CN206171802U - Unmanned helicopter of microlight -type - Google Patents
Unmanned helicopter of microlight -type Download PDFInfo
- Publication number
- CN206171802U CN206171802U CN201621124486.0U CN201621124486U CN206171802U CN 206171802 U CN206171802 U CN 206171802U CN 201621124486 U CN201621124486 U CN 201621124486U CN 206171802 U CN206171802 U CN 206171802U
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- tail
- microlight
- rotor
- depopulated helicopter
- aluminium alloy
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Abstract
The utility model relates to an unmanned air vehicle technique field specifically discloses an unmanned helicopter of microlight -type, including fuselage, rotor system, mechanical control system, main shaft, hold -in range system, cooling system, engine, undercarriage, multistage reduction gear, tail boom, tail -rotor system and oil tank, the output shaft of engine respectively with hold -in range system and cooling system connect, the output of hold -in range system respectively with multistage reduction gear and tail -rotor headtotail, the output shaft of multistage reduction gear with rotor system connects, hold -in range system and cooling system's band pulley is made by the aluminum alloy, the reducing gear of multistage reduction gear is made by nylon. The utility model discloses a lightweight design, the complete machine uses nonmetallic composite material in a large number, and complete machine weight is little, simple structure, high transmission efficiency, the effectual time of endurance that has increased has improved the load coefficient.
Description
Technical field
This utility model is related to unmanned air vehicle technique field, more particularly to a kind of microlight-type depopulated helicopter.
Background technology
Unmanned plane is a kind of unmanned vehicle manipulated by radio robot or itself presetting apparatus.Nothing
Man-machine to be widely used for taking photo by plane and transport, at present, aviation UAV field is usually medium-sized, large-scale unmanned plane reduces pattern,
Light-duty unmanned plane generally drives blade to rotate using motor, and adopts accumulator for power output.
In prior art, light-duty depopulated helicopter is to reduce the weight and volume of itself, generally using motor as dynamic
Power is exported, but the power output of motor is less, and cruising time is short, and load factor is relatively low, and adopts electromotor conduct
Power output have the shortcomings that again own wt weight, can not be excessive carrying.So, these light-duty depopulated helicopters all can not be managed
The carrying out thought is flown.
Utility model content
The purpose of this utility model is to provide a kind of microlight-type depopulated helicopter, with overcome it is of the prior art it is light-duty nobody
Helicopter cruising time is short, the low problem of load factor.
In order to solve above-mentioned technical problem, this utility model provides a kind of microlight-type depopulated helicopter, including fuselage, rotation
Wing system, mechanical manoeuvring system, main shaft, Timing Belt system, cooling system, electromotor, undercarriage, multi-stage speed reducer, tail boom, tail
Oar system and fuel tank, the output shaft of the electromotor is connected respectively with the Timing Belt system and cooling system, the Timing Belt
The outfan of system is connected respectively with the multi-stage speed reducer and tail-rotor system, the output shaft of the multi-stage speed reducer and the rotation
Wing system connects, and the belt wheel of the Timing Belt system and cooling system is made by aluminium alloy, the deceleration of the multi-stage speed reducer
Gear is made up of nylon.
Preferably, also including mechanical stability augmentation system, the mechanical manoeuvring system and mechanical stability augmentation system are installed in described
On main shaft, the mechanical manoeuvring system and mechanical stability augmentation system are made by aluminium alloy.
Preferably, the fuselage includes wainscot, lower wall panels and connecting framework, and the wainscot and lower wall panels are fine by carbon
Dimension is made, and the connecting framework is made up of aluminium alloy.
Preferably, also including horizontal tail, horizontal tail mounting seat and vertical fin, the tail-rotor system includes tail-rotor casing, the tail-rotor
Casing is made up of aluminium alloy, and the horizontal tail mounting seat is made up of nylon, and the horizontal tail, vertical fin and tail boom are made by carbon fiber.
Preferably, the undercarriage and rotor system are made by aluminium alloy.
Preferably, also including steering wheel and steering wheel mounting seat, the steering wheel mounting seat is made up of nylon.
Preferably, also including reducer stent, the reducer stent is made up of aluminium alloy.
Preferably, the aluminium alloy is 6013 aluminium alloys.
Preferably, the nylon is nylon PA66.
