CN207809768U - A kind of unmanned vehicle - Google Patents
A kind of unmanned vehicle Download PDFInfo
- Publication number
- CN207809768U CN207809768U CN201721619662.2U CN201721619662U CN207809768U CN 207809768 U CN207809768 U CN 207809768U CN 201721619662 U CN201721619662 U CN 201721619662U CN 207809768 U CN207809768 U CN 207809768U
- Authority
- CN
- China
- Prior art keywords
- wing
- unmanned vehicle
- attack
- installation axle
- angle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 238000009434 installation Methods 0.000 claims abstract description 38
- 230000007246 mechanism Effects 0.000 claims abstract description 15
- 230000009471 action Effects 0.000 claims abstract description 11
- 239000000463 material Substances 0.000 claims description 11
- 238000013016 damping Methods 0.000 claims description 10
- 230000005484 gravity Effects 0.000 claims description 10
- 230000000694 effects Effects 0.000 abstract description 9
- 238000005265 energy consumption Methods 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 7
- 230000008859 change Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 230000009514 concussion Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000009467 reduction Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000007665 sagging Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The utility model discloses a kind of unmanned vehicles, including：Fuselage, bindiny mechanism and at least one wing；The wing is rotatably installed in by the bindiny mechanism on the fuselage；The unmanned vehicle is in flight course, and under the action of incoming air, the wing automatically adjusts the angle of attack.The unmanned vehicle on the fuselage by being rotatablely connected at least one wing, the wing can automatically adjust the angle of attack under the action of incoming air, to persistently generate stable lift in unmanned vehicle flight course, greatly improve the lift-rising effect of the wing, its overall structure is simple, it is easy for installation, energy consumption is reduced, while improving the flight efficiency of unmanned vehicle.
Description
Technical field
The utility model is related to unmanned flight's equipment technical field more particularly to a kind of unmanned vehicles.
Background technology
When multi-rotor aerocraft carries out flight, especially high-speed flight when, need the nose-down attitude of larger angle steady
Determine flying speed, efficiency is low and high energy consumption.More rotors or other VTOL (vertical take-off and landing, vertically
Landing) aircraft one of the effective means that improves cruise efficiency is to increase fixed wing, but the available range of angles of attack of fixed wing
It is smaller, the angle of attack required when multi-rotor aerocraft high-speed flight cannot be met.If the installation angle and optimizing of fixed wing is being revolved more
When rotor aircraft high-speed flight in required range of angles of attack, although larger odds for effectiveness can be obtained under high-speed flight, when more
When rotor craft is in low velocity cruise, the wing angle of attack is in stall conditions, is not only nearly free from lift, also will produce huge
Big resistance.
Utility model content
In order to overcome the shortcomings of Related product in the prior art, the utility model proposes a kind of unmanned vehicles, to improve
The flight efficiency of unmanned vehicle.
The utility model provides a kind of unmanned vehicle, including：Fuselage, bindiny mechanism and at least one wing；
The wing is rotatably installed in by the bindiny mechanism on the fuselage；
The unmanned vehicle is in flight course, and under the action of incoming air, the wing automatically adjusts the angle of attack.
It is characterized in that：The distance between rear of pivot center and wing that wing is rotated relative to fuselage is more than wing
Aerodynamic center and wing the distance between rear.
In the certain embodiments of the utility model, during unmanned vehicle flies, in the work of incoming air
Under, the angle of attack of the wing is stabilized in the target angle of attack.
In the certain embodiments of the utility model, the target angle of attack is true according to the rear camber of the wing
It is fixed.
In the certain embodiments of the utility model, when the quantity of the wing is at least two, described at least two
A wing is symmetrically rotatably installed in the both sides of the fuselage.
In the certain embodiments of the utility model, the bindiny mechanism includes installation axle and installation axle component,
The installation axle component is arranged on fuselage, and one end of the installation axle is rotatably connected on installation axle component, institute
The other end for stating installation axle is fixedly connected with the wing.
In the certain embodiments of the utility model, the installation axle component includes bearing.
In the certain embodiments of the utility model, it is provided between the installation axle and the installation axle component
Damping material.
In the certain embodiments of the utility model, the unmanned vehicle further includes tractive unit, for limiting nobody
The angle of attack of aircraft wing in hovering or low-speed operations.
In the certain embodiments of the utility model, the tractive unit includes one or more elastomeric elements.
