CN209427011U - A kind of helicopter - Google Patents
A kind of helicopter Download PDFInfo
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- CN209427011U CN209427011U CN201822272857.5U CN201822272857U CN209427011U CN 209427011 U CN209427011 U CN 209427011U CN 201822272857 U CN201822272857 U CN 201822272857U CN 209427011 U CN209427011 U CN 209427011U
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Abstract
The utility model belongs to gyroplane technical field, it is related to a kind of helicopter, including fuselage, engine, main rotor body, propulsive mechanism, tail vane and undercarriage, it is characterized by: the main rotor body includes the main shaft of rolling assembling, the upper end of main shaft is equipped with main rotor by variable-distance rotor nose assembly, the lower end of main shaft is connected by the main speed reduction box of main clutch and engine, the propulsive mechanism includes two angle gear-boxes being symmetrically mounted at left and right sides of fuselage on bracket, the power intake of two corners gear-box passes through the main speed reduction box transmission connection of the transmission shaft component and engine that are correspondingly arranged respectively, variable-distance propeller component is separately installed on the power output shaft at two corners gear-box rear portion.Gyroplane can be taken off in the utility model with VTOL, gyroplane, and required site area is small, gyroplane use scope is wide.
Description
Technical field
The utility model relates to a kind of gyroplanes, belong to gyroplane technical field, more specifically, the utility model relates to
A kind of helicopter.
Background technique
Known aircraft has fixed wing aircraft, helicopter, tilt wing aircraft (helicopter+fixed-wing), autogyro,
Autogyro refers to " aircraft " for being provided lift with unpowered rotor, being overweighted air.Autogyro mainly wraps
Including rack and fuselage, rack are the skeletons of gyroplane, and other component is direct or indirect to be mounted on the rack, autogyro machine
As open and closed.It provides thrust by propulsion device to advance, propulsion device has propeller and two kinds of jet.The prior art
In autogyro runway takeoff is necessarily provided, provide the wind blows that head on to rotor, make autorotation and lift
Increase, this needs the place of larger area taking off for gyroplane, limits the use scope of gyroplane；It is in the prior art
Helicopter, which is able to achieve, to take off vertically, but when helicopter flight, feathering system, main reducing gear are being run always, increases fuel
Consumption, work noise is big, safety coefficient is low, and helicopter does not have the flight performance of gyroplane mode, does not have gyroplane one yet
The excellent security performance of sample.
Therefore, in order to reduce site area required when gyroplane takes off, increase the use scope of gyroplane, this is practical new
Type changes the mode of taking off of gyroplane, proposes a kind of helicopter.
Utility model content
Based on the above technical problem, the utility model provides a kind of helicopter, to solve previous gyroplane
The technical problem that the required site area that takes off is big, gyroplane use scope is limited.
In order to solve the above technical problems, the technical solution adopted in the utility model is as follows:
A kind of helicopter, including fuselage, engine, main rotor body, propulsive mechanism, tail vane and undercarriage, it is described
Main rotor body includes the main shaft of rolling assembling, and the upper end of main shaft is equipped with main rotor by variable-distance rotor nose assembly, main
The lower end of axis is connected by the main speed reduction box of main clutch and engine, and the propulsive mechanism includes two and is symmetrically mounted on fuselage
Angle gear-box on the bracket of the left and right sides, the power intake of two corners gear-box pass through respectively the transmission shaft component that is correspondingly arranged with
The main speed reduction box of engine is sequentially connected, and variable-distance propeller is separately installed on the power output shaft at two corners gear-box rear portion
Component.
The variable-distance rotor nose assembly includes the rotor head that main shaft upper end is fixedly mounted, and the main rotor can turn
Dynamic is assemblied on rotor head, and pitch component is equipped with below rotor head, and pitch component lower part passes through
First connecting rod component is connected with main rotor steering engine, and the top of the pitch component is corresponding with main rotor by second connecting rod component
Transmission connection.
The pivot center of the power output shaft of the two corners gear-box is parallel to each other and the rotation with the main shaft simultaneously
Axial space is vertical.
Propulsion clutch is additionally provided between the transmission shaft component and engine main speed reduction box.
