CN207943171U - A kind of aircraft based on tip vortex lift-rising - Google Patents
A kind of aircraft based on tip vortex lift-rising Download PDFInfo
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- CN207943171U CN207943171U CN201820106476.7U CN201820106476U CN207943171U CN 207943171 U CN207943171 U CN 207943171U CN 201820106476 U CN201820106476 U CN 201820106476U CN 207943171 U CN207943171 U CN 207943171U
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- canard
- fuselage
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- arcwall face
- host wing
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Abstract
The utility model is related to aircraft fields, disclose a kind of aircraft based on tip vortex lift-rising, including fuselage and the host wing being fixed on fuselage, host wing power packages are installed on host wing, host wing power packages include host wing motor and host wing propeller, it is characterized in that, it further include the canard being fixed on fuselage, and the canard power packages on canard, canard power packages include canard motor and canard propeller, wherein, canard is located at the top of host wing, canard propeller is located at the wing tip of canard, and the rotation direction of canard propeller is consistent with the rotation direction of the tip vortex of place canard.The utility model by canard wing tip setting with tip vortex to identical canard propeller, enhance the tip vortex of canard to provide vortex lift to host wing, to achieve the effect that lift-rising, the lift resistance ratio of aircraft is improved, increases aircraft load-carrying and cruising ability.
Description
Technical field
The utility model is related to aircraft fields, more particularly, to unmanned vehicle field.
Background technology
With the development of technology, unmanned plane is in logistics transportation, high-tension bus-bar inspection, oil-gas pipeline inspection, geological prospecting, ring
The application potential in the fields such as border monitoring, deep woods fire prevention, precision agriculture, frontier defense patrol is wide.
Fixed Wing AirVehicle is one kind in aircraft, refers to and generates lift, fixed-wing by the wing being fixed on fuselage
The principle for generating lift is the pressure difference between lower aerofoil, which, can also be in wing other than it will produce lift
Wing tip generate tip vortex, so-called tip vortex refers to that the air-flow of lower aerofoil flows to winding after top airfoil around wing tip and formed
Whirlpool, which flows out backward forms tip vortex, and tip vortex can cause the unstable of aircraft, while can weaken place
The lift of aerofoil, therefore aircraft in the prior art usually passes through reinforcement to weaken based on tip vortex without attempting
Tip vortex is to increase the scheme of lift.
Utility model content
For overcome the deficiencies in the prior art, the utility model provides a kind of aircraft based on tip vortex lift-rising, uses
In breaking mistaken ideas in the prior art, efficiently using for tip vortex is realized.
Technical solution adopted by the utility model to solve its technical problems is：
A kind of aircraft based on tip vortex lift-rising, including fuselage and the host wing that is fixed on fuselage, on host wing
Host wing power packages are installed, host wing power packages include host wing motor and host wing propeller, which is characterized in that further include
The canard being fixed on fuselage, and the canard power packages on canard, canard power packages include canard motor and canard
Propeller, wherein canard is located at the top of host wing, and canard propeller is located at the wing tip of canard, and the rotation direction of canard propeller
It is consistent with the rotation direction of the tip vortex of place canard.
As the mode that is further improved of said program, the upper surface of fuselage includes protruded to external fuselage direction first
The lower surface of arcwall face, fuselage includes the 5th arcwall face, and the curvature of the first arcwall face is more than the curvature of the 5th arcwall face.
As the mode that is further improved of said program, the lower surface of fuselage further includes being connect with the front end of the 5th arcwall face
The second arcwall face, and the third arcwall face that is connect with the rear end of the 5th arcwall face, the front end of the first arcwall face and the second arc
The angle of tangent line between shape face and between the rear end of the first arcwall face and third arcwall face is not more than 90 °.
As the mode that is further improved of said program, the axis of the spacing of the first arcwall face to the 5th arcwall face along fuselage
The direction of line to both sides is sequentially reduced.
As the mode that is further improved of said program, the side of fuselage includes the 4th arc protruded to external fuselage direction
Shape face, and the spacing of the 4th arcwall face of both sides is successively increased by the direction of front end to the rear end of fuselage.
As the mode that is further improved of said program, canard power packages are located at the top of the center of gravity of aircraft, host wing
Power packages are located at the lower section of the center of gravity of aircraft.
