CN207791152U - A kind of aircraft driving mechanism and aircraft - Google Patents
A kind of aircraft driving mechanism and aircraft Download PDFInfo
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- CN207791152U CN207791152U CN201721749764.6U CN201721749764U CN207791152U CN 207791152 U CN207791152 U CN 207791152U CN 201721749764 U CN201721749764 U CN 201721749764U CN 207791152 U CN207791152 U CN 207791152U
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- aircraft
- holding firmware
- driving mechanism
- gear
- connecting hole
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Abstract
The utility model discloses a kind of aircraft driving mechanism and aircraft, the aircraft driving mechanism includes installation bucket, driving motor and rotation axis, the installation bucket is equipped with the first connecting hole, the driving motor is arranged in first connecting hole, the installation barrel side wall extends fixed part, and the fixed part is equipped with the second connecting hole, and the rotation axis is arranged in second connecting hole, gear is fixedly connected in the rotation axis, the drive shaft of the driving motor is engaged with the gear.The utility model safety, stability, durability and resistance to falling property are good.
Description
Technical field
The utility model is related to aircraft accessories fields, more specifically, being related to a kind of aircraft driving mechanism and flight
Device.
Background technology
Aircraft includes that unmanned plane drives aircraft and piloted vehicle, and unmanned plane drives aircraft referred to as " nobody
Machine " is the not manned aircraft manipulated using radio robot or embedded program.Gyroplane be it is a kind of using it is preceding winged when
Relative wind blows autorotation to generate the rotary wing aircraft of lift.Its forward force is directly carried by driven by engine propeller
For.
Present gyroplane is in flight, by driven by engine propeller rotational, the propeller of present gyroplane with
The rotation axis of engine is usually all directly connected to, and when unexpected air crash occurs, is usually all that propeller first lands, is existed in this way
When propeller damages, it is easy also to damage engine.
Utility model content
The technical problem to be solved by the utility model is to provide a kind of safety, the better aircraft driving machines of stability
Structure and aircraft.
The purpose of this utility model is achieved through the following technical solutions：
One side according to the present utility model, the utility model include a kind of aircraft driving mechanism, the aircraft
Driving mechanism includes installation bucket, driving motor and rotation axis, and the installation bucket is equipped with the first connecting hole, and the driving motor is set
It sets in first connecting hole, the installation barrel side wall extends fixed part, and the fixed part is equipped with the second connecting hole, institute
It states rotation axis to be arranged in second connecting hole, gear, the drive shaft of the driving motor is fixedly connected in the rotation axis
It is engaged with the gear.
Further, the fixed part includes the first holding firmware and the second holding firmware, and first holding firmware and second block
Firmware is correspondingly arranged, and second connecting hole runs through first holding firmware and the second holding firmware, and the gear is arranged described
Between first holding firmware and second holding firmware, and it is connected to first connecting hole.
Using this structure so that gear is arranged between the first holding firmware and the second holding firmware, can make tooth in this way
The connective stability higher of wheel.
Further, be arranged with bearing in the rotation axis, the bearing setting the fixing piece and the gear it
Between.Bearing is used so that rotation can be coordinated between holding firmware and gear, will not to be formed between rotation axis and holding firmware dry
It relates to, influences the rotation of rotation axis.
Further, the bearing includes first bearing and second bearing, and the first bearing setting is in first card
Between firmware and the gear, the second bearing is arranged between second holding firmware and the gear.Ensure tooth in this way
Wheel will not all be interfered both sides up and down, ensure the smooth rotation of rotation axis.
Further, the installation barrel side wall is equipped with mounting plate, and second holding firmware is by the mounting plate and installation bucket
It is extended to form to side.In this way so that the fastness of the second holding firmware formation is stronger.
Further, it is connected with gusset between the mounting plate and the installation barrel side wall.It can ensure mounting plate in this way
Installation strength, it is ensured that the stability of the second holding firmware.
Further, the rotation axis of second holding firmware bottom is connected with screw.
Further, the rotation axis passes through the upper end of first holding firmware to be fixedly connected with connecting shaft, the connection
Axis is fixedly connected with the pivoting leaf.
Further, one end end that the connecting shaft is connect with the pivoting leaf is hexagonal bolt, the pivoting leaf
Bottom is equipped with jack, and the hexagon bolt is inserted into the jack and is fixedly connected.This assembly method is more convenient simple.
Another convenience according to the present utility model, including a kind of aircraft make a kind of above-mentioned aircraft driving mechanism.
Compared with prior art, the utility model has the technical effect that：The first connecting hole by installing bucket installs driving
Motor installs rotation axis, the pivoting leaf connection of rotation axis and aircraft, the drive shaft driving of driving motor by the second connecting hole
Gear rotates, and the rotation of gear band turn moving axis usually only can damage rotation axis in this way when pivoting leaf receives shock, and not allow
Easily directly damage driving motor, so that driving motor safety in operation with stablize higher, even if repeatedly touching and dropping
It is less likely to be damaged, substantially increases resistance to the falling property of aircraft, increase the service life of aircraft, improve durability, finally
Using this structure, when replacing the component of damage, leaf is more convenient and cheap.
