CN109823523A - A kind of coaxial double-oar aircraft - Google Patents
A kind of coaxial double-oar aircraft Download PDFInfo
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- CN109823523A CN109823523A CN201711178494.2A CN201711178494A CN109823523A CN 109823523 A CN109823523 A CN 109823523A CN 201711178494 A CN201711178494 A CN 201711178494A CN 109823523 A CN109823523 A CN 109823523A
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- shell
- bevel gear
- shaft
- paddle components
- coaxial double
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Abstract
The present invention relates to vehicle technology fields, disclose a kind of coaxial double-oar aircraft, including shell and multiple groups rotor assemblies, shell includes the upper housing being detachably arranged and lower case, and multiple groups rotor assemblies are rotationally connected with upper housing and lower case, and each rotor assemblies include the paddle components of two settings symmetrical above and below, each paddle components include blade and shaft, the shaft of the paddle components of setting symmetrical above and below is concentric, and one end of shaft stretches out shell and is connected with blade, and bevel gear is arranged in the other end；Driving assembly is set between two paddle components, and the rotation axis of driving assembly and the shaft of two rotors are perpendicular, and second bevel gear is arranged in the rotation axis of driving assembly, and second bevel gear is meshed with the bevel gear of two paddle components.The blade for two paddle components that the structure drives shaft concentric simultaneously by a driving assembly is reversed and constant velocity rotation, the lift superposition of aircraft reduce costs, solve the problems, such as to spin when aircraft work.
Description
Technical field
The present invention relates to vehicle technology field more particularly to a kind of coaxial double-oar aircraft.
Background technique
In recent years, the multi-rotor aerocraft constantly risen because cost that it has it is low, it is easy to operate, there is high flexibility
With can be increasingly widely used by all trades and professions with the features such as hedgehopping, existing most of aircraft are mainly applied
In scientific research, geographical detection, agricultural is poured and the fields such as video capture.
Rotor craft is usually to provide lift using the different rotor in multipair direction of rotation.In order to avoid rotor flying
Device, since the torque that rotor wing rotation generates rotates rotorcraft body, is equipped with coaxial double-oar flight during flight
Device.Two same size motors are selected to respectively drive the rotor of coaxial mounted reverse rotation i.e. on its same rotor.Motor
When work, two motors drive two blade high speed rotations simultaneously.Two coaxial blades are provided which upward lift, but to keep
Two blade revolving speeds are identical, turn on the contrary, solving the problems, such as that aircraft spins with this for offsetting the anti-twisted power generated when work.
But the quantity of increased motor can be such that the cost of aircraft greatly improves, and be influenced each other by upper and lower blade, can make
It is difficult to preferably control at the revolving speed of motor, the flying quality of unmanned vehicle is caused to decline.
Summary of the invention
It is an object of the invention to propose a kind of coaxial double-oar aircraft, solves existing coaxial double-oar aircraft to keep away
Exempt from aircraft spin using the two blade rotations of two motors while driving, the problem of increasing cost, reduce flight.
To achieve this purpose, the present invention adopts the following technical scheme:
A kind of coaxial double-oar aircraft, comprising:
Shell comprising the upper housing and lower case being detachably arranged；And
Multiple groups rotor assemblies, are rotationally connected with the upper housing and the lower case, and each rotor assemblies are wrapped
Include the paddle components of two settings symmetrical above and below, each paddle components include blade and shaft, setting symmetrical above and below
The shaft of two paddle components is concentric, and one end of the shaft stretches out the shell and is connected with the blade, other end setting cone
Gear；Driving assembly is set between two paddle components, and the shaft of the driving component and the shaft of two rotors are mutually hung down
Directly, second bevel gear, the cone of the second bevel gear and two paddle components are set in the rotation axis of the driving component
Gear is meshed, and the driving component rotation drives the second bevel gear rotation, so that two bevel gears drive and correspond to
The blade is reversed and constant velocity rotation.