In the certain embodiments of the utility model, the unmanned vehicle further includes providing flight for unmanned vehicle
The rotor of power, wherein the wing is located at except induced draft range caused by rotor wing rotation.
In the certain embodiments of the utility model, the total life center of at least one wing and unmanned vehicle
Position of centre of gravity essentially coincide.
Compared with prior art, the utility model has the advantage that：
Unmanned vehicle described in the utility model embodiment, on the fuselage at least by bindiny mechanism's rotation connection
One wing, at least one wing are used to generate lift-rising effect when the unmanned vehicle is gradually accelerated forwardly,
Since the wing can automatically adjust the angle of attack in the target angle of attack, to fly in unmanned vehicle under the action of incoming air
Lasting in the process to generate stable lift, overall structure is simple, easy for installation, reduces energy consumption, while improving nobody and flying
The flight efficiency of row device verts system compared to existing rotor, has the cost advantage of bigger, can meet personal consumption grade
The consumption demand of unmanned vehicle.
Description of the drawings
In order to illustrate more clearly of the technical scheme in the embodiment of the utility model, will make below to required in embodiment
Attached drawing is briefly described, it should be apparent that, the accompanying drawings in the following description is only some embodiments of the utility model,
For those of ordinary skill in the art, without creative efforts, it can also be obtained according to these attached drawings
Other attached drawings.
Fig. 1 is the structural schematic diagram of unmanned vehicle described in the utility model；
Fig. 2 is the schematic diagram that unmanned vehicle described in the utility model automatically adjusts the wing angle of attack in flight course；
Fig. 3 is the curve synoptic diagram of the pitching moment slope of curve and lift coefficient of wing described in the utility model；
Fig. 4 is another structural schematic diagram of unmanned vehicle described in the utility model；
Fig. 5 is another structural schematic diagram of unmanned vehicle described in the utility model；
Reference sign：
1, fuselage；
2, bindiny mechanism；
3, wing；
4, tractive unit；
5, rotor；
21, installation axle；
22, installation axle component；
23, damping material.
Specific implementation mode
In order to make those skilled in the art more fully understand the utility model, below in conjunction with the utility model reality
The attached drawing in example is applied, the technical scheme in the utility model embodiment is clearly and completely described.Obviously, described
Embodiment is only that the utility model a part of the embodiment gives the utility model instead of all the embodiments in attached drawing
Preferred embodiment.The utility model can be realized in many different forms, however it is not limited to embodiment described herein,
It is made the understanding of the disclosure of the utility model more thorough and comprehensive on the contrary, purpose of providing these embodiments is.It is based on
The embodiments of the present invention, those of ordinary skill in the art are obtained all without creative efforts
Other embodiment shall fall within the protection scope of the present invention.
Unless otherwise defined, all of technologies and scientific terms used here by the article is led with the technology for belonging to the utility model
The normally understood meaning of technical staff in domain is identical.Terminology used in the description of the utility model herein only be
The purpose of description specific embodiment, it is not intended that in limitation the utility model.The specification and right of the utility model are wanted
Ask the term " comprising " and " having " in book and above-mentioned attached drawing and their any deformations, it is intended that cover non-exclusive packet
Contain.
Referenced herein " embodiment " is it is meant that a particular feature, structure, or characteristic described can wrap in conjunction with the embodiments
It is contained at least one embodiment of the utility model., which there is the phrase, in each position in the description to be each meant
Identical embodiment, nor the independent or alternative embodiment with other embodiments mutual exclusion.Those skilled in the art are explicit
Ground and implicitly understand, embodiment described herein can be combined with other embodiments.
Refering to fig. 1 with shown in Fig. 2, by the structural schematic diagram for the unmanned vehicle that the utility model embodiment provides.This
Unmanned vehicle in embodiment can be more rotor unmanned aircrafts, be illustrated by taking quadrotor unmanned vehicle as an example here
Property explanation, certainly, in other implementations, the unmanned vehicle can also be other kinds of unmanned vehicle.
The unmanned vehicle includes fuselage 1, bindiny mechanism 2 and at least one wing 3, and the wing 3 passes through the company
Connection mechanism 2 is rotatably installed on the fuselage 1；The wing 3 in the unmanned vehicle flight for providing additionally
Lift, in the utility model embodiment, the unmanned vehicle is described under the action of incoming air in flight course
Wing 3 automatically adjusts the angle of attack.During unmanned vehicle flies, under the action of incoming air, the angle of attack of wing 3 can be with
It is adjusted in available range of angles of attack, lift is provided for unmanned vehicle, improve the flight efficiency of unmanned vehicle.
As shown in figure 3, Fig. 3 is the curve synoptic diagram of the pitching moment slope of curve and lift coefficient of wing 3, wherein X-axis
For the lift coefficient of wing 3, lift coefficient can characterize the angle of attack of wing 3 here, and Y-axis indicates the pitching moment of wing 3, Y-axis
Positive axis indicate that new line pitching moment, the negative axis of Y-axis indicate nose-down pitching moment.The pitching moment slope of curve of the wing 3
Relative position between the pivot center that rotates relative to fuselage 1 of wing and unmanned vehicle aerodynamic center is related.When wing 3
The distance between rear of the pivot center and wing 3 that are rotated relative to fuselage 1 is equal to the aerodynamic center and wing 3 of wing 3
The distance between rear, i.e., when the pivot center is in its aerodynamic center position, no matter how its angle of attack changes, wing 3
Pitching moment it is constant；When the distance between the rear of pivot center and wing 3 that wing 3 is rotated relative to fuselage 1 is less than machine
The aerodynamic center of the wing 3 and the distance between the rear of wing 3, i.e., when the pivot center is located at after aerodynamic center, wing 3
The pitching moment slope of curve be positive value, from the point of view of the curve and the intersection point A (zero lift moment point) of X-axis, the increase of the angle of attack can produce
Raw new line pitching moment, the new line trend of the wing 3 to further increase, the reduction of the angle of attack will produce nose-down pitching moment,
The trend of bowing of wing 3 to further increase produces the unstable characteristic of 3 angle of attack of wing；When wing 3 is relative to fuselage
The distance between the pivot center of 1 rotation and the rear of wing 3 are more than between the aerodynamic center and the rear of wing 3 of wing 3
Distance, i.e., before the rotary shaft of wing 3 is located at its aerodynamic center when, the pitching moment slope of curve of wing 3 is positive value, with this
From the point of view of the intersection points B (zero lift moment point) of curve and X-axis, the increase of the angle of attack can make wing 3 generate nose-down pitching moment, to provide
Reduce the trend of the angle of attack of wing 3, the reduction of the angle of attack can make wing 3 generate new line pitching moment, increase wing 3 to provide
The trend of the angle of attack produces the characteristic of 3 angle of attack of wing stabilization, then if pivot center and machine that wing 3 is rotated relative to fuselage 1
The distance between rear of the wing 3 is more than the distance between the rear of the aerodynamic center and wing 3 of wing 3, when unmanned vehicle height
When fast flight, the angle of attack of wing 3 has stable trend.If the angle of attack of wing 3 is stabilized in available range of angles of attack, machine
The wing 3 provides lift for unmanned vehicle, improves the flight efficiency of unmanned vehicle.
Specifically, the distance between the rear of pivot center and wing 3 that wing 3 is rotated relative to fuselage 1 is more than wing 3
Aerodynamic center and wing 3 the distance between rear when, during unmanned vehicle flies, in the effect of incoming air
Under, the angle of attack of the wing 3 is stabilized in the target angle of attack.Wherein, the target angle of attack can be less than any of stall angle
One angle of attack, it is generally the case that the target angle of attack can be determined according to stall angle with a safety coefficient, such as safety system
Number can be 0.7, and the target angle of attack can be the product of stall angle and safety coefficient, for example, stall angle is 10 degree, at this point,
The target angle of attack can be 7 degree.
In certain embodiments, the target angle of attack is determined according to the rear camber of the wing 3.Specifically, target
Zero liter of pitching moment of the angle of attack corresponding angle of attack when can be zero liter of pitching moment, the wing 3 is according to after the wing 3
Edge camber determines, therefore can accordingly adjust zero liter of pitching power of the wing 3 by changing the rear camber of the wing 3
Square, the size of zero liter of pitching moment are the intersection point of pitching moment curve and X-axis in Fig. 3.If the pitching moment of wing 3 is oblique
Rate is negative, i.e., the distance between wing 3 is rotated relative to fuselage 1 pivot center and the rear of wing 3 are more than the pneumatic of wing 3
When center and the distance between the rear of wing 3, the corresponding angle of attack of lift coefficient is target when wing 3 is in zero liter of pitching moment
The angle of attack, during unmanned vehicle flies, under the action of incoming air, wing 3 can be attacked by stablizing naturally at this
On angle, to persistently generate stable lift in unmanned vehicle flight course.
