CN206031774U - Wing reaches decides wing machine - Google Patents
Wing reaches decides wing machine Download PDFInfo
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- CN206031774U CN206031774U CN201621035500.XU CN201621035500U CN206031774U CN 206031774 U CN206031774 U CN 206031774U CN 201621035500 U CN201621035500 U CN 201621035500U CN 206031774 U CN206031774 U CN 206031774U
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Abstract
The utility model provides a wing reaches decides wing machine belongs to the aerospace field, and the wing includes wing body and supplementary riser, and wing body is provided with the installation through -hole, and the installation through -hole runs through wing body along wing body's thickness direction, and supplementary riser is for lift fan or screw or rotor and installs in the installation through -hole, and the both ends of installation through -hole all are provided with guarantor's type apron, and guarantor's type apron movably set up in the wing in order to seal or to open the installation through -hole. Much more more install on the fuselage back with the wing and form and decide wing machine, form one kind and neotypely decide wing machine fixed -wing aircraft and supplementary riser are compound, can realize VTOL or the short distance of deciding wing machine and take off and land, require to reduce to the place of taking off and land etc. Can make and decide wing machine adaptation use occasion, the function of deciding the wing quick -witted is more diversified. Behind wing machine the reaches cruising speed of settlement that it can't be shaken, will install the through -hole through guarantor's type apron and seal, supplementary riser can not influence decides normally cruising of wing machine.
Description
Technical field
This utility model is related to aerospace field, in particular to a kind of wing and fixed wing machine.
Background technology
Fixed wing machine, also known as fixed wing airplane, is a kind of common aircraft.Fixed wing machine is referred to and produces advance by power set
Thrust or pulling force, lift is produced by the fixed wing of fuselage, that what is flown in atmosphere overweights the airborne vehicle of air, fixed wing machine
Wing position, the parameter such as angle of sweep immobilizes in flight course.At present aircraft major part in the world is fixed wing machine, example
Such as civil aviaton's aircraft, unmanned plane etc..
There is larger restriction in the landing length of fixed wing machine, most of fixed wing machine is required for entering landing in airport, generally
Longer runway is needed to supply landing, the condition requirement to landing is harsher.
In prior art, some fixed wing machine increased vertical lift device etc. and be aided in, but it is tight to be vertically moved up or down device meeting
Ghost image rings the normal flight of fixed wing machine, makes troubles to the flight of fixed wing machine.
Utility model content
First purpose of the present utility model is to provide a kind of wing, by assistance for lifting device is arranged on fixed-wing,
Wing-body can concurrently or separately provide lift with assistance for lifting device, when using assistance for lifting device, can pass through
Installation through-hole and assistance for lifting device are closed by guarantor's type cover plate, and assistance for lifting device does not interfere with the normal flight of fixed wing machine.
Second purpose of the present utility model is to provide a kind of fixed wing machine, and fixed wing machine application has the machine of assistance for lifting device
The wing, it is possible to achieve VTOL or short take-off and landing etc., the function of fixed wing machine are more perfect.
What embodiment of the present utility model was realized in：
Embodiment of the present utility model provides a kind of wing, including wing-body and assistance for lifting device, the wing sheet
Body is provided with installation through-hole, and the installation through-hole runs through the wing-body along the thickness direction of the wing-body, described auxiliary
Lifter is helped to be lift fan or propeller or rotor and be installed in the installation through-hole that the two ends of the installation through-hole are all provided with
Guarantor's type cover plate is equipped with, guarantor's type cover plate is movably disposed in the wing to close or open the installation through-hole.
Alternatively, at least two assistance for lifting devices are provided with the wing-body, partly or entirely the assistance for lifting
Device is distributed along the width of the wing-body.
Alternatively, the wing also includes control system, and the rotating speed of the assistance for lifting device is respectively by the control system
System is individually controlled.
Alternatively, the wing-body is provided with rotating shaft, and guarantor's type cover plate is rotatablely arranged at institute around the rotating shaft
Wing is stated, the axis of the rotating shaft is arranged along the width of the wing-body.
