CN208915438U - A kind of composite wing aviation aircraft - Google Patents
A kind of composite wing aviation aircraft Download PDFInfo
- Publication number
- CN208915438U CN208915438U CN201821375356.3U CN201821375356U CN208915438U CN 208915438 U CN208915438 U CN 208915438U CN 201821375356 U CN201821375356 U CN 201821375356U CN 208915438 U CN208915438 U CN 208915438U
- Authority
- CN
- China
- Prior art keywords
- tensioning
- rotor
- fuselage
- wing
- driving wheel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Transmission Devices (AREA)
- Toys (AREA)
Abstract
The utility model discloses a kind of composite wing aviation aircrafts, include fuselage, be connected to fuselage side and symmetrically arranged left and right wing, fuselage is internally provided with flight controller, the rack of integrated plastotype is connected with above fuselage, the top of rack is provided with rotor, the tail portion of fuselage is provided with the propeller with the output axis connection of engine, and rotor passes through the output axis connection of clutch transmission and engine.The utility model includes rotor and fixed-wing, is controlled by drive control to rotor different phase and revolving speed, shortening take off apart from while, and improve flying speed and flight efficiency.
Description
Technical field
The utility model relates to field of aviation flight, specifically a kind of composite wing aviation aircraft.
Background technique
The mankind always never stop the pursuit of aircraft, since the 21th century, with the development of General Aviation,
The pattern of aircraft is more and more, and society is increasing to the demand of transatmospheric vehicle, will be used wider and wider, example
Such as: Aerial photography, agricultural plant protection, police tour, electric inspection process, geological prospecting, battlefield investigation, special reconnaissance, Material Transportation, sea
The fields such as empty Syndicating search.However, existing all purpose aircraft, generally comprises fixed-wing, helicopter, more rotors and tilting rotor
A few class aircraft such as machine, emphasis can only often select one both in low speed and high speed, flying speed range and voyage range compared with
It is small, thus application range is also relatively small.The shortcomings that being primarily present is as follows: 1. pairs of runways are more demanding, such as fixed-wing；2. empty
Middle engine is easy air crash, such as fixed-wing, helicopter, more rotors once stopping；3. cruising speed is lower, such as helicopter, more rotations
The wing, autogyro；4. a couple pilot has higher technical requirements, such as fixed-wing, helicopter.
Utility model content
The technical problem to be solved by the present invention is to provide a kind of composite wing aviation aircrafts, include rotor and fixation
The wing is controlled by drive control to rotor different phase and revolving speed, shortening take off apart from while, and improve flying speed
And flight efficiency.
The technical solution of the utility model are as follows:
A kind of composite wing aviation aircraft includes fuselage, is connected to fuselage side and symmetrically arranged left and right wing, institute
The fuselage stated is internally provided with flight controller, and the rack of integrated plastotype, the top setting of rack are connected with above fuselage
There is rotor, the tail portion of fuselage is provided with the propeller with the output axis connection of engine, and the rotor passes through clutch transmission machine
The output axis connection of structure and engine；The clutch transmission includes rotary-wing transmission belt, fixed conveyor axis, telescopic
Transmission shaft is respectively fixedly connected in the first driving wheel and the second driving wheel on fixed conveyor axis both ends and fixed respectively connects
The third driving wheel and the 4th driving wheel being connected on unequallength drivershaft both ends are fixedly connected on the output shaft of the engine
There is driving engine gear, rotor disk gear is fixedly connected on the rotor, the rotary-wing transmission belt is wound in hair
On motivation transmission gear and the first driving wheel, and the rotary-wing transmission belt carries out tensioning transmission by tensioning apparatus, described
Unequallength drivershaft bottom end third driving wheel and fixed conveyor axis on the second driving wheel be intermeshed, described is telescopic
Under transmission shaft elongation state, the 4th driving wheel on the unequallength drivershaft top is engaged with rotor disk gear, and described
Rotary damper, the tensioning of the telescoping drive mechanism, tensioning apparatus of the unequallength drivershaft are provided on rotor disk gear
Driving mechanism, the driving mechanism of rotary damper are attached realization control with flight controller.
The telescoping drive mechanism of the unequallength drivershaft selects telescopic cylinder, and unequallength drivershaft further includes having fixation
It is connected to the lower drive shaft of telescopic cylinder cylinder body bottom end, the third driving wheel is fixedly connected on lower drive shaft, stretch gas
The 4th driving wheel is fixedly connected on the piston rod that cylinder stretches out upwards, the flight controller is driven by telescopic cylinder
Dynamic device is connect with telescopic cylinder.