Rotor assemblies include the paddle components of two settings symmetrical above and below, and shaft one end of each paddle components and blade connect
It connects, the other end is connect with bevel gear, and driving assembly, the output end setting second of driving assembly are provided between two paddle components
Bevel gear, second bevel gear rotation drives to be meshed with symmetrically arranged two paddle components, i.e., is by a driving assembly
The blade of two rotor assemblies can be driven reversed simultaneously and constant velocity rotation, the lift superposition of aircraft, and counteract blade rotation
The reaction torque generated when turning, reduces costs, and flies more stable, solves the problems, such as to spin when aircraft work.
As a kind of preferred embodiment of above-mentioned coaxial double-oar aircraft, the group number odd number of the rotor assemblies.
As a kind of preferred embodiment of above-mentioned coaxial double-oar aircraft, the group number of the rotor assemblies is 3 groups.
As a kind of preferred embodiment of above-mentioned coaxial double-oar aircraft, the inclination of the bevel gear and the second bevel gear
Angle is 45 °.The tilt angle of bevel gear and second bevel gear is 45 °, and preparation is convenient.
As a kind of preferred embodiment of above-mentioned coaxial double-oar aircraft, the multiple groups rotor assemblies are along the center of the shell
Axis is circumferentially uniformly distributed.So that the flight of aircraft is more stable.
As a kind of preferred embodiment of above-mentioned coaxial double-oar aircraft, bearing assembly, the axis are provided in the shaft
Between the blade and the bevel gear, the rotor assemblies are rotationally connected with described bearing assembly by the bearing assembly
Shell.
As a kind of preferred embodiment of above-mentioned coaxial double-oar aircraft, the bearing assembly includes being arranged along the shaft
Two bearings.
As a kind of preferred embodiment of above-mentioned coaxial double-oar aircraft, the upper housing and the lower case include main body
Shell and multiple horn shells, one end of the horn shell are connected with the body shell, and rotor assemblies described in the other end and one group rotate
Connection, the body shell and horn shell of the upper housing are fastened with the body shell of corresponding lower case and horn shell phase.
As a kind of preferred embodiment of above-mentioned coaxial double-oar aircraft, the body shell and horn shell one of the upper housing at
Type preparation, the body shell of the lower case and the horn shell are integrally formed preparation.
Beneficial effects of the present invention:
Coaxial double-oar aircraft proposed by the present invention, rotor assemblies include the paddle components of two settings symmetrical above and below, often
Shaft one end of a paddle components is connect with blade, and the other end is connect with bevel gear, is provided with driving between two paddle components
Second bevel gear is arranged in component, the output end of driving assembly, and second bevel gear rotation drives and symmetrically arranged two blade groups
The bevel gear of part is meshed, i.e., the blade for two paddle components that can drive shaft concentric simultaneously by a driving assembly is anti-
To and constant velocity rotation, aircraft lift superposition, it is easy to operate, reduce costs, fly it is more stable, counteract blade rotation when
The reaction torque of generation solves the problems, such as to spin when aircraft work.
Detailed description of the invention
Fig. 1 is the structural schematic diagram for the coaxial double-oar aircraft that the specific embodiment of the invention provides；
Fig. 2 is the structural schematic diagram for the rotor assemblies that the specific embodiment of the invention provides.
Wherein:
1, shell；2, rotor assemblies；
11, upper housing；12, lower case；21, paddle components；22, driving assembly；23, bearing assembly；
111, upper body shell；112, upper horn shell；121, lower body shell；122, lower horn shell；211, blade；212, turn
Axis；213, bevel gear；221, second bevel gear；231, bearing.
Specific embodiment
To further illustrate the technical scheme of the present invention below with reference to the accompanying drawings and specific embodiments.
Present embodiment provides a kind of coaxial double-oar aircraft, as shown in Figure 1, aircraft includes shell 1 and multiple groups rotor
Component 2, multiple groups rotor assemblies 2 are circumferentially uniformly distributed along the central axis of shell 1, so that the flight of aircraft is more stable.