Alternatively, one end of the wing-body is the connection end for connecting fuselage, and the rotating shaft is arranged at the peace
The side away from the connection end of dress through hole.
Alternatively, the both sides of the wing-body are provided with holding tank, and guarantor's type cover plate is embedded in the holding tank,
The holding tank of the wing-body both sides is connected by the installation through-hole, outer surface and the machine of guarantor's type cover plate
The aerofoil of wing body is flushed.
Alternatively, the maximum opening angle positioned at guarantor's type cover plate of the wing-body upper surface is 45 ° -75 °.
Alternatively, the outer wall curvature of guarantor's type cover plate is corresponding with the airfoil curvature of the wing-body.
Embodiment of the present utility model additionally provides a kind of fixed wing machine, including fuselage and wing as described above, described
The relative both sides of fuselage are fixedly installed the wing respectively, and the fixed wing machine is additionally provided with for providing to the aircraft
Power and make the wing-body aerofoil produce lift built-in actuating unit and for the assistance for lifting device provide
The auxiliary power mechanism of power.
Alternatively, the assistance for lifting device of the opposite sides of the fuselage with regard to the fuselage it is symmetrical and it is described auxiliary rise
The centre of lift of drop device is overlapped with the center of gravity place vertical curve of the fixed wing machine.
Compared with prior art, the beneficial effects of the utility model are：By installation through-hole is arranged on wing, install logical
Assistance for lifting device is installed in hole and installation through-hole is opened or is closed by guarantor's type cover plate, by fixed wing airplane and assistance for lifting
Device is compounded to form a kind of new fixed wing machine, it is possible to achieve the VTOL of fixed wing machine or short take-off and landing, to landing place etc.
Require to reduce, fixed wing machine can be made to adapt to more use occasions, the function of fixed wing machine is more diversified.Set when fixed wing machine reaches
After fixed cruising speed, installation through-hole is closed by guarantor's type cover plate, assistance for lifting device does not interfere with normaling cruise for fixed wing machine.
Description of the drawings
Fixed wing machine structural representation under guarantor's type cover plate open mode that Fig. 1 is provided for this utility model embodiment；
Wing structure schematic diagrams of the Fig. 2 for Fig. 1；
Fixed wing machine structural representation under guarantor's type cover plate closed mode that Fig. 3 is provided for this utility model embodiment.
Icon：
100- fixed wing machines；
11- fuselages；
12- wings；
121- wing-bodies；1211- installation through-holes；1213- holding tanks；
123- assistance for lifting devices；
125- guarantor's type cover plates；1251- rotating shafts.
Specific embodiment
It is to make purpose, technical scheme and the advantage of this utility model embodiment clearer, new below in conjunction with this practicality
Accompanying drawing in type embodiment, is clearly and completely described to the technical scheme in this utility model embodiment, it is clear that retouched
The embodiment stated is a part of embodiment of this utility model, rather than the embodiment of whole.Based on the enforcement in this utility model
Example, the every other embodiment obtained under the premise of creative work is not made by those of ordinary skill in the art are belonged to
The scope of this utility model protection.
Therefore, the detailed description of embodiment of the present utility model below to providing in the accompanying drawings is not intended to limit requirement
The scope of the present utility model of protection, but it is merely representative of selected embodiment of the present utility model.Based in this utility model
Embodiment, the every other embodiment obtained under the premise of creative work is not made by those of ordinary skill in the art, all
Belong to the scope of this utility model protection.
It should be noted that：Similar label and letter represent similar terms in following accompanying drawing, therefore, once a certain Xiang Yi
It is defined in individual accompanying drawing, then in subsequent accompanying drawing which further need not be defined and is explained.
In description of the present utility model, in addition it is also necessary to explanation, unless otherwise clearly defined and limited, term " sets
Put ", " connection " should be interpreted broadly, for example, it may be being fixedly connected, or being detachably connected, or be integrally connected；Can
Being to be mechanically connected, or electrically connect；Can be joined directly together, it is also possible to be indirectly connected to by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in utility model.
Embodiment：
As shown in figure 1, this utility model embodiment provides a kind of fixed wing machine 100, the fixed wing machine 100 includes 11 He of fuselage
Wing 12.
