CN208993924U - Deformable rotor flapping wing fixed-wing one aircraft - Google Patents
Deformable rotor flapping wing fixed-wing one aircraft Download PDFInfo
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- CN208993924U CN208993924U CN201820635944.XU CN201820635944U CN208993924U CN 208993924 U CN208993924 U CN 208993924U CN 201820635944 U CN201820635944 U CN 201820635944U CN 208993924 U CN208993924 U CN 208993924U
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- wing
- fixed
- back segment
- limit
- aileron
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Abstract
The utility model provides a kind of deformable rotor flapping wing fixed-wing one aircraft, is related to vehicle technology field, solves existing fixed-wing and be difficult to keep stable technical problem with shape after deformation before being deformed.The aircraft includes that fuselage, fixed-wing and shape keep aileron, fixed-wing includes the leading portion wing connecting with fuselage and the back segment wing being flexibly connected with the leading portion wing, and the back segment wing can switch relative to the position of the leading portion wing between limit unfolded state, limit folded state；Shape keeps aileron to be connected to the back segment wing between fuselage and can switch between limit unfolded state, limit folded state together with the companion back segment wing；Fixed-wing in limit unfolded state and in limit folded state is able to maintain that dimensionally stable under the supporting role that self structure and shape keep aileron common until fixed-wing is resetted or deformed by driving.The utility model is for making fixed-wing keep stabilization with shape after deformation before being deformed.
Description
Technical field
The utility model relates to vehicle technology fields, integrally fly more particularly, to a kind of deformable rotor flapping wing fixed-wing
Row device.
Background technique
Gyroplane be it is a kind of using it is preceding winged when relative wind blow autorotation to generate the rotary wing aircraft of lift.It
Forward force directly provided by driven by engine propeller, gyroplane is a kind of aircraft between helicopter and aircraft,
Equipped with rotor and fixed aerofoil.Gyroplane have landing apart from it is short, low speed low-latitude flying can be made, it is simple light and handy, convenient for hidden etc.
Feature, can be used for taking photo in the sky, arm discharge, battlefield scout etc..
Gyroplane is divided into active gyroplane and driven gyroplane according to power device itself whether is had；There are also between going straight up to
The fixed-wing aircraft that verts between machine and fixed-wing can be flown with VTOL fixed-wing, but no matter tilting rotor or fixation of verting
The wing, fixed-wing will not fold.This gyroplane fuselage size is big, it is flat fly with hung down it is more demanding when switching；In addition also
There are combined wing aircraft, the rotor of existing vertical lift, and has fixed-wing.But it is neither foldable, fuselage size is big, dynamical system
It is again complicated.
The fixed-wing of common gyroplane cannot deform or deform after also can only using rotor itself vert and twist come
It realizes that lifting peace flies, needs to install additional on propeller set and vert or wrench device, the structure of such aircraft is more complicated,
Complete machine safety is relatively low, and installation and maintenance are inconvenient.
And the fixed-wing or fuselage of existing deformable rotor flapping wing fixed-wing one aircraft can utilize deformation driving
It device deformation and resets, and in its deformation or realizes aircraft entirety center of gravity position during reset in fixed-wing or fuselage
The change set so as to adjust the lifting and flat winged state of aircraft, and equals winged speed, and so there is no need to the spiral shells in rotor
It installs additional and verts or wrench device on rotation paddle device, simplify airframe structure and its installation and maintenance process, increase its safety.
Applicants have discovered that at least there is following technical problem in the prior art: in the prior art fixed-wing before being deformed and become
Shape is difficult to keep stable after shape.
Utility model content
It is existing to solve the purpose of this utility model is to provide a kind of deformable rotor flapping wing fixed-wing one aircraft
There are fixed-wings to be difficult to keep stable technical problem with shape after deformation before being deformed in technology.It is provided by the utility model all
Many technical effects elaboration as detailed below that optimal technical scheme in more technical solutions can be generated.
To achieve the above object, the utility model provides following technical scheme:
Deformable rotor flapping wing fixed-wing one aircraft provided by the utility model, including fuselage, fixed-wing and shape
Shape keeps aileron, in which:
The fixed-wing includes the leading portion wing connecting with the fuselage and the back segment wing that is flexibly connected with the leading portion wing,
The back segment wing can switch relative to the position of the leading portion wing between limit unfolded state, limit folded state；The shape
Shape keeps aileron to be connected to the back segment wing between fuselage and can fold in company with together with the back segment wing in limit unfolded state, the limit
Switch between state；
The support that the fixed-wing in limit unfolded state keeps aileron common in self structure and the shape
Dimensionally stable is able to maintain that under effect until the fixed-wing is driven and is reset to limit folded state；In limit folded state
The fixed-wing be able to maintain that dimensionally stable is straight under the supporting role that self structure and the shape keep aileron common
To being deformed into limit unfolded state by driving again.
Further, the junction of the shape holding aileron and the back segment wing is located at the central section of the back segment wing.
Further, the shape keeps aileron to include the inboard wing being flexibly connected with the fuselage and live with the inboard wing
The ala lateralis of dynamic connection, the ala lateralis are flexibly connected with the back segment wing.
Further, when the fixed-wing is in the limit folded state, the ala lateralis is fitted in the back segment wing
The back segment wing is simultaneously limited in limit folded state by inside；It is described outer when the fixed-wing is in the limit unfolded state
Flank is in the same plane with the inboard wing and the back segment wing is limited to limit unfolded state.
Further, when the shape keeps aileron to be in the limit folded state, the inboard wing and the ala lateralis
Junction to the free extreme direction of the back segment wing bend.
Further, the junction of the inboard wing and the ala lateralis is equipped with deformation driving device.
Further, the back segment wing and the shape keep the junction of aileron to be equipped with deformation driving device and/or institute
State the company that shape keeps the junction of aileron and the fuselage to be equipped with deformation driving device and/or the leading portion wing and the back segment wing
The place of connecing is equipped with deformation driving device.
Further, rotor, the rotor installation are also equipped on the deformable rotor flapping wing fixed-wing one aircraft
At the top of the back segment wing.
Further, the fixed-wing is equipped at least one downward lifting support protrusion；The deformable rotor flapping wing is solid
Determine the bottom of wing one aircraft lifting support protrusion when droping to ground under the fixed-wing is in limit folded state
Portion is with ground face contact and by the deformable rotor flapping wing fixed-wing one aircraft support on ground.
Further, folding joint, the deformable rotor flapping wing fixed-wing one aircraft are additionally provided on the inboard wing
Folding cutting ferrule, the deformable rotor flapping wing fixed-wing one aircraft are arranged with when in running order at the folding joint
When in off working state, the folding cutting ferrule can be moved into except the folding joint and make the inboard wing in the folding
Folded joint folds.
The utility model has the following beneficial effects: being mounted with that shape keeps aileron between the back segment wing and fuselage, make fixed-wing
Under the supporting role that self structure and shape keep aileron common, whether folded in limit unfolded state or the limit
State can maintain the dimensionally stable of fixed-wing, until fixed-wing is driven and changes status to and (reset or deform), in this way
It avoids and drives fixed-wing to deform or reset by deformation driving device merely but the state after deformation or reset
It is not easy the defect kept, makes the deformation of fixed-wing and the limit unfolded state after reset and limit reset state can be effective
It keeps.
Detailed description of the invention
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Or attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is only
It is some embodiments of the utility model, for those of ordinary skill in the art, in the premise not made the creative labor
Under, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is that the deformable rotor flapping wing fixed-wing one aircraft of the utility model is in limit folded state schematic diagram；
Fig. 2 is that the deformable rotor flapping wing fixed-wing one aircraft of the utility model is in limit unfolded state schematic diagram；
Fig. 3 is that the deformable rotor flapping wing fixed-wing one aircraft of the utility model is in full folded state schematic diagram.
In figure: 1, fuselage；2, the leading portion wing；3, the back segment wing；4, inboard wing；5, ala lateralis.
Specific embodiment
To keep the purpose of this utility model, technical solution and advantage clearer, below by the technology to the utility model
Scheme is described in detail.Obviously, the described embodiments are only a part of the embodiments of the utility model, rather than all
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are not before making creative work
Obtained all other embodiment is put, the range that the utility model is protected is belonged to.
As shown in Figure 1-3, deformable rotor flapping wing fixed-wing one aircraft provided by the utility model include fuselage 1,
Fixed-wing and shape keep aileron, and fixed-wing includes the leading portion wing 2 connecting with fuselage 1 and is flexibly connected with the leading portion wing 2
The back segment wing 3, the back segment wing 3 can switch relative to the position of the leading portion wing 2 between limit unfolded state, limit folded state；Shape
Holding aileron is connected between the back segment wing 3 and fuselage 1 and can be in company with the back segment wing 3 together in limit unfolded state, limit rugosity
Switch between state；
Fixed-wing in limit unfolded state energy under the supporting role that self structure and shape keep aileron common
Dimensionally stable is enough maintained until fixed-wing is driven and is reset to limit folded state；Fixed-wing in limit folded state is certainly
Dimensionally stable is able to maintain that under the supporting role that body structure and shape keep aileron common until again extremely by driving deformation
Limit unfolded state.
In the present embodiment, it is mounted with that shape keeps aileron between the back segment wing 3 and fuselage 1, makes fixed-wing in self structure
And shape is kept under the common supporting role of aileron, is whether in limit unfolded state or limit folded state, it can
The dimensionally stable of fixed-wing is enough maintained, until fixed-wing is driven and changes status to and (reset or deform), this avoid lists
The pure state for driving fixed-wing to deform or reset after still deforming or resetting by deformation driving device is not easy to protect
The defect held keep the deformation of fixed-wing and the limit unfolded state after reset and limit reset state can effectively.
The junction of optionally embodiment, shape holding aileron and the back segment wing 3 is located at the middle region of the back segment wing 3
Section.In order to make shape that aileron be kept to the back segment wing 3 to play the role of support, shape can be kept aileron with the back segment wing 3 from
It is connected by end, aileron can also be kept to be connected with the middle section of the back segment wing 3 shape；When being in limit unfolded state in this way,
Shape, which keeps aileron to be connected with the middle section of the back segment wing 3, can be used shorter shape and keeps aileron that can rise to the back segment wing 3
To the effect of support, compare saving material.
Optionally embodiment, it includes the inboard wing 4 and and inboard wing being flexibly connected with fuselage 1 that shape, which keeps aileron,
4 ala lateralis 5 being flexibly connected, ala lateralis 5 are flexibly connected with the back segment wing 3.Since shape keeps aileron that can play branch to the back segment wing 3
Support acts on and switches between limit unfolded state, limit folded state together in company with the back segment wing 3, and shape keeps aileron itself
Deformation can use Telescopic shaft type, i.e., as the deformation of the back segment wing 3 changes the length that shape keeps aileron；Or shape is kept
Aileron is set as two parts being flexibly connected: inboard wing 4 and ala lateralis 5, when deformation occurs for the back segment wing 3, inboard wing 4 and outside
Angle between the wing 5 also changes correspondingly, and such structure is simply easily worked, and the supporting role played to the back segment wing 3 is also more
It is ideal.
Optionally embodiment, when fixed-wing is in limit folded state, ala lateralis 5 is fitted in the interior of the back segment wing 3
The back segment wing 3 is simultaneously limited in limit folded state by side；When fixed-wing is in limit unfolded state, ala lateralis 5 is in inboard wing 4
Limit unfolded state is limited in approximately the same plane and by the back segment wing 3.Ala lateralis 5 is fitted in the inside of the back segment wing 3, is in this way
The deformation of folded state keeps aileron to be in maximum folding degree and can not be further continued for folding；And when ala lateralis 5 with it is interior
Flank 4 is in the same plane, and deformation keeps aileron to be in maximum unfolded state and can not be further continued for being unfolded；Therefore
Deformation keeps the two states of aileron that can support fixed-wing to the maximum extent, make its also in corresponding limit unfolded state and
Limit folded state is able to maintain dimensionally stable.
Optionally embodiment, when shape keeps aileron to be in limit folded state, inboard wing 4 and ala lateralis 5
Junction is bent to the free extreme direction of the back segment wing 3.The junction of inboard wing 4 and ala lateralis 5 can be to the back segment wing 3 and the leading portion wing
The direction of 2 junction is bent, and can also be bent to the free extreme direction of the back segment wing 3, is bent to the free extreme direction of the back segment wing 3
Design can make fixed-wing and shape that aileron be kept to form a more stable support structure, make in limit unfolded state and
The shape of the fixed-wing of limit folded state keeps more stable.