Preferably, the fuselage is provided with lightening hole.
The fuselage of microlight-type depopulated helicopter of the present utility model adopts light-weight design, whole machine airframe structure to use in a large number
Nonmetallic composite, main screw lift is little, simple structure, transmission efficiency, effectively increases cruising time, improves load-carrying
Coefficient.
Description of the drawings
Fig. 1 is the microlight-type depopulated helicopter front view of this utility model embodiment；
Fig. 2 is the microlight-type depopulated helicopter top view of this utility model embodiment；
Fig. 3 is the microlight-type depopulated helicopter axonometric drawing of this utility model embodiment；
Fig. 4 is the Local map of the fuselage framework of the microlight-type depopulated helicopter of this utility model embodiment.
In figure, 1：Rotor system；2：Mechanical stability augmentation system；3：Mechanical manoeuvring system；4：Main shaft；5：Steering wheel；6：Timing Belt
System；7：Cooling system；8：Figure is passed；9：Photographic head；10：Electromotor；11：Undercarriage；12：Lever system；13：Multi-stage speed-reducing
Device；14：Gyroscope and installing rack；15：Number is passed；16：Tail boom；17：GPS location and horizontal tail；18：Vertical fin；19：Tail-rotor system；20：
Steering wheel and mounting seat；21：Fuel tank；22：Wainscot；23：Connecting framework；24：Lower wall panels.
Specific embodiment
Embodiment of the present utility model is described in further detail with reference to the accompanying drawings and examples.Following examples
For illustrating this utility model, but can not be used for limiting scope of the present utility model.
In description of the present utility model, it should be noted that unless otherwise clearly defined and limited, term " peace
Dress ", " connected ", " connection " should be interpreted broadly, for example, it may be fixedly connected, or be detachably connected, or integratedly
Connection；Can be mechanically connected, or electrically connect；Can be joined directly together, it is also possible to be indirectly connected to by intermediary,
It can be the connection of two element internals.For the ordinary skill in the art, above-mentioned art can be understood with concrete condition
Concrete meaning of the language in this utility model.
As Figure 1-4, the present embodiment microlight-type depopulated helicopter includes：Rotor system 1, mechanical stability augmentation system 2, machinery
Steerable system 3, main shaft 4, steering wheel 5, Timing Belt system 6, cooling system 7, figure pass 8, photographic head 9, electromotor 10, undercarriage 11,
Lever system 12, multi-stage speed reducer 13, gyroscope and installing rack 14, number pass 15, tail boom 16, GPS location and horizontal tail 17, vertical fin
18th, tail-rotor system 19, steering wheel and mounting seat 20, fuel tank 21, wainscot 22, connecting framework 23 and lower wall panels 24.Wherein, this enforcement
The concrete structure of depopulated helicopter, the annexation of each several part and operation principle of example etc. are with of the prior art nobody is straight
The machine of liter is similar, and here is omitted.
The output shaft of electromotor 10 is connected respectively with Timing Belt system 6 and cooling system 7, the outfan of Timing Belt system 6
It is connected with multi-stage speed reducer 13 and tail-rotor system 19 respectively, the output shaft of multi-stage speed reducer 13 is connected with rotor system 1；Specifically
, the output shaft of electromotor 10 installs the primary speed-down of synchronous pulley 6 transmission power, and drives cooling system 7, is that electromotor 10 is provided
Air-cooled, it is ensured that electromotor 10 is safe and reliable, the outfan of Timing Belt system 6 is connected respectively to multi-stage speed reducer 13 and tail-rotor system
System 19 enters action edge transmission, and the output shaft of multi-stage speed reducer 13 is connected with rotor system 1, and for whole machine lift is provided.Timing Belt system 6
Made by aluminium alloy with the belt wheel of cooling system 7, such as 6013 aluminium alloys, coordinate the Timing Belt can be with during transmitting torque
Mitigate weight, reduce vibrations, the reduction gearing of multi-stage speed reducer 13 is made up of nylon, meeting intensity and reducing weight demands
Meanwhile, material is corrosion-resistant, can self-lubricating.