It should be noted that wing 12 can be individually to carry out producing, manufacture, use, in the present embodiment, in order to retouch
State convenient and be easy to illustrate the architectural feature and operation principle of wing 12, be described with fixed wing machine 100.
The structure of fuselage 11 can adopt prior art, such as unmanned aerial vehicle body 11, civil aircraft fuselage 11 etc., correspondence
Ground, fixed wing machine 100 can also be unmanned plane, manned aircraft etc., and in the present embodiment, fuselage 11 is internally provided with built-in engine
Structure, certainly, built-in actuating unit is arranged at also possible in wing 12, and built-in actuating unit is main as fixed wing machine 100
Power source, pushes or pulls to fixed wing machine 100, it is ensured that the normal flight of fixed wing machine 100.In addition, having inside fuselage 11
For the computer control system of control.
Wing 12 adopts fixed-wing form, the quantity of wing 12 to be at least two and be symmetrically distributed in the both sides of fuselage 11,
In the present embodiment, the quantity of wing 12 is two, and one end of each wing 12 is fixedly connected with the sidepiece of fuselage 11, wing 12
Angle of sweep can be between 10 ° -43 °.
As shown in Fig. 2 wing 12 is mainly made up of wing-body 121 and assistance for lifting device 123, enter below for each several part
Row is discussed in detail.
The structure of wing-body 121 is referred to prior art, and wing-body 121 includes top airfoil and lower aerofoil, wing
121 points of body is thickness direction, length direction and width, and the thickness direction of wing-body 121 refers to wing-body 121
Direction of the top airfoil to lower aerofoil, the length direction of wing-body 121 refer to one end of the close fuselage 11 from wing 12 to another
The direction of outer one end, the width of wing-body 121 refer to the side of the front edge of wing-body 121 to rear end side edge
To.
Wing-body 121 is provided with installation through-hole 1211, and installation through-hole 1211 runs through along the thickness direction of wing-body 121
Wing-body 121, i.e. installation through-hole 1211 extend through top airfoil and lower aerofoil, installation through-hole 1211 can for circular hole, square hole,
The various forms such as irregular hole, in the present embodiment, installation through-hole 1211 can be selected as circular hole, installation through-hole 1211 be in order to
A passage (duct) is provided, air can flow along the passage.
The production method of installation through-hole 1211 is varied, such as integrally manufactured with wing 12, or wing 12 is being made
Punching etc. is carried out after finishing.
The quantity of installation through-hole 1211 and position need to be determined according to the quantity of assistance for lifting device 123 and position.
Assistance for lifting device 123 is rotatably arranged in the installation through-hole 1211 of wing-body 121 by rotary shaft, rotary shaft
It is fixedly connected with the inner surface of installation through-hole 1211, the rotary shaft of assistance for lifting device 123 is set along the thickness direction of wing-body 121
Put, the axis of the rotary shaft of assistance for lifting device 123 can be worked with the dead in line of installation through-hole 1211, assistance for lifting device 123
When, air is flowed into from the upper end of installation through-hole 1211 and is flowed out from the lower end of installation through-hole 1211, so as to provide to fixed wing machine 100
Lift.
Assistance for lifting device 123 can be in lift fan (ducted fan), propeller (shrouded propeller) and rotor
Kind, certainly, the assistance for lifting device 123 on different wings 12 can adopt different forms, from sides such as convenient making, Stability Analysis of Structures
Face is set out, and all assistance for lifting devices 123 on fixed wing machine 100 can adopt same type.
Propeller refers to and rotated by blade in atmosphere, and engine rotation power is converted into the device of propulsive force, can be by
Two or more leaf are connected with hub, and the one side backward of leaf is helicoid or the propeller for being similar to helicoid.Lift fan is
It is connected with hub by the diminish blade of (relative to propeller) of multiple aspect ratio examples, by rotation driving air flows down producing
The device of lift.Rotor is the propeller that a kind of aspect ratio is increased, and is used for airborne vehicle, can also provide lift.