Description of the drawings
Included attached drawing is used for providing being further understood from the embodiment of the present application, and which constitute one of specification
Point, for illustrating presently filed embodiment, and with verbal description come together to illustrate the principle of the application.Under it should be evident that
Attached drawing in the description of face is only some embodiments of the present application, for those of ordinary skill in the art, is not paying wound
Under the premise of the property made is laborious, other drawings may also be obtained based on these drawings.In the accompanying drawings：
Fig. 1 is a kind of decomposition texture schematic diagram of aircraft driving mechanism of the utility model embodiment；
Fig. 2 is a kind of structural schematic diagram of aircraft driving mechanism of the utility model embodiment；
Fig. 3 is a kind of side structure schematic diagram of aircraft driving mechanism of the utility model embodiment.
Wherein：1, bucket is installed, the 11, first connecting hole, 12, fixed part, the 121, first holding firmware, the 122, second holding firmware,
13, the second connecting hole, 14, mounting plate, 15, gusset, 2, driving motor, 3, rotation axis, 4, gear, 5, bearing, 51, first axle
It holds, 52, second bearing, 6, screw, 7, connecting shaft, 8, pivoting leaf.
Specific implementation mode
The utility model is described in further detail with preferred embodiment below in conjunction with the accompanying drawings.
In the description of the present invention, it should be understood that term "center", " transverse direction ", "upper", "lower", " left side ",
The orientation or positional relationship of the instructions such as " right side ", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on ... shown in the drawings
Orientation or positional relationship is merely for convenience of describing the present invention and simplifying the description, and does not indicate or imply the indicated dress
It sets or element must have a particular orientation, with specific azimuth configuration and operation, therefore should not be understood as to the utility model
Limitation.In addition, term " first ", " second " are used for description purposes only, it is not understood to indicate or imply relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include one or more this feature.In the description of the present invention, unless otherwise indicated, the meaning of " multiple "
It is two or more.In addition, term " comprising " and its any deformation, it is intended that cover and non-exclusive include.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " is pacified
Dress ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally
Connection；It can be mechanical connection, can also be electrical connection；Can be directly connected, can also indirectly connected through an intermediary,
It can be the connection inside two elements.For the ordinary skill in the art, it can understand above-mentioned art with concrete condition
The concrete meaning of language in the present invention.
As shown in Figures 1 to 3, include a kind of aircraft driving mechanism, aircraft the utility model discloses the utility model
Driving mechanism includes installation bucket 1, driving motor 2 and rotation axis 3, and installation bucket 1 is equipped with the first connecting hole 11, and driving motor 2 is set
It sets in the first connecting hole 11, installation 1 side wall of bucket extends fixed part 12, and fixed part 12 is equipped with the second connecting hole 13, rotation
Axis 3 is arranged in the second connecting hole 13, gear 4 is fixedly connected in rotation axis 3, the drive shaft of driving motor 2 is engaged with gear 4.
The first connecting hole 11 by installing bucket 1 installs driving motor 2, installs rotation axis 3 by the second connecting hole 13, turns
Moving axis 3 is connect with the pivoting leaf 8 of aircraft, and the drive shaft driving gear 4 of driving motor 2 rotates, and gear 4 drives 3 turns of rotation axis
It is dynamic, in this way when pivoting leaf 8 receives shock, rotation axis 3 only usually can be damaged, and be not easy directly to damage driving motor 2, in this way
So that 2 safety in operation of driving motor and stablizing higher, even if repeatedly touching and being less likely to be damaged if dropping, substantially increase
Resistance to the falling property of aircraft, increases the service life of aircraft, improves durability, is finally replacing damage using this structure
Component when leaf it is more convenient and cheap.
Wherein, fixed part 12 includes the first holding firmware 121 and the second holding firmware 122, and the first holding firmware 121 and second fixes
Part 122 is correspondingly arranged, and the second connecting hole 13 runs through the first holding firmware 121 and the second holding firmware 122, and the setting of gear 4 is in the first card
It is connected between firmware 121 and the second holding firmware 122 and with the first connecting hole 11.Using this structure so that the setting of gear 4 is the
Between one holding firmware 121 and the second holding firmware 122, it can make the connective stability higher of gear 4 in this way.
Wherein, bearing 5 is arranged in rotation axis 3, bearing 5 is arranged between holding firmware and gear 4.Bearing 5 is used to make
Rotation can be coordinated between fixed part and gear 4, will not to form interference between rotation axis 3 and holding firmware, influence rotation axis 3
Rotation.Further, bearing 5 includes first bearing 51 and second bearing 52, and first bearing 51 is arranged in the first holding firmware 121
Between gear 4, second bearing 52 is arranged between the second holding firmware 122 and gear 4.Ensure about 4 both sides of gear all in this way
It will not be interfered, ensure the smooth rotation of rotation axis 3.