Mechanical manoeuvring system 3 and mechanical stability augmentation system 2 are installed on main shaft 5, are controlled with lever system 12 by steering wheel 5
The mechanical stability augmentation system of system, it is ensured that aircraft flight is steady, mechanical manoeuvring system 3 and mechanical stability augmentation system 2 are made by aluminium alloy, such as
6013 aluminium alloys.
In the present embodiment, the fuselage of microlight-type depopulated helicopter can include：Wainscot 22, lower wall panels 24 and connecting framework
23, wainscot 22 and lower wall panels 24 are made by carbon fiber, while can also arrange in pairs or groups rubber, ABS, POM, LDPE, glass fibre
Deng connecting framework 23 is made up of aluminium alloy, such as 6013 aluminium alloys.
The transmission of tail-rotor system 19 is driven by the Timing Belt exported in reduction box, and Timing Belt is delivered to tail by tail boom 16
Oar main shaft, the angle of attack of tail-rotor blade is manipulated by the steering wheel 20 of tail boom end, the vertical fin 18 being fixed on rear side of tail-rotor, not only
Stabilization can be played, the normal work of aircraft tail-rotor blade in the way of takeoff and landing can be protected.Horizontal tail is by flat
Tail mounting seat is arranged on tail boom 16, and tail-rotor system 19 includes tail-rotor casing, and tail-rotor casing is made up of aluminium alloy, and such as 6013 aluminum are closed
Gold, horizontal tail mounting seat is made up of nylon, such as nylon PA66, and horizontal tail, vertical fin 18 and tail boom 16 are made by carbon fiber, not only can
Stabilization is played, the normal work of aircraft tail-rotor blade in the way of takeoff and landing can be also protected.
Undercarriage 11 and rotor system 1 are made by aluminium alloy, and steering wheel mounting seat is made up of nylon, such as nylon PA66, subtract
Fast device support is made up of aluminium alloy.
In the present embodiment, each load bearing component of the fuselage of microlight-type depopulated helicopter or support member can be all or part of
It is provided with lightening hole, such as wainscot 22, lower wall panels 24, connecting framework 23 and some passive casing, box body and tabulars
Part etc., to mitigate main screw lift.
In the present embodiment, whole machine employs in a large number light-weighted metal material and nonmetallic composite, wherein driving section
Part mostly is 6063 aluminum, nylon PA66, and material is corrosion-resistant, can self-lubricating, and reduction box be semi-closed structure, can avoid dust,
The materials such as sandstone are entered in reduction box, and destruction deceleration system transmission, fuselage framework easily adopts 6061 aluminum, 6063 aluminum, web, tail
The relatively low structure of beam pipe equivalent-load mostly is and adopts carbon fibre composite.
In the present embodiment, microlight-type depopulated helicopter provides power output when working by electromotor 10, is passed by Timing Belt
Dynamic to reduce electromotor 10 vibrations of itself, multi-stage speed reducer 13 is whole machine by the power drive rotor system 1 that Timing Belt transmit
Lift is provided.The transmission of whole machine power can be by transmitting mutually, according to machine between fuselage connecting framework 23, sidewall paneling, tail boom 16
The bearing distribution lightening core of body, and while large-area carbon fiber board mitigation weight, it is possible to reach support, connection and carry
Purpose.Light-weighted mechanical stability augmentation system 2 and mechanical manoeuvring system 3, regulating guarantee aircraft can be flown at any time by small-sized steering machine
Row is steady, can reach the dual weight loss effect of fuselage, control system.Travelling gear adopts nylon, and material is corrosion-resistant, Ke Zirun
It is sliding；Without the need for enclosed construction and lubricating arrangement.And reduction box is semi-closed structure, and the materials such as dust, sandstone can be avoided to enter into
In reduction box, destruction deceleration system transmission.
The fuselage of microlight-type depopulated helicopter of the present utility model adopts light-weight design, whole machine airframe structure to use in a large number
Nonmetallic composite, main screw lift is little, simple structure, transmission efficiency, effectively increases cruising time, improves load-carrying
Coefficient.
Embodiment of the present utility model in order to example and description for the sake of and be given, and be not exhaustively or will
This utility model is limited to disclosed form.Many modifications and variations are for the ordinary skill in the art aobvious and easy
See.It is, in order to more preferably illustrate principle of the present utility model and practical application, and to make this area to select and describe embodiment
Those of ordinary skill is it will be appreciated that this utility model is so as to designing the various embodiments with various modifications for being suitable to special-purpose.