Assistance for lifting device 123 can adopt axial-flow type, axle stream to refer to that the axle of flabellum is parallel with the direction of air-flow, the number of flabellum
It is at least two leaves to measure, and can be directly driven by motor, it is also possible to be connected with motor through decelerator or drive mechanism, electricity
The type of cooling of motivation can select air cooling.
The quantity of the assistance for lifting device 123 on each wing 12 is at least one, in the present embodiment, on each wing 12
Assistance for lifting device 123 quantity be two.Two assistance for lifting devices 123 are distributed along the width of wing-body 121, also
To say, assistance for lifting device 123 is forward, an assistance for lifting device 123 rearward, the wing 12 positioned at 11 both sides of fuselage symmetrically sets
Put, assistance for lifting device 123 can also be symmetrical arranged, so that the centre of lift of multiple assistance for lifting devices 123 and fixed wing machine 100
Center of gravity place vertical curve overlap or essentially coincide, fixed wing machine 100 is more stable.
Certainly, the assistance for lifting device 123 on each wing 12 can also be one, three, four etc., in order that auxiliary rises
Drop device 123 does not interfere with the normal manufacture and use of fixed wing machine 100, and the quantity of the assistance for lifting device 123 on each wing 12 is most
Five are not exceeded well.
Each 123 one installation through-hole 1211 of independent correspondence of assistance for lifting device, and the edge of assistance for lifting device 123 is close
The inner surface of installation through-hole 1211, this design can increase the intensity of wing-body 121, certainly, each wing as much as possible
Different assistance for lifting device 123 on 12 can also share installation through-hole 1211.Assistance for lifting device 123 passes through auxiliary power mechanism
Drive and realize rotating, the position of auxiliary power mechanism do not limit, for example, may be located in fuselage 11 or in wing 12 etc..
Different assistance for lifting devices 123 can be controlled simultaneously and rotating speed is identical or speed discrepancy is constant, it is also possible to individually control
Realize the independent regulation of rotating speed.In the present embodiment, assistance for lifting devices 123 different on each wing 12 passes through control system list
Solely control, i.e., the rotating speed of different assistance for lifting devices 123 will not influence each other, and rotating speed be able to can also be differed with identical.Pass through
Adjust the assistance for lifting device 123 on the rotating speed or the different wings 12 of adjustment of assistance for lifting devices 123 different on same wing 12
Rotating speed can realize the adjustment of aspect.Control system for controlling assistance for lifting device 123 can be integrated in fixed wing machine
In 100 computer control system, it is also possible to be separately provided.
Guarantor's type cover plate 125 is respectively arranged with the two ends of installation through-hole 1211, is worked assistance for lifting device 123 is not needed
When, it is by guarantor's type cover plate 125 by the closed at both ends of installation through-hole 1211, if installation through-hole 1211 is multiple, multiple to install logical
Hole 1211 can share guarantor's type cover plate 125, it is also possible to guarantor's type cover plate 125 is separately configured.
Guarantor's type cover plate 125 1251 is movably disposed in wing-body 121 around the shaft, in the present embodiment, guarantor's type cover plate
125 1251 are rotatablely arranged at wing-body 121 around the shaft, and the rotation of guarantor's type cover plate 125 can pass through computer controls system
System is realized.The direction of rotating shaft 1251 sets as needed, and preferably rotating shaft 1251 is fuselage 11 along the width of wing 12
Length direction is arranged, and guarantor's type cover plate 125 can open or close installation through-hole 1211 when 1251 rotate around the shaft, rotating shaft 1251
Direction cause guarantor's type cover plate 125 effective stop area (i.e. under 100 state of flight of fixed wing machine, guarantor's type cover plate 125 with wind direction hang down
Projected area in straight plane) it is less, the resistance suffered by fixed wing machine 100 is less.
Certainly, guarantor's type cover plate 125 can also be slideably positioned in wing-body 121, or other model of action, for example
Rotating bar is provided with wing-body 121, one end and the wing-body 121 of rotating bar are hinged, the other end and guarantor's type cover plate 125
It is hinged, realizes that guarantor's type cover plate 125 opens or closes installation through-hole 1211 by the rotation of rotating bar.
