CN109466762A - A kind of unmanned plane - Google Patents
A kind of unmanned plane Download PDFInfo
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- CN109466762A CN109466762A CN201910017151.0A CN201910017151A CN109466762A CN 109466762 A CN109466762 A CN 109466762A CN 201910017151 A CN201910017151 A CN 201910017151A CN 109466762 A CN109466762 A CN 109466762A
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- Prior art keywords
- wing
- unmanned plane
- rocker arm
- connecting rod
- control circuit
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- 230000000712 assembly Effects 0.000 claims abstract description 6
- 238000000429 assembly Methods 0.000 claims abstract description 6
- 230000005540 biological transmission Effects 0.000 claims description 9
- 229910003460 diamond Inorganic materials 0.000 claims description 6
- 239000010432 diamond Substances 0.000 claims description 6
- 238000013461 design Methods 0.000 claims description 3
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000010006 flight Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000009966 trimming 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
-
- 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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
A kind of unmanned plane, including multi-rotor unmanned aerial vehicle body, the multi-rotor unmanned aerial vehicle body include fuselage and several rotor assemblies；It further include auxiliary wing system, the auxiliary wing system includes the wing components for being symmetrically arranged at fuselage two sides, the driving mechanism for driving wing components to rotate and the control circuit for accurately controlling wing rotation angle, the driving mechanism and control circuit are integrated in mounting base, and the mounting base is fixed in fuselage.The present invention adds wing in the two sides of unmanned aerial vehicle body, the lift that wing is generated when air passes through wing in cruise using unmanned plane, to undertake the most weight of unmanned plane itself, the consumption of unmanned aerial vehicle body own wt is held up to reduce propeller, therefore can substantially extend the cruise time of multi-rotor unmanned aerial vehicle.
Description
Technical field
The present invention relates to unmanned planes, particularly with the addition of the multi-rotor unmanned aerial vehicle of auxiliary wing.
Background technique
Multi-rotor unmanned aerial vehicle flight it is quite steady, can be easy accomplish all bad flight accomplished of pure helicopter
Control ability, many unmanned plane products generally use four axis on the market now or six axis unmanned planes, such unmanned plane are handling
It is good, stable flight environment of vehicle can be provided for shooting head.This kind of commonly used function of unmanned plane includes police investigation, patrol, determines
Point monitoring, forestry patrol, power-line patrolling, agricultural spray etc., or even by largely with afield.The rotor of multiaxis unmanned plane
It is relatively simple for structure, do not need the trimming movement structure of system helicopter complexity, it is only necessary to which the revolving speed of controller rotor can reach
To the purpose of control posture.
Multi-rotor unmanned aerial vehicle can not utilize air fluid lift force in cruise, but completely by providing lift by propeller
With forward thrust, this kind of single power mode keeps multi-rotor unmanned aerial vehicle energy consumption in cruise excessive, leads to the type
The unmanned plane cruise time is all very short, limits the use scope of unmanned plane.
Summary of the invention
Technical problem to be solved by the invention is to provide a kind of unmanned planes, solve the existing multi-rotor unmanned aerial vehicle cruise time
Short problem, auxiliary wing system is versatile, and all multi-rotor unmanned aerial vehicles is suitble to install and use.