Claims (10)
1. a kind of microlight-type depopulated helicopter, including fuselage, rotor system, mechanical manoeuvring system, main shaft, Timing Belt system, dissipate
Hot systems, electromotor, undercarriage, multi-stage speed reducer, tail boom, tail-rotor system and fuel tank, it is characterised in that the electromotor it is defeated
Shaft is connected respectively with the Timing Belt system and cooling system, and the outfan of the Timing Belt system multistage subtracts respectively with described
Fast device and tail-rotor system connect, and the output shaft of the multi-stage speed reducer be connected with the rotor system, the Timing Belt system with
The belt wheel of cooling system is made by aluminium alloy, and the reduction gearing of the multi-stage speed reducer is made up of nylon.
2. microlight-type depopulated helicopter according to claim 1, it is characterised in that described also including mechanical stability augmentation system
Mechanical manoeuvring system and mechanical stability augmentation system are installed on the main shaft, and the mechanical manoeuvring system and mechanical stability augmentation system are equal
It is made up of aluminium alloy.
3. microlight-type depopulated helicopter according to claim 2, it is characterised in that the fuselage includes wainscot, lower wall
Plate and connecting framework, the wainscot and lower wall panels are made by carbon fiber, and the connecting framework is made up of aluminium alloy.
4. microlight-type depopulated helicopter according to claim 3, it is characterised in that also including horizontal tail, horizontal tail mounting seat and
Vertical fin, the tail-rotor system includes tail-rotor casing, and the tail-rotor casing is made up of aluminium alloy, and the horizontal tail mounting seat is by nylon system
Into the horizontal tail, vertical fin and tail boom are made by carbon fiber.
5. microlight-type depopulated helicopter according to claim 4, it is characterised in that the undercarriage and rotor system by
Aluminium alloy is made.
6. microlight-type depopulated helicopter according to claim 5, it is characterised in that also including steering wheel and steering wheel mounting seat,
The steering wheel mounting seat is made up of nylon.
7. microlight-type depopulated helicopter according to claim 6, it is characterised in that described to subtract also including reducer stent
Fast device support is made up of aluminium alloy.
8. microlight-type depopulated helicopter according to claim 7, it is characterised in that the aluminium alloy is 6013 aluminium alloys.
9. microlight-type depopulated helicopter according to claim 7, it is characterised in that the nylon is nylon PA66.
10. the microlight-type depopulated helicopter according to any one of claim 1-9, it is characterised in that the fuselage sets
There is lightening hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621124486.0U CN206171802U (en) | 2016-10-14 | 2016-10-14 | Unmanned helicopter of microlight -type |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621124486.0U CN206171802U (en) | 2016-10-14 | 2016-10-14 | Unmanned helicopter of microlight -type |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206171802U true CN206171802U (en) | 2017-05-17 |
Family
ID=58677641
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621124486.0U Active CN206171802U (en) | 2016-10-14 | 2016-10-14 | Unmanned helicopter of microlight -type |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206171802U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107352014A (en) * | 2017-07-28 | 2017-11-17 | 珠海紫燕无人飞行器有限公司 | A kind of electric unmanned helicopter frame |
| CN108216555A (en) * | 2018-03-12 | 2018-06-29 | 珠海紫燕无人飞行器有限公司 | A kind of electric unmanned helicopter |
| CN112829954A (en) * | 2021-01-11 | 2021-05-25 | 林春 | Oil moves unmanned aerial vehicle engine protection device |
-
2016
- 2016-10-14 CN CN201621124486.0U patent/CN206171802U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107352014A (en) * | 2017-07-28 | 2017-11-17 | 珠海紫燕无人飞行器有限公司 | A kind of electric unmanned helicopter frame |
| CN107352014B (en) * | 2017-07-28 | 2023-10-31 | 珠海紫燕无人飞行器有限公司 | Electric unmanned helicopter frame |
| CN108216555A (en) * | 2018-03-12 | 2018-06-29 | 珠海紫燕无人飞行器有限公司 | A kind of electric unmanned helicopter |
| CN112829954A (en) * | 2021-01-11 | 2021-05-25 | 林春 | Oil moves unmanned aerial vehicle engine protection device |
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