CN109878709B - Auxiliary flying device of multi-rotor aircraft - Google Patents
Auxiliary flying device of multi-rotor aircraft Download PDFInfo
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- CN109878709B CN109878709B CN201910272234.4A CN201910272234A CN109878709B CN 109878709 B CN109878709 B CN 109878709B CN 201910272234 A CN201910272234 A CN 201910272234A CN 109878709 B CN109878709 B CN 109878709B
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- 238000000034 method Methods 0.000 description 5
- 230000004048 modification Effects 0.000 description 5
- 238000012986 modification Methods 0.000 description 5
- 230000008859 change Effects 0.000 description 3
- 230000003993 interaction Effects 0.000 description 3
- 230000001105 regulatory effect Effects 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000002542 deteriorative effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Abstract
The embodiment of the invention discloses an auxiliary flying device of a multi-rotor aircraft, which relates to the technical field of aircrafts and comprises a first auxiliary wing component, a first driving component, a second auxiliary wing, a second driving component and an engine body, wherein the first auxiliary wing component, the first driving component, the second auxiliary wing and the second driving component are all arranged on the engine body, the first driving component is connected with the first auxiliary wing component through a first adjusting component, the axial direction of the first auxiliary wing component is in a horizontal plane, the second driving component is connected with the second auxiliary wing through a second adjusting component, and the axial direction of the second auxiliary wing is in a vertical plane.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an auxiliary flying device of a multi-rotor aircraft.
Background
The unmanned plane is called as unmanned plane for short, and is a unmanned plane operated by radio remote control equipment and a self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device and other devices. Personnel on the ground, ships or on a mother machine remote control station track, position, remote control, telemetere and digital transmission through radar and other equipment. The method is widely used for air reconnaissance, monitoring, communication, anti-diving, electronic interference and the like.
Various traditional large, medium and small-sized, electric, oil-powered and hybrid aircrafts and unmanned aerial vehicles at present adopt methods for instantaneously increasing and reducing voltage and current and oil supply, so that the rotating speeds of motors and engines are instantaneously changed, and the rotating speeds and the lifting force of a rotor wing are further changed to achieve the purpose of adjusting the flying attitude and the flying speed.
The existing method needs to continuously adjust various parameters affecting the lift force of the rotor wing, so that the power device is always in an unstable variable speed working state, thereby obviously increasing the power consumption and the oil consumption, deteriorating the endurance capacity, and solving the problems of shortened service life, increased engine heat load, poor lubrication, increased failure rate and the like caused by the increase of instantaneous current and voltage of a motor and a battery and the heating of a motor engine battery.
Disclosure of Invention
The embodiment of the invention aims to provide an auxiliary flying device of a multi-rotor aircraft, which is used for solving the problems of increased heat load, poor cruising ability and the like of an aircraft or unmanned aerial vehicle engine in the prior art.
In order to achieve the above objective, an embodiment of the present invention provides an auxiliary flying device for a multi-rotor aircraft, including a first auxiliary wing assembly, a first driving assembly, a second auxiliary wing, a second driving assembly and a body;
the first auxiliary wing assembly, the first driving assembly, the second auxiliary wing and the second driving assembly are all arranged on the machine body;
the first driving component is connected with the first auxiliary wing component through a first adjusting component;
the axial direction of the first auxiliary wing component is in a horizontal plane;
the second driving component is connected with the second auxiliary wing through a second adjusting component;
the axis direction of the second auxiliary wing is in a vertical plane.
Further, the machine body comprises a machine body, a first machine arm, a second machine arm, a third machine arm, a fourth machine arm and a fifth machine arm;
the first horn and the second horn, the third horn and the fourth horn are symmetrically arranged on two sides of the machine body and are arranged in parallel;
the fifth horn is connected with the machine body and is perpendicular to the planes where the axes of the first horn, the second horn, the third horn and the fourth horn are located.
Further, the first auxiliary wing component comprises a first auxiliary wing, a second auxiliary wing, a third auxiliary wing and a fourth auxiliary wing;
the first auxiliary wing is arranged on the first horn;
the second auxiliary wing is arranged on the second arm;
the third auxiliary wing is arranged on the third arm;
the fourth auxiliary wing is arranged on the fourth arm.