The tensioning driving mechanism of the tensioning apparatus selects tensioning cylinder, is connected with tensioning on the piston rod of tensioning cylinder
Wheel, the tensioning apparatus is located at the inner ring of rotary-wing transmission belt and tensioning wheel stretches to rotary-wing transmission belt, the flight control
Device processed is connect by tensioning cylinder driver with tensioning cylinder.
The rotary damper includes lifting cylinder and the dampened disk that is connected on lifting cylinder piston rod, described
Dampened disk is located at the underface of the rotor disk gear, and the flight controller passes through lifting cylinder driver and lifting air
Cylinder connection.
The composite wing aviation aircraft further includes that there are two the vertical fin for being set to fuselage rear side side, two vertical fin difference
Be fixedly connected by corresponding tail supporting rod with corresponding wing, and be connected with horizontal tail between two vertical fins, two vertical fins and
Undercarriage is provided on the bottom of fuselage.
The advantages of the utility model:
(1), highly-safe: since in flight course, rotor is in autonomous rotation status under the action of air-flow always, to be
Aircraft provides certain lift, awing if there is engine flame-out in flight or other mechanical breakdowns, as long as releasing pair
The limitation of rotor revolving speed, rotor can quickly be spun up, and provided more lift for aircraft, guaranteed its safe landing.
(2), landing is apart from short: in takeoff phase, engine provides power by clutch transmission for rotor, i.e., in cunning
Lift can be provided before race for aircraft, therefore distance of taking off is very short；In landing period, due to the rotation of rotor, aircraft can be with
It is landed with very low flying speed, and the angle by increasing rotor disk can increase considerably resistance, therefore landing distance
Also very short.
(3), cruising speed is big, voyage is remote: in the flight cruise stage, rotor rotates under the action of air-flow in autonomous,
Rotor revolving speed is reduced at this time, wing is the main source of lift, therefore flying speed is essentially close to fixed-wing (wing) aircraft,
Speed is big, voyage is remote.
(4), structure is simple, at low cost: the utility model composite wing aviation aircraft is simple relative to helicopter structure, does not have
There are tail-rotor transmission system, retarder, auto-bank unit and main-rotor drive system, so not only price is low, but also failure rate
Low, furthermore working service is simple and convenient, and maintenance cost is low.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model;
Fig. 2 is the structural schematic diagram for the clutch transmission that the utility model is connected between engine and rotor;
Fig. 3 is the structural schematic diagram of the utility model tensioning apparatus.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
See that Fig. 1, a kind of composite wing aviation aircraft include fuselage 1, are connected to 1 side of fuselage and a symmetrically arranged left side
Starboard wing 2, fuselage 1 are internally provided with flight controller, and the top of fuselage 1 is connected with the rack 3 of integrated plastotype, rack 3
Top is provided with rotor 4, and there are two vertical fin 5, two vertical fins 5 to pass through corresponding tail supporting rod 6 respectively for the setting of 1 rear side side of fuselage
It is fixedly connected with corresponding wing 2, and is connected with horizontal tail 7 between two vertical fins 5, be all provided on the bottom of two vertical fins 5 and fuselage 1
It is equipped with undercarriage 8, the tail portion of fuselage 1 is provided with the propeller 9 with the output axis connection of engine 10, and rotor 4 is passed by clutch
The output axis connection of motivation structure and engine 10；
See that Fig. 2, clutch transmission include rotary-wing transmission belt 11, fixed conveyor axis 12, unequallength drivershaft, difference
It the first driving wheel 15 and the second driving wheel 16 that are fixedly connected on fixed conveyor axis both ends and is respectively fixedly connected in flexible
Third driving wheel 17 and the 4th driving wheel 18 in formula both ends of the drive shaft are fixedly connected with engine on the output shaft of engine 10
Transmission gear 19 is fixedly connected with rotor disk gear 20 on rotor 4, and rotary-wing transmission belt 11 is wound in driving engine gear 20
On the first driving wheel 15, and rotary-wing transmission belt 11 carries out tensioning transmission by tensioning apparatus, unequallength drivershaft perpendicular to
Fixed conveyor axis 12, the third driving wheel 17 of unequallength drivershaft bottom end and the second driving wheel 16 on fixed conveyor axis 12 are mutual
It engaging, under unequallength drivershaft elongation state, the 4th driving wheel 18 on unequallength drivershaft top is engaged with rotor disk gear 20,
And rotary damper is provided on rotor disk gear 20；
Wherein, the telescoping drive mechanism of unequallength drivershaft selects telescopic cylinder 13, and unequallength drivershaft further includes having admittedly
Surely it is connected to the lower drive shaft 14 of 13 cylinder body bottom end of telescopic cylinder, third driving wheel 17 is fixedly connected on lower drive shaft 14, stretches
The 4th driving wheel 18 is fixedly connected on the piston rod that contracting cylinder 13 stretches out upwards, flight controller passes through telescopic cylinder driver
It is connect with telescopic cylinder 13；See Fig. 3, the tensioning driving mechanism of tensioning apparatus selects tensioning cylinder 21, the piston of tensioning cylinder 21
Tensioning wheel 22 is connected on bar, tensioning apparatus is located at the inner ring of rotary-wing transmission belt 11 and tensioning wheel 22 stretches to rotary-wing transmission belt
11, flight controller passes through tensioning cylinder driver and tensioning gas, 21 connections；Rotary damper includes lifting cylinder 23 and connects
The dampened disk 24 being connected on 23 piston rod of lifting cylinder, dampened disk 24 are located at the underface of rotor disk gear 20, flight controller
It is connect by lifting cylinder driver with lifting cylinder 23.
