CN207683769U - A kind of spanwise length variable geometry and the aircraft with it - Google Patents
A kind of spanwise length variable geometry and the aircraft with it Download PDFInfo
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- CN207683769U CN207683769U CN201721564182.0U CN201721564182U CN207683769U CN 207683769 U CN207683769 U CN 207683769U CN 201721564182 U CN201721564182 U CN 201721564182U CN 207683769 U CN207683769 U CN 207683769U
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- wing
- sliding rail
- variable geometry
- driving device
- spanwise
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Abstract
The utility model is related to a kind of spanwise length variable geometries comprising：First wing, first wing have opening far from fuselage side；Sliding rail, the sliding rail are set in the first wing and extend from described be open to fuselage direction；Second wing, second wing are installed on the sliding rail, are slided from the opening to fuselage direction along the sliding rail：And driving device, the driving device is arranged along wing spanwise direction, and one end is fixed with aircaft configuration, and the other end is connected to second wing, for driving second wing to be moved to fuselage direction.The spanwise length variable geometry of the utility model makes aircraft wing realize that length is adjustable in the spanwise direction, to change wing area, by releasing the second wing to obtain lift when aircraft being enable to need compared with lift, and withdraw the second wing to reduce lift when needing to reduce airplane ascensional force, with simple in structure, high reliability.
Description
Technical field
The utility model belongs to technical field of aircraft structure design more particularly to a kind of spanwise length variable geometry.
Background technology
Wing is one of important component of aircraft, is mounted on fuselage, and main effect is to generate lift.Ordinary circumstance
Under, wing area is directly proportional to the lift of offer.Such as in takeoff phase, it can make if making aircraft that there is larger wing area
Aircraft has larger lift, shortens distance of taking off；And smaller wing then so that aircraft is provided with preferable mobility, is convenient for
Aircraft maneuvering.
However in existing aircraft, the integrally-built area of wing or length are immutable, are only set at trailing edge position
The variable rudder face of low-angle is set to change airplane ascensional force size, the lift that the method provides is limited, for this reason, it may be necessary to a kind of wing by
The adjustable aircraft of power area is to meet the requirement of aircraft in varied situations.
Utility model content
The purpose of this utility model is to provide a kind of spanwise length variable geometry and aircraft, for solving above-mentioned ask
Topic.
In order to achieve the above objectives, the technical solution adopted in the utility model is：A kind of spanwise length variable geometry,
Including
First wing, first wing have opening far from fuselage side；
Sliding rail, the sliding rail are set in the first wing and extend from described be open to fuselage direction；
Second wing, second wing are installed on the sliding rail, from the opening along the sliding rail to fuselage side
To sliding：And
Driving device, the driving device is arranged along wing spanwise direction, and one end is fixed with aircaft configuration, and the other end connects
It is connected to second wing, for driving second wing to be moved to fuselage direction.
In one preferred embodiment of the utility model, the driving device is collinear in wing chord length line.
In one preferred embodiment of the utility model, the quantity of the driving device is no less than two.
In one preferred embodiment of the utility model, the driving device is hydraulic actuator.
In one preferred embodiment of the utility model, the sliding rail includes being symmetrically disposed on driving device both sides up and down
Upper sliding rail and glidepath, upper sliding rail is identical with glidepath structure.
In one preferred embodiment of the utility model, the quantity of the sliding rail is identical as the quantity of the driving device, and
The plane and the driving device that the upper sliding rail and glidepath are constituted are coplanar.
In one preferred embodiment of the utility model, second wing) outer surface be provided with the upper sliding rail and under
The matched sliding part of sliding rail.
In one preferred embodiment of the utility model, the cross-sectional area of first wing is more than the cross section of the second wing
Product, and the openings of sizes of first wing is identical close to the end face size in fuselage direction as second wing.
The utility model additionally provides a kind of aircraft with spanwise length variable geometry, and the variable geometry is to fly
Machine fuselage is arranged for axisymmetrical.
The spanwise length variable geometry of the utility model makes aircraft wing realize that length is adjustable in the spanwise direction,
To change wing area so that can obtain lift by releasing the second wing when aircraft is needed compared with lift, and need
The second wing is withdrawn to reduce lift, with simple in structure, high reliability when reducing airplane ascensional force.
Description of the drawings
The drawings herein are incorporated into the specification and forms part of this specification, and shows and meets the utility model
Embodiment, and for explaining the principles of the present invention together with specification.
Fig. 1 is the spanwise length variable geometry structure chart of one embodiment of the utility model.
Fig. 2 is the drive arrangement position view of one embodiment of the utility model.
Reference numeral：
The first wings of 1-, the second wings of 2-, 3- sliding rails, 4- driving devices, 5- fuselages, the upper sliding rails of 31-, 32- glidepaths.
Specific implementation mode
To keep the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Attached drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the utility model.