In order to solve the above technical problems, the technical scheme is that a kind of unmanned plane, including multi-rotor unmanned aerial vehicle machine
Body, the multi-rotor unmanned aerial vehicle body include fuselage and several rotor assemblies；It further include auxiliary wing system, the auxiliary wing
System includes the wing components for being symmetrically arranged at fuselage two sides, the driving mechanism for driving wing components to rotate and controls for accurate
The control circuit of wing rotation angle processed, the driving mechanism and control circuit are integrated in mounting base, and the mounting base is fixed
In fuselage；
The wing components include wing and connecting rod, and one end of the connecting rod is out of the end carriage of wing insertion wing, connection
The other end of bar is equipped with threaded hole；
The driving mechanism includes turning-bar, Servo-controller and transmission mechanism, and Servo-controller drives turning-bar by transmission mechanism
Rotation；The both ends of the turning-bar are respectively equipped with stud, and the connecting rod is threadedly coupled with turning-bar；The transmission mechanism includes
With the first rocker arm of Servo-controller output axis connection and the second rocker arm connecting with turning-bar, one end of the first rocker arm is shaken with second
One end of arm is connected by first connecting rod, and the other end of the first rocker arm is connect with the other end of the second rocker arm by second connecting rod,
First rocker arm, the second rocker arm, first connecting rod and second connecting rod form parallelogram；
The control circuit includes master control borad, gyroscope and the encoder for detecting Servo-controller corner, the gyroscope and
Encoder is connect with master control borad, and master control borad, which obtains the flight attitude of unmanned plane by gyroscope and controls driving mechanism, drives wing
Specified angle is rotated to, master control borad obtains the corner of wing by encoder；
When unmanned plane flight vertically upward, control circuit control wing is threaded to vertically；
When 45 ° of upward flight of unmanned plane, control circuit control wing rotates 45 ° counterclockwise；
When unmanned plane keeps height cruising flight, control circuit control wing is threaded to horizontality.
As an improvement, cutting connecting rod according to the width of fuselage, the end face of wing is made to be adjacent to fuselage.
As an improvement, first rocker arm assumes diamond in shape, the output shaft of Servo-controller passes through the center of the first rocker arm, described the
Two rocker arms assume diamond in shape, and the turning-bar passes through the center of the second rocker arm.
As an improvement, the wing is convexo-plane wing.
As an improvement, the mounting base includes the first mounting plate, the second mounting plate being located above the first mounting plate and sets
Support plate between the first mounting plate and the second mounting plate, the driving mechanism design is on the first mounting plate, the control
Circuit is located on the second mounting plate.
As an improvement, the rotor assemblies include paddle arm, the motor and rotor that are located in paddle arm.
The beneficial effect of the invention compared with the existing technology is:
Wing is added in the two sides of unmanned aerial vehicle body, wing is generated when air passes through wing in cruise using unmanned plane
Lift, so that the most weight of unmanned plane itself is undertaken, so that unmanned aerial vehicle body own wt will be held up by reducing propeller
Consumption, therefore can substantially extend the cruise time of multi-rotor unmanned aerial vehicle.Auxiliary wing system structure is simple, integrally can be used as one
Module, it is convenient for disassembly and assembly, it is suitble to all multi-rotor unmanned aerial vehicles to install and use.
Detailed description of the invention
Fig. 1 is unmanned plane top view.
Fig. 2 is unmanned plane perspective view.
Fig. 3 is auxiliary aerofoil system structure chart.
Fig. 4 is driving mechanism enlarged drawing.
Fig. 5 is that driving mechanism is integrated in the schematic diagram in mounting base.
Fig. 6 is control circuit module block diagram.
Fig. 7 is the state diagram of unmanned plane vertical ascent.
Fig. 8 is 45 ° of unmanned plane upward state of flight figures.
Specific embodiment
The invention is further explained in the following combination with the attached drawings of the specification.
A kind of unmanned plane, including multi-rotor unmanned aerial vehicle body and auxiliary wing system.
As shown in Figure 1, 2, the multi-rotor unmanned aerial vehicle body includes fuselage 3 and several rotor assemblies 2, the rotor assemblies
2 include paddle arm, the motor and rotor being located in paddle arm.There are certain accommodating space, the two sides of fuselage 3 in fuselage 3 of the present invention
With perforation, for installing auxiliary wing system
As shown in figure 3, the auxiliary wing system includes the wing components for being symmetrically arranged at 3 two sides of fuselage, for driving wing group
The driving mechanism 4 of part rotation and the control circuit 7 that angle is rotated for accurately controlling wing, the driving mechanism and control circuit
7 are integrated in mounting base 5, and the mounting base 5 is fixed in fuselage 3.