The junction of optionally embodiment, inboard wing 4 and ala lateralis 5 is equipped with deformation driving device.Such as Fig. 1-3
Shown, the junction of inboard wing 4 and ala lateralis 5 is labeled as c, and installation deformation driving device makes shape that aileron be kept to fold at c
And expansion, can effectively driving the back segment wing 3, deformation occurs, and the deformation of fixed-wing is combined to keep the support of aileron to make in shape
Under, then together with the supporting role of deformation driving device itself, so that it may preferably be kept fixed the deformation of the wing.
Optionally embodiment, the back segment wing 3 and shape keep the junction of aileron be equipped with deformation driving device and/
Or shape keeps the junction of aileron and fuselage 1 to be equipped with the junction for deforming driving device and/or the leading portion wing 2 and the back segment wing 3
Deformation driving device is installed.Similarly, in fig. 1-3, the back segment wing 3 and shape keep the junction of aileron to be marked as b, shape
The junction of aileron and fuselage 1 is kept to be marked as e, the leading portion wing 2 and the junction of the back segment wing 3 are marked as a, in a, b, e tri-
Locate any one place or many places installation deformation driving device therein, can effectively driving the back segment wing 3, deformation occurs, and combines
The deformation of fixed-wing shape keep aileron supporting role under, then together with deformation driving device itself supporting role, so that it may
To be preferably kept fixed the deformation of the wing.
Optionally embodiment is also equipped with rotor, rotor on deformable rotor flapping wing fixed-wing one aircraft
It is mounted on the top of the back segment wing 3.Rotor is that the vertical rise and fall peace of aircraft flies to provide the device of power, and rotor can be installed
On the fuselage 1, it also may be mounted on fixed-wing, and the spacing between the leading portion wing 2 is smaller, therefore the present embodiment installs rotor
On the back segment wing 3, rotor is designed on the fixed-wing of such two sides, such lift is larger, strengthen aircraft lift and its
Stability.
Optionally embodiment, fixed-wing are equipped at least one downward lifting support protrusion；Deformable rotor is flutterred
Wing fixed-wing one aircraft when droping to ground under fixed-wing is in the limit folded state bottom of lifting support protrusion with
Ground face contact and by deformable rotor flapping wing fixed-wing one aircraft support on ground.Deformable rotor flapping wing fixed-wing one
Aircraft needs undercarriage in landing to support, and in order to substitute undercarriage, the lower end of fixed-wing is provided with downward rise and fall
Support protrusion, may not necessarily thus install undercarriage, and fixed-wing can inherently substitute the function of undercarriage, alleviate flight
The overall weight of device is allowed to lighter.
Optionally embodiment, is additionally provided with folding joint on inboard wing 4, i.e. at d in Fig. 1-3, deformable rotor
Folding cutting ferrule is arranged with when flapping wing fixed-wing one aircraft is in running order at folding joint, deformable rotor flapping wing is fixed
When wing one aircraft is in off working state, folding cutting ferrule can be moved into except folding joint and fold inboard wing 4
Joint folds.In order to enable deformable rotor flapping wing fixed-wing one aircraft more to be filled when in off working state
Point ground folds, and is more convenient for storing and carry, folding joint will be provided on inboard wing 4, and in order to allow folding joint in aircraft
It arbitrarily will not disorderly be put in working condition, folding cutting ferrule is arranged at folding joint, inboard wing 4 is just in state of flight in this way
It keeps expansion and when off working state can then be folded to full folded state, meets the needs of different conditions.
Above description is only a specific implementation of the present invention, but the protection scope of the utility model is not limited to
In this, anyone skilled in the art within the technical scope disclosed by the utility model, can readily occur in variation
Or replacement, it should be covered within the scope of the utility model.Therefore, the protection scope of the utility model should be with the power
Subject to the protection scope that benefit requires.
Claims (10)
1. a kind of deformable rotor flapping wing fixed-wing one aircraft, which is characterized in that protected including fuselage, fixed-wing and shape
Hold aileron, in which:
The fixed-wing includes the leading portion wing connecting with the fuselage and the back segment wing that is flexibly connected with the leading portion wing, described
The back segment wing can switch relative to the position of the leading portion wing between limit unfolded state, limit folded state；The shape is protected
It holds aileron and is connected to the back segment wing between fuselage and together with the energy companion back segment wing in limit unfolded state, limit folded state
Between switch；
The supporting role that the fixed-wing in limit unfolded state keeps aileron common in self structure and the shape
Under be able to maintain that dimensionally stable until the fixed-wing is driven and is reset to limit folded state；Institute in limit folded state
It states fixed-wing and is able to maintain that dimensionally stable until again under the supporting role that self structure and the shape keep aileron common
It is secondary that limit unfolded state is deformed by driving.
2. deformable rotor flapping wing fixed-wing one aircraft according to claim 1, which is characterized in that the shape is protected
The junction for holding aileron and the back segment wing is located at the central section of the back segment wing.
3. deformable rotor flapping wing fixed-wing one aircraft according to claim 1, which is characterized in that the shape is protected
Hold the ala lateralis that aileron includes the inboard wing being flexibly connected with the fuselage and is flexibly connected with the inboard wing, the ala lateralis
It is flexibly connected with the back segment wing.
4. deformable rotor flapping wing fixed-wing one aircraft according to claim 3, which is characterized in that the fixed-wing
When in the limit folded state, the ala lateralis is fitted in the inside of the back segment wing and the back segment wing is limited in pole
Limit folded state；When the fixed-wing is in the limit unfolded state, the ala lateralis is in same with the inboard wing
Limit unfolded state is limited in plane and by the back segment wing.
5. deformable rotor flapping wing fixed-wing one aircraft according to claim 4, which is characterized in that the shape is protected
When holding aileron and being in the limit folded state, the freedom of the junction of the inboard wing and the ala lateralis to the back segment wing
Extreme direction bending.
6. deformable rotor flapping wing fixed-wing one aircraft according to claim 3, which is characterized in that the inboard wing
Deformation driving device is installed with the junction of the ala lateralis.
7. deformable rotor flapping wing fixed-wing one aircraft according to claim 1, which is characterized in that the back segment wing
Keep the junction of aileron that deformation driving device and/or shape holding aileron and the fuselage are installed with the shape
Junction is equipped with deformation driving device and/or the leading portion wing and the junction of the back segment wing is equipped with deformation driving device.
8. deformable rotor flapping wing fixed-wing one aircraft according to claim 1, which is characterized in that described deformable
It is also equipped with rotor on rotor flapping wing fixed-wing one aircraft, the rotor is mounted on the top of the back segment wing.
9. deformable rotor flapping wing fixed-wing one aircraft according to claim 1, which is characterized in that the fixed-wing
Equipped at least one downward lifting support protrusion；The deformable rotor flapping wing fixed-wing one aircraft is in the fixed-wing
The bottom of the lifting support protrusion and ground face contact are drop to when ground under limit folded state and will be described deformable
Rotor flapping wing fixed-wing one aircraft support is on ground.
10. deformable rotor flapping wing fixed-wing one aircraft according to claim 3, which is characterized in that the inside
Be additionally provided with folding joint on the wing, the deformable rotor flapping wing fixed-wing one aircraft when in running order the folding close
Folding cutting ferrule is arranged at section, when the deformable rotor flapping wing fixed-wing one aircraft is in off working state, the folding
Stacking set can be moved into except the folding joint and fold the inboard wing at the folding joint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820635944.XU CN208993924U (en) | 2018-04-28 | 2018-04-28 | Deformable rotor flapping wing fixed-wing one aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820635944.XU CN208993924U (en) | 2018-04-28 | 2018-04-28 | Deformable rotor flapping wing fixed-wing one aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208993924U true CN208993924U (en) | 2019-06-18 |
Family
ID=66794768
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820635944.XU Expired - Fee Related CN208993924U (en) | 2018-04-28 | 2018-04-28 | Deformable rotor flapping wing fixed-wing one aircraft |
Country Status (1)
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| CN (1) | CN208993924U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110271659A (en) * | 2019-07-03 | 2019-09-24 | 北京航空航天大学 | A kind of small drone fold concertina-wise wing based on paper folding principle |
-
2018
- 2018-04-28 CN CN201820635944.XU patent/CN208993924U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110271659A (en) * | 2019-07-03 | 2019-09-24 | 北京航空航天大学 | A kind of small drone fold concertina-wise wing based on paper folding principle |
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| 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: 20190618 Termination date: 20210428 |