As described in the prior art, existing aircraft wing generally controls the liter of aircraft using deflectable small area rudder face
Power, small area rudder face is for big aircaft configuration, and wing structure is larger, trailing edge setting rudder face can be realized, however for
For some Medium Planes or baby plane, wing structure is smaller, if rudder face is arranged in trailing edge again, can increase answering for wing
Polygamy, the utility model proposes the wing structures that a kind of span can be changed thus, to meet the needs of aircraft is to lift.
It is shown in Figure 1, the spanwise length variable geometry of the utility model comprising：First wing 1, the first machine
1 one end of the wing is connect with airframe 5, and its side far from fuselage 5 has opening, this opening is for accommodating or connecting the second machine
The wing 2；Sliding rail 3, sliding rail 3 are set in the first wing 1 and extend from the opening of the first wing 1 to the direction of fuselage 5；Second wing
2, the second wing 2 is attached or connected on sliding rail 3, can be slided from opening to the direction of fuselage 5 along sliding rail：And driving device
4, driving device 4 is arranged along wing spanwise direction, and one end is fixed with aircaft configuration, and the other end is connected to the second wing 2, is used for
The second wing 2 is driven to be moved to the direction of fuselage 5.
As shown in the figure, the first wing 1 is made of two ribs 11 and covering, and rib 11 is used to support covering, to constitute wing
Whole, the opening that driving device 4 needs guiding through two ribs 11 arrival right side is fixedly connected with the rib of the second wing 2, due to rib
11 constitute the supporting mechanism of the first wing 1, in order to not influence the structural strength of the first wing 1, are only opened up in rib 11 for driving
The circular hole that dynamic device 4 passes through.For second wing 2 under the driving of driving device 1, stroke is 11 right side rib of the first wing
The distance between 11 and right openings.
In one preferred embodiment of the utility model, driving device 4 is collinear in wing chord length line, and dotted line is shown i.e. in Fig. 1
For wing chord length (center lines of Airfoil Sections), driving device 4 is arranged in wing chord length, is conducive to driving device 4 to the
The driving of two wings 2, i.e., so that the uniform force of the second wing 2 in the horizontal direction, its unbalance stress will not be caused and along figure
Middle dotted line is swung up and down.
Preferably, the quantity of the driving device 4 is no less than two.It is using two driving devices as shown in Figure 2
Embodiment, two driving devices 4 both pass through the rib 11 in the first wing 1, and two driving devices 4 are collinear in wing chord length, therefore two
The plane that driving device 4 is constituted is opened up with wing to parallel.The second wing 2 can be driven to be moved along sliding rail 3 by driving device 4.
When two driving devices 4 drive the first wing 2, it may make the second wing 2 to be unlikely to centered on driving device 4 and swing or revolve
Turn, driving is made more to stablize.
It is understood that attached drawing 2 only schematically depicts the embodiment using two driving devices 4, and use more
When the case where a driving device 4, it can arrange successively according to the above situation.It, can be successively by itself and institute in figure 2 when such as using three
Two 4 upper right sides of driving device shown or lower left side arrangement.
In the present invention, above-mentioned driving device 4 can provide larger driving with hydraulic actuator, hydraulic actuator
Power.
In another preferred embodiment of the utility model, sliding rail 3 includes being symmetricly set on the upper of about 4 both sides of driving device
Sliding rail 31 and glidepath 32, upper sliding rail 31 is identical with the structure of glidepath 32, referring to Fig. 1, the above-mentioned noun of locality it is " upper and lower " for based on
Shown in the orientation Fig. 1.In Fig. 1, spanwise z, fuselage axis are perpendicular to z to inwardly or outwardly.
Preferably, the quantity of quantity with driving device 4 of sliding rail 3 is identical in the utility model, and upper sliding rail 31 and downslide
The plane and driving device 4 that rail 32 is constituted are coplanar.
In one preferred embodiment of the utility model, the outer surface of the second wing 2 is provided with and upper sliding rail 31 and glidepath
32 matched sliding parts.Specifically, upper and lower slide rail can be male-type sliding rail, or fluted body sliding rail, correspondingly, then
The outer surface of second wing 2 then could be provided as the fluted body sliding part to match with male-type sliding rail, or with fluted body sliding rail
The male-type sliding part to match.
In one preferred embodiment of the utility model, the cross-sectional area of the first wing 1 is more than the cross section of the second wing 2
Product, and the openings of sizes of the first wing 1 is identical close to the end face size in fuselage direction as the second wing 2.In the present invention,
First wing 1 is the transition structure of the second wing 2 and fuselage 5, should have the stronger rigidity of structure to have the second machine of support
The ability of the wing 2.The opening in the first wing 1 is arranged in the left side of second wing 2, it is kept by sliding rail 3 and driving device 4
Position, in order to reduce influence of the air-flow to wing, the second wing 2 should keep preferably being bonded with the junction of the first wing 1.It removes
The above-mentioned openings of sizes for making the first wing 1 is identical outer close to the end face size in fuselage direction with the second wing 2, can also make described
Opening has certain elasticity and contractility, so that and opening keeps being bonded therewith at the leftmost side of the second wing 2, and
Opening also keeps being bonded at position as shown in the figure.
