CN107089323B

CN107089323B - A kind of aircraft rotor driver and aircraft

Info

Publication number: CN107089323B
Application number: CN201610087474.3A
Authority: CN
Inventors: 徐丛逸
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-02-17
Filing date: 2016-02-17
Publication date: 2019-07-19
Anticipated expiration: 2036-02-17
Also published as: CN107089323A

Abstract

The invention discloses a kind of aircraft rotor driver and aircraft.Aircraft rotor driver includes driving track, rotating mechanism and blade.Driving rail section is band cavity annular, and inner wall trench is wound with several coil groups, forms the primary of line-like driving motor, generate magnetic field after energization；Rotating mechanism includes driving unit and flexible connector, and interval is connected.The secondary of driving unit line-like driving motor generates circumferential driving force under track magnetic fields.Flexible connector can multidirectional deformation, allow rotating mechanism moved along the track of variable curvature.Magnet is set on driving unit, the suspended motion in track magnetic field；Blade is mounted on driving unit, is moved along driving track and is generated aerodynamic force.The invention provides a kind of aircraft rotor driver, blade can be moved along non-circular orbit, and blade average length pneumatic efficiency is high, aerodynamic arrangement's design is easy, and provide new selection for new configuration rotor craft.

Description

A kind of aircraft rotor driver and aircraft

Technical field

The present invention relates to vehicle technology fields, more particularly to a kind of aircraft rotor driver and aircraft.

Background technique

Rotor (blade) technology is mainly used in helicopter and propeller aero, wherein the most with the application of helicopter Extensively.

Lifting airscrew is generally made of propeller hub and blade, and propeller hub center is connected in a live spindle, blade connection On propeller hub support arm, blade the piece number is several to be differed.

Helicopter drives rotor blade rotation by driving spindle, and blade and air occur speed of related movement and generate liter Power.It is big close to blade tip radius in certain angular velocity of rotation, it is big with air relative linear velocity and lift is big.It is logical The direction for crossing control rotor disk lift flies winged, rear winged and left and right side before helicopter.

Lifting airscrew revolving speed is generally constant, and the maximum line velocity of blade tip is subject to certain restrictions.Mainly with it is preceding rapidly Degree superposition after, to prevent from causing resistance to sharply increase close to velocity of sound, blade tip linear velocity be generally defined in 220 meter per seconds with It is interior.When hovering, blade tip linear velocity is preferred with 160 meter per seconds or so.By adjusting the angle of attack of blade or adjusting blade revolving speed, It can control the size of lift.

Currently, the in-service helicopter in the whole world be nearly all more than drive mode, i.e., rotor is passed through by a main shaft Hub driving blade rotates and generates lift.The difference is that the difference on configuration, specifically includes that single rotor magnetic tape trailer paddle, DCB Specimen Cross-arranging type, DCB Specimen lap siding and DCB Specimen close coupled type.Wherein most commonly seen with single rotor magnetic tape trailer paddle, quantity is most, referred to as For pure helicopter.

It has the drawback that in the prior art

1, the blade of traditional rotor is long, almost to blade tip by rotation center position (about 10%).Therefore, blade rotates When, it is very big along radial direction (10% to 100%) and the relative velocity difference of air, cause aerodynamic force effect gap big；

2, the blade linear velocity close to blade root part is low, low efficiency, high close to blade tip partial linear velocity, is easy to produce shock wave Total pneumatic efficiency of stall, a piece of blade is low；

3, the aerodynamic configuration for having a relative efficiency high the blade of different rotating speeds is adaptation blade root between blade tip Large span rotation speed change, blade aerodynamic shape select and radially distribute rationally it is difficult；

4, all blades can only surround a center rotating, determine that blade swept area is disk, cause helicopter Vertical, horizontal size it is suitable.

Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.

Summary of the invention

Overcome the purpose of the present invention is to provide a kind of aircraft with rotor driver or is at least mitigated in the prior art At least one drawbacks described above.

To achieve the above object, the present invention provides a kind of aircraft rotor driver, aircraft rotor driver packet Include: driving track, the driving track includes force transmission mechanism and track framework, is provided with annular receiving in the track framework Slot, the opening of the annular receiving groove are oriented back to annular center direction；Rotating mechanism, the rotating mechanism are arranged described In annular receiving groove, the rotating mechanism and the force transmission mechanism are sequentially connected；Blade, the quantity of the blade are multiple, and It is uniformly mounted on the rotating mechanism, and extends at each blade spin rotation mechanism, and stretched out from the opening of annular receiving groove； Wherein, the force transmission mechanism can drive the rotating mechanism to move around the driving track；Described in the rotating mechanism drives Blade movement, so that blade be made to generate power.

