CN206502023U - A kind of birotary engine is laid out small-sized unmanned helicopter - Google Patents
A kind of birotary engine is laid out small-sized unmanned helicopter Download PDFInfo
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- CN206502023U CN206502023U CN201720162096.0U CN201720162096U CN206502023U CN 206502023 U CN206502023 U CN 206502023U CN 201720162096 U CN201720162096 U CN 201720162096U CN 206502023 U CN206502023 U CN 206502023U
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Abstract
The utility model is related to machine design and manufacture field, specifically related to a kind of birotary engine is laid out small-sized unmanned helicopter, it includes fuselage girder, the fuselage girder right-hand member is connected with vertical fin, rotary engine and gearbox are installed on the fuselage girder, the rotary engine is connected with gearbox by attachment means, Servo-controller is provided with the gear-box case, clutch end is outer shaft and interior axle on the gearbox, lower propeller hub is connected with the outer shaft, propeller hub is connected with the interior axle, the lower propeller hub is connected with lower rotor, the upper propeller hub is connected with rotor, interior axle rotates in opposite directions to drive upper rotor to rotate in opposite directions with lower rotor with outer shaft, power set are used as using two New rotor engines, engine is left and right symmetrically arranged on rotor axis, it can solve to increase the technical problem of load-carrying commercial, improve flight safety, it is unlikely to cause machine to ruin accident, it is worthy to be popularized.
Description
Technical field
The utility model is related to machine design and manufacture field, and in particular to a kind of birotary engine layout is small-sized coaxial
Depopulated helicopter.
Background technology
At present, known small-sized unmanned helicopter is by dynamical system, fuselage platform, transmission system, manipulation and rotor
System, fuselage cover etc. are constituted, and because rotor system is using coaxial positive and negative double-deck rotor system, is eliminated tail-rotor, are made it have contracting
The characteristics of short fuselage length and lifting lifting capacity, small-sized unmanned helicopter engine system uses separate unit under normal circumstances
, installed in fore-body, there is both sides in complete machine layout in piston gasoline engine：One is piston type gasoline engine
The system of machine determines that power-weight ratio (abbreviation power to weight ratio) is smaller, and comparatively engine own wt is larger, the result is that
The own wt of depopulated helicopter complete machine is increased, makes its load-carrying commercial no more than 1/3,260 kilograms fly weights of total take-off weight
Measure commercial transport be no more than 85 kilograms, two be engine arrangement in front of fuselage and engine weight weight volume it is larger so that before fuselage
Weight is lacked of proper care afterwards, therefore is moved after load weight and can just be made main screw lift anterior-posterior balance, in the case where load-carrying is low, it is necessary to increase volume
Outer counterweight, causes to waste actual load-carrying and endurance efficiency, in addition in the case of the load (such as pesticide spraying) of weight change, such as
The whole load of fruit have been discharged with the time, body weight can be caused unbalance, and to prevent weight imbalance problem, actual load-carrying will be less than finger
Load-carrying is marked, separate unit piston gasoline engine complete machine flight safety coefficient is relatively low in addition, because dynamical system uses separate unit engine, if
Engine awing flame-out in flight for some reason, will cause aircraft accident.
Utility model content
For problem above, the utility model provides a kind of birotary engine and is laid out small-sized unmanned helicopter,
Using two New rotor engines as power set, engine is left and right symmetrically arranged on rotor axis, can solve to increase
Plus the technical problem of load-carrying commercial, reach and conventional load-carrying commercial is brought up to 1/2nd from 1/3rd of total take-off weight
Effect, while the problem of in-flight load weight change influence main screw lift is balanced can be solved.