Further, the first driving assembly comprises a first driving piece, a second driving piece, a third driving piece and a fourth driving piece;
the first adjusting component comprises a first adjusting piece, a second adjusting piece, a third adjusting piece and a fourth adjusting piece;
the first driving piece is connected with the first auxiliary wing through the first adjusting piece;
the second driving piece is connected with the second auxiliary wing through the second adjusting piece;
the third driving piece is connected with the third auxiliary wing through the third adjusting piece;
the fourth driving piece is connected with the fourth auxiliary wing through the fourth adjusting piece.
Further, the rotation direction of the first auxiliary wing is opposite to that of the second auxiliary wing;
the rotation direction of the third auxiliary wing is opposite to that of the fourth auxiliary wing;
the rotation direction of the first auxiliary wing is the same as that of the third auxiliary wing.
Further, the first auxiliary wing, the second auxiliary wing, the third auxiliary wing and the fourth auxiliary wing all comprise a first top surface, a first bottom surface and a first side surface;
the first side surface comprises a first plane and a first cambered surface connected with the first plane.
Further, the second auxiliary wing comprises a second top surface, a second bottom surface and a second side surface;
the second side surface comprises a second cambered surface and a third cambered surface connected with the second cambered surface.
Further, the first adjusting piece comprises a first driving wheel and a first driven wheel;
the first driving wheel is arranged on the first horn;
the first driven wheel is arranged on the output shaft of the first driving piece and meshed with the first driving wheel;
the second adjusting piece comprises a second driving wheel and a second driven wheel;
the second driving wheel is arranged on the second arm;
the second driven wheel is arranged on the output shaft of the second driving piece and meshed with the second driving wheel;
the third adjusting piece comprises a third driving wheel and a third driven wheel;
the third driving wheel is arranged on the third arm;
the third driven wheel is arranged on the output shaft of the third driving piece and meshed with the third driving wheel;
the fourth adjusting piece comprises a fourth driving wheel and a fourth driven wheel;
the fourth driving wheel is arranged on the fourth arm;
the fourth driven wheel is arranged on the output shaft of the fourth driving piece and meshed with the fourth driving wheel.
Further, the second adjusting component comprises a fifth driving wheel and a fifth driven wheel;
the fifth driving wheel is arranged on the fifth arm;
the fifth driven wheel is arranged on the output shaft of the second driving assembly and meshed with the fifth driving wheel.
The embodiment of the invention has the following advantages:
the auxiliary flying device of the multi-rotor aircraft comprises a first auxiliary wing component, a first driving component, a second auxiliary wing, a second driving component and a machine body, wherein the machine body is used as a mounting foundation of the first auxiliary wing component, the first driving component, the second auxiliary wing and the second driving component, the first driving component is connected with the first auxiliary wing component through a first adjusting component, the axial direction of the first auxiliary wing component is positioned in a horizontal plane, the first adjusting component can adjust the deflection angle of the first auxiliary wing component, the magnitude of lift force is changed by changing the rotation angle and the direction of the first auxiliary wing component, the interaction force between the first auxiliary wing components is changed to play a role of adjusting flying posture, the second driving component is connected with the second auxiliary wing through a second adjusting component, the axial direction of the second auxiliary wing is positioned in a vertical plane, the second adjusting component can adjust the deflection angle of the second auxiliary wing, the deflection angle and the direction of the second auxiliary wing are changed, so that the deflection force and the direction are changed, the purpose of adjusting the flight heading is achieved, the application is additionally arranged on the aircraft or the unmanned aerial vehicle, when the aircraft or the unmanned aerial vehicle takes off, as the aircraft or the unmanned aerial vehicle does not have enough flight speed, the flight control system firstly controls the motor and the engine to adjust the flight attitude and accelerate and decelerate the take-off, when the aircraft or the unmanned aerial vehicle reaches a certain flight speed, the application intervenes in adjusting the flight attitude, the first auxiliary wing component generates enough lift force, the second auxiliary wing generates enough deflection force, and at the moment, the motor and the engine do not participate in adjusting the flight attitude before landing, the application increases the endurance of the aircraft or the unmanned aerial vehicle, prolongs the service life of the motor and the engine, reduces the fault rate, and improves the cruising flight speed, because the first auxiliary wing component can generate certain lifting force, the lifting force counteracts a part of gravity in the flying process, the load of the aircraft or the unmanned aerial vehicle is reduced, the cruising flying speed is improved again, the electric vehicle is different from the situation that the whole course of the electric vehicle or the unmanned aerial vehicle needs to be adjusted continuously by a motor and an engine in the prior art, the electric vehicle and the engine do not participate in adjusting the flying posture except the rest time when taking off and landing, the electric vehicle and the engine are always kept in an ideal state with economy and stability, and the problems that the electric power consumption and the oil consumption are greatly increased due to the fact that the rotation speed of the electric vehicle and the engine is increased and decreased frequently in the prior art are avoided.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It will be apparent to those of ordinary skill in the art that the drawings in the following description are exemplary only and that other implementations can be obtained from the extensions of the drawings provided without inventive effort.