The quantity of the wing 3 is matched according to the total lift demand of the unmanned vehicle, and at least one wing 3
Total life center and the position of centre of gravity of unmanned vehicle essentially coincide, since the flight of unmanned vehicle is put down by lift
Weigh the gravity of its own, when the total life center of the wing 3 differs larger in position with the center of gravity of unmanned vehicle, meeting
Cause to increase the unstable trend of unmanned vehicle, influences the stabilized flight of the unmanned vehicle.
Meanwhile the quantity of the wing 3 can be selected according to actual demand.For example, when the quantity of the wing 3 is one
When a, the wing 3 can be rotatably installed in 1 top of the fuselage or lower part by the bindiny mechanism 2；When the wing 3
Quantity be at least two when, as shown in figure 4, at least two wing 3 is symmetrically rotatably installed in the two of the fuselage 1
Side；Certainly, the installation site of above-mentioned wing 3 is intended only as example, in actual installation process, according to the unmanned vehicle
1 structure of fuselage and the wing 3 quantity determines and states the mounting means of wing 3, the utility model embodiment has no this
Limitation.
In the utility model embodiment, the material of the wing 3 can select different lightweights multiple according to actual demand
Condensation material or metal etc. can keep enough rigids in the case where not increasing the gravity burden of the fuselage 1 as possible, meet
Flight demand under different scenes.
As shown in figure 4, the bindiny mechanism 2 includes installation axle 21 and installation axle component 22, the installation axle cooperation
Component 22 is arranged on the fuselage 1, and one end of the installation axle 21 is rotatably connected on installation axle component 22, the installation axle
21 other end is fixedly connected with the wing 3, and the installation axle component 22 includes bearing or other structures that are rotatably assorted.
Damping material 23, the damping material 23 are provided between the installation axle 21 and the installation axle component 22
The stability moved in the flight course of the unmanned vehicle for increasing the wing 3, avoids the wing 3 at nobody
When the flight attitude suddenly change of aircraft, cause the violent concussion of the wing 3；For unmanned vehicle, especially more rotations
For wing unmanned vehicle, the dynamic for being frequently accompanied by flight attitude according to environmental change or flight demand in flight course becomes
Change, for example, conventional dogled, height rises or the variation of the flight attitudes such as decline can all lead to the machine in unexpected occur
The violent concussion of the wing 3, when the wing 3 shakes, can influence nobody since the wing 3 is rotatably installed on the fuselage 1
The flight stability of aircraft.Therefore, in order to increase the wing 3 moved in the flight course of the unmanned vehicle it is steady
Qualitative, damping material 23 is arranged in contact position of the present embodiment between the installation axle 21 and the installation axle component 22,
To reduce concussion of the wing 3 in the flight attitude suddenly change of unmanned vehicle.Wherein, the damping material 23 can be
It is one or more in rubber, plastics, damping grease, damping oil.
The unmanned vehicle further includes tractive unit 4, is hovering or is flying at low speed opportunity for limiting unmanned vehicle
The angle of attack of the wing 3；In conjunction with shown in Fig. 1, when the unmanned vehicle be in hovering or low-speed operations scene under, in the effect of gravity
Under, the wing 3 can be in hang, and the angle of attack of wing 3 is likely larger than stall angle, when the wing 3 is sagging, if institute
It states unmanned vehicle to fly at low speed, then the wing 3 can form resistance to influence the flight shape of the unmanned vehicle
Tractive unit 4 is arranged in state, therefore, the present embodiment, limits the angle of attack of unmanned vehicle wing 3 in hovering or low-speed operations, this
Sample can reduce the flight resistance that wing 3 is brought to unmanned vehicle when unmanned vehicle flies at low speed device.Wherein, described
Tractive unit 4 may include one or more elastomeric elements (such as spring, rubber material etc.).