The spanwise length variable geometry of the utility model makes aircraft wing realize that length is adjustable in the spanwise direction,
To change wing area so that can obtain lift by releasing the second wing when aircraft is needed compared with lift, and need
The second wing is withdrawn to reduce lift, with simple in structure, high reliability when reducing airplane ascensional force.
In addition, a kind of aircraft with spanwise length variable geometry is also provided in the present invention, in this practicality
In novel aircraft, variable geometry is arranged by axisymmetrical of airframe, for providing lift.
The above, the only optimal specific implementation mode of the utility model, but the scope of protection of the utility model is not
It is confined to this, any one skilled in the art within the technical scope disclosed by the utility model, can readily occur in
Change or replacement, should be covered within the scope of the utility model.Therefore, the scope of protection of the utility model should be with
Subject to the scope of the claims.
Claims (9)
1. a kind of spanwise length variable geometry, which is characterized in that the variable geometry includes
First wing (1), first wing (1) have opening far from fuselage (5) side；
Sliding rail (3), the sliding rail (3) are set in the first wing (1) and extend from described be open to fuselage direction；
Second wing (2), second wing (2) is installed on the sliding rail (3), from the opening along the sliding rail (3)
It is slided to fuselage direction：And
Driving device (4), the driving device (4) is arranged along wing spanwise direction, and one end is fixed with aircaft configuration, the other end
It is connected to second wing (2), for driving second wing (2) to be moved to fuselage direction.
2. according to spanwise length variable geometry described in claim 1, which is characterized in that the driving device (4) is collinear in
Wing chord length line.
3. according to the spanwise length variable geometry described in claim 2, which is characterized in that the quantity of the driving device (4)
No less than two.
4. according to any spanwise length variable geometry of claims 1 to 3, which is characterized in that the driving device (4)
For hydraulic actuator.
5. spanwise length variable geometry according to claim 1, which is characterized in that the sliding rail (3) includes symmetrical
It is set to the upper sliding rail (31) and glidepath (32) of the driving device or more both sides, upper sliding rail (31) and glidepath (32) structure
It is identical.
6. spanwise length variable geometry according to claim 5, which is characterized in that the quantity of the sliding rail (3) with
The quantity of the driving device (4) is identical, and the plane that the upper sliding rail (31) is constituted with glidepath (32) is filled with the driving
It is coplanar to set (4).
7. spanwise length variable geometry according to claim 5, which is characterized in that the second wing (2) appearance
Face is provided with and the upper sliding rail (31) and glidepath (32) matched sliding part.
8. spanwise length variable geometry according to claim 1, which is characterized in that the cross of first wing (1)
Sectional area is more than the cross-sectional area of the second wing (2), and the openings of sizes of first wing (1) and second wing (2)
End face size close to fuselage direction is identical.
9. a kind of aircraft, which is characterized in that the aircraft has spanwise length as described in any of the claims 1 to 8 can
Become wing, the variable geometry is arranged by axisymmetrical of airframe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721564182.0U CN207683769U (en) | 2017-11-21 | 2017-11-21 | A kind of spanwise length variable geometry and the aircraft with it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721564182.0U CN207683769U (en) | 2017-11-21 | 2017-11-21 | A kind of spanwise length variable geometry and the aircraft with it |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207683769U true CN207683769U (en) | 2018-08-03 |
Family
ID=62998439
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721564182.0U Active CN207683769U (en) | 2017-11-21 | 2017-11-21 | A kind of spanwise length variable geometry and the aircraft with it |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207683769U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018303A (en) * | 2018-08-14 | 2018-12-18 | 晨龙飞机（荆门）有限公司 | A kind of aircraft horizontal tail wing that can quickly face upward with nutation |
| WO2021114578A1 (en) * | 2019-12-13 | 2021-06-17 | 浙江大学 | Telescopic wing structure with continuously variable wingspan |
-
2017
- 2017-11-21 CN CN201721564182.0U patent/CN207683769U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018303A (en) * | 2018-08-14 | 2018-12-18 | 晨龙飞机（荆门）有限公司 | A kind of aircraft horizontal tail wing that can quickly face upward with nutation |
| CN109018303B (en) * | 2018-08-14 | 2020-05-19 | 晨龙飞机（荆门）有限公司 | Plane flat tail wing capable of quickly pitching up and down |
| WO2021114578A1 (en) * | 2019-12-13 | 2021-06-17 | 浙江大学 | Telescopic wing structure with continuously variable wingspan |
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