The structures, proportions, sizes, etc. shown in the present specification are shown only for the purposes of illustration and description, and are not intended to limit the scope of the invention, which is defined by the claims, so that any structural modifications, proportional changes, or adjustments of size, which do not affect the efficacy of the invention or the objects achieved, should fall within the scope of the invention.
FIG. 1 is a schematic perspective view of an auxiliary flying device for a multi-rotor aircraft according to the present invention;
FIG. 2 is a schematic perspective view of the auxiliary flying device of the multi-rotor aircraft of FIG. 1 in another direction;
FIG. 3 is a schematic perspective view of the auxiliary flying device of the multi-rotor aircraft of FIG. 1 in another direction;
FIG. 4 is a schematic perspective view of the auxiliary flying device of the multi-rotor aircraft of FIG. 1 in another direction;
fig. 5 is a top view of the auxiliary flying device of the multi-rotor aircraft shown in fig. 1.
Icon: 1-a first wing assembly; 2-a first drive assembly; 3-a second auxiliary wing; 4-a second drive assembly; 5-the body; 6-a first adjustment assembly; 7-a second adjustment assembly; 11-a first auxiliary wing; 12-a second auxiliary wing; 13-third auxiliary wings; 14-fourth auxiliary wings; 111-a first plane; 112-a first cambered surface; 21-a first driving member; 22-a second driving member; 23-a third driving member; 24-fourth driving member; 31-a second cambered surface; 32-a third cambered surface; 51-a body; 52-a first horn; 53-a second horn; 54-a third horn; 55-a fourth horn; 56-a fifth horn; 61-a first adjustment member; 62-a second adjustment member; 63-a third adjustment member; 64-fourth adjustment member; 611-a first drive wheel; 612—a first driven wheel; 621-a second driving wheel; 622-second driven wheel; 631-a third drive wheel; 632-a third driven wheel; 641-fourth drive wheel; 642 to fourth driven wheel; 71-a fifth driving wheel; 72-fifth driven wheel.
Detailed Description
Other advantages and advantages of the present invention will become apparent to those skilled in the art from the following detailed description, which, by way of illustration, is to be read in connection with certain specific embodiments, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The terms such as "upper", "lower", "left", "right", "middle" and the like are also used in the present specification for convenience of description, but are not intended to limit the scope of the present invention, and the changes or modifications of the relative relationship thereof are considered to be within the scope of the present invention without substantial modification of the technical content.
As shown in fig. 1 to 5, the present embodiment provides a multi-rotor aircraft auxiliary flying device with a steel wire rope 6, which comprises a first auxiliary wing assembly 1, a first driving assembly 2, a second auxiliary wing 3, a second driving assembly 4 and a machine body 5;
the first auxiliary wing component 1, the first driving component 2, the second auxiliary wing 3 and the second driving component 4 are all arranged on the machine body 5;
the first driving assembly 2 is connected with the first auxiliary wing assembly 1 through a first adjusting assembly 6;
the axial direction of the first auxiliary wing assembly 1 is in the horizontal plane;
the second driving component 4 is connected with the second auxiliary wing 3 through a second adjusting component 7;
the axial direction of the second auxiliary wing 3 is in a vertical plane.
The auxiliary flying device of the multi-rotor aircraft comprises a first auxiliary wing component 1, a first driving component 2, a second auxiliary wing 3, a second driving component 4 and a machine body 5, wherein the machine body 5 is used as a mounting base of the first auxiliary wing component 1, the first driving component 2, the second auxiliary wing 3 and the second driving component 4, the first driving component 2 is connected with the first auxiliary wing component 1 through a first adjusting component 6, the axial direction of the first auxiliary wing component 1 is in a horizontal plane, the first adjusting component 6 can adjust the deflection angle of the first auxiliary wing component 1, the rotation angle and the direction of the first auxiliary wing component 1 are changed, the lifting force is changed, the interaction force between the first auxiliary wing component 1 is changed, the second driving component 4 and the second auxiliary wing 3 play a role of adjusting the flying gesture, the axial direction of the second auxiliary wing 3 is in a vertical plane, the second adjusting component 7 can adjust the deflection angle of the second auxiliary wing 3, the deflection angle and the deflection direction of the second auxiliary wing 3 are changed, so that the magnitude and the direction of deflection force are changed, the purpose of adjusting the flying heading is achieved, the flying attitude and the acceleration and deceleration take-off are firstly adjusted by the control motor and the motor under the control of the flying control system when the flying speed of the flying vehicle or the unmanned plane is insufficient due to the fact that the flying vehicle or the unmanned plane is additionally arranged on the flying vehicle, when the flying vehicle or the unmanned plane takes off, the first auxiliary wing component 1 generates enough lifting force when the flying speed is reached, the second auxiliary wing 3 generates enough deflection force, at the moment, the motor and the motor do not participate in adjusting the flying attitude before landing, the flying capability of the flying vehicle or the unmanned plane is increased, the service life of the motor and the motor is prolonged, the device reduces the fault rate, improves the cruising flying speed, and because the first auxiliary wing component 1 can generate a certain lifting force, the lifting force counteracts a part of gravity in the flying process, reduces the load of the aircraft or the unmanned aerial vehicle, improves the cruising flying speed again, and is different from the prior art that the motor and the engine are required to continuously adjust the flying posture in the whole course, the motor and the engine are not involved in adjusting the flying posture except for the rest time when taking off and landing, the motor and the engine are always kept in an economic and stable ideal state, and the problems that the power consumption and the oil consumption are greatly increased due to the frequent acceleration and deceleration of the motor and the engine in the prior art are solved.
With continued reference to fig. 1 to 5, the machine body 5 includes a machine body 51, a first arm 52, a second arm 53, a third arm 54, a fourth arm 55 and a fifth arm 56;
the first horn 52 and the second horn 53 and the third horn 54 and the fourth horn 55 are symmetrically arranged at two sides of the body 51 and are arranged in parallel;
the fifth horn 56 is connected to the body 51 and is perpendicular to the plane in which the axes of the first, second, third, and fourth horns 52, 53, 54, and 55 are located.
Further, the first auxiliary wing assembly 1 comprises a first auxiliary wing 11, a second auxiliary wing 12, a third auxiliary wing 13 and a fourth auxiliary wing 14;
the first auxiliary wing 11 is arranged on the first horn 52;
the second auxiliary wing 12 is arranged on the second arm 53;
the third auxiliary wing 13 is arranged on the third arm 54;
the fourth auxiliary wing 14 is provided on the fourth horn 55.
Further, the rotation direction of the first auxiliary wing 11 is opposite to that of the second auxiliary wing 12;
the rotation direction of the third auxiliary wing 13 is opposite to that of the fourth auxiliary wing 14;
the first auxiliary wing 11 and the third auxiliary wing 13 rotate in the same direction.