In certain embodiments, one end of the tractive unit 4 connects the fuselage 1, and the other end connects the rear of wing 3,
Tractive unit 4 draws the rear of wing 3, and the wing 3 is made to be protected when unmanned vehicle is hovered or is flown at low speed
A smaller angle of attack is held, wing 3 is avoided to form a larger angle of attack under the effect of gravity.
As shown in fig.5, in certain embodiments, the tractive unit 4 can surround the installation axle 21 and be arranged, described to lead
Draw portion 4 for being drawn to it when the installation axle 21 rotate, make the wing 3 hover in unmanned vehicle or
A smaller angle of attack is kept when low-speed operations, and wing 3 is avoided to form a larger angle of attack under the effect of gravity.
As shown in Fig. 2, the unmanned vehicle further includes the rotor 5 for providing flying power for unmanned vehicle, wherein institute
It states wing 3 to be located at except induced draft range caused by rotor 5 rotates, the induced draft refers to rotation of the air in rotor 5
It transfers to and holds steady air flow perpendicular to wing extending direction and downward with lower formation, to be provided for the unmanned vehicle
Power is risen, the induced draft range refers to then the sphere of action that rotor 5 forms the air-flow in rotary course.By wing
3 are arranged except the caused induced draft range of rotor wing rotation, and gas is induced caused by being rotated in this way to avoid the rotor 5
Stream, which can adaptively adjust the angle of attack of the wing 3, causes resistance to interfere.
Unmanned vehicle described in the utility model embodiment, on the fuselage 1 extremely by the rotation connection of bindiny mechanism 2
A few wing 3, at least one wing 3 are used to generate lift-rising effect when the unmanned vehicle is gradually accelerated forwardly
Fruit, since the wing 3 can automatically adjust the angle of attack in the target angle of attack, in unmanned vehicle under the action of incoming air
Persistently generate stable lift in flight course, while by the damping material 23 and described between wing 3 and fuselage 1
Under the mating reaction of tractive unit 4, effectively prevent wing 3 in flight course it is violent variation and under the effect of gravity under
It hangs down, greatly improves the lift-rising effect of the wing 3, overall structure is simple, easy for installation, reduces energy consumption, carries simultaneously
The high flight efficiency of unmanned vehicle verts system compared to existing rotor, has the cost advantage of bigger, can meet
The consumption demand of personal consumption grade unmanned vehicle.
It these are only the embodiments of the present invention, be not intended to limit the scope of the claims of the utility model, although with reference to before
Embodiment is stated the utility model is described in detail, it, still can be right for those skilled in the art comes
Technical solution recorded in aforementioned each specific implementation mode is modified, or carries out equivalent replace to which part technical characteristic
It changes.Every equivalent structure done using the utility model specification and accompanying drawing content is directly or indirectly used in other correlations
Technical field, similarly within the utility model patent protection domain.
Claims (12)
1. a kind of unmanned vehicle, which is characterized in that including fuselage, bindiny mechanism and at least one wing；
The wing is rotatably installed in by the bindiny mechanism on the fuselage；
The unmanned vehicle is in flight course, and under the action of incoming air, the wing automatically adjusts the angle of attack.
2. unmanned vehicle according to claim 1, it is characterised in that：The pivot center that wing is rotated relative to fuselage with
The distance between rear of wing is more than the distance between the rear of the aerodynamic center and wing of wing.
3. unmanned vehicle according to claim 2, it is characterised in that：During unmanned vehicle flies, coming
Under the action of flowing air, the angle of attack of the wing is stabilized in the target angle of attack.
4. unmanned vehicle according to claim 3, which is characterized in that the target angle of attack is according to after the wing
Edge camber determines.
5. unmanned vehicle according to claim 1, it is characterised in that：When the quantity of the wing is at least two,
At least two wing is symmetrically rotatably installed in the both sides of the fuselage.
6. unmanned vehicle according to claim 1, it is characterised in that：The bindiny mechanism includes installation axle and installation axle
Component, the installation axle component are arranged on fuselage, and one end of the installation axle is rotatably connected on installation axle cooperation
On component, the other end of the installation axle is fixedly connected with the wing.
7. unmanned vehicle according to claim 6, it is characterised in that：The installation axle component includes bearing.
8. unmanned vehicle according to claim 6, it is characterised in that：The installation axle and the installation axle component
Between be provided with damping material.
9. unmanned vehicle according to claim 1, it is characterised in that：The unmanned vehicle further includes tractive unit, is used
The angle of attack of wing when limiting unmanned vehicle in hovering or low-speed operations.