A kind of flight control method of composite wing aviation aircraft has specifically included following several flight rate-determining steps:
(1), when taking off, flight controller controls unequallength drivershaft elongation, so that the 4th driving wheel 18 and rotor disk tooth
20 engagement of wheel, while flight controller control tensioning apparatus is tensioned rotary-wing transmission belt 11, at this point, 10 output end of transmitter is dynamic
On the one hand power is transferred to propeller 9 and is rotated, be on the other hand transferred to rotor 4,10 band of engine by clutch transmission
Dynamic rotor 4 starts sliding race after rotating to certain revolving speed, while flight controller control unequallength drivershaft and tensioning apparatus reset,
So that the 4th driving wheel 18 is separated with rotor disk gear 20, rotary-wing transmission belt 11, which loosens, to be driven, i.e., rotor 4 is detached from
The transmission of engine 10, the rotor 4 of aircraft is independently rotated under the action of air-flow at this time, and aircraft realizes that short distance rises at this time
Fly even richochet, so as to shorten distance of taking off；
(2), when entering cruising phase after taking off, actively increase flying speed, while flight controller control rotation resistance
Buddhist nun's device carries out speed limit to rotor disk gear 20, and (i.e. lifting cylinder 23 drives dampened disk 24 to move up and resists rotor disk gear 20 and limit it
Rotation), 4 revolving speed of rotor is reduced, the lift of cruising phase is largely provided by wing 2, and aircraft is made to keep flying at high speed；
(3), before landing, flying speed is actively reduced, flight controller controls clutch transmission and is in separation shape
State, while limitation of the rotary damper to 4 revolving speed of rotor is released, 4 revolving speed of rotor is gradually increased, and the main source of airplane ascensional force turns
Become rotor 4, to keep lower flying speed, and adjusts rotor front face area and effectively increase rotor resistance, realize short distance
From landing；
(4), in the flight cruise stage, when flame-out in flight occurs in engine 10, flight controller releases damping due to rotation
Limitation of the device to 4 revolving speed of rotor, rotor 4 will carry out independently rotating to improve revolving speed under the action of air-flow, become aircraft
The main source of lift realizes that the safety and steady of aircraft lands.
While there has been shown and described that the embodiments of the present invention, for the ordinary skill in the art,
It is understood that these embodiments can be carried out with a variety of variations in the case where not departing from the principles of the present invention and spirit, repaired
Change, replacement and variant, the scope of the utility model is defined by the appended claims and the equivalents thereof.
Claims (5)
1. a kind of composite wing aviation aircraft includes fuselage, is connected to fuselage side and symmetrically arranged left and right wing, special
Sign is: the fuselage is internally provided with flight controller, and the rack of integrated plastotype is connected with above fuselage, rack
Top is provided with rotor, and the tail portion of fuselage is provided with the propeller with the output axis connection of engine, the rotor by from
Close the output axis connection of transmission mechanism and engine；The clutch transmission includes rotary-wing transmission belt, fixed conveyor
Axis, is respectively fixedly connected in the first driving wheel and the second driving wheel, Yi Jifen on fixed conveyor axis both ends unequallength drivershaft
The third driving wheel and the 4th driving wheel not being fixedly connected on unequallength drivershaft both ends, on the output shaft of the engine
It is fixedly connected with driving engine gear, rotor disk gear, the rotary-wing transmission belt are fixedly connected on the rotor
It is wound on driving engine gear and the first driving wheel, and the rotary-wing transmission belt carries out tensioning biography by tensioning apparatus
Dynamic, the third driving wheel of the unequallength drivershaft bottom end and the second driving wheel on fixed conveyor axis are intermeshed, described
Unequallength drivershaft elongation state under, the 4th driving wheel on the unequallength drivershaft top is engaged with rotor disk gear,
And rotary damper is provided on the rotor disk gear, telescoping drive mechanism, the tensioning dress of the unequallength drivershaft
Tensioning driving mechanism, the driving mechanism of rotary damper set are attached realization control with flight controller.