As shown in figure 4, the wing components include wing 1 and connecting rod, the wing 1 is convexo-plane wing, the company
Out of the end carriage of wing 1 insertion wing 1, the other end of connecting rod 43 is equipped with threaded hole for one end of extension bar 43；Connecting rod 43 is stretched out
One end it is longer, can be cut according to the width of unmanned aerial vehicle body 3, enable wing 1 install after its end face be close to fuselage
3。
As shown in figure 4, the driving mechanism 4 includes turning-bar 42, Servo-controller 41 and transmission mechanism；The turning-bar 42
Both ends be respectively equipped with stud, the connecting rod 43 is threadedly coupled with turning-bar 42, Servo-controller 41 pass through transmission mechanism drive
Turning-bar 42,42 drive connection bar 43 of turning-bar, and then wing 1 is driven to rotate.The transmission mechanism includes and Servo-controller 41
The second Rocker arm 45 for exporting the first Rocker arm 44 of axis connection and being connect with turning-bar 42, one end of the first Rocker arm 44 and the second rocker arm
45 one end is connected by first connecting rod 46, and the other end of the other end of the first Rocker arm 44 and the second Rocker arm 45 passes through second connecting rod
47 connections, the first Rocker arm 44, the second Rocker arm 45, first connecting rod 46 and second connecting rod 47 form parallelogram；Described first shakes
Arm 44 assumes diamond in shape, and the output shaft of Servo-controller 41 passes through the center of the first Rocker arm 44, and second Rocker arm 45 assumes diamond in shape, and described turn
The center of the second Rocker arm 45 is passed through to bar 42；The output shaft of Servo-controller 41 is parallel with turning-bar 42 and hangs down with parallelogram
Directly, when Servo-controller 41 rotates, the first Rocker arm 44 is driven, the first Rocker arm 44 drives the second Rocker arm 45 by connecting rod, makes parallel
The shape of quadrangle changes, so that turning-bar 42 be driven to rotate.
As shown in fig. 6, the control circuit 7 includes master control borad, gyroscope and the volume for detecting 41 corner of Servo-controller
Code device, the gyroscope and encoder are connect with master control borad, and master control borad obtains flight attitude and the control of unmanned plane by gyroscope
Driving mechanism driving wing 1 processed rotates to specified angle, and master control borad obtains the corner of wing 1 by encoder.
As shown in figure 5, the mounting base 5 include the first mounting plate, the second mounting plate for being located above the first mounting plate and
The support plate being located between the first mounting plate and the second mounting plate, the driving mechanism design is on the first mounting plate, the control
Circuit 7 processed is located on the second mounting plate.Auxiliary wing system structure is simple, integrally can be used as a module, convenient for disassembly and assembly, is suitble to
All multi-rotor unmanned aerial vehicle installations and use.
Wing 1 of the present invention generates the principle of lift: when the air-flow for being parallel to chordwise flows through wing 1, due to wing 1
Obstruction cause flow tube section to become smaller, and cause the air velocity of 1 upper and lower surface of wing to increase, but due to 1 upper surface of wing
Camber is greater than the camber of lower surface, is higher than lower surface air-flow on the whole according to the flow velocity of Bernoulli's theorem upper surface air-flow
Speed, that is to say, that static pressure of the airflow function in 1 upper surface of wing is less than the static pressure for acting on lower surface on the whole, due to upper and lower
The presence of surface pressure difference, so that wing 1 is finally by upward resultant force, that is, lift.
Certainly with the variation of the 1 relative wind angle of attack of wing, the air flow field around aerofoil profile can also occur significantly to change.
When 1 angle of attack of wing increases, since inhibition of the aerofoil profile to air-flow causes downwash, so that air-flow stationary point phase near leading edge
Leading edge locus is moved down, so as to cause the lift effect become apparent.
For multiaxis unmanned plane when executing aerial mission, there are many state of flights for meeting, such as vertical ascent and decline, flight forward
When rise or fall, keep height cruise etc..It just needs to meet the stability of the various state of flights of unmanned plane according to different
The angle of state of flight adjustment wing 1.The angle change of wing 1 is realized automatically by driving mechanism and control circuit 7: such as Fig. 7 institute
Show, when unmanned aerial vehicle control system issues flight directive vertically upward to unmanned plane, auxiliary wing system can be according to unmanned plane
Wing chord is gone to vertical 90 ° by state of flight, to reduce air drag caused by wing 1 when unmanned plane rises；Such as Fig. 8 institute
Show, when unmanned aerial vehicle control system issues 45 ° of upward flight directives to unmanned plane, auxiliary wing system can fly according to unmanned plane
1 wing chord of wing is rotated 45 ° by row state counterclockwise；Height cruising flight is kept to refer to when unmanned aerial vehicle control system is issued to unmanned plane
When enabling, wing 1 can be gone to horizontality according to the state of flight of unmanned plane by auxiliary wing system.Encoder real-time monitoring wing
Positive counter deflexion or halt instruction are transmitted to driving mechanism by control circuit 7 in 1 inclination angle, and the moment allows wing 1 to keep optimum angle of incidence.
The present invention adds wing 1 in the two sides of unmanned aerial vehicle body 3, and using unmanned plane, in cruise, air passes through wing 1
When to wing 1 generate lift, so that the most weight of unmanned plane itself is undertaken, so that unmanned plane will be held up by reducing propeller
The consumption of 3 own wt of fuselage, therefore can substantially extend the cruise time of multi-rotor unmanned aerial vehicle.Auxiliary wing system structure letter
It is single, it integrally can be used as a module, it is convenient for disassembly and assembly, it is suitble to all multi-rotor unmanned aerial vehicles to install and use.
Claims (6)
1. a kind of unmanned plane, including multi-rotor unmanned aerial vehicle body, the multi-rotor unmanned aerial vehicle body includes fuselage and several rotors
Component；It is characterized by also including auxiliary wing system, the auxiliary wing system includes the wing for being symmetrically arranged at fuselage two sides
Component, the driving mechanism for driving wing components to rotate and the control circuit for accurately controlling wing rotation angle, it is described
Driving mechanism and control circuit are integrated in mounting base, and the mounting base is fixed in fuselage；
The wing components include wing and connecting rod, and one end of the connecting rod is out of the end carriage of wing insertion wing, connection
The other end of bar is equipped with threaded hole；
The driving mechanism includes turning-bar, Servo-controller and transmission mechanism, and Servo-controller drives turning-bar by transmission mechanism
Rotation；The both ends of the turning-bar are respectively equipped with stud, and the connecting rod is threadedly coupled with turning-bar；The transmission mechanism includes
With the first rocker arm of Servo-controller output axis connection and the second rocker arm connecting with turning-bar, one end of the first rocker arm is shaken with second
One end of arm is connected by first connecting rod, and the other end of the first rocker arm is connect with the other end of the second rocker arm by second connecting rod,
First rocker arm, the second rocker arm, first connecting rod and second connecting rod form parallelogram；
The control circuit includes master control borad, gyroscope and the encoder for detecting Servo-controller corner, the gyroscope and
Encoder is connect with master control borad, and master control borad, which obtains the flight attitude of unmanned plane by gyroscope and controls driving mechanism, drives wing
Specified angle is rotated to, master control borad obtains the corner of wing by encoder；
When unmanned plane flight vertically upward, control circuit control wing is threaded to vertically；
When 45 ° of upward flight of unmanned plane, control circuit control wing rotates 45 ° counterclockwise；
When unmanned plane keeps height cruising flight, control circuit control wing is threaded to horizontality.