Specifically, shell 1 includes the upper housing 11 being detachably arranged and lower case 12, upper housing 11 and lower case 12 are assembled
Form hollow structure after the completion, upper housing 11 and lower case 12 include shell main body and horn shell, one end of horn shell and master
Body shell is connected, and the other end and one group of paddle components 21 are rotatablely connected, and the body shell and horn shell of upper housing 11 are respectively upper main body
Shell 111 and upper horn shell 112, the respectively lower body shell 121 of the body shell and horn shell of lower case 12 and lower horn shell 122, on
Body shell 111 and upper horn shell 112 are integrally formed preparation, and lower body shell 121 and lower horn shell 122 are integrally formed preparation.Upper master
Body shell 111 and corresponding lower body shell 121, which fasten, forms the first cavity structure, for installing control circuit board, battery etc..On
Horn shell 112 and the corresponding lower fastening of horn shell 122 also form the second cavity structure, the second cavity structure and the first cavity machine
Structure is connected.
Multiple groups rotor assemblies 2 are rotationally connected with upper housing 11 and lower case 12, and further, the rotation of rotor assemblies 2 connects
It is connected to horn shell 112 and lower horn shell 122.As shown in Fig. 2, each rotor assemblies 2 include two settings symmetrical above and below
Paddle components 21, each paddle components 21 include blade 211 and shaft 212, the two of the paddle components 21 of setting symmetrical above and below
With one heart, shaft 212 is rotationally connected with corresponding shell 1 to a shaft 212.
Specifically, shaft 212 is rotationally connected with the upper horn shell 112 or lower horn shell of shell 1 by bearing assembly 23
122, one end of shaft 212 stretches out upper horn shell 112 or lower horn shell 122 is connected with blade 211, and bevel gear is arranged in the other end
213；Further, each axis in shaft 212 and between blade 211 and bevel gear 213 is arranged in above-mentioned bearing assembly 23
Bearing assembly 23 includes two bearings 231 being arranged along shaft 212.
Driving assembly 22, the shaft of the rotation axis of driving assembly 22 and two rotors are provided between two paddle components 21
212 is perpendicular, in the rotation axis of driving assembly 22 be arranged second bevel gear 221, second bevel gear 221 with symmetrically arranged two
Two bevel gears 213 of paddle components 21 are meshed, and the rotation of driving assembly 22 drives second bevel gear 221 to rotate, so that two
A bevel gear 213 drives corresponding two blades 211 reversed and constant velocity rotation.Preferably, in the present embodiment, driving assembly 22 is
Column construction is placed in the second cavity that horn shell 112 and lower horn shell 122 are formed.Further, bevel gear 213 and
The tilt angle of two bevel gears 221 is 45 °.The tilt angle of bevel gear 213 and second bevel gear 221 is 45 °, and preparation is convenient.
The group number of rotor assemblies 2 is odd number, and corresponding, the group number of upper horn shell 112 and lower horn shell 122 is also accordingly
Odd number.When rotor assemblies 2 are odd number, due to two blades 211 of two paddle components 21 symmetrically arranged in rotor assemblies 2
It constant speed and rotates backward, anti-twisted power can be offset, branch's device can have a smooth flight.Preferably, the group number of rotor assemblies 2 is 3 groups,
Upper horn shell 112 and lower horn shell 122 are 3 groups, and the group number of rotor assemblies 2 is not limited to 3 groups, and rotor can be arranged according to demand
The group number of component 2, for example, the group number of rotor assemblies 2 may be arranged as 5 groups, 7 groups etc..
Rotor assemblies 2 include the paddle components 21 of two settings symmetrical above and below, 212 one end of shaft of each paddle components 21
It is connect with blade 211, the other end is connect with bevel gear 213, is provided with driving assembly 22, driving group between two paddle components 21
Second bevel gear 221 is arranged in the output end of part 22, and the rotation of second bevel gear 221 drives and symmetrically arranged two paddle components 21
Bevel gear 213 be meshed, i.e., two paddle components 21 that can drive shaft 212 concentric simultaneously by a driving assembly 22
Blade 211 is reversed and constant velocity rotation, the lift superposition of aircraft, and counteract the reaction torque generated when blade 211 rotates,
It solves the problems, such as to spin when aircraft work.
Note that above are only presently preferred embodiments of the present invention.It will be appreciated by those skilled in the art that the present invention is not limited to here
The specific embodiment, be able to carry out for a person skilled in the art it is various it is apparent variation, readjust and substitution and
Without departing from the scope of protection of the present invention.Therefore, although the present invention has been described in more detail through the above examples,
But the present invention is not limited to the above embodiments only, without departing from the inventive concept, can also include it is more other
Equivalent embodiment, and the scope of the invention is determined by the scope of the appended claims.