2. a kind of composite wing aviation aircraft according to claim 1, it is characterised in that: the unequallength drivershaft
Telescoping drive mechanism selects telescopic cylinder, and unequallength drivershaft further includes having the biography down for being fixedly connected on telescopic cylinder cylinder body bottom end
Moving axis is fixedly connected with the third driving wheel on lower drive shaft, is fixedly connected on the piston rod that telescopic cylinder stretches out upwards
There is the 4th driving wheel, the flight controller is connect by telescopic cylinder driver with telescopic cylinder.
3. a kind of composite wing aviation aircraft according to claim 1, it is characterised in that: the tensioning of the tensioning apparatus
Driving mechanism selects tensioning cylinder, and tensioning wheel is connected on the piston rod of tensioning cylinder, and the tensioning apparatus is located at rotor biography
The inner ring and tensioning wheel of dynamic belt stretch to rotary-wing transmission belt, and the flight controller passes through tensioning cylinder driver and tensioning
Cylinder connection.
4. a kind of composite wing aviation aircraft according to claim 1, it is characterised in that: the rotary damper includes
The dampened disk for having lifting cylinder and being connected on lifting cylinder piston rod, the dampened disk are located at the rotor disk gear
Underface, the flight controller are connect by lifting cylinder driver with lifting cylinder.
5. a kind of composite wing aviation aircraft according to claim 1, it is characterised in that: the composite wing aviation flight
Device further include there are two being set to the vertical fin of fuselage rear side side, two vertical fins pass through respectively corresponding tail supporting rod with it is corresponding
Wing is fixedly connected, and horizontal tail is connected between two vertical fins, is provided with undercarriage on the bottom of two vertical fins and fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821375356.3U CN208915438U (en) | 2018-08-24 | 2018-08-24 | A kind of composite wing aviation aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821375356.3U CN208915438U (en) | 2018-08-24 | 2018-08-24 | A kind of composite wing aviation aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208915438U true CN208915438U (en) | 2019-05-31 |
Family
ID=66703973
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821375356.3U Active CN208915438U (en) | 2018-08-24 | 2018-08-24 | A kind of composite wing aviation aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208915438U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050908A (en) * | 2018-08-24 | 2018-12-21 | 安徽云翼航空技术有限公司 | A kind of composite wing aviation aircraft and its flight control method |
-
2018
- 2018-08-24 CN CN201821375356.3U patent/CN208915438U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109050908A (en) * | 2018-08-24 | 2018-12-21 | 安徽云翼航空技术有限公司 | A kind of composite wing aviation aircraft and its flight control method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4469294A (en) | V/STOL Aircraft | |
| US10696391B2 (en) | Extended range quad tiltrotor aircraft | |
| US6513752B2 (en) | Hovering gyro aircraft | |
| CN202754143U (en) | Rotating engine vertical take-off and landing aircraft | |
| CN204660020U (en) | One is distributed independently controls multi-rotor aerocraft | |
| CN103395492B (en) | A kind of unpowered short take-off and landing (STOL) unmanned plane turning rotor | |
| RU2629475C1 (en) | High-speed turbofan combined helicopter | |
| CN103935517B (en) | Aircraft | |
| CN103552686B (en) | A kind of compound type duct aerial reconnaissance machine people | |
| CN103057702B (en) | Jet-propelled type helicopter with rotating wings | |
| CN201419624Y (en) | Double-bypass propeller aerocar capable of vertical taking off and landing | |
| RU2673933C1 (en) | Gyroplane | |
| CN109050908A (en) | A kind of composite wing aviation aircraft and its flight control method | |
| CN105711831B (en) | The fixed-wing unmanned plane of VTOL | |
| CN102490897A (en) | Multi-driving embedded rotor manned helicopter | |
| RU2609856C1 (en) | Fast-speed convertible compound helicopter | |
| CN206826927U (en) | Mixed layout unmanned plane | |
| CN208915438U (en) | A kind of composite wing aviation aircraft | |
| CN103832584B (en) | A kind of with fixed wing, collapsible empennage to switch rotor aircraft | |
| US3458160A (en) | Rotating-wing aircraft | |
| RU130951U1 (en) | RUNWING AIRCRAFT WITH AUTOMOTIVE ROLLING SCREW AND WING | |
| RU2618832C1 (en) | Multirotor high-speed combined helicopter | |
| US2230370A (en) | Aircraft | |
| UA94184U (en) | Unmanned convertiplane | |
| CN105438464B (en) | A kind of aircraft and its control method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |