CN207843318U - A kind of fuselage unmanned plane that verts with the design of driving part inclination angle - Google Patents
A kind of fuselage unmanned plane that verts with the design of driving part inclination angle Download PDFInfo
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- CN207843318U CN207843318U CN201820057112.4U CN201820057112U CN207843318U CN 207843318 U CN207843318 U CN 207843318U CN 201820057112 U CN201820057112 U CN 201820057112U CN 207843318 U CN207843318 U CN 207843318U
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- driving part
- unmanned plane
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- inclination angle
- fuselage
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Abstract
The utility model provides a kind of fuselage unmanned plane that verts with the design of driving part inclination angle, including：At least two fix wing；Supporting rack among two fixed wings；Two fixed wing Parallel Symmetric settings, and in symmetrical one driving part of installation respectively in respective middle part, the driving part tilts installation with an angle to the fixed inboard.The utility model mechanical structure is simple, can VTOL and spot hover and with high-speed remote from cruise, and can be in both state of flight free switchings；The design of driving part inclination angle can utilize torque compensation yawing caused by driving part speed discrepancy, accelerate the response speed of yaw angle.
Description
Technical field
The utility model is related to air vehicle technique fields, and in particular, to a kind of machine that verts with the design of motor inclination angle
The polymorphic unmanned plane of body.
Background technology
Traditional Fixed Wing AirVehicle is restricted to landing site, and most fixed-wing aircraft is required for airport to lift, and needs
There is longer runway for landing, the condition of landing is required harsher.The multiple rotors of dependence of traditional multi-rotor aerocraft
The power of generation overcomes gravity and provides the power of advance.During flying before level, the power that multiple rotors generate only has one
Part is used for providing the power of advance, remaining power will provide upward lift to overcome gravity to keep height, so power consumption is big,
Efficiency is low, and cruising ability is insufficient.
Traditional tiltrotor aircraft is using relative to the rotatable power plant of fuselage, such as the wing installed
On rotatable nacelle, rotatable rotor hanger etc..These, which are designed, has manned vehicle certain advantage, but for
Unmanned plane, verting for fuselage have no effect on its performance.In addition, being usually required more relative to the rotatable power plant of fuselage
Maintenance and more complicated mechanical structure, and the latter would generally limit maintenance and safety inspection.
Such as the Chinese utility model of Publication No. CN104044734A, provide a kind of more with tiltable wing and rotor
Rotor wing unmanned aerial vehicle, the unmanned plane include the multiple rotors being arranged in connecting rod in structure, symmetrically pacify at left and right sides of fuselage
Set it is a pair of can be perpendicular to fuselage direction and be parallel to inclined wing between fuselage direction and installed on wing two
It can inclined rotor synchronous with wing.
The for another example Chinese utility model of Publication No. CN106986019A discloses a kind of changeable multi-rotor unmanned aerial vehicle rotation
The motor cabinet at aerofoil angle of inclination is related to multi-rotor unmanned aerial vehicle rotor face angle of inclination control field, including motor mounting plate, institute
It states and is fixed with deflection tube on installation panel seat, armed draw ring is fixedly connected on the deflection tube, is socketed with outside the deflection tube
Arc opening, the armed is arranged along middle part circumferencial direction in fixed sleeving for connecting unmanned plane horn, the fixed sleeving
The male arms of draw ring can be rotated along the arc opening of the fixed sleeving, and the armed draw ring is connect with servo driving.
Above CN104044734A uses tilting rotor and wing in flight course fast to promote unmanned plane cruise
The purpose of degree, mechanical structure and control are complex；Using the motor cabinet that can be verted in CN106986019A, to control motor
Rotation angle.These design mechanical structures are all complex, and exist and control unstable risk.Simultaneously to these mechanical structures
Also higher, reliability necessarily reduce for maintenance requirement with part, and maintenance difficulties are necessarily increased with cost.
Utility model content
For the defects in the prior art, the purpose of this utility model is to provide a kind of verting with the design of motor inclination angle
Fuselage unmanned plane controls the problems such as unstable to solve above-mentioned complicated in mechanical structure, and mechanical structure is simple, can vertically rise
Drop and spot hover, and can be with high-speed remote from cruise, and it can be in both state of flight free switchings.
The utility model is realized using following technical scheme：
A kind of fuselage unmanned plane that verts with the design of driving part inclination angle, including：
At least two fix wing, the fixed wing Parallel Symmetric setting；
Supporting rack among at least two fixed wings；
It is respectively mounted at least two driving parts on each fixed wing and two driving parts are symmetrical arranged, often
A driving part is with an angle to the intermediate, inclined of the fixed wing at place.
Preferably, each driving part is with an angle to the intermediate, inclined of the fixed wing at place, wherein
Angular range is 5 °~45 °.
Preferably, two driving parts installed on each fixed wing, two driving part relative tilts are set
It sets, and on the extended line of the fixed wing line of symmetry of itself where the inclined direction direction of the driving part.
Preferably, a propeller is set on each driving part end, is arranged altogether on two fixed wings
There are four propeller, the propeller is also inclined to set with the driving part at place.
Preferably, in the utility model：
In the state of flight of VTOL or spot hover, four propeller center points are formed flat the unmanned plane
Face and ground level level of approximation；
The unmanned plane is in average flight state, plane water approximate with ground level that four propeller center points are formed
It is flat；
When the unmanned plane is in an interim state, fuselage is in state of verting, and four propeller center points are formed flat
There is angle in face with ground level.
Preferably, a propeller is installed on each driving part, the direction of rotation of the adjacent propeller is opposite.
Preferably, the unmanned plane is further provided with tripod, plays a supporting role at ground for the unmanned plane.
Preferably, the fuselage unmanned plane that verts, wherein it refers to that the state of flight of unmanned plane is turned to by hovering mode to vert
The transition of flat winged mode.
The utility model can provide flight using the fixation wing being arranged symmetrically in unmanned plane average flight state
Required lift, while the design of symmetrical wing can allow unmanned plane to be flexibly turned in both direction, have high maneuverability.
Propellerslip generates torque on fixed wing in the existing fuselage unmanned plane that verts leads to the unmanned plane yaw angle
Response speed it is slower, or even diverging.In order to solve yaw angle divergence problem, improves gesture stability stability and yaw control is rung
Speed is answered, the utility model is used driving part to be tilted to inboard with an angle and installed, utilized in prior art basis
Torque compensation yawing caused by driving part speed discrepancy, yaw when improving unmanned plane VTOL or spot hover are rung
Answer sensitivity.
Compared with prior art, the utility model has following advantageous effect：
The utility model it is above-mentioned with driving part inclination angle design the fuselage formula unmanned plane that verts, use driving part with
One angle tilts installation to fixed inboard, installation driving part and propeller on fixed wing, when in vertical lift
When spot hover, transition flight state, the speed discrepancy of propeller is controlled, realizes the control of flight attitude；When in cruising flight
When state, fixed wing can provide lift, by controlling the speed discrepancy of driving part, realize pitching, roll, adjustment course angle
Deng action so that polymorphic aircraft is efficient, and cruising ability is outstanding, and mechanical structure is simple, and functional reliability improves.
The design of driving part inclination angle can utilize torque compensation caused by driving part speed discrepancy inclined in the utility model
Boat torque, accelerates the response speed of yaw angle.
Description of the drawings
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other spies of the utility model
Sign, objects and advantages will become more apparent upon：
Fig. 1 is structural schematic diagram in one embodiment of the utility model；
Fig. 2 is the motor in one embodiment of the utility model with respect to the structural schematic diagram that inboard is installed；
In Fig. 1：1 is fixed wing, and 2 be tripod, and 3 be instrument room, and 4 be motor, and 5 be supporting rack, and 6 be propeller.
Specific implementation mode
The utility model is described in detail with reference to specific embodiment.Following embodiment will be helpful to this field
Technical staff further understands the utility model, but does not limit the utility model in any form.It should be pointed out that ability
For the those of ordinary skill in domain, without departing from the concept of the premise utility, various modifications and improvements can be made.
These belong to the scope of protection of the utility model.
As shown in Figure 1, being the structure chart of entire aircraft in an embodiment.
As shown, a kind of fuselage unmanned plane that verts with the design of motor inclination angle, which includes two fixations
Wing, driving part use motor.Certainly, can also be to be fixed more than the even numbers of two fixed wings in other embodiments
Wing.
Specifically, a kind of fuselage unmanned plane that verts with the design of motor inclination angle, including：Two fixed wings 1；
Supporting rack 5 among two fixed wings；Wherein：
Two 1 Parallel Symmetric of fixed wing settings, and one motor 4 is symmetrically installed respectively at respective middle part, it is described
Motor 4 is tilted to 1 inside of the fixed wing with an angle and is installed.
In the embodiment shown in fig. 1, two fix on wings 1 that installation installs propeller there are four motor 4 on motor 4 altogether
6.The direction of rotation of the adjoining spiral paddle 6 is opposite.
When the motor 4 is installed, an angle is tilted to 1 inside of fixed wing, each motor 4 is with an angle to place
The intermediate, inclined of the fixed wing, wherein inclined angular range is preferably 5 °~45 °.Such design can pass through motor
Torque compensation yawing caused by speed discrepancy, yaw response when improving unmanned plane VTOL or spot hover are sensitive
Degree.
As shown in Fig. 2, two motors 4 installed on each fixed wing, two 4 relative tilt of motor settings,
And the 4 inclined direction of motor is directed toward on the extended line of the fixed wing line of symmetry of itself at place.
Further, a propeller is set on the end of each motor, is arranged altogether on two fixed wings
There are four propeller 6, corresponding to the motor being obliquely installed, the propeller is with being also inclined to set.
In embodiment shown in Fig. 1-2, it can be carried in unmanned plane average flight state using symmetrical fixed wing 1
Design for the required lift that flies, while symmetrical fixed wing can allow unmanned plane to be flexibly turned in both direction, have height
Mobility.
In embodiment shown in Fig. 1-2, unmanned plane is in the state of flight of VTOL or spot hover, four propellers
The plane approximation for the plane composition that 6 central points are formed is horizontal；The unmanned plane is in average flight state, in four propellers 6
The plane and horizontal plane near normal of heart point composition；When unmanned plane is in an interim state, fuselage is in state of verting, four spirals
The plane of 6 central point of paddle composition has angle with horizontal plane.
Further, in other embodiments, the unmanned plane further includes tripod 2, when unmanned plane is placed on ground, tripod
2 provide the effect of support.
Further, in other embodiments, the unmanned plane further includes instrument room 3, and instrument room 3 has gathered flight control system
With various sensor devices, the streamlined design of shape.Such design can provide excellent aerodynamic configuration, reduce unmanned plane
Air drag when average flight state.
In this hair above-described embodiment, by be tilted a certain angle installation motor, utilizing power caused by motor speed difference
Square compensates yawing, accelerates the response speed of yaw angle；Unmanned plane is improved when hovering mode, unmanned plane yaw response
Sensitivity.The inclined angle of motor is designed according to actual size, the shape of aircraft.
In the utility model above-described embodiment, the fuselage of the unmanned plane preferably uses carbon fiber bar material, have it is light,
The big feature of mechanical strength.
The fuselage formula unmanned plane that verts with the design of motor inclination angle of the utility model above-described embodiment, by solid at two
Determine that rotor is installed on wing 1, when in vertical lift spot hover, transition flight state, is controlled using flight control system
The speed discrepancy of four motors 4 realizes the control of flight attitude；When in average flight state, fixed wing can provide liter
Power realizes the actions such as pitching, roll, adjustment course angle so that polymorphic aircraft efficiency by controlling the speed discrepancy of four motors
Height, cruising ability is outstanding, and mechanical structure is simple, and functional reliability improves.The design of motor inclination angle can utilize motor speed difference institute
The torque compensation yawing of generation, accelerates the response speed of yaw angle.
The utility model solves the problems, such as that yaw angle control ability is insufficient, improves gesture stability stability and yaw control
Response speed is used motor to be tilted to inboard with an angle and installed, inclined using torque compensation caused by motor speed difference
Boat torque, accelerates the response speed of yaw angle.
It is the section Example of the utility model above, the utility model also has other embodiments, for example adjusts spiral
The quantity or number of motors of paddle, may be constructed different embodiments, this realizes the utility model not substantive shadow
It rings, to those skilled in the art, is easily achieved on the basis of the utility model foregoing description, it is therefore, right
In the embodiments of other numbers of motors, details are not described herein.
Specific embodiment of the utility model is described above.It is to be appreciated that the utility model not office
It is limited to above-mentioned particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims,
This has no effect on the substantive content of the utility model.
Claims (7)
1. a kind of fuselage unmanned plane that verts with the design of driving part inclination angle, including：
At least two fix wing, the fixed wing Parallel Symmetric setting；
Supporting rack among at least two fixed wings；
It is characterized in that：
It is respectively mounted at least two driving parts on each fixed wing and two driving parts are symmetrical arranged, Mei Gesuo
The intermediate, inclined that driving part is stated with an angle to the fixed wing at place.
2. the fuselage unmanned plane that verts according to claim 1 with the design of driving part inclination angle, it is characterised in that：Each
For the driving part with an angle to the intermediate, inclined of the fixed wing at place, wherein angular range is 5 °~45 °.
3. the fuselage unmanned plane that verts according to claim 1 with the design of driving part inclination angle, it is characterised in that：Each
Two driving parts installed on the fixed wing, two driving part relative tilt settings, and the driving part inclines
It is directed toward on the extended line of the fixed wing line of symmetry of itself at place in oblique direction.
4. the fuselage unmanned plane that verts according to claim 1 with the design of driving part inclination angle, it is characterised in that：Each
One propeller is at least set on the driving part end, and at least there are four spirals for setting altogether on two fixed wings
Paddle, the propeller are also inclined to set with the driving part at place.
5. the fuselage unmanned plane that verts according to claim 4 with the design of driving part inclination angle, it is characterised in that：
The unmanned plane in the state of flight of VTOL or spot hover, plane that four propeller center points are formed with
Ground level level of approximation；
The unmanned plane is in average flight state, plane and ground level level of approximation that four propeller center points are formed；
When the unmanned plane is in an interim state, fuselage is in state of verting, the plane that four propeller center points are formed with
Ground level has angle.
6. having the fuselage unmanned plane that verts of driving part inclination angle design, feature according to claim 1-5 any one of them
It is：At least one propeller is installed on each driving part, the direction of rotation of the adjacent propeller is opposite.
7. having the fuselage unmanned plane that verts of driving part inclination angle design, feature according to claim 1-5 any one of them
It is：The unmanned plane is further provided with tripod, plays a supporting role at ground for the unmanned plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820057112.4U CN207843318U (en) | 2018-01-15 | 2018-01-15 | A kind of fuselage unmanned plane that verts with the design of driving part inclination angle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820057112.4U CN207843318U (en) | 2018-01-15 | 2018-01-15 | A kind of fuselage unmanned plane that verts with the design of driving part inclination angle |
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| Publication Number | Publication Date |
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| CN207843318U true CN207843318U (en) | 2018-09-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201820057112.4U Active CN207843318U (en) | 2018-01-15 | 2018-01-15 | A kind of fuselage unmanned plane that verts with the design of driving part inclination angle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108248855A (en) * | 2018-01-15 | 2018-07-06 | 上海交通大学 | A kind of fuselage unmanned plane that verts with the design of driving part inclination angle |
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2018
- 2018-01-15 CN CN201820057112.4U patent/CN207843318U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108248855A (en) * | 2018-01-15 | 2018-07-06 | 上海交通大学 | A kind of fuselage unmanned plane that verts with the design of driving part inclination angle |
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