Claims (9)
1. a kind of coaxial double-oar aircraft characterized by comprising
Shell (1) comprising the upper housing (11) and lower case (12) being detachably arranged；And
Multiple groups rotor assemblies (2) are rotationally connected with the upper housing (11) and the lower case (12), each rotor group
Part (2) includes the paddle components (21) of two settings symmetrical above and below, and each paddle components (21) include blade (211)
With shaft (212), the shaft (212) of two paddle components (21) of setting symmetrical above and below with one heart, one end of the shaft (212)
It stretches out the shell (1) to be connected with the blade (211), bevel gear (213) are arranged in the other end；Between two paddle components (21)
It is arranged driving assembly (22), the rotation axis of the driving component (22) and the shaft (212) of two rotor assemblies (2) are mutually hung down
Directly, in the rotation axis of the driving component (22) be arranged second bevel gear (221), the second bevel gear (221) with symmetrically set
The bevel gear (213) of two set the paddle components (21) is meshed, and the driving component (22) rotation drives described second
Bevel gear (221) rotation, so that two bevel gears (213) drive the corresponding blade (211) reversed and constant velocity rotation.
2. coaxial double-oar aircraft according to claim 1, which is characterized in that the group number of the rotor assemblies (2) is surprise
Number.
3. coaxial double-oar aircraft according to claim 2, which is characterized in that the group number of the rotor assemblies (2) is 3
Group.
4. coaxial double-oar aircraft according to claim 1, which is characterized in that the bevel gear (213) and described second
The tilt angle of bevel gear (221) is 45 °.
5. coaxial double-oar aircraft according to claim 1, which is characterized in that the multiple groups rotor assemblies (2) are along described
The central axis of shell (1) is circumferentially uniformly distributed.
6. any coaxial double-oar aircraft in -5 according to claim 1, which is characterized in that set on the shaft (212)
It is equipped with bearing assembly (23), the bearing assembly (23) is described between the blade (211) and the bevel gear (213)
Rotor assemblies (2) are rotationally connected with the shell (1) by the bearing assembly (23).
7. coaxial double-oar aircraft according to claim 6, which is characterized in that the bearing assembly (23) includes along described
Two bearings (231) of shaft (212) setting.
8. coaxial double-oar aircraft according to claim 1, which is characterized in that the upper housing (11) and the lower case
It (12) include body shell and multiple horn shells, one end of the horn shell is connected with the body shell, the other end and one group of institute
State paddle components (21) rotation connection, the body shell of the upper housing and horn shell and the body shell of corresponding lower case and horn
Shell phase fastens.
9. coaxial double-oar aircraft according to claim 8, which is characterized in that the body shell and horn shell of the upper housing
It is integrally formed preparation, the body shell of the lower case and the horn shell are integrally formed preparation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711178494.2A CN109823523A (en) | 2017-11-23 | 2017-11-23 | A kind of coaxial double-oar aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711178494.2A CN109823523A (en) | 2017-11-23 | 2017-11-23 | A kind of coaxial double-oar aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109823523A true CN109823523A (en) | 2019-05-31 |
Family
ID=66858211
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711178494.2A Pending CN109823523A (en) | 2017-11-23 | 2017-11-23 | A kind of coaxial double-oar aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN109823523A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112278264A (en) * | 2020-11-06 | 2021-01-29 | 湖南浩天翼航空技术有限公司 | Double-deck rotor formula unmanned aerial vehicle of rotor angle adjustable |
| CN113483059A (en) * | 2021-07-07 | 2021-10-08 | 重庆大学 | Torque-dividing transmission speed reducing device for coaxial helicopter |
-
2017
- 2017-11-23 CN CN201711178494.2A patent/CN109823523A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112278264A (en) * | 2020-11-06 | 2021-01-29 | 湖南浩天翼航空技术有限公司 | Double-deck rotor formula unmanned aerial vehicle of rotor angle adjustable |
| CN113483059A (en) * | 2021-07-07 | 2021-10-08 | 重庆大学 | Torque-dividing transmission speed reducing device for coaxial helicopter |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190531 |
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| WD01 | Invention patent application deemed withdrawn after publication |