To achieve these goals, the technical solution adopted in the utility model is as follows：A kind of birotary engine layout is small
Type unmanned helicopter, it includes fuselage girder, and the fuselage girder right-hand member is connected with vertical fin, the fuselage girder and installed
There are rotary engine and gearbox, the rotary engine is connected with gearbox by attachment means, the gear-box case
On to be provided with Servo-controller, the gearbox clutch end be to be connected with lower propeller hub, institute on outer shaft and interior axle, the outer shaft
State and propeller hub is connected with interior axle, the lower propeller hub is connected with lower rotor, the upper propeller hub is connected with rotor, interior axle and outer shaft
Rotate in opposite directions to drive rotor to rotate in opposite directions with lower rotor.
Further, the fuselage girder lower end is provided with foot stool.
Further, the upper propeller hub upper end is provided with trim tab system.
Further, the gearbox left end is provided with preceding fuel tank, and the gearbox right-hand member is provided with rear fuel tank, it is described before
Carburetor is provided between fuel tank and Servo-controller.
Further, it is provided with cooling water tank on the vertical fin.
The beneficial effects of the utility model：
The utility model is using two New rotor engines as power set, and engine left and right on rotor axis is right
Claim to install, can solve to increase the technical problem of load-carrying commercial, reach by conventional load-carrying commercial from the three of total take-off weight/
One brings up to 1/2nd effect, while the problem of in-flight load weight change influence main screw lift is balanced can be solved,
Small-sized unmanned helicopter load-carrying commercial increase, by heavy 80 kilograms of liftings published originally to 120 kg, unloaded or load-carrying dynamic change
In the case of complete machine can keep weight balancing, shut down if being happened suddenly in an engine flight, another engine can complete aircraft
It is urgent chase after drop, improve flight safety, it is unlikely to cause machine to ruin accident.
Brief description of the drawings
Fig. 1 is the utility model overall structure diagram；
Fig. 2 is the inside and outside axle construction schematic diagram of the utility model.
In figure marked as：Oar under 1- fuselage girders, 2- foot stools, 3- vertical fins, 4- outer shafts, 5- gearboxes, 6- Servo-controllers, 7-
Fuel tank, 14- rear fuel tanks, 15- before rotor under hub, the upper propeller hubs of 8-, 9-, the upper rotors of 10-, 11- interior axles, 12- trim tab systems, 13-
Carburetor, 16- cooling water tanks, 17- rotary engine, 18- attachment means.
Embodiment
In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, below in conjunction with accompanying drawing and implementation
Example, the utility model is further elaborated.It should be appreciated that specific embodiment described herein is only to explain
The utility model, is not used to limit the utility model.
Embodiment：
As depicted in figs. 1 and 2, a kind of birotary engine is laid out small-sized unmanned helicopter, and it includes fuselage girder
1, the right-hand member of fuselage girder 1 is connected with vertical fin 3, the fuselage girder 1 and is provided with rotary engine 17 and gearbox 5, institute
State rotary engine 17 with gearbox 5 by attachment means 18 to be connected, Servo-controller 6 be provided with the shell of gearbox 5,
Clutch end is to be connected with outer shaft 4 and interior axle 11, the outer shaft 4 in lower propeller hub 7, the interior axle 11 on the gearbox 5
Propeller hub 8 is connected with, the lower propeller hub 7 is connected with lower rotor 9, and the upper propeller hub 8 is connected with rotor 10, interior axle 11 and outer shaft
4 rotate in opposite directions to drive rotor 10 to rotate in opposite directions with lower rotor 9.
On above-described embodiment preferably, the lower end of fuselage girder 1 is provided with foot stool 2, well can park helicopter
On land, the stability of helicopter is added.
On above-described embodiment preferably, the upper upper end of propeller hub 8 is provided with trim tab system 12, can keep going straight up to well
The balance of machine.
On above-described embodiment preferably, the left end of gearbox 5 is provided with preceding fuel tank 13, and the right-hand member of gearbox 5 is set
There is rear fuel tank 14, carburetor 15 is provided between the preceding fuel tank 13 and Servo-controller 6, innage can be increased and improve helicopter
Flying distance and lifting capacity.
On above-described embodiment preferably, cooling water tank 16 is provided with the vertical fin 3, can be radiated well, it is ensured that hung down
The normal work of tail 3.
