CN209581874U - A kind of vertical take-off and landing drone - Google Patents
A kind of vertical take-off and landing drone Download PDFInfo
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- CN209581874U CN209581874U CN201920055207.7U CN201920055207U CN209581874U CN 209581874 U CN209581874 U CN 209581874U CN 201920055207 U CN201920055207 U CN 201920055207U CN 209581874 U CN209581874 U CN 209581874U
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Abstract
The utility model discloses a kind of vertical take-off and landing drone, are related to unmanned plane field.The unmanned plane includes the bracket that verts；Pairs of rotor bracket is separately positioned on the both ends of the bracket that verts；At least two rotors, at least two rotor are divided into two groups, and rotor described in every group passes through rotorshaft respectively and is rotatably installed on pairs of rotor bracket；With the lift wing, setting is verted on bracket described, and relative to the rotor chassis plane adjustable angle where the pairs of rotor bracket.The utility model reduces deadweight of unmanned plane during cruising condition and landing, solves the excessively high technical problem of extra power consumption generally existing in the prior art by the tilt angle of the control lift wing.
Description
Technical field
The utility model relates to unmanned plane field more particularly to a kind of vertical take-off and landing drone.
Background technique
Currently, unmanned plane is used cooperatively the technology, it can be achieved that VTOL (VTOL) by fixed-wing and multiple rotors
It is required that.It taking off, landing and floating state, providing lift and gesture stability by rotor.And under cruising condition, it is mentioned by fixed-wing
The power consumption that flight system is reduced for lift, the advantages that making unmanned plane have both high voyage, can hover with low landing condition.Related skill
There are two types of typical structures for vertical take-off and landing drone tool in art:
The fixed-wing and rotor assemblies of the first vertical take-off and landing drone are fixedly installed in unmanned plane body respectively, by landing
After unmanned plane is promoted to certain altitude by rotor, landing rotor is closed, provides cruising flight by fixed-wing and cruising power source
Lift and thrust.The rotor of this vertical take-off and landing drone is without pitch motion, reliability with higher and low operation difficulty,
But deadweight (component weight for being not involved in work) is not can avoid to the adverse effect of power consumption.Specifically: under cruising condition,
Rotor is not involved in work, and will affect the aerodynamic arrangement of unmanned plane, generates additional air drag.And it in VTOL and hangs
Stop state, fixed-wing is deadweight, will increase dramatically system power dissipation.
Second of vertical take-off and landing drone has the rotor of ability of centainly verting by being arranged on fixed-wing, in landing and
When floating state, rotate rotor to provide upward power in horizontal plane；And in cruising condition, it controls rotor and flies to unmanned plane
Line direction verts, and rotates rotor to provide forward power in vertical plane.The vertical take-off and landing drone of this structure by pair
Each rotor tilt angle is controlled, and makes unmanned plane without additional deadweight；But it needs to pass through empennage under cruising level flight state
Carry out gesture stability, and in VTOL, fixed-wing can generate biggish frontal resistance, cause unmanned plane take-off weight big and
Load capacity is insufficient, and controls the complicated in mechanical structure that rotor verts, and reliability is low, and manufacturing cost is higher.
Utility model content
At least one purpose of the utility model is to propose a kind of vertical take-off and landing drone, solve in the prior art nobody
The technical problem that machine ineffective power consumption accounting is big, control difficulty is high.Preferred skill in many technical solutions provided by the utility model
Many technical effects elaboration as detailed below that art scheme can be generated.
To achieve the above object, the utility model provides following technical scheme:
A kind of vertical take-off and landing drone characterized by comprising
Vert bracket；
Pairs of rotor bracket is separately positioned on the both ends of the bracket that verts；
At least two rotors, at least two rotor are divided into two groups, and rotor described in every group passes through rotorshaft respectively can
It is rotationally mounted on pairs of rotor bracket；With
The lift wing, setting are verted on bracket described, and relative to the rotor bracket where the pairs of rotor bracket
Plane Angle is adjustable.
In some embodiments, the rotor includes two rotors, is separately mounted to the both ends of the rotor bracket.
In some embodiments, the bracket that verts includes the shaft being arranged along the length direction of the lift wing, described
The lift wing can rotate predetermined angle relative to the shaft.
In some embodiments, the axis of the shaft is located in the plane vertical with the length direction of the lift wing.
In some embodiments, the lift wing is the straight wing.
In some embodiments, the aerodynamic center of the lift wing is located on the axis of the shaft of the bracket that verts.
In some embodiments, the lift wing is the all-wing aircraft of airfoil.
In some embodiments, the axis of the shaft of the bracket that verts by the thriving type leading edge of the lift and it is pneumatic in
Between the heart.
In some embodiments, unmanned plane further include:
The airfoil trailing edge of the lift wing is arranged in aileron, and the rudder face of the aileron is deflectable relative to the lift wing.
In some embodiments, unmanned plane further include:
Lift wing driving mechanism, for driving the lift wing to rotate relative to the rotor bracket, to change the liter
Angle between the power wing and the rotor chassis plane.
In some embodiments, unmanned plane further include:
Controller is communicated to connect with the lift wing driving device and the driving mechanism of the rotor, for according to nobody
The state of flight and environmental factor of machine control the angle that the lift wing driving mechanism adjusts the lift wing, and described in control
The driving mechanism of rotor adjusts the revolving speed of the rotor.
In some embodiments, unmanned plane further include:
Digiplex is wirelessly communicated with the controller and is connected, for sending control instruction to the controller, so as to
The controller controls the angle of the lift wing and the revolving speed of the rotor according to the control instruction.
In some embodiments, adjustable angle of the rotorshaft relative to the rotor bracket.
Based on the above-mentioned technical proposal, the utility model embodiment at least can produce following technical effect: in cruising condition
Under, the control lift wing verts around the bracket that verts, and so that the lift wing is kept basic horizontal, and be maintained at setting with rotor chassis plane
On angle, the lift wing is made to provide part lift, reduces unmanned plane power consumption；And during landing, the lift wing is rotated to perpendicular
Histogram is to reduction unmanned plane overall air resistance improves capacity usage ratio.
The utility model embodiment also has following technical effect that under cruising condition, according to unmanned plane cruising speed and
Local wind speed determines the deflection angle between the lift wing and rotor chassis plane, and the lift wing is enable to mention as much as possible for unmanned plane
For lift, overall power consumption is reduced；And during unmanned plane landing, the angle of the lift wing is controlled according to wind behaviour, such as in wind
When speed is greater than given threshold, the adjustment lift wing is in a horizontal state, and to reduce influence of the beam wind to unmanned plane stability, avoids deviateing
Course line.
Detailed description of the invention
Attached drawing described herein is used to provide a further understanding of the present invention, and is constituted part of this application,
The exemplary embodiment of the utility model and the description thereof are used to explain the utility model, does not constitute to the improper of the utility model
It limits.In the accompanying drawings:
Fig. 1 is the isometric side structure schematic diagram of the utility model unmanned plane one embodiment；
Fig. 2 is embodiment illustrated in fig. 1 overhead view；
Fig. 3 is the positive angle schematic diagram of embodiment illustrated in fig. 1；
Fig. 4 is embodiment illustrated in fig. 1 VTOL status diagram；
Fig. 5 is embodiment illustrated in fig. 1 cruising condition schematic diagram；
Fig. 6 is winged side view angle schematic diagram before embodiment illustrated in fig. 1 cruising condition；
Fig. 7 is another embodiment overhead view of the utility model；
Fig. 8 is embodiment illustrated in fig. 7 side view angle schematic diagram；
Fig. 9 is embodiment illustrated in fig. 7 VTOL status diagram；
Figure 10 is embodiment illustrated in fig. 7 cruising condition schematic diagram；
Figure 11 is embodiment illustrated in fig. 7 cruising condition side view angle schematic diagram；
Figure 12 is the utility model another embodiment overhead view；
Figure 13 is embodiment illustrated in fig. 12 cruising condition schematic diagram；
Figure 14 is embodiment illustrated in fig. 12 VTOL status diagram；
Appended drawing reference: 1, rotor；2, the lift wing；3, rotor bracket；4, vert bracket；5, rotorshaft；6, aileron.
Specific embodiment
Be referred to attached drawing below and word content understand the utility model content and the utility model with it is existing
Distinctive points between technology.Hereafter attached drawing and by way of enumerating some alternative embodiments of the utility model, to this reality
It is described in further detail with novel technical solution (including optimal technical scheme).
It should be understood that any technical characteristic, any technical solution in the present embodiment are the technologies of plurality of optional
One or more of feature or optional technical solution, in order to describe it is succinct need in this document impossible to exhaust it is practical new
All alternative technical characteristics of type and alternative technical solution, the embodiment for being also not easy to each technical characteristic are equal
It is emphasized for one of optional numerous embodiments, so those skilled in the art will appreciate that the utility model can be mentioned
Supply any technological means be replaced or will any two or more technological means provided by the utility model or technology spy
Sign, which is combined with each other, obtains new technical solution.
Any technical characteristic and any technical solution in the present embodiment do not limit the protection scope of the utility model,
The protection scope of the utility model should include that those skilled in the art do not make the creative labor the thinkable any substitution of institute
Technical solution and those skilled in the art are special by any two or more technological means provided by the utility model or technology
Sign technical solution new obtained from being combined with each other.
It is as shown in Figs 1-4 one embodiment of the utility model, a kind of vertical take-off and landing drone, including the bracket that verts；
Pairs of rotor bracket is separately positioned on the both ends of the bracket that verts；At least two rotors, at least two rotor are divided into
Two groups, rotor described in every group passes through rotorshaft respectively and is rotatably installed on pairs of rotor bracket；With the lift wing, setting
It verts on bracket described, and relative to the rotor chassis plane adjustable angle where the pairs of rotor bracket.
During the lift wing 2 refers to winged before unmanned plane, air-flow differential above and below the lift wing can be passed through and generate lift
Airfoil cross-section shape.Typical lift aerofoil profile has the longer top airfoil of direction of flow and shorter lower aerofoil, passes through gas
It flows had speed difference when passing through lift wing top and bottom and generates pressure difference, the lift during flying before being provided with this.Furthermore originally
The lift wing can also take other kinds of lift airfoil structure in utility model, to provide the liter during flying before unmanned plane
Power.
Pairs of rotor bracket 3 is separately positioned on the both ends of the bracket 4 that verts in the present embodiment, and together constitutes with rotor
Chassis plane, and at least two rotor 1 is substantially parallel with the rotor chassis plane, ensure that around the bracket 4 that verts
The lift wing 2 does not interfere with the relative positional relationship of unmanned plane other assemblies during verting, and is easier to unmanned plane integrally
Manipulation, stability are higher.In addition, other brackets can be introduced between the rotor bracket 3 to connect two rotor brackets, with
Enhance the stability of unmanned plane structure；It may be incorporated into the frame structures such as undercarriage, adapt to differently face ring to enhance unmanned plane
The ability in border.
Rotor described in described every group includes two rotors, is separately mounted to the both ends of the rotor bracket, with preferably real
The control of existing unmanned plane.In fact, the quantity of rotor 1 need to only be greater than two, and it provides power and unmanned plane can be made integrally to protect
It holds basicly stable.Such as: it is six, after being divided into two groups that the quantity of rotor 1, which can choose, and every group of three rotors can be distinguished
Positioned at the both ends and midpoint of the rotor bracket 3；The quantity of rotor 1 may be odd number, such as can choose is three, point
After two groups, only wherein one group of two rotors need to be guaranteed to the lift of unmanned plane and the lift of torque and another group of single rotor
It is corresponding to torque to be consistent.
It is as shown in Figure 5, Figure 6 the schematic diagram of above-described embodiment cruising condition, the bracket that verts includes along described at this time
The shaft of the length direction setting of the lift wing, the lift wing can rotate predetermined angle relative to the shaft.
Under cruising condition, by rotate the lift wing 2, make the lift wing 2 keep basic horizontal under the premise of with rotor bracket
Plane is maintained at the angle of a setting.Rotor 1 is capable of providing the power of unmanned plane part lift and advance at this time, and lift
The wing 2 can provide another part lift for unmanned plane, the power consumption of rotor is effectively reduced in the case where there is certain level speed,
Make unmanned plane that there is longer voyage.In addition, the lift wing 2 can change pitch angle under the limitation of shaft, rotor is not being influenced
In the case where power, auxiliary unmanned plane completes the technical movements climbed or declined.And during taking off or landing, it can control
The lift wing 2 verts to vertical direction, reduces additional friction and do that the lift wing 2 generates in unmanned plane vertical direction flight course
It disturbs, keeps the landing process of unmanned plane more fast, more stable.
Correspondingly, the bracket that verts may also comprise the shaft of the width direction setting along the lift wing, by being rationally arranged
Angle where the lift wing 2 and rotor between plane, the equally energy generating unit decilitre power of the lift wing 2 is under cruising condition to reduce nothing
Man-machine power consumption；In addition, the lift wing 2 being set in the above way can also effect of verting by it, make unmanned plane in the sky compared with
It is fast to turn to, to adapt to the task of complicated flight environment of vehicle.
In order to reach preferable control effect, the lift wing 2 is chosen as the straight wing, at this time in order to make unmanned plane control lift
The not disequilibrium by aerodynamic the influence when wing 2 rotates, vert bracket should with where the lift wing aerodynamic center
Straight line be overlapped.The aerodynamic center refers to: when airfoil angle-of-attack changes, conjunction of the air force suffered by aerofoil profile for this point
Torque is constant, then this point is known as aerodynamic center of the aerofoil profile under current Reynolds Number, also referred to as focus.And it is described pneumatic
Straight line where center is the line of aerofoil profile whole cross section aerodynamic center, and when the lift wing is the straight wing, this line is straight line,
Enable to vert bracket 4 at this time and the line coincident makes the lift wing that can guarantee air suffered by unmanned plane entirety at any angle
Power does not deviate the center of multiple rotors, to control unmanned plane whole machine balancing.
Another embodiment as illustrated in figures 7-11, wherein the lift wing may be the all-wing aircraft of airfoil.Not with the straight wing
Together, each cross sectional centroid line of the lift wing of airfoil flying wing structure and non-rectilinear, the bracket 4 that verts at this time should be by described
At 2 symmetry axis of the lift wing between aerofoil profile leading edge and aerodynamic center, to obtain more preferably control effect and flight stability.With it is straight
The wing is compared, and the lift wing of swept-back wing flying wing configuration is taken to have smaller aerodynamic drag, bigger lift and higher structure
Intensity makes unmanned plane during preceding fly, can obtain bigger lift at the same speed, therefore the plane where rotor
It is able to maintain between horizontal plane under bigger angle, to obtain higher flying speed, this will further decrease nobody
Machine power consumption, and the load weight of higher amount is provided.
Another embodiment as shown in figs. 12-14, wherein unmanned plane further include: the wing of the lift wing is arranged in aileron
Type rear, and the rudder face of the aileron is deflectable relative to the lift wing, and rotation, rolling or pitching power can be provided for unmanned plane
Square.Such as there are two the ailerons, and it respectively symmetrically is hinged on the left and right sides of 2 rear of the lift wing, when unmanned plane needs to turn
Xiang Shi need to only lift the aileron 6 of wherein side, so that it may complete unmanned plane in the case where whole 1 power of rotor do not adjust
Fast steering；And when unmanned plane will complete pitch angle variation or tumbling action, the left and right sides need to be only lifted simultaneously
Aileron 6, and control its relative to the lift wing 2 deflect angle can change unmanned plane in the case where not changing 1 power of rotor
Flight attitude.
In order to preferably control the flight attitude of unmanned plane, the unmanned plane further include: lift wing driving mechanism, for driving
It moves the lift wing to rotate relative to the rotor bracket, to change the folder between the lift wing and the rotor chassis plane
Angle, and it is maintained at the lift wing in one specific rotation angle.In entire flight course, lift wing driving machine can be passed through
Structure forward direction be driven in the reverse direction, be readily achieved lift flapwise different directions rotation task.
In some embodiments, in order to drive the lift wing 2 to rotate relative to the rotor bracket 3, the lift wing
Driving mechanism, which can be configured as, rotates the lift wing 2 relative to the bracket 4 that verts.Bracket 4 is verted along length described in making
Degree direction is articulated with the lift wing 2, and is fixedly connected with the rotor bracket 3, can be by the lift wing 2 relative to institute
Adjustable angle of the lift wing 2 relative to the rotor chassis plane is completed in the rotary motion for stating the bracket 4 that verts.
For the hinged of bracket 4 and the lift wing 2 of verting described in realizing, the lift wing 2 can internal setting through-hole, with
It is rotatably coupled the bracket 4 that verts in the form of axis with the lift wing 2；The lift wing 2 is close to the rotation
A pair of of blind hole also can be set in two sides of wing support 3 so that it is described vert bracket 4 in the form of a pair of of short axle with the liter
The power wing 2 is rotatably connected.Further, the lift wing driving mechanism can use independent rotating device, such as rotation electricity
Machine is set to the inside of the lift wing 2, to reduce air drag as far as possible and guarantee the balance of unmanned plane.
Correspondingly, in other embodiments, the lift wing driving mechanism, which also can be configured as, makes described vert
Bracket 4 is rotated relative to the rotor bracket 3.At this point, bracket 4 and the lift wing 2 of verting is fixedly installed, and with it is described
Rotor bracket 3 is hinged, to realize adjustable angle of the lift wing 2 relative to the rotor chassis plane.The bracket 4 that verts
Setting can be fixed to one another integrated forming technique or by way of being fixedly connected with the lift wing 2.Further, due to hair
The region of raw pitch motion be located at it is described vert between bracket 4 and the rotor bracket 3, close to the rotor 1, therefore described
Lift wing driving mechanism can obtain power from the relative motion component of the rotor 1, vert described in realization bracket 4 with it is described
Rotary motion between rotor bracket 3, to simplify the movement mechanism of unmanned plane and reduce construction weight.
In addition, further including controller in the utility model embodiment to realize the adaptation to different wind conditions, with institute
The driving mechanism communication connection for stating lift wing driving device and the rotor, for according to the state of flight of unmanned plane and environment because
Element controls the lift wing driving mechanism and adjusts the angle of the lift wing, and the driving mechanism for controlling the rotor adjusts institute
State the revolving speed of rotor.
Telecommunication and control are thought in order to realize, further include Digiplex in the utility model embodiment, and it is described
Controller wireless communication connection, for sending control instruction to the controller, so that the controller refers to according to the control
Order controls the angle of the lift wing and the revolving speed of the rotor.
In order to more directly, more quickly control UAV Attitude, rotorshaft described in the utility model embodiment
Adjustable angle relative to the rotor bracket.The rotorshaft 5 in adjustable direction can greatly reinforce the handling of unmanned plane, cooperation
With the lift wing 2 that can be verted and the aileron 6 that can be overturn relative to the lift wing, enable unmanned plane under the lesser radius of gyration
Realize divertical motion, adaptability of the enhancing unmanned plane to complicated airspace environment.
In some embodiments, multiple rotors 1 of unmanned plane are respectively by corresponding motor driven.At this point, to realize
Adjustable angle of the rotorshaft 5 relative to the rotor bracket 3 can make motor relative to 3 angle of rotor bracket
It is adjustable, and then drive the rotorshaft 5 being arranged on the motor；The motor can also be made relative to the rotor bracket 3
Angle is fixed, and keeps the rotorshaft 5 adjustable relative to the motor angle, provides power side to the rotor 1 to realize
To control.
The utility model additionally provides a kind of vertical take-off and landing drone control flow, and the control flow includes:
During cruise, the angle of the lift wing Yu the rotor chassis plane is adjusted, so as in the lift wing
Under conditions of keeping basic horizontal, make the rotor chassis plane and the lift wing in set angle.
During the take-off process of the unmanned plane and/or landing, if local wind speed is more than default wind speed threshold value,
The lift wing is adjusted, so that the lift wing keeps horizontality, the lift wing is otherwise maintained at vertical state.
After the unmanned plane takes off, control the revolving speed of the rotor 1, for the rotor chassis plane provide relative to
The pitching moment of horizontal plane makes the rotor chassis plane with respect to the horizontal plane deflect and reach set angle；
After angle between the rotor chassis plane and horizontal plane reaches set angle, the revolving speed of the rotor 1 is controlled,
The rotor chassis plane is set to maintain set angle.
The unmanned plane landing before, control the revolving speed of the rotor 1, for the rotor chassis plane provide relative to
The pitching moment of horizontal plane makes the rotor chassis plane with respect to the horizontal plane deflect and reach basic horizontal；
After the rotor chassis plane reaches basic horizontal, the revolving speed of the rotor 1 is controlled, keeps the rotor bracket flat
Face keeps basic horizontal.
In the entire airborne period of unmanned plane, controller, which is sent with the frequency of 200~400hz to the driver of rotor, to be turned
Speed instruction constantly adjusts the revolving speed of each driver, and the torque stabilized flight posture generated by the rotational speed difference of rotor.And
After rotor chassis plane reaches set angle, controller continues to control the driver of rotor, and making rotor respectively has specifically
Revolving speed, so that unmanned plane maintains under specific flight attitude.
Such as after unmanned plane takes off, in the pitch angle for controlling the rotor chassis plane from 0 ° to 30 ° of the variation of bowing
Cheng Zhong, control becomes larger along the rotor revolving speed of heading rearward first, while forward rotor revolving speed becomes smaller, to generate unmanned plane
The pitching moment bowed.Pitching moment starts unmanned plane with angular acceleration, and as angular speed constantly becomes larger and reaches
After setting value, angular speed is just gradually reduced, and when unmanned plane pitch angle is close to 30 °, by the driver of controller control rotor
Reversed pitching moment is generated, reducing angular speed to 0 and is maintained at the rotor chassis plane under 30 ° of attitude angles.And nobody
The descent of machine is then corresponding with the control mode of the take-off process, adjusts nobody by controlling the revolving speed of the rotor
The pitch attitude of machine changes.
Above-mentioned unmanned aerial vehicle (UAV) control process, which only passes through the revolving speed for changing rotor and verting for the lift wing, can reach, and operate
Journey is simple and reliable；And deadweight is effectively reduced in the overall process of unmanned plane during flying, significantly reduces the power consumption of unmanned plane；Also
It can change the tilt angle of the lift wing, according to local wind condition to reduce during landing lateral crosswind to unmanned plane
Interference.In addition, unmanned plane integral pitch, steering and tumbling action then can adjust rotorshaft by adjusting aileron angle
Angle changing rate easily realize, improve the ability that unmanned plane adapts to complicated flight environment of vehicle.
Meanwhile if above-mentioned the utility model discloses or relates to the components or structural member of connection fastened to each other,
Unless otherwise stated, it is fixedly connected it is to be understood that connection (such as connecting using bolt or screw) can be removedly fixed,
It is to be understood that non-removable be fixedly connected with (such as riveting, welding), certainly, connection fastened to each other or integral type
Structure (such as manufacturing using casting technique is integrally formed) is replaced (obviously can not be using except integrally formed technique).
In addition, for indicating positional relationship or shape applied in above-mentioned any technical solution disclosed by the utility model
Term its meaning includes approximate with its, similar or close state or shape unless otherwise stated.It is provided by the utility model
Either component by multiple individual component parts either assembled, or the list that integrally formed technique manufactures
Only component.
In the description of the utility model if used term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
"left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" etc., then the orientation or position of the instruction of above-mentioned term are closed
System is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of describing the present invention and simplifying the description, rather than
Equipment, mechanism, component or the element of indication or suggestion meaning must have a particular orientation, constructed and grasped with specific orientation
Make, therefore should not be understood as the limitation to scope of protection of the utility model.
Finally it should be noted that: above embodiments are only to illustrate the technical solution of the utility model rather than limit it
System；Although the utility model has been described in detail with reference to the preferred embodiment, those of ordinary skill in the art should
Understand: specific implementation of the utility model can still be modified or is equally replaced to some technical characteristics
It changes；Without departing from the spirit of technical solutions of the utility model, should all cover in the claimed technical solution of the utility model
In range.
Claims (13)
1. a kind of vertical take-off and landing drone characterized by comprising
It verts bracket (4)；
Pairs of rotor bracket (3) is separately positioned on the both ends of bracket (4) of verting；
At least two rotors (1), at least two rotor (1) are divided into two groups, and rotor described in every group (1) is turned by rotor respectively
Axis (5) is rotatably installed on pairs of rotor bracket (3)；With
The lift wing (2) is arranged on the bracket that verts (4), and relative to the rotor where the pairs of rotor bracket (3)
Chassis plane adjustable angle.
2. vertical take-off and landing drone according to claim 1, which is characterized in that rotor described in every group (1) includes two rotations
The wing (1) is separately mounted to the both ends of the rotor bracket (3).
3. vertical take-off and landing drone according to claim 1, which is characterized in that the bracket that verts (4) includes along described
The shaft of the length direction setting of the lift wing (2), the lift wing (2) can rotate predetermined angle relative to the shaft.
4. vertical take-off and landing drone according to claim 3, which is characterized in that the axis of the shaft is located at and the liter
In the vertical plane of the length direction of the power wing (2).
5. vertical take-off and landing drone according to claim 3, which is characterized in that the lift wing (2) is the straight wing.
6. vertical take-off and landing drone according to claim 5, which is characterized in that the aerodynamic center position of the lift wing (2)
In on the axis of the shaft of the bracket that verts (4).
7. vertical take-off and landing drone according to claim 3, which is characterized in that the lift wing (2) is airfoil
All-wing aircraft.
8. vertical take-off and landing drone according to claim 7, which is characterized in that the axis of the shaft of the bracket that verts (4)
Line passes through between the lift wing (2) the aerofoil profile leading edge and aerodynamic center.
9. vertical take-off and landing drone according to claim 1, which is characterized in that further include:
The airfoil trailing edge in the lift wing (2) is arranged in aileron (6), and the rudder face of the aileron (6) is relative to the lift wing (2)
It is deflectable.
10. vertical take-off and landing drone according to claim 1, which is characterized in that further include:
Lift wing driving mechanism, for driving the lift wing (2) to rotate relative to the rotor bracket (3), described in changing
Angle between the lift wing (2) and the rotor chassis plane.
11. vertical take-off and landing drone according to claim 10, which is characterized in that further include:
Controller is communicated to connect with the lift wing driving device and the driving mechanism of the rotor (1), for according to unmanned plane
State of flight and environmental factor, control the angle that the lift wing driving mechanism adjusts the lift wing (2), and described in controlling
The driving mechanism of rotor (1) adjusts the revolving speed of the rotor (1).
12. vertical take-off and landing drone according to claim 11, which is characterized in that further include:
Digiplex is wirelessly communicated with the controller and is connected, for sending control instruction to the controller, so as to described
Controller controls the angle of the lift wing (2) and the revolving speed of the rotor (1) according to the control instruction.
13. vertical take-off and landing drone according to claim 1, which is characterized in that the rotorshaft (5) is relative to described
The adjustable angle of rotor bracket (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920055207.7U CN209581874U (en) | 2019-01-14 | 2019-01-14 | A kind of vertical take-off and landing drone |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920055207.7U CN209581874U (en) | 2019-01-14 | 2019-01-14 | A kind of vertical take-off and landing drone |
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| CN209581874U true CN209581874U (en) | 2019-11-05 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114457773A (en) * | 2022-01-21 | 2022-05-10 | 西南石油大学 | Novel jacket platform suitable for offshore oil and gas exploitation |
-
2019
- 2019-01-14 CN CN201920055207.7U patent/CN209581874U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114457773A (en) * | 2022-01-21 | 2022-05-10 | 西南石油大学 | Novel jacket platform suitable for offshore oil and gas exploitation |
| CN114457773B (en) * | 2022-01-21 | 2023-11-14 | 西南石油大学 | Novel jacket platform suitable for offshore oil and gas exploitation |
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