2. a kind of unmanned plane according to claim 1, it is characterised in that: cut connecting rod according to the width of fuselage, make machine
The end face of the wing is adjacent to fuselage.
3. a kind of unmanned plane according to claim 1, it is characterised in that: first rocker arm assumes diamond in shape, Servo-controller
Output shaft passes through the center of the first rocker arm, and second rocker arm assumes diamond in shape, and the turning-bar passes through the center of the second rocker arm.
4. a kind of unmanned plane according to claim 1, it is characterised in that: the wing is convexo-plane wing.
5. a kind of unmanned plane according to claim 1, it is characterised in that: the mounting base includes the first mounting plate, is located at
The second mounting plate above first mounting plate and the support plate being located between the first mounting plate and the second mounting plate, the driving machine
Structure designs on the first mounting plate, and the control circuit is located on the second mounting plate.
6. a kind of unmanned plane according to claim 1, it is characterised in that: the rotor assemblies include paddle arm, are located at paddle arm
On motor and rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910017151.0A CN109466762A (en) | 2019-01-08 | 2019-01-08 | A kind of unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910017151.0A CN109466762A (en) | 2019-01-08 | 2019-01-08 | A kind of unmanned plane |
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| Publication Number | Publication Date |
|---|---|
| CN109466762A true CN109466762A (en) | 2019-03-15 |
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| CN201910017151.0A Pending CN109466762A (en) | 2019-01-08 | 2019-01-08 | A kind of unmanned plane |
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|---|---|---|---|---|
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| JP2010254264A (en) * | 2009-04-24 | 2010-11-11 | Kenta Yasuda | Unmanned aircraft landing and departing perpendicularly by tilt wing mechanism |
| CN102358420A (en) * | 2011-07-29 | 2012-02-22 | 中国科学院长春光学精密机械与物理研究所 | Attitude transforming aircraft |
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| CN104608924A (en) * | 2015-02-12 | 2015-05-13 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Multi-rotor-wing craft with tilting fixed wing and control method of multi-rotor-wing craft |
| CN106314761A (en) * | 2016-08-31 | 2017-01-11 | 北京航空航天大学 | All-moving wing mechanism applied to small compound helicopter |
| CN107074352A (en) * | 2014-09-02 | 2017-08-18 | 瑞格夫·阿米特 | multi-rotor aircraft |
| US20180086446A1 (en) * | 2015-10-05 | 2018-03-29 | Sikorsky Aircraft Corporation | Pivot systems for tiltwing aircraft |
| 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 |
| CN209382264U (en) * | 2019-01-08 | 2019-09-13 | 贵州剑河中和时代科技有限公司 | A kind of unmanned plane |
-
2019
- 2019-01-08 CN CN201910017151.0A patent/CN109466762A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101010235A (en) * | 2004-07-02 | 2007-08-01 | 塞米肯公司 | Hybrid aircraft |
| US20090266941A1 (en) * | 2008-04-25 | 2009-10-29 | Abe Karem | Combination Spar and Trunnion Structure for a Tilt Rotor Aircraft |
| JP2010254264A (en) * | 2009-04-24 | 2010-11-11 | Kenta Yasuda | Unmanned aircraft landing and departing perpendicularly by tilt wing mechanism |
| CN102358420A (en) * | 2011-07-29 | 2012-02-22 | 中国科学院长春光学精密机械与物理研究所 | Attitude transforming aircraft |
| CN104044734A (en) * | 2014-06-20 | 2014-09-17 | 中国科学院合肥物质科学研究院 | Multi-rotor unmanned airplane with inclined wings and rotors and control system and method |
| CN107074352A (en) * | 2014-09-02 | 2017-08-18 | 瑞格夫·阿米特 | multi-rotor aircraft |
| CN104608924A (en) * | 2015-02-12 | 2015-05-13 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Multi-rotor-wing craft with tilting fixed wing and control method of multi-rotor-wing craft |
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