In conclusion by adopting the above-described technical solution, the beneficial effects of the utility model are:
The helicopter of the utility model has had both the excellent performance of conventional helicopters and traditional autogyro, is rising
When flying and landing, main rotor body can make its taking off vertically as conventional helicopters by engine offer power and drop
It falls, and the variable-distance propeller component of fuselage two sides can be by adjusting pitch, production when making fuselage that main rotor body be overcome to rotate
Raw torque guarantees fuselage stability, thus this helicopter required site area that takes off is small, to increase rotor
The use scope of machine；Meanwhile the helicopter of the utility model can cut off after take off main rotor body and engine it
Between be connected by power, so that main rotor body is provided the lift of aircraft as traditional autogyro, and utilize fuselage
The variable-distance propeller component of two sides, which works at the same time, provides aircraft forward power, generation when so as to be significantly reduced flight
Noise, reduce flight energy consumption, and substantially increase the safety of aircraft.
Detailed description of the invention
Fig. 1 is the perspective view of the utility model helicopter；
Fig. 2 is the main view that the utility model goes straight up to rotary-wing transmission mechanism.
Marked in the figure: 1- fuselage；2- engine；3- main rotor body；4- propulsive mechanism；5- undercarriage；6- tail vane；30-
Main shaft；31- rotor head；32- paddle；33- pitch component；34- first connecting rod component；35- main rotor steering engine；36- second
Link assembly；40- bracket；The angle 41- gear-box；42- variable-distance propeller component；43- transmission shaft component.
Specific embodiment
The utility model will be further described below with reference to the accompanying drawings.The embodiments of the present invention includes but unlimited
In the following example.
The specific structure of the helicopter of the utility model is as shown in Figure 1 and Figure 2, mainly by fuselage 1, engine 2,
Main rotor body 3, propulsive mechanism 4, undercarriage 5 and more than 6 part of tail vane composition, main rotor body 3 are installed on the top of fuselage 1,
It includes main shaft 30, and the upper end of main shaft 30 is equipped with main rotor 32 by variable-distance rotor nose assembly, and the lower end of main shaft 20 is logical
The main speed reduction box for crossing main clutch 37 and engine 2 is sequentially connected, wherein variable-distance rotor nose assembly includes being installed on main shaft
The rotor head 31 of 30 upper ends, a pair of of main rotor 32 is rotatably mounted on the rotor head 31, under rotor head 31
Side is equipped with pitch component 33, and the lower part of the pitch component 33 is connected with main rotor steering engine by first connecting rod component 34
35, the top of the pitch component 33 passes through the transmission connection corresponding with a pair of of main rotor 32 of second connecting rod component 36.Propulsive mechanism 4
The angle gear-box 41 being symmetrically mounted on 1 left and right sides bracket 40 of fuselage including two, the power intake of two corners gear-box 41
It is sequentially connected respectively by the main speed reduction box of the transmission shaft component 43 and engine 2 that are correspondingly arranged, at 41 rear portion of two corners gear-box
Power output shaft on be separately installed with variable-distance propeller component 42.The rotation axis of the power output shaft of the two corners gear-box 41
Line is parallel to each other and while the pivot center spatial vertical with main shaft 30.In the main speed reduction box of transmission shaft component 43 and engine 2
Between be additionally provided with promote clutch (not regarded out in figure).
When taking off or landing, main clutch 37 is attracted the helicopter of the utility model, and the power of engine is passed
It is delivered on main shaft 30,32 active rotation of main rotor is driven by main shaft 30, and main rotation is adjusted by variable-distance rotor nose assembly
The wing always away from, so that main rotor 32 is generated the similar the same lift of conventional helicopters under the drive of engine, meanwhile, adjustment promotes
Pitch in mechanism between two variable-distance propeller components 42, to make to generate not between two variable-distance propeller components 42
Same thrust forms it into the work of similar conventional helicopters tail-rotor using the thrust difference between two variable-distance propeller components 42
With the reaction torque that the rotation of Lai Pingheng main rotor body 3 generates, to guarantee stability of the fuselage when taking off or landing.At this
After the helicopter of utility model is taken off, when aircraft flying speed be greater than speed per hour 70Km after, pilot control operating stick to
Reduce while back stay throttle and main rotor body always away from main rotor face bottom is in state time control windward after aircraft new line
Main clutch 37 processed separates, and the power cut off between engine 2 and main shaft 30 transmits, and main rotor body 3 is advanced using aircraft to be produced
Raw Wind power propelling enters spin states, meanwhile, the positive propulsion simultaneously of two variable-distance propeller components 42 is manipulated, at this point, hair
The power of motivation 2 is fully allocated to two variable-distance propeller components 42 and aircraft is pushed to move ahead, and aircraft is completely into rotation at this time
Gyroplane mode is flown.