In this embodiment, the first auxiliary wing 11, the second auxiliary wing 12, the third auxiliary wing 13 and the fourth auxiliary wing 14 are respectively installed at two sides of the main body 51 and are symmetrically arranged, and the rotation directions of the first auxiliary wing 11 and the second auxiliary wing 12 positioned at one side of the main body 51 are the same, and are opposite to the rotation directions of the third auxiliary wing 13 and the fourth auxiliary wing 14 arranged at the other side, so that lift force is generated, and the aircraft or the unmanned aerial vehicle maintains a stable flight state.
With continued reference to fig. 1-5, the first driving assembly 2 includes a first driving member 21, a second driving member 22, a third driving member 23, and a fourth driving member 24;
the first adjusting assembly 6 includes a first adjusting member 61, a second adjusting member 62, a third adjusting member 63, and a fourth adjusting member 64;
the first driving member 21 is connected with the first auxiliary wing 11 through the first adjusting member 61;
the second driving member 22 is connected with the second auxiliary wing 12 through a second adjusting member 62;
the third driving member 23 is connected with the third auxiliary wing 13 through a third adjusting member 63;
the fourth drive member 24 is connected to the fourth auxiliary wing 14 via a fourth adjustment member 64.
Further, the first adjusting member 61 includes a first driving wheel 611 and a first driven wheel 612;
the first driving wheel 611 is disposed on the first arm 52;
the first driven wheel 612 is disposed on the output shaft of the first driving member 21 and meshed with the first driving wheel 611;
the second regulating member 62 includes a second driving wheel 621 and a second driven wheel 622;
the second driving wheel 621 is arranged on the second arm 53;
the second driven wheel 622 is disposed on the output shaft of the second driving member 22 and engaged with the second driving wheel 621;
the third regulating member 63 includes a third driving wheel 631 and a third driven wheel 632;
the third driving wheel 631 is arranged on the third arm 54;
the third driven wheel 632 is disposed on the output shaft of the third driving member 23 and engaged with the third driving wheel 631;
the fourth regulating member 64 includes a fourth driving wheel 641 and a fourth driven wheel 642;
the fourth driving wheel 641 is arranged on the fourth arm 55;
the fourth driven wheel 642 is provided on the output shaft of the fourth driver 24 and is engaged with the fourth driving wheel 641.
Further, the second adjusting assembly 7 comprises a fifth driving wheel 71 and a fifth driven wheel 72;
the fifth driving wheel 71 is arranged on the fifth arm 56;
the fifth driven wheel 72 is provided on the output shaft of the second drive assembly 4 and is meshed with the fifth driving wheel 71.
In this embodiment, taking the connection between the first driving member 21 and the first auxiliary wing 11 through the first adjusting member 61 as an example, the first driving member 21 is started, the first driving member 21 drives the first driving wheel 611 to rotate, so that the first driven wheel 612 meshed with the first driving wheel 611 rotates in the opposite direction to the first driving wheel 611, so as to change the rotation angle and direction of the first auxiliary wing 11, thereby changing the lift magnitude, and changing the interaction force between the first auxiliary wing components 1, so as to play a role in adjusting the flying attitude, and similarly, the adjustment modes of the second auxiliary wing 12, the third auxiliary wing 13 and the fourth auxiliary wing 14 are the same, and are not repeated herein, the second driving component 4 is started, the second driving component 4 drives the fifth driving wheel 71 to rotate, so that the fifth driven wheel 72 meshed with the fifth driving wheel 71 rotates in the opposite direction to the fifth driving wheel 71, so as to change the deflection angle of the second auxiliary wing 3, and change the deflection angle and direction of the second auxiliary wing 3, so as to play a role in adjusting the magnitude and direction of the deflecting force, thereby playing an effect of adjusting the flying direction, and the purpose of applying for adjusting the flying heading, and the first auxiliary wing 1, and enough deflecting force is generated by the unmanned aerial vehicle.
With continued reference to fig. 1 to 5, the first auxiliary wing 11, the second auxiliary wing 12, the third auxiliary wing 13 and the fourth auxiliary wing 14 each include a first top surface, a first bottom surface and a first side surface;
the first side includes a first plane 111 and a first arc surface 112 connected to the first plane 111.