10. unmanned vehicle according to claim 9, it is characterised in that：The tractive unit includes one or more elasticity
Component.
11. unmanned vehicle according to claim 10, it is characterised in that：The unmanned vehicle further includes flying for nobody
Row device provides the rotor of flying power, wherein the wing is located at except induced draft range caused by rotor wing rotation.
12. unmanned vehicle according to claim 1, which is characterized in that the total life center of at least one wing
It is essentially coincided with the position of centre of gravity of unmanned vehicle.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721619662.2U CN207809768U (en) | 2017-11-28 | 2017-11-28 | A kind of unmanned vehicle |
| PCT/CN2017/118620 WO2019104796A1 (en) | 2017-11-28 | 2017-12-26 | Unmanned aerial vehicle |
| CN201780066040.8A CN110418755A (en) | 2017-11-28 | 2017-12-26 | A kind of unmanned vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721619662.2U CN207809768U (en) | 2017-11-28 | 2017-11-28 | A kind of unmanned vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207809768U true CN207809768U (en) | 2018-09-04 |
Family
ID=63333628
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721619662.2U Expired - Fee Related CN207809768U (en) | 2017-11-28 | 2017-11-28 | A kind of unmanned vehicle |
| CN201780066040.8A Pending CN110418755A (en) | 2017-11-28 | 2017-12-26 | A kind of unmanned vehicle |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780066040.8A Pending CN110418755A (en) | 2017-11-28 | 2017-12-26 | A kind of unmanned vehicle |
Country Status (2)
| Country | Link |
|---|---|
| CN (2) | CN207809768U (en) |
| WO (1) | WO2019104796A1 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109466762A (en) * | 2019-01-08 | 2019-03-15 | 贵州剑河中和时代科技有限公司 | A kind of unmanned plane |
| CN110418755A (en) * | 2017-11-28 | 2019-11-05 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle |
| CN114313241A (en) * | 2020-09-29 | 2022-04-12 | 盐城辉空科技有限公司 | flying body |
| US12151811B2 (en) * | 2019-08-13 | 2024-11-26 | Textron Innovations Inc. | Tilting wing rotorcrafts and wing rotation systems |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111891349B (en) * | 2020-08-03 | 2025-02-18 | 西北工业大学太仓长三角研究院 | A quadrotor-flapping wing hybrid layout aircraft |
| CN112278239A (en) * | 2020-11-09 | 2021-01-29 | 中国人民解放军总参谋部第六十研究所 | A non-stall floating lift airfoil of an aircraft and its realization method |
| CN112660364B (en) * | 2020-12-25 | 2022-08-12 | 台州学院 | Wing capable of automatically adjusting attack angle |
| CN114476040B (en) * | 2021-04-26 | 2024-05-17 | 远超航空科技(成都)有限公司 | Unmanned aerial vehicle for achieving posture adjustment through folding rotating paddles |
| DE102022000073A1 (en) | 2022-01-12 | 2023-07-13 | Gerd BERCHTOLD | Adjustable auxiliary wing as lift support for vertical take-off aircraft with non-pivotable lift rotors |
| WO2023188267A1 (en) * | 2022-03-31 | 2023-10-05 | 三共木工株式会社 | Aircraft |
Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102009004239A1 (en) * | 2009-01-05 | 2010-07-08 | Ivan Novikov-Kopp | Method for the complex increase of aerodynamic and transport properties, ground effect vehicle for carrying out the method (variants) and flight method |
| GB201202441D0 (en) * | 2012-02-13 | 2012-03-28 | Reiter Johannes | Wing adjustment mechanism |
| TW201337098A (en) * | 2012-03-15 | 2013-09-16 | Univ Nat Taiwan | Wind machine |
| CN105339262A (en) * | 2013-03-14 | 2016-02-17 | 宾夕法尼亚大学理事会 | Passive rotor control mechanism for micro air vehicles |
| CN104589939B (en) * | 2014-03-20 | 2017-01-18 | 中国特种飞行器研究所 | Cross-medium aircraft with changeable shape like sailfish |
| CN103991541B (en) * | 2014-05-30 | 2015-12-23 | 佛山市神风航空科技有限公司 | A kind of rotary flapping wing aircraft of mini zone spring |
| IL234443B (en) * | 2014-09-02 | 2019-03-31 | Regev Amit | Tilt winged multirotor |
| CN104477389B (en) * | 2014-12-15 | 2016-06-15 | 佛山市神风航空科技有限公司 | A kind of miniature flutter aircraft |
| CN104443381B (en) * | 2014-12-15 | 2016-07-13 | 佛山市神风航空科技有限公司 | A kind of small-sized four wing flutter aircraft |
| CN204507265U (en) * | 2015-02-12 | 2015-07-29 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Be with the multi-rotor aerocraft of the fixed-wing that verts |
| CN104608924B (en) * | 2015-02-12 | 2018-07-06 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Band verts the multi-rotor aerocraft and its control method of fixed-wing |
| GB2540169B (en) * | 2015-07-08 | 2018-08-08 | Ge Aviation Systems Llc | Aircraft wing shaped to counter aerodynamic effects of propeller wake |
| CN205381400U (en) * | 2016-02-22 | 2016-07-13 | 武汉智能鸟无人机有限公司 | Aircraft |
| CN106314761B (en) * | 2016-08-31 | 2018-11-23 | 北京航空航天大学 | A kind of all-moving wing mechanism applied to small compound helicopter |
| CN106428524B (en) * | 2016-11-25 | 2019-09-13 | 南京柯尔航空科技有限公司 | A kind of multi-rotor aerocraft with the free wing |
| CN207809768U (en) * | 2017-11-28 | 2018-09-04 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle |
-
2017
- 2017-11-28 CN CN201721619662.2U patent/CN207809768U/en not_active Expired - Fee Related
- 2017-12-26 WO PCT/CN2017/118620 patent/WO2019104796A1/en active Application Filing
- 2017-12-26 CN CN201780066040.8A patent/CN110418755A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110418755A (en) * | 2017-11-28 | 2019-11-05 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle |
| CN109466762A (en) * | 2019-01-08 | 2019-03-15 | 贵州剑河中和时代科技有限公司 | A kind of unmanned plane |
| US12151811B2 (en) * | 2019-08-13 | 2024-11-26 | Textron Innovations Inc. | Tilting wing rotorcrafts and wing rotation systems |
| CN114313241A (en) * | 2020-09-29 | 2022-04-12 | 盐城辉空科技有限公司 | flying body |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2019104796A1 (en) | 2019-06-06 |
| CN110418755A (en) | 2019-11-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207809768U (en) | A kind of unmanned vehicle | |
| US11851173B2 (en) | Vertical take-off and landing (VTOL) winged air vehicle with complementary angled rotors | |
| CA2748875C (en) | Forward swept winglet | |
| CN107042884A (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| CN108382579A (en) | A kind of new and effective tilting rotor unmanned vehicle | |
| CN204660020U (en) | One is distributed independently controls multi-rotor aerocraft | |
| CN107628244A (en) | A kind of double lift culvert vertical take-off and landing aircrafts based on tilting duct | |
| CN108791874A (en) | A kind of tilting duct power unmanned vehicle | |
| CN207417149U (en) | A kind of double lift culvert vertical take-off and landing aircrafts based on tilting duct | |
| WO2017000156A1 (en) | Double-blade tandem helicopter | |
| CN108583867A (en) | A kind of three ducted fan bionic Aircraft of torque self-balancing | |
| CN109703748A (en) | Rotor craft | |
| CN206552261U (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| CN209225395U (en) | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure | |
| CN106828911A (en) | String wing unmanned plane | |
| CN107521680A (en) | A kind of active wind resistance coaxal helicopter and active wind resistance attitude control method | |
| CN204871605U (en) | Gyroplane can vert | |
| CN207902734U (en) | A kind of unmanned plane of aerodynamic arrangement | |
| CN209581874U (en) | A kind of vertical take-off and landing drone | |
| CN207902741U (en) | Rotor craft | |
| CN206704538U (en) | The long continuation of the journey aerofoil multi-rotor unmanned aerial vehicle of one kind | |
| CN202219839U (en) | Omnidirectional flying wing structure of vertical lifting aircraft | |
| CN216332756U (en) | A distributed electric tail rotor helicopter | |
| CN209870731U (en) | Unmanned plane | |
| CN104229130A (en) | Four-rotor wing unmanned aerial vehicle with pneumatic structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180904 |