It is further improved mode as said program, it is poor by the thrust between host wing propeller and canard propeller
Generate the nose-up pitching moment loaded for reducing canard.
It is further improved mode as said program, further includes the vertical empennage being fixed on fuselage, vertical empennage exists
Fuselage supports fuselage when being in VTOL state.
It is further improved mode as said program, further includes the adjusting rudder face being rotatably connected on vertical empennage.
It is further improved mode as said program, further includes the wing tip spiral of the tip location mounted on host wing
Paddle, the rotation direction of wing tip propeller are oppositely oriented with the tip vortex of place host wing.
The utility model has the beneficial effects that：
The utility model in the wing tip setting of canard and tip vortex by, to identical canard propeller, enhancing canard
Tip vortex improves the lift resistance ratio of aircraft to provide vortex lift to host wing to achieve the effect that lift-rising, increases winged
The load-carrying of row device and cruising ability.
Description of the drawings
The utility model is further illustrated with reference to the accompanying drawings and examples.
Fig. 1 is the stereoscopic schematic diagram of the utility model one embodiment；
Fig. 2 is the front view of the utility model one embodiment；
Fig. 3 is the side view of the utility model one embodiment.
Specific implementation mode
The technique effect of the design of the utility model, concrete structure and generation is carried out below with reference to embodiment and attached drawing
Clear, complete description, to be completely understood by the purpose of this utility model, scheme and effect.It should be noted that not conflicting
In the case of, the features in the embodiments and the embodiments of the present application can be combined with each other.
It should be noted that unless otherwise specified, when a certain feature is referred to as " fixing ", " connection " is in another feature,
It can directly fix, be connected in another feature, can also fix, be connected in another feature indirectly.In addition, this
The descriptions such as the up, down, left, right, before and after used in utility model are only relative to each composition portion of the utility model in attached drawing
For the mutual alignment relation divided.
In addition, unless otherwise defined, the technology of all of technologies and scientific terms used here by the article and the art
The normally understood meaning of personnel is identical.Term used in the description is intended merely to description specific embodiment herein, without
It is to limit the utility model.Term " and or " used herein includes appointing for one or more relevant Listed Items
The combination of meaning.
Referring to figs. 1 to Fig. 3, the stereoscopic schematic diagram, front view and side view of the utility model one embodiment are respectively illustrated
Figure.As shown, aircraft includes fuselage 1, host wing 2, canard 3, host wing power packages and canard power packages.
The fuselage 1 of the utility model is also used as lifting body auxiliary other than as the bearing structure of connection wing
Lift is provided.Specifically, fuselage 1 includes upper surface, lower surface and connection side upper and lower surfaces of, wherein lower surface includes
5th arcwall face 15, upper surface include the first arcwall face 11 protruded to 1 outside direction of fuselage, and the curvature of the first arcwall face 11 is big
In the curvature of the 5th arcwall face 15, it is similar to the construction of the upper and lower aerofoil of wing, lift is provided by pressure difference.
In order to reduce windage, the lower surface of fuselage further includes the second arcwall face being connect with the front end of the 5th arcwall face 15
12, and the third arcwall face 13 that is connect with the rear end of the 5th arcwall face 15, front end and the second arcwall face of the first arcwall face 11
The angle of tangent line between 12 and between the rear end and third arcwall face 13 of the first arcwall face 11 is not more than 90 ° so that fuselage
Integral into fairing.
In addition, the side of fuselage includes the 4th arcwall face 14 protruded to external fuselage direction, and the 4th arcwall face of both sides
14 spacing is successively increased by the direction of front end to the rear end of fuselage 1.The spacing edge of first arcwall face, 11 to the 5th arcwall face 15
The direction of the central axes of fuselage 1 to both sides is sequentially reduced.
The airframe structure of the utility model is on the basis of ensureing to have enough load spaces, additionally it is possible to provide certain liter
Power forms fuselage 1, host wing 2, canard 3 and provides lift jointly to share the dispersed structure of main screw lift.
Critical piece of the host wing 2 as output lift, may be used well known wing structure.Host wing 2 is symmetrically solid
The both sides of fuselage 1 are scheduled on, host wing power packages are installed thereon, host wing power packages include host wing propeller 4 and host wing
Motor 5, host wing power packages are equally symmetrical.It is installed on side host wing 2 in the present embodiment there are one host wing power packages,
But this is not construed as limitations of the present invention, in other examples, can also be on side host wing 2 install it is more
A host wing power packages, to form distributed propulsion, the rotation direction of host wing propeller 4 can be adjusted as needed.