In above-described embodiment, the variable-distance rotor nose assembly and two variable-distance spirals of main rotor body displacement are controlled
Pitch-changing mechanism in paddle component can use existing mature technology, for example, variable-distance rotor nose assembly can use it is practical
The elevating control group structure or utility model patent open file recorded in new patent open file CN2324062Y
The kind unmanned plane rotor mechanism recorded in CN207917150U；And the pitch-changing mechanism in two variable-distance propeller components can be used
The pitch-changing mechanism of conventional helicopters tail-rotor, such as nobody is straight for one kind disclosed in utility model patent open file CN205098462U
Tail rotary wing changing is risen away from linkage mechanism and equipped with its unmanned plane.
It is as described above the embodiments of the present invention.Design parameter in above-described embodiment and embodiment be only for
The utility model verification process of clear statement utility model people, not to limit the scope of patent protection of the utility model,
The scope of patent protection of the utility model is still subject to the claims, all specifications with the utility model and attached
The variation of equivalent structure made by figure content, similarly should be included in the protection scope of the utility model.
Claims (4)
1. a kind of helicopter, including fuselage, engine, main rotor body, propulsive mechanism, tail vane and undercarriage, feature
Be: the main rotor body includes the main shaft of rolling assembling, and the upper end of main shaft is equipped with by variable-distance rotor nose assembly
The lower end of main rotor, main shaft is connected by the main speed reduction box of main clutch and engine, and the propulsive mechanism includes two symmetrical
It is mounted on the angle gear-box at left and right sides of fuselage on bracket, the power intake of two corners gear-box passes through the biography being correspondingly arranged respectively
The transmission connection of the main speed reduction box of moving axis component and engine, being separately installed on the power output shaft at two corners gear-box rear portion can
Variable-pitch propeller component.
2. a kind of helicopter according to claim 1, it is characterised in that: the variable-distance rotor nose assembly packet
The rotor head that main shaft upper end is fixedly mounted is included, the main rotor is rotatably mounted on rotor head, in rotor head
Lower section is equipped with pitch component, and pitch component lower part is connected with main rotor steering engine by first connecting rod component, described
The top of pitch component passes through the transmission connection corresponding with main rotor of second connecting rod component.
3. a kind of helicopter according to claim 1, it is characterised in that: the power output of the two corners gear-box
The pivot center of axis is parallel to each other and while the pivot center spatial vertical with the main shaft.
4. a kind of helicopter according to claim 1, it is characterised in that: in the transmission shaft component and mobilize owner
Propulsion clutch is additionally provided between reduction gearbox.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822272857.5U CN209427011U (en) | 2018-12-29 | 2018-12-29 | A kind of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822272857.5U CN209427011U (en) | 2018-12-29 | 2018-12-29 | A kind of helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209427011U true CN209427011U (en) | 2019-09-24 |
Family
ID=67975124
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822272857.5U Active CN209427011U (en) | 2018-12-29 | 2018-12-29 | A kind of helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209427011U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109466751A (en) * | 2018-12-29 | 2019-03-15 | 河南三和航空工业有限公司 | A kind of helicopter |
-
2018
- 2018-12-29 CN CN201822272857.5U patent/CN209427011U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109466751A (en) * | 2018-12-29 | 2019-03-15 | 河南三和航空工业有限公司 | A kind of helicopter |
| CN109466751B (en) * | 2018-12-29 | 2024-02-06 | 河南三和航空工业有限公司 | Helicopter gyroplane |
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