art, on being understood by concrete condition
State concrete meaning of the term in the utility model.
Describe the utility model in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
As shown in figure 1, the utility model provides a kind of aerofoil profile variable wing, be provided with fuselage central controller and
The pitot tube being connected with the central controller, wing includes multiple ribs 1, multiple tie-beams 2, multiple bull sticks 3 and steering wheel 4,
It is disposed in parallel relation to one another between multiple ribs 1, and horizontal direction of the rib 1 along wing is set, each edge of rib 1
Being horizontally arranged at interval has multiple tie points 11, and the tie point 11 on each described rib 1 is mutually relative in a longitudinal direction
Should, the tie-beam 2 is vertically connected on the tie point 11 of the rib 1, all connections between the adjacent rib 1
Beam 2 is connected by the same bull stick 3 laterally set, and each bull stick 3 is provided with a steering wheel 4, the steering wheel 4
Central controller described in controlled connection, the output shaft of the steering wheel 4 is connected the bull stick 3 by gear 5.
Wing includes four ribs 1, and each the rib 1 is laterally spaced is provided with eight tie points 11, each described
The tie-beam 2 that eight tie points 11 of rib 1 are respectively connected between a tie-beam 2, the adjacent rib 1 passes through
A piece bull stick 3 is connected.
Also include gravity sensor, the gravity sensor is connected to the central controller.
A kind of aircraft of the variable wing of application aerofoil profile.
The course of work of this example：The size of front air speed of incoming flow in pitot tube monitoring flight course, and will prison
The front air speed of incoming flow information transfer measured is to central controller, so as to may be implemented in flight course, with speed of incoming flow
The deformation of wing is controlled for foundation, the Deformation control of wing controls gear 5 to be driven by the steering wheel 4 on every bull stick 3,
And then drive tie-beam 2 to rotate, it is deformed wing, the transmission degree of accuracy of gear 5 is high, wing deformation accuracy rate is high, so as to control
The camber of wing processed.Speed of incoming flow is bigger, and wing camber is smaller；Speed of incoming flow is smaller, and wing camber is bigger.
Gravity sensor can detect weight information, and the weight information monitored is transferred into central controller, center
Controller can according to perform task difference, control wing camber, when aircraft needs rapid flight, wing camber is small,
Moreover, when aircraft needs load-carrying object flight, wing camber is big.
The output shaft of steering wheel 4 is rotated by the transmission control bull stick 3 of gear 5, so as to drive tie-beam 2 to rotate, occurs rib 1
Rotate, realize control wing camber, aerofoil profile deforms, so as to change the parameters such as the lift-drag ratio of aircraft, while this wing is deformed
Using the type of belt drive of gear 5, wing deformation accuracy rate is high, which solve unmanned plane because fixing defect caused by aerofoil profile, carries
The aircraft for having deformable wing is compared for fixed aerofoil profile aircraft, and its environment-adapting ability enhancing, completion that can be outstanding is more
Purposes function.
Preferred embodiment of the present utility model is the foregoing is only, it is all at this not to limit the utility model
Within the spirit and principle of utility model, any modification, equivalent substitution and improvements made etc. should be included in the utility model
Protection domain within.
Claims (4)
1. central controller and the flow velocity being connected with the central controller are provided with a kind of variable wing of aerofoil profile, fuselage
Pipe, it is characterised in that：Wing is included between multiple ribs, multiple tie-beams, multiple bull sticks and steering wheel, multiple ribs mutually
It is arranged in parallel, and horizontal direction of the rib along wing is set, each the rib is laterally spaced is provided with multiple connections
In a longitudinal direction in correspondence with each other, the tie-beam is vertically connected on described the tie point on point, and each described rib
On the tie point of rib, all tie-beams between the adjacent rib are connected by the same bull stick laterally set
Connect, each bull stick is provided with a steering wheel, central controller described in the steering wheel controlled connection, the output of the steering wheel
Axle connects the bull stick by gear drive.
2. the variable wing of aerofoil profile according to claim 1, it is characterised in that：Wing includes four ribs, each described
Rib is laterally spaced to be provided with eight tie points, and eight tie points of each rib are respectively connected with a connection
The tie-beam between beam, the adjacent rib is connected by a bull stick.
3. the variable wing of aerofoil profile according to claim 1, it is characterised in that：Also include gravity sensor, the gravity
Sensor is connected to the central controller.
4. being provided with and using the aircraft of the variable wing of the aerofoil profile described in claim any one of 1-3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720099927.4U CN206537487U (en) | 2017-01-23 | 2017-01-23 | A kind of aircraft of the variable wing of aerofoil profile and the application wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720099927.4U CN206537487U (en) | 2017-01-23 | 2017-01-23 | A kind of aircraft of the variable wing of aerofoil profile and the application wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206537487U true CN206537487U (en) | 2017-10-03 |
Family
ID=59939564
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720099927.4U Expired - Fee Related CN206537487U (en) | 2017-01-23 | 2017-01-23 | A kind of aircraft of the variable wing of aerofoil profile and the application wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206537487U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107933882A (en) * | 2017-12-09 | 2018-04-20 | 佛山市神风航空科技有限公司 | One kind deformation aerodone wing |
| CN107933886A (en) * | 2017-12-09 | 2018-04-20 | 佛山市神风航空科技有限公司 | A kind of special wing |
| CN107985546A (en) * | 2017-12-09 | 2018-05-04 | 佛山市神风航空科技有限公司 | A kind of deformable wing |
| CN108100226A (en) * | 2017-11-30 | 2018-06-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of leading edge of a wing support frame and variable radius leading edge of a wing structure |
| CN110182354A (en) * | 2019-05-23 | 2019-08-30 | 厦门大学 | A kind of flying wing that aerofoil profile is variable |
| CN110654530A (en) * | 2019-11-01 | 2020-01-07 | 北京航空航天大学 | Variable camber wing structure with deformation feedback |
| WO2022000367A1 (en) * | 2020-07-01 | 2022-01-06 | 西湖大学 | Wing structure for vehicle, and vehicle |
-
2017
- 2017-01-23 CN CN201720099927.4U patent/CN206537487U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100226A (en) * | 2017-11-30 | 2018-06-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of leading edge of a wing support frame and variable radius leading edge of a wing structure |
| CN107933882A (en) * | 2017-12-09 | 2018-04-20 | 佛山市神风航空科技有限公司 | One kind deformation aerodone wing |
| CN107933886A (en) * | 2017-12-09 | 2018-04-20 | 佛山市神风航空科技有限公司 | A kind of special wing |
| CN107985546A (en) * | 2017-12-09 | 2018-05-04 | 佛山市神风航空科技有限公司 | A kind of deformable wing |
| CN110182354A (en) * | 2019-05-23 | 2019-08-30 | 厦门大学 | A kind of flying wing that aerofoil profile is variable |
| CN110654530A (en) * | 2019-11-01 | 2020-01-07 | 北京航空航天大学 | Variable camber wing structure with deformation feedback |
| WO2022000367A1 (en) * | 2020-07-01 | 2022-01-06 | 西湖大学 | Wing structure for vehicle, and vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171003 Termination date: 20180123 |