The rear side of host wing 2 is additionally provided with host wing rudder face 21, and host wing rudder face 21 is rotatablely connected with host wing 2, and is passed through
Unshowned servo driving, 21 independent control of host wing rudder face of both sides.
Canard 3 is symmetrically fixed on the both sides of fuselage 1, and opposite host wing 2 is located at the front end of fuselage 1, and is located at host
The top of the wing 2.Canard power packages are installed, canard power packages include canard propeller 6 and canard motor 7, and canard is dynamic on canard 3
Power group is equally symmetrical.
Canard 3 is shorter in length than host wing 2 in the utility model, and canard power packages are mounted on the tip location of canard 3, and
The rotation direction of canard propeller 6 is consistent with the rotation direction of the tip vortex of place canard 3, i.e., for shown in Fig. 2, the canard on right side
Propeller 6 rotates in the counterclockwise direction, and the canard propeller 6 in left side is along rotating clockwise.
The utility model in the wing tip setting of canard 3 and tip vortex by that, to identical canard propeller 6, can increase
The intensity of tip vortex can provide vortex lift when tip vortex flows to the top airfoil of host wing 2 backward to host wing 2,
Although tip vortex can affect to the lift of canard 3, since the lift that host wing 2 is provided is more than canard
3, on the whole, tip vortex, which promotes the lift of host wing 2 to be more than, weakens the lift of canard 3, i.e., by rationally increasing
Tip vortex on strong canard 3, can promote the whole lift of aircraft.
To ensure stability, the position of centre of gravity of aircraft changes in the range of should be before complete machine aerodynamic center, and more leans on
Forward stability is better, however for traditional canard configuration airplane, center of gravity is too forward to bear the lift for increasing canard, from
And the angle of attack of canard is forced to increase, resistance is consequently increased.Based on this, the canard power packages in the utility model are located at aircraft
Center of gravity top, host wing power packages are located at the lower section of the center of gravity of aircraft, the torque that the two counterweight is formed centrally, to have
Adjust the effect of body pitching, such as in the case where canard load is too big, can by increasing the thrust of host wing power packages,
The thrust generation nose-up pitching moment for reducing canard power packages reduces the load of canard to offset the nose-down pitching moment of part, and then subtracts
Slight drag reduces the degree of dependence to position of centre of gravity, extended flight envelope curve so that aircraft being capable of more flexible carrier
Body.
The rear side of canard 3 is equipped with canard rudder face 31, and canard rudder face 31 is rotatablely connected with canard 3, and by unshowned steering engine
Driving, 31 independent control of canard rudder face of both sides.Host wing rudder face 21, canard rudder face 31, host wing power packages and canard power
The common control realized to aircraft flight posture of group, specifically, canard rudder face 31 and the differential completion of host wing rudder face 21 fly
Row device is operated around the pitching of Y-axis, and the differential completion aircraft of fuselage both sides rudder face is around the rolling of X-axis, and in addition fuselage both sides are dynamic
The thrust difference of power group completes the yaw operation of aircraft about the z axis, the aircraft of the utility model may be used it is any of and
The attitude regulation system that propeller works can be coordinated, is not especially limited this.
Preferably, canard rudder face 31 is located at the rear of canard propeller 6, and host wing rudder face 21 is located at host wing propeller 4
Rear, using canard propeller 6, host wing propeller 4 to air disturbance strengthen rudder face manipulation ability.
The utility model is preferably additionally provided with vertical empennage 8, and vertical empennage 8 is fixed on the both sides up and down of fuselage 1, one side
The stable effect of yaw is played in face, on the other hand can also be used as support construction, for the branch when aircraft is in vertical state
Fuselage is supportted, realizes the VTOL of the utility model.
Further, the utility model can also include the adjusting rudder face (not shown) being rotatably connected on vertical empennage,
So that empennage also functions to the effect of yaw adjustment.
In addition, in order to weaken adverse effect of the tip vortex on host wing 2 to lift, the utility model can also include
Mounted on the wing tip propeller (not shown) of the tip location of host wing 2, the wing of the rotation direction and place host wing of wing tip propeller
Point is vortexed oppositely oriented, to offset tip vortex.
It is illustrating for progress to be implemented to the preferable of the utility model, but the invention is not limited to the reality above
Example is applied, those skilled in the art can also make various equivalent variations without departing from the spirit of the present invention
Or replace, these equivalent deformations or replacement are all contained in the application claim limited range.
Claims (10)
1. a kind of aircraft based on tip vortex lift-rising, including fuselage and the host wing being fixed on the fuselage, the master
Host wing power packages are installed, the host wing power packages include host wing motor and host wing propeller, feature on wing
It is, further includes the canard being fixed on the fuselage, and the canard power packages on the canard, the canard is dynamic
Power group includes canard motor and canard propeller, wherein the canard is located at the top of the host wing, the canard propeller
Positioned at the wing tip of the canard, and the rotation direction of the canard propeller is consistent with the rotation direction of the tip vortex of place canard.
2. the aircraft according to claim 1 based on tip vortex lift-rising, which is characterized in that the upper surface of the fuselage
Include the first arcwall face protruded to external fuselage direction, the lower surface of the fuselage includes the 5th arcwall face, first arc
The curvature in shape face is more than the curvature of the 5th arcwall face.
3. the aircraft according to claim 2 based on tip vortex lift-rising, which is characterized in that the lower surface of the fuselage
Further include the second arcwall face being connect with the front end of the 5th arcwall face, and connect with the rear end of the 5th arcwall face
Third arcwall face, between the front end of the first arcwall face and second arcwall face and rear end of first arcwall face
The angle of tangent line between the third arcwall face is not more than 90 °.
4. the aircraft according to claim 2 based on tip vortex lift-rising, which is characterized in that first arcwall face is extremely
The spacing of 5th arcwall face is sequentially reduced along the direction of the central axes of the fuselage to both sides.
5. the aircraft according to claim 1 based on tip vortex lift-rising, which is characterized in that wrap the side of the fuselage
Include the 4th arcwall face protruded to external fuselage direction, and the spacing of the 4th arcwall face described in both sides by the fuselage front end extremely
The direction of rear end successively increases.
6. the aircraft according to any one of claim 1 to 5 based on tip vortex lift-rising, which is characterized in that described
Canard power packages are located at the top of the center of gravity of the aircraft, and the host wing power packages are located under the center of gravity of the aircraft
Side.
7. the aircraft according to claim 6 based on tip vortex lift-rising, which is characterized in that pass through the host wing spiral shell
Thrust difference between rotation paddle and the canard propeller generates the nose-up pitching moment loaded for reducing the canard.
8. the aircraft according to any one of claim 1 to 5 based on tip vortex lift-rising, which is characterized in that also wrap
The vertical empennage being fixed on the fuselage is included, described in the vertical empennage is supported when the fuselage is in VTOL state
Fuselage.
9. the aircraft according to claim 8 based on tip vortex lift-rising, which is characterized in that further include being rotatably connected on
Adjusting rudder face on the vertical empennage.
10. the aircraft according to any one of claim 1 to 5 based on tip vortex lift-rising, which is characterized in that also wrap
Include the wing tip propeller of the tip location mounted on the host wing, the wing of the rotation direction and place host wing of the wing tip propeller
Point is vortexed oppositely oriented.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820106476.7U CN207943171U (en) | 2018-01-23 | 2018-01-23 | A kind of aircraft based on tip vortex lift-rising |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820106476.7U CN207943171U (en) | 2018-01-23 | 2018-01-23 | A kind of aircraft based on tip vortex lift-rising |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207943171U true CN207943171U (en) | 2018-10-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820106476.7U Active CN207943171U (en) | 2018-01-23 | 2018-01-23 | A kind of aircraft based on tip vortex lift-rising |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108177777A (en) * | 2018-01-23 | 2018-06-19 | 南方科技大学 | A kind of aircraft based on tip vortex lift-rising |
-
2018
- 2018-01-23 CN CN201820106476.7U patent/CN207943171U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108177777A (en) * | 2018-01-23 | 2018-06-19 | 南方科技大学 | A kind of aircraft based on tip vortex lift-rising |
| CN108177777B (en) * | 2018-01-23 | 2023-11-10 | 南方科技大学 | Aircraft based on wingtip vortex rise |
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