Further, the second auxiliary wing 3 includes a second top surface, a second bottom surface, and a second side surface;
the second side surface includes a second cambered surface 31 and a third cambered surface 33 connected with the second cambered surface 31.
In this embodiment, the first auxiliary wing 11, the second auxiliary wing 12, the third auxiliary wing 13 and the fourth auxiliary wing 14 are identical to the section shape of the fixed wing aircraft wing, the flow rate of the wind flowing over the first plane 111 and the first cambered surface 112 is different, the flow rate of the air passing over the first cambered surface 112 is greater than the flow rate of the air passing over the first plane 111, thereby generating lift force, the second auxiliary wing 3 is different from the first auxiliary wing 11, the second auxiliary wing 12, the third auxiliary wing 13 and the fourth auxiliary wing 14, the section shape of the vertical tail of the fixed wing aircraft is identical to that of the fixed wing aircraft, the second cambered surface 31 and the third cambered surface 33 are included, and the deflection angle of the second auxiliary wing 3 is changed by the second adjusting component 7 so as to achieve the purpose of adjusting the flying heading.
While the invention has been described in detail in the foregoing general description and specific examples, it will be apparent to those skilled in the art that modifications and improvements can be made thereto. Accordingly, such modifications or improvements may be made without departing from the spirit of the invention and are intended to be within the scope of the invention as claimed.
Claims (5)
1. An auxiliary flying device of a multi-rotor aircraft is characterized by comprising a first auxiliary wing assembly, a first driving assembly, a second auxiliary wing, a second driving assembly and a machine body;
the first auxiliary wing assembly, the first driving assembly, the second auxiliary wing and the second driving assembly are all arranged on the machine body;
the first driving component is connected with the first auxiliary wing component through a first adjusting component;
the axial direction of the first auxiliary wing component is in a horizontal plane;
the second driving component is connected with the second auxiliary wing through a second adjusting component;
the axis direction of the second auxiliary wing is in a vertical plane;
the machine body comprises a machine body, a first machine arm, a second machine arm, a third machine arm, a fourth machine arm and a fifth machine arm;
the first horn and the second horn, the third horn and the fourth horn are symmetrically arranged on two sides of the machine body and are arranged in parallel;
the fifth horn is connected with the machine body and is perpendicular to the planes of the axes of the first horn, the second horn, the third horn and the fourth horn;
the first driving assembly comprises a first driving piece, a second driving piece, a third driving piece and a fourth driving piece;
the first auxiliary wing component comprises a first auxiliary wing, a second auxiliary wing, a third auxiliary wing and a fourth auxiliary wing;
the first adjusting component comprises a first adjusting piece, a second adjusting piece, a third adjusting piece and a fourth adjusting piece;
the first driving piece is connected with the first auxiliary wing through the first adjusting piece;
the second driving piece is connected with the second auxiliary wing through the second adjusting piece;
the third driving piece is connected with the third auxiliary wing through the third adjusting piece;
the fourth driving piece is connected with the fourth auxiliary wing through the fourth adjusting piece;
the second auxiliary wing comprises a second top surface, a second bottom surface and a second side surface;
the second side surface comprises a second cambered surface and a third cambered surface connected with the second cambered surface;
the first adjusting piece comprises a first driving wheel and a first driven wheel;
the first driving wheel is arranged on the first horn;
the first driven wheel is arranged on the output shaft of the first driving piece and meshed with the first driving wheel;
the second adjusting piece comprises a second driving wheel and a second driven wheel;
the second driving wheel is arranged on the second arm;
the second driven wheel is arranged on the output shaft of the second driving piece and meshed with the second driving wheel;
the third adjusting piece comprises a third driving wheel and a third driven wheel;
the third driving wheel is arranged on the third arm;
the third driven wheel is arranged on the output shaft of the third driving piece and meshed with the third driving wheel;
the fourth adjusting piece comprises a fourth driving wheel and a fourth driven wheel;
the fourth driving wheel is arranged on the fourth arm;
the fourth driven wheel is arranged on the output shaft of the fourth driving piece and meshed with the fourth driving wheel.
2. The multi-rotor aircraft auxiliary flying device according to claim 1, wherein,
the first auxiliary wing is arranged on the first horn;
the second auxiliary wing is arranged on the second arm;
the third auxiliary wing is arranged on the third arm;
the fourth auxiliary wing is arranged on the fourth arm.
3. The multi-rotor aircraft auxiliary flying device according to claim 2, wherein the first auxiliary wing and the second auxiliary wing rotate in opposite directions;
the rotation direction of the third auxiliary wing is opposite to that of the fourth auxiliary wing;
the rotation direction of the first auxiliary wing is the same as that of the third auxiliary wing.
4. The multi-rotor aircraft auxiliary flying device of claim 2 wherein the first auxiliary wing, the second auxiliary wing, the third auxiliary wing and the fourth auxiliary wing each comprise a first top surface, a first bottom surface and a first side surface;
the first side surface comprises a first plane and a first cambered surface connected with the first plane.
5. The multi-rotor aircraft auxiliary flying device according to claim 1, wherein the second adjustment assembly comprises a fifth drive wheel and a fifth driven wheel;
the fifth driving wheel is arranged on the fifth arm;
the fifth driven wheel is arranged on the output shaft of the second driving assembly and meshed with the fifth driving wheel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910272234.4A CN109878709B (en) | 2019-04-04 | 2019-04-04 | Auxiliary flying device of multi-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910272234.4A CN109878709B (en) | 2019-04-04 | 2019-04-04 | Auxiliary flying device of multi-rotor aircraft |
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| Publication Number | Publication Date |
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| CN109878709A CN109878709A (en) | 2019-06-14 |
| CN109878709B true CN109878709B (en) | 2024-03-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910272234.4A Active CN109878709B (en) | 2019-04-04 | 2019-04-04 | Auxiliary flying device of multi-rotor aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108725772A (en) * | 2018-05-31 | 2018-11-02 | 江苏常探机器人有限公司 | A kind of band is without the rear single-screw paddle composite wing aircraft for pushing away the compound auxiliary wing |
| CN109263874A (en) * | 2018-10-30 | 2019-01-25 | 佛山市神风航空科技有限公司 | A kind of oil electric mixed dynamic multi-rotor aerocraft |
| JP2019026236A (en) * | 2017-08-02 | 2019-02-21 | 独立行政法人国立高等専門学校機構 | Vertical take-off and landing machine |
| CN210162248U (en) * | 2019-04-04 | 2020-03-20 | 李明珠 | Auxiliary flight device of multi-rotor aircraft |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130092799A1 (en) * | 2011-10-17 | 2013-04-18 | Yu Tian | Fixed-wing and electric multi-rotor composite aircraft |
| US9994313B2 (en) * | 2014-11-26 | 2018-06-12 | XCraft Enterprises, LLC | High speed multi-rotor vertical takeoff and landing aircraft |
| IL256941A (en) * | 2018-01-15 | 2018-03-29 | Colugo Systems Ltd | A free wing multirotor with vertical and horizontal rotors |
-
2019
- 2019-04-04 CN CN201910272234.4A patent/CN109878709B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2019026236A (en) * | 2017-08-02 | 2019-02-21 | 独立行政法人国立高等専門学校機構 | Vertical take-off and landing machine |
| CN108725772A (en) * | 2018-05-31 | 2018-11-02 | 江苏常探机器人有限公司 | A kind of band is without the rear single-screw paddle composite wing aircraft for pushing away the compound auxiliary wing |
| CN109263874A (en) * | 2018-10-30 | 2019-01-25 | 佛山市神风航空科技有限公司 | A kind of oil electric mixed dynamic multi-rotor aerocraft |
| CN210162248U (en) * | 2019-04-04 | 2020-03-20 | 李明珠 | Auxiliary flight device of multi-rotor aircraft |
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| CN109878709A (en) | 2019-06-14 |
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