Wherein, installation barrel side wall is equipped with mounting plate 14, and the second holding firmware 122 is prolonged from mounting plate 14 and installation bucket 1 to side
It stretches to be formed.In this way so that the fastness of the second holding firmware 122 formation is stronger.
Wherein, it is connected with gusset 15 between mounting plate 14 and installation 1 side wall of bucket.It can ensure the installation of mounting plate 14 in this way
Intensity, it is ensured that the stability of the second holding firmware 122.
Wherein, the rotation axis 3 of 122 bottom of the second holding firmware is connected with screw 6.
Wherein, rotation axis 3 passes through the upper end of the first holding firmware 121 to be fixedly connected with connecting shaft 7, connecting shaft 7 and pivoting leaf 8
It is fixedly connected.Wherein, connecting shaft 7 can be plastic column, can also be metal column or pin, to connecting shaft 7 in the present embodiment
The material specifically used is not specifically limited, cannot by connecting shaft 7 by simple material replacement think in the present embodiment
Technical solution has substantive difference.
Wherein, one end end that connecting shaft 7 is connect with pivoting leaf 8 is hexagonal bolt, and 8 bottom of pivoting leaf is equipped with jack,
Hexagon bolt is inserted into jack and is fixedly connected.This assembly method is more convenient simple.
Another convenience according to the present utility model, including a kind of aircraft make a kind of above-mentioned aircraft driving mechanism.
As further improvement of this embodiment, wherein the material of glue-line 2 used is polyurethane.Primarily serve increase
Thickness, enhances the effect of place elasticity, and place elasticity increase is more advantageous to sphere rebound, is conducive to Athletess.
Claims (10)
1. a kind of aircraft driving mechanism, which is characterized in that the aircraft driving mechanism include installation bucket, driving motor and
Rotation axis, the installation bucket are equipped with the first connecting hole, and the driving motor is arranged in first connecting hole, the installation bucket
Side wall extends fixed part, and the fixed part is equipped with the second connecting hole, and the rotation axis is arranged in second connecting hole,
Gear is fixedly connected in the rotation axis, the drive shaft of the driving motor is engaged with the gear.
2. a kind of aircraft driving mechanism according to claim 1, which is characterized in that the fixed part includes the first fixing
Part and the second holding firmware, first holding firmware and the second holding firmware are correspondingly arranged, and second connecting hole runs through described first
Holding firmware and the second holding firmware, the gear are arranged between first holding firmware and second holding firmware and with described the
One connecting hole is connected to.
3. a kind of aircraft driving mechanism according to claim 2, which is characterized in that be arranged with axis in the rotation axis
It holds, the bearing is arranged between the fixed part and the gear.
4. a kind of aircraft driving mechanism according to claim 3, which is characterized in that the bearing include first bearing and
Second bearing, the first bearing are arranged between first holding firmware and the gear, and the second bearing is arranged in institute
It states between the second holding firmware and the gear.
5. a kind of aircraft driving mechanism according to claim 2, which is characterized in that the installation barrel side wall is equipped with installation
Plate, second holding firmware are extended to form from the mounting plate and installation bucket to side.
6. a kind of aircraft driving mechanism according to claim 5, which is characterized in that the mounting plate and the installation bucket
Gusset is connected between side wall.
7. a kind of aircraft driving mechanism according to claim 2, which is characterized in that second holding firmware bottom turns
Moving axis is connected with screw.
8. a kind of aircraft driving mechanism according to claim 2, which is characterized in that the rotation axis passes through described first
The upper end of holding firmware is fixedly connected with connecting shaft, and the connecting shaft is fixedly connected with pivoting leaf.
9. a kind of aircraft driving mechanism according to claim 8, which is characterized in that the connecting shaft and the pivoting leaf
One end end of connection is hexagonal bolt, and the pivoting leaf bottom is equipped with jack, and the hexagon bolt is inserted into the jack
Inside it is fixedly connected.
10. a kind of aircraft, which is characterized in that use a kind of aircraft driving mechanism as described in claim 1 to 9 is any.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721749764.6U CN207791152U (en) | 2017-12-15 | 2017-12-15 | A kind of aircraft driving mechanism and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721749764.6U CN207791152U (en) | 2017-12-15 | 2017-12-15 | A kind of aircraft driving mechanism and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207791152U true CN207791152U (en) | 2018-08-31 |
Family
ID=63284192
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721749764.6U Active CN207791152U (en) | 2017-12-15 | 2017-12-15 | A kind of aircraft driving mechanism and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207791152U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022036732A1 (en) * | 2020-08-17 | 2022-02-24 | 哈尔滨工业大学（深圳） | Telescopic device and unmanned aerial vehicle applying telescopic device |
-
2017
- 2017-12-15 CN CN201721749764.6U patent/CN207791152U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022036732A1 (en) * | 2020-08-17 | 2022-02-24 | 哈尔滨工业大学（深圳） | Telescopic device and unmanned aerial vehicle applying telescopic device |
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