Based on above-mentioned, the utility model is using two New rotor engines as power set, and engine is in rotor shaft
It is left and right symmetrically arranged on line, can solves to increase the technical problem of load-carrying commercial, reaches conventional load-carrying commercial the fly weight from total
/ 3rd of amount bring up to 1/2nd effect, are put down while in-flight weight change loading effect main screw lift can be solved
The problem of weighing apparatus, small-sized unmanned helicopter load-carrying commercial increase, by heavy 80 kilograms of liftings published originally to 120 kg, unloaded or load
Complete machine can keep weight balancing in the case of weight dynamic change, be shut down if being happened suddenly in an engine flight, another engine
The urgent of aircraft can be completed and chase after drop, flight safety is improved, it is unlikely to cause machine to ruin accident.
Preferred embodiment of the present utility model is the foregoing is only, it is all at this not to limit the utility model
Any modifications, equivalent substitutions and improvements made within the spirit and principle of utility model etc., should be included in the utility model
Protection domain within.
Claims (5)
1. a kind of birotary engine is laid out small-sized unmanned helicopter, it is characterised in that：It includes fuselage girder, the machine
Body girder right-hand member, which is connected with vertical fin, the fuselage girder, is provided with rotary engine and gearbox, the rotary engine with
Gearbox is connected by attachment means, and power output on Servo-controller, the gearbox is provided with the gear-box case
Hold as outer shaft and interior axle, be connected with the outer shaft in lower propeller hub, the interior axle and be connected with propeller hub, the lower propeller hub is connected with
Lower rotor, the upper propeller hub is connected with rotor, and interior axle rotates in opposite directions to drive rotor and lower rotor with outer shaft
Rotate in opposite directions.
2. a kind of birotary engine according to claim 1 is laid out small-sized unmanned helicopter, it is characterised in that：Institute
State fuselage girder lower end and be provided with foot stool.
3. a kind of birotary engine according to claim 1 is laid out small-sized unmanned helicopter, it is characterised in that：Institute
State propeller hub upper end and be provided with trim tab system.
4. a kind of birotary engine according to claim 1 is laid out small-sized unmanned helicopter, it is characterised in that：Institute
State gearbox left end and be provided with preceding fuel tank, the gearbox right-hand member is provided with rear fuel tank, between the preceding fuel tank and Servo-controller
It is provided with carburetor.
5. a kind of birotary engine according to claim 1 is laid out small-sized unmanned helicopter, it is characterised in that：Institute
State and cooling water tank is provided with vertical fin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720162096.0U CN206502023U (en) | 2017-02-22 | 2017-02-22 | A kind of birotary engine is laid out small-sized unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720162096.0U CN206502023U (en) | 2017-02-22 | 2017-02-22 | A kind of birotary engine is laid out small-sized unmanned helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206502023U true CN206502023U (en) | 2017-09-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720162096.0U Active CN206502023U (en) | 2017-02-22 | 2017-02-22 | A kind of birotary engine is laid out small-sized unmanned helicopter |
Country Status (1)
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| CN (1) | CN206502023U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108945486A (en) * | 2018-08-04 | 2018-12-07 | 江苏东翼通用航空科技有限公司 | A kind of unmanned helicopter and its working method |
| WO2019137146A1 (en) * | 2018-01-15 | 2019-07-18 | 松芝机器人股份有限公司 | Uniaxial twin-rotor unmanned aerial-vehicle device, system having the device, and remote control method |
-
2017
- 2017-02-22 CN CN201720162096.0U patent/CN206502023U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019137146A1 (en) * | 2018-01-15 | 2019-07-18 | 松芝机器人股份有限公司 | Uniaxial twin-rotor unmanned aerial-vehicle device, system having the device, and remote control method |
| CN108945486A (en) * | 2018-08-04 | 2018-12-07 | 江苏东翼通用航空科技有限公司 | A kind of unmanned helicopter and its working method |
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