Rotating shaft 1251 can be arranged at the side away from fuselage 11 of installation through-hole 1211, it is also possible to be arranged at installation through-hole
The side of 1211 close fuselage 11, if in addition, 121 side of wing-body includes two or more guarantor's type cover plates 125,
The both sides of installation through-hole 1211 can arrange rotating shaft 1251 and correspond with each guarantor's type cover plate 125.
Also, guarantor's type cover plate 125 can be integrated the tabular of manufacture, or folding Split type structure, if guarantor's type
Cover plate 125 is folding Split type structure, then guarantor's type cover plate 125 includes at least two parts, between two adjacent parts
It is hinged, diameter parallel of the axis that the two relatively rotates preferably with rotating shaft.
The angle that guarantor's type cover plate 125 is rotated is not limited, in order that assistance for lifting device 123 preferably works, can make Bao Xinggai
The maximum opening angle of plate 125 is defined to 45 ° -75 ° and (installation through-hole 1211 is completely enclosed as 0 ° of position with protecting type cover plate 125
Put), in the present embodiment, 75 ° of maximum rotation angles as guarantor's type cover plate 125 are selected, through long-term experiment and in a large number
Data determine that the scope can both make assistance for lifting device 123 play one's part to the full, again cause guarantor's type cover plate 125 to fixed wing machine
100 impact is minimized.In addition, positioned at 121 top airfoil of wing-body guarantor's type cover plate 125 flip angle can be located at
The flip angle of guarantor's type cover plate 125 of 121 lower aerofoil of wing-body is identical or different.Certainly, the maximum unlatching of guarantor's type cover plate 125
Angle is arbitrarily to limit as needed, such as 30 °, 90 °, 180 ° etc., and 45 ° -75 ° is preferably scope.
The side away from installation through-hole 1211 of guarantor's type cover plate 125 is outer surface, and the shape of outer surface can be with wing sheet
The aerofoil correspondence of body 121, the curvature of the outer surface of guarantor's type cover plate 125 are corresponding with aerofoil, seamlessly transit therebetween, work as Bao Xinggai
After plate 125 is closed, outer surface can provide lift to fixed wing machine 100 jointly as a part for aerofoil.
The space that guarantor's type cover plate 125 causes assistance for lifting device 123 inswept is completely submerged in the three dimensions of lifting surface, is protected
Type cover plate 125 close after, assistance for lifting device 123 be closed it is built-in, will not on fixed wing machine 100 produce impact, it is ensured that fixed wing machine 100
Normal flight.
Can be sealed using rubber ring etc. between guarantor's type cover plate 125 and wing-body 121, it is ensured that guarantor's type cover plate 125
There is no gap between wing-body 121, the impact that 1211 grade of installation through-hole is produced to the fixed wing machine 100 of normal flight can be with
Minimize degree.
In order that the outer surface of guarantor's type cover plate 125 is coordinated with the aerofoil of wing-body 121, on the surface of wing-body 121
Holding tank 1213 can be opened up, inner recess of the holding tank 1213 towards wing-body 121, guarantor's type cover plate 125 can be embedded
In holding tank 1213, after installation through-hole 1211 is closed by guarantor's type cover plate 125, the outer surface of guarantor's type cover plate 125 can be with wing
Body 121 aerofoil correspondence and seamlessly transit, guarantor's type cover plate 125 can as a part of common offer lift of aerofoil, while
The air flow for flowing through aerofoil is not interfered with.
The fixed wing machine 100 can be the various forms such as unmanned plane, manned aircraft, in addition, the fixed wing machine 100 can also be winged
The wing, all-wing aircraft, also known as all-wing machine, are a kind of do not have empennage and the major part of fuselage is hidden in the airborne vehicle in thick wing.
Fixed-wing integration of the patent by assistance for lifting device 123 with fixed wing machine 100 is compounded to form new aircraft, can make to determine the wing
Machine 100 completes vertically/short take-off and landing and normal cruising flight.
Adopt the operation principle (by taking the lifting method of fixed wing machine 100 as an example) of the fixed wing machine 100 of said structure as follows：
The lifting method of fixed wing machine 100, successively including preparation process, transition step and cruise step.
For convenience, remained static with fixed wing machine 100, guarantor's type cover plate 125 is closed, built-in actuating unit and auxiliary
Power-assist force mechanisms stop illustrating for original state.
Preparation process：Rotate the guarantor's type cover plate 125 on 100 wing-body 121 of fixed wing machine by control system, Bao Xinggai
Plate 125 1251 is turned an angle around the shaft, and angular range is not limited, preferably between 45 ° -75 °, 1211 two ends of installation through-hole
After guarantor's type cover plate 125 is opened, installation through-hole 1211 exposes to form air inlet/outlet passage, and installation through-hole 1211 is substantially at vertically
Direction, assistance for lifting device 123 is sudden and violent to be leaked.
Transition step：Built-in actuating unit and auxiliary power mechanism are controlled by the computer control system of fixed wing machine 100
Work, built-in actuating unit produce pulling force or thrust to fixed wing machine 100, and aerofoil produces the first lift upwards, while auxiliary is dynamic
Force mechanisms drive assistance for lifting device 123 to rotate, the blowing downwards of assistance for lifting device 123 and fixed wing machine 100 is applied upwards second
Lift.In the original state that fixed wing machine 100 takes off, the first lift is less, the second lift is larger, with fixed wing machine 100 gradually
Accelerate, the first lift gradually increases, and can now control the second lift and be gradually reduced, the mode of control can be reduction auxiliary
The rotating speed of lifter 123, during the rotating speed of assistance for lifting device 123 is reduced or after assistance for lifting device 123 stops operating, passes through
Control system control guarantor's type cover plate 125 1251 is rotated and is progressively closed off around the shaft, and wing-body 121 gradually obtains complete outer
Shape.
In transition step, attitude regulation step can also be carried out：The appearance of fixed wing machine 100 is detected by attitude transducer
State, the different auxiliary for being controlled optionally through the computer control system of fixed wing machine 100 on each wing 12 as needed rise
The rotating speed of drop device 123, makes the different assistance for lifting device 123 on each wing 12 provide different lift, due to part or complete
Portion assistance for lifting device 123 is distributed along the length direction of fuselage 11, that is to say, that the assistance for lifting device 123 that has is forward, the auxiliary that has
Lifter 123 rearward, according to the difference of lift so that the fuselage 11 of fixed wing machine 100 is inclined, so as to realize 100 attitude of fixed wing machine
Adjustment.Furthermore it is also possible to the rotating speed for passing through to control the assistance for lifting device 123 on different wings 12 is different, fixed wing machine is controlled
The 100 any adjustment tilted to realize the attitude in three dimensions of fixed wing machine 100.
Cruise step：As shown in figure 3, installation through-hole 1211 is closed by guarantor's type cover plate 125, assistance for lifting device 123 stops turning
Dynamic, the outer wall of guarantor's type cover plate 125 provides lift with the aerofoil collective effect of wing-body 121, determines the wing as a part for aerofoil
Machine 100 can be at the uniform velocity or speed change.It should be noted that the lift of fixed wing machine 100 is mainly provided by the aerofoil of wing-body 121
Lift, the surface of guarantor's type cover plate 125 can also provide certain lift for fixed wing machine 100.
It should be noted that above-mentioned situation is only one of which working method, guarantor's type cover plate 125 is made to open and make auxiliary
The opportunity that lifter 123 is rotated selects as needed, for example can be with opening guarantor's type cover plate in the flight course of fixed wing machine 100
125 and assistance for lifting device 123 is made to work, alternatively, it is also possible to (now can only make auxiliary power in 100 VTOL of fixed wing machine
Mechanism drives assistance for lifting device 123 to rotate, and built-in actuating unit does not work) and fixed wing machine 100 the speed of a ship or plane less than lifting surface most
Using assistance for lifting device 123 etc. during low stalling speed, certainly, assistance for lifting device 12 can also be in the descent of fixed wing machine 100
Used in, 100 descent of fixed wing machine is contrary with aforesaid raising process.
It should be noted that in the case where not conflicting, the feature in embodiment in this utility model mutually can be tied
Close.
Preferred embodiment of the present utility model is the foregoing is only, this utility model is not limited to, for this
For the technical staff in field, this utility model can have various modifications and variations.It is all it is of the present utility model spirit and principle
Within, any modification, equivalent substitution and improvements made etc. are should be included within protection domain of the present utility model.
Claims (10)
1. a kind of wing, it is characterised in that including wing-body and assistance for lifting device, it is logical that the wing-body is provided with installation
The wing-body is run through along the thickness direction of the wing-body in hole, the installation through-hole, and the assistance for lifting device is lift
Fan or propeller or rotor and it is installed in the installation through-hole, the two ends of the installation through-hole are provided with guarantor's type cover plate,
Guarantor's type cover plate is movably disposed in the wing to close or open the installation through-hole.
2. wing according to claim 1, it is characterised in that at least two assistance for lifting are provided with the wing-body
Device, partly or entirely width distribution of the assistance for lifting device along the wing-body.
3. wing according to claim 2, it is characterised in that the wing also includes control system, the assistance for lifting
The rotating speed of device is individually controlled by the control system respectively.
4. wing according to claim 1, it is characterised in that the wing-body is provided with rotating shaft, guarantor's type cover plate
The wing is rotatablely arranged at around the rotating shaft, the axis of the rotating shaft is arranged along the width of the wing-body.
5. wing according to claim 4, it is characterised in that one end of the wing-body is the company for connecting fuselage
End is connect, the rotating shaft is arranged at the side away from the connection end of the installation through-hole.
6. wing according to claim 1, it is characterised in that the both sides of the wing-body are provided with holding tank, described
Guarantor's type cover plate is embedded in the holding tank, and the holding tank of the wing-body both sides is connected by the installation through-hole,
The outer surface of guarantor's type cover plate is flushed with the aerofoil of the wing-body.
7. wing according to claim 1, it is characterised in that positioned at guarantor's type cover plate of the wing-body upper surface
Maximum opening angle be 45 ° -75 °.
8. wing according to claim 1, it is characterised in that the outer wall curvature of guarantor's type cover plate and the wing-body
Airfoil curvature correspondence.
9. a kind of fixed wing machine, it is characterised in that including fuselage and the wing as described in claim 1-8 any one, the machine
The relative both sides of body are fixedly installed the wing respectively, and the fixed wing machine is additionally provided with for providing dynamic to the aircraft
Power and the aerofoil of the wing-body is made to produce the built-in actuating unit of lift and for providing dynamic to the assistance for lifting device
The auxiliary power mechanism of power.
10. fixed wing machine according to claim 9, it is characterised in that the assistance for lifting of the opposite sides of the fuselage
Device is symmetrical with regard to the fuselage and the centre of lift of assistance for lifting device is overlapped with the center of gravity place vertical curve of the fixed wing machine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621035500.XU CN206031774U (en) | 2016-08-31 | 2016-08-31 | Wing reaches decides wing machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621035500.XU CN206031774U (en) | 2016-08-31 | 2016-08-31 | Wing reaches decides wing machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206031774U true CN206031774U (en) | 2017-03-22 |
Family
ID=58298293
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621035500.XU Active CN206031774U (en) | 2016-08-31 | 2016-08-31 | Wing reaches decides wing machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206031774U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106314789A (en) * | 2016-08-31 | 2017-01-11 | 张峣 | Wing, fixed-wing aircraft and fixed-wing aircraft lifting method |
| RU2748043C1 (en) * | 2020-03-10 | 2021-05-19 | Дмитрий Сергеевич Дуров | Watercraft aviation and rocket anti-satellite system |
-
2016
- 2016-08-31 CN CN201621035500.XU patent/CN206031774U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106314789A (en) * | 2016-08-31 | 2017-01-11 | 张峣 | Wing, fixed-wing aircraft and fixed-wing aircraft lifting method |
| RU2748043C1 (en) * | 2020-03-10 | 2021-05-19 | Дмитрий Сергеевич Дуров | Watercraft aviation and rocket anti-satellite system |
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