Preferably, the driving track is multiple, and each driving track is overlapped mutually setting and is connected with each other, the rotation The quantity of mechanism is equal with the driving quantity of track, and the annular of a driving track is arranged in each rotating mechanism In holding tank；The blade is separately positioned on different rotating mechanisms.

Preferably, the force transmission mechanism is electromagnetic coil, and the electromagnetic coil is connect with the power supply unit of the aircraft, Magnetic field is generated when the electromagnetic coil is powered；Conductor and magnet are provided on the rotating mechanism, when the electromagnetic coil When generating magnetic field, the conductor, which generates induced current, moves rotating mechanism around the driving track to generate motoricity.

Preferably, the rotating mechanism includes the driving unit that multiple head and the tail are mutually connected, wherein setting on several driving units It is equipped with mounting portion, which is known as mounting portion driving unit, other driving units are known as ordinary drive units, each Mounting portion on mounting portion driving unit is for installing a blade；Any one mounting portion driving unit is immediate another with its The quantity for the ordinary drive units that one mounting portion driving unit is separated by is equal；Pass through elasticity between each driving unit Connection unit connection.

Preferably, the driving unit includes conductor body and the magnet that conductor body edge is arranged in.

Preferably, the conductor body is cuboid or square, and its inner hollow, the magnet setting are led described On the angle of body ontology.

Preferably, the aircraft further comprises with rotor driver: peripheral annular body, and the peripheral annular body is hollow, The driving track, rotating mechanism and blade are arranged at the hollow inside of the peripheral annular body, the peripheral annular body The shape that is surrounded of inner wall to be formed by the shape of motion profile identical for the blade tip of the blade when moving with the blade, and There is gap, between the inner wall and the blade tip of the blade between the inner wall of the peripheral annular body and the blade tip of the blade Gap formed duct.

Preferably, the force transmission mechanism includes force transmission shaft and connecting shaft, the input terminal of the force transmission shaft and aircraft Engine connection；The input terminal of the connecting shaft is connect with the output end of the force transmission shaft, the output end of the connecting shaft and institute State rotating mechanism connection；Or the force transmission mechanism includes driving motor and driving wheel, it is single that the driving motor is integrated in driving In member；The output axis connection of the driving wheel and the driving motor, under the driving of the driving motor, the rotating mechanism It is moved along driving track.

The present invention also provides a kind of aircraft, the aircraft includes aircraft fuselage and aircraft as described above With rotor driver, the aircraft rotor driver is connect with the aircraft fuselage, and the aircraft fuselage is the flight Device provides power with rotor driver, and the aircraft is made to be worked with rotor driver；The aircraft rotor driver is for providing Lift, to make the aircraft flight.

Preferably, the generally circular framework or ellipse of the track framework of the driving track in the aircraft rotor driver Circular framework, and the middle part of the track framework is hollow；The middle part of the track framework is arranged in the aircraft fuselage, and It is connect with the track framework；The aircraft fuselage is in flying saucer or strip, described to fly when the aircraft fuselage is strip The middle part of the aircraft fuselage, any end are arranged in rotor driver or is arranged in the two of the aircraft fuselage for row device End.

Blade is arranged on rotating mechanism aircraft rotor driver of the invention, and opposite around driving orbit rotation, To generate power, which can make aircraft flight；Using this structure, provides a kind of course of new aircraft and filled with rotor It sets；This kind of aircraft is had the advantages that with rotor driver

1, drive the length of track that can design, so as to voluntarily adjust the quantity and blade of blade as needed Length, to provide more possibilities for design；

It 2, can be using the relatively fast of the blade number combinations of shorter blade length+more, blade root and blade tip and air It is small to spend difference, the case where volatile speed in root low efficiency, tip substantially improves, and blade average length pneumatic efficiency significantly improves；

3, radially blade and angle of attack variation demand do not protrude, and aerodynamic arrangement's design difficulty becomes smaller；

4, track can be designed to circle, oval, rounding off a variety of curve combinations, straight line or straight line and curve Combination, it is more flexible changeable, it is suitble to diversified configuration demand.

Detailed description of the invention

Fig. 1 is the structural schematic diagram of aircraft rotor driver according to a first embodiment of the present invention.

Fig. 2 is the structural schematic diagram of the rotating mechanism and blade in the aircraft rotor driver of embodiment illustrated in fig. 1.

Fig. 3 is the structural schematic diagram of the mounting portion driving unit in the rotating mechanism of embodiment illustrated in fig. 1.

Fig. 4 is the structural schematic diagram of common portion's driving unit in the rotating mechanism of embodiment illustrated in fig. 1.

Fig. 5 is the structural schematic diagram of the elastic connection unit in the rotating mechanism of embodiment illustrated in fig. 1.

Fig. 6 is the cross section structure schematic diagram of the driving track of embodiment illustrated in fig. 1.

Fig. 7 is the structural schematic diagram of aircraft rotor driver according to a second embodiment of the present invention.

Fig. 8 is the structural schematic diagram of aircraft rotor driver according to a third embodiment of the present invention.

Fig. 9 is the structural schematic diagram of the aircraft of first embodiment of the invention.

Figure 10 is the structural schematic diagram of the aircraft of second embodiment of the invention.

Appended drawing reference:

Specific embodiment

To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under Face is described in detail the embodiment of the present invention in conjunction with attached drawing.

In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear", The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention The limitation of range.

Fig. 1 is the structural schematic diagram of aircraft rotor driver according to a first embodiment of the present invention.Fig. 2 is shown in Fig. 1 The structural schematic diagram of rotating mechanism and blade in the aircraft rotor driver of embodiment.Fig. 3 is the rotation of embodiment illustrated in fig. 1 The structural schematic diagram of mounting portion driving unit in rotation mechanism.Fig. 4 is that the common portion in the rotating mechanism of embodiment illustrated in fig. 1 drives The structural schematic diagram of moving cell.Fig. 5 is the structural schematic diagram of the elastic connection unit in the rotating mechanism of embodiment illustrated in fig. 1. Fig. 6 is the cross section structure schematic diagram of the driving track of embodiment illustrated in fig. 1.Fig. 7 is flight according to a second embodiment of the present invention The structural schematic diagram of device rotor driver.Fig. 8 is that the structure of aircraft rotor driver according to a third embodiment of the present invention is shown It is intended to.Fig. 9 is the structural schematic diagram of the aircraft of first embodiment of the invention.Figure 10 is the aircraft of second embodiment of the invention Structural schematic diagram.

If Fig. 1, Fig. 7 and aircraft shown in Fig. 8 rotor driver include driving track 1, rotating mechanism 2 and blade 3, driving track 1 includes force transmission mechanism and track framework 11, and annular receiving groove 111 is provided in track framework 11, and annular is held The opening of slot 111 received is oriented back to annular center direction；Rotating mechanism 2 is arranged in annular receiving groove 111, rotating mechanism 2 It is sequentially connected with force transmission mechanism；The quantity of blade 3 is multiple, and is uniformly mounted on rotating mechanism 2, and each blade 3 spins Extend at rotation mechanism, and is stretched out from the opening of annular receiving groove；Wherein, force transmission mechanism can drive rotating mechanism 2 around driving rail Road 1 moves；Rotating mechanism 2 drives blade 3 to move, so that blade 3 be made to generate power.

In the embodiment shown in fig. 1, driving track 1 is one.It is understood that the quantity of driving track can basis It needs and sets itself.For example, driving the quantity of track is two, each driving rail in Fig. 7 and embodiment shown in Fig. 8 Road 1 is overlapped mutually setting and is connected with each other, and the quantity of rotating mechanism 2 is equal with the driving quantity of quantity of track 1, and each rotation Rotation mechanism 2 is arranged in the annular receiving groove 111 of a driving track 1；Blade 3 is separately positioned on different rotating mechanisms 2. In Fig. 7 and embodiment shown in Fig. 8, the direction of rotation of the blade on each driving track is different.It is formed and to be operated in opposite directions Double drive track rotor form.

It is understood that as needed, driving the quantity of track can also be more.For example, the quantity of driving track is 3 A, 4 or other quantity.

Referring to Fig. 6, in the present embodiment, the inside of track framework 11, i.e. annular receiving groove 111 is arranged in force transmission mechanism It is interior.Force transmission mechanism is electromagnetic coil 4, and electromagnetic coil 4 is connect with the power supply unit of aircraft, generates magnetic when the solenoid is activated ?；Conductor and magnet are provided on rotating mechanism 2, when electromagnetic coil 4 generates magnetic field, conductor generates induced current, thus Motoricity is generated, moves rotating mechanism 2 around driving track 1.Magnet is for being arranged rotating mechanism by maglev mode In track framework, prevent rotating mechanism that there is interference with track framework when rotated.Specifically, in Fig. 1, Fig. 7 and Fig. 8 Shown in embodiment, rotating mechanism is driven using electromagnetic drive mode.

It is understood that can also be driven using other driving methods.For example, passing through electronic or machine driving Mode.For example, in an alternative embodiment, force transmission mechanism includes force transmission shaft and connecting shaft, the input terminal of force transmission shaft with The engine of aircraft connects；The input terminal of connecting shaft and the output end of force transmission shaft connect, the output end and whirler of connecting shaft Structure connection.In this way, the power drive directly transmitted with the engine of aircraft, to realize rotating mechanism around driving Track movement.In another example in another embodiment, force transmission mechanism includes driving motor and driving wheel, driving motor is integrated In driving unit 21；The output axis connection of driving wheel and driving motor, under the driving of driving motor, rotating mechanism 2 is along drive Dynamic rail road 1 moves.

Referring to Fig. 6, in this embodiment, the outer edge part of the annular receiving groove 111 of track framework 11 is provided with backstop Portion, the stopper section reduce the openings of sizes of annular receiving groove 111, so as to prevent from being arranged in annular receiving groove 111 Rotating mechanism is detached from.And the openings of sizes is suitable for stretching out blade.

Advantageously, stopper section is arranged to unidirectionally open, specifically, opened towards outside (paper outward direction in Fig. 6), In this way, rotating mechanism will not be hindered to be placed on annular receiving due to stopper section when rotating mechanism is arranged in annular receiving groove In slot.

In Fig. 1, Fig. 7 and embodiment shown in Fig. 8, track framework 11 is circular framework, and its middle part is hollow.It adopts With this structure, it is suitable for using a kind of course of new aircraft configuration.Specifically, the aircraft fuselage of this kind of aircraft is suitable for placing At the hollow middle part of track framework 11.

It is understood that the shape of track framework 11 can also be other arbitrary shapes.For example, in an alternative implementation In example, track framework 11 is oval ring-type framework, and its middle part is hollow.Using this structure, and shown in Fig. 1, Fig. 7 and Fig. 8 Embodiment it is identical, be suitable for use a kind of course of new aircraft configuration.Specifically, the aircraft fuselage of this kind of aircraft is suitable for putting It sets at the hollow middle part of track framework 11.In another example track framework 11 is rounding off in another alternative embodiment A variety of curve combinations, and its middle part is hollow.It is identical as Fig. 1, Fig. 7 and embodiment shown in Fig. 8 using this structure, it fits In using a kind of course of new aircraft configuration.Specifically, the aircraft fuselage of this kind of aircraft is adapted for placement in track framework 11 Hollow middle part.

It is understood that the shape of track framework 11 can not also use hollow shape, can be provided with middle part Bindiny mechanism's (force transmission shaft as escribed above and connecting shaft), connect for the fuselage with standard aircraft, and passes through middle part The force transmission mechanism of bindiny mechanism and aircraft fuselage connection, thus as described in the embodiment of above-mentioned mechanically operated mode , it is connected by the force transmission mechanism of bindiny mechanism and aircraft fuselage, to realize the flight of aircraft.

Referring to Fig. 1 to Fig. 5, in the present embodiment, rotating mechanism is arranged in annular receiving groove 111, therefore, rotating mechanism Global shape should be adapted with the shape of annular receiving groove 111.For example, when track framework 11 is oval ring-type framework, On annular receiving groove be also ellipse, at this point, the global shape of rotating mechanism is also corresponding ellipse.In another example working as rail When road framework is circular framework, annular receiving groove thereon is also annular shape, at this point, the global shape of rotating mechanism is also phase The annular shape answered.

Referring to fig. 2, in the present embodiment, rotating mechanism includes the driving unit 21 that multiple head and the tail are mutually connected, wherein several Mounting portion 211 is provided on driving unit 21, which is known as mounting portion driving unit, other driving units are known as Ordinary drive units, the mounting portion 211 on each mounting portion driving unit is for installing a blade 3；Any one mounting portion Driving unit is equal with the quantity of ordinary drive units that its another immediate mounting portion driving unit is separated by.

It is understood that there are many connection types for being connected each driving unit head and the tail mutually.For example, each driving is single One end of member is provided with loop connecting portion, and the other end of each driving unit is provided with hook-shaped interconnecting piece, hook-shaped interconnecting piece and ring Shape interconnecting piece cooperation, so as to form the connection type being mutually connected from beginning to end.

In another example can make to be provided with an attachment device between every two driving unit interconnected, to make each A driving unit forms the structure that head and the tail are mutually connected.

In the embodiment depicted in figure 2, using specific attachment device is provided with, i.e., between each driving unit 21 It is connected by elastic connection unit 22.Specifically, referring to Fig. 5, elastic connection unit 22 includes two connectors 221 and connection The elastic component 222 of two connectors 221, one of connector 221 is for connecting a driving unit 21, another connector 221 for connecting another driving unit 21.Using this structure, elastic connection unit can guarantee driving unit in driving rail Normal direction plastic deformation when being run on road.

In structure other than increasing and having mounting portion, other structures are identical for mounting portion driving unit and ordinary drive units. Therefore, mounting portion driving unit and ordinary drive units can be referred to as driving unit.

Referring to Fig. 3 and Fig. 4, in the present embodiment, driving unit 21 includes conductor body 212 and is arranged in conductor body The magnet 213 at edge.The magnetic field interaction in induced current, with track is generated when forming magnetic field, in conductor body, thus Form power.

Referring to Fig. 3 and Fig. 4, in the present embodiment, conductor body 212 is cuboid.And its inner hollow, magnet 213 are set It sets on the angle of conductor body 212.It is understood that the shape of conductor body can according to need and sets itself.For example, Conductor body is square or warp architecture.It is understood that conductor body is along the camber line (outer edge of whole rotating mechanism Be formed by camber line) width by blade quantity and the radius of curvature of arc track depending on, guarantee driving unit in variable curvature rail It can trouble-free operation in road.

Referring to Fig. 1, in the present embodiment, the quantity of blade is multiple, and is evenly arranged on driving unit, specifically, uniformly distributed On mounting portion driving unit.It is conventional set that shape, quantity, length, aerofoil profile, the chord length of blade, which are extended to distribution characteristics etc., It is fixed.As long as on the aircraft that the aircraft rotor driver that can satisfy the application is mounted on, providing satisfaction for aircraft and flying The power of row device flying condition.

For example, by taking aircraft rotor driver shown in FIG. 1 as an example, it is assumed that can be taken by way of electromagnetic drive The track drawing speed or driving speed obtained is 500 kilometers/hour, and (electromagnetic drive mode is fully able to reach in the prior art 500 kilometers/hour or more), at this point, linear velocity is about 139 meter per seconds, this is that (blade is connect propeller shank with driving unit One end) speed.

Assuming that at this time propeller shank guide rail radius of curvature be 1.5 meters (i.e. at this time annular receiving groove be it is round, rotating mechanism is Circle, rotating mechanism rotation is formed by track as circle, and the circular radius of curvature is 1.5 meters).By formula calculate or Person's conversion, the linear velocity that can obtain 139 meter per seconds are equivalent to 885 revs/min of angular speed, it is assumed that blade length takes 1 meter at this time, changes Calculate tip speed (other end of blade) about 232 meter per second, the blade long for one meter, the linear speed of -232 meter per second of 139 meter per second Degree range can cover the best effort velocity interval of the blade shape of the prior art completely, therefore, for setting for blade Meter, the blade of the prior art can complete the theoretical flight of the application completely.

And the size of blade lift, it can be controlled by the combination of the running speed and blade angle of attack size of blade, example Such as, it can add the blade change angle of attack, blade speed change degree that the blade perseverance angle of attack or blade speed change degree is added to add blade using blade constant speedpump Become the design combination of the various conventionals such as the angle of attack to achieve the purpose that the application.

It is in the 3rd embodiment of the application referring to Fig. 8, Fig. 8, the 3rd embodiment and second embodiment shown in Fig. 7 have There is following difference:

Referring to Fig. 8, in this embodiment, aircraft rotor driver further comprises peripheral annular body 5, peripheral annular body 5 is hollow, and driving track 1, rotating mechanism 2 and blade 3 are arranged at the hollow inside of peripheral annular body 5, peripheral annular body 5 It is identical to be formed by the shape of motion profile for the blade tip of blade when the shape that inner wall is surrounded and blade move, and peripheral annular body There is gap, the gap between inner wall and the blade tip of blade 3 forms duct between 5 inner wall and the blade tip of blade 3.Using this The aircraft of the application is designed to culvert type with rotor driver by structure, generates Additional pneumatic power using duct.This blade tool Have following series of advantages: harmful windward side resistance of aircraft reduces.

It is understood that in the embodiment shown in fig. 8, in addition to the differences mentioned above, other structures and embodiment illustrated in fig. 7 All the same, details are not described herein.

It is understood that can also be to be equipped with Fig. 8 embodiment in embodiment shown in Fig. 1 or other variant embodiments Shown in peripheral annular body.

It is understood that the aircraft rotor driver of the application can be adapted for existing various types of flights Device.For example, unmanned plane, helicopter, passenger aircraft, cargo aircraft etc..It is understood that the aircraft of the application revolves Swing device is especially suitable for helicopter and unmanned plane.It is understood that the aircraft rotor driver of the application can be single It solely uses on board the aircraft, other power can also be cooperated to provide mechanism and be used together on board the aircraft.For example, in a frame jet It is also feasible that the technical solution of the aircraft rotor driver of the application is provided on formula aircraft.

Advantageously, the aircraft includes flight present invention also provides the aircraft of such as Fig. 8 or embodiment illustrated in fig. 9 Device fuselage and aircraft rotor driver as described above, aircraft rotor driver are connect with aircraft fuselage 6, aircraft Fuselage 6 provides power with rotor driver for aircraft, and aircraft is made to be worked with rotor driver；Aircraft rotor driver is for mentioning For lift, to make aircraft flight.

Referring to Fig. 8 or Fig. 9, in the two embodiments, the rail of the driving track in the aircraft rotor driver of use The generally circular framework of road framework, and the hollow configuration in middle part of track framework；The aircraft fuselage 6 is arranged in track framework 11 middle part, and connect with track framework 11.

It is understood that the concrete shape of track framework can also be other shapes.For example, the shape of track framework is Elliptical annular framework.

It is understood that the shape of aircraft fuselage also can according to need and sets itself.For example, with reference to Figure 10, In this embodiment, the shape of aircraft fuselage is UFO shape.Referring to Fig. 9, in this embodiment, aircraft fuselage 6 is in a strip shape, And the middle part of aircraft fuselage is arranged in rotor driver for aircraft.It is understood that in the reality that aircraft fuselage is strip It applies in example, aircraft rotor driver can also be arranged in the middle any end of aircraft fuselage 6 or be arranged in aircraft machine The both ends of body.

It, can also be with it is understood that aircraft fuselage can be unmanned plane type, the small fuselage that can not accommodate people It is the fuselage that can only accommodate pilot's type, can also be the big fuselage for carrying out loading or carrying type.

Aircraft using the above structure, has the advantages that

1, aircraft fuselage setting, according to the size and shape of required aircraft fuselage, can optimize in the middle part of driving track Drive the shapes and sizes of track.

2, since aircraft fuselage can be completely disposed at driving track interior space, top (Fig. 8 or Fig. 9 shown in top) nothing It blocks, can not influence to use Aircrew Escape Technology, make it possible collective's passenger's Aircrew Escape Technology of carrying formula aircraft.

3, blade upper and lower part do not have it is any pneumatically block or block, relatively conventional aircraft (such as helicopter), effect Rate is improved.

4, under the premise of not interfering with aircraft fuselage, rotor, which can according to need, is moved to any of aircraft fuselage One end further increases hovering and takes off efficiency.

5, since aircraft fuselage is arranged in driving track interior, track curvature and shape be can according to need and oneself Row setting, will not due to aircraft fuselage interfere and limit shape.

It is had the advantages that using the aircraft of the application with rotor driver

1, the length of track can design, and can place more blades, to adapt to the aircraft fuselage of different lift.

2, the relative velocity difference of the blade number combinations of shorter blade length+more, blade root and blade tip and air is small, The case where substantially improving the volatile speed in root low efficiency, tip, blade average length pneumatic efficiency significantly improves.

4, track can be designed to circle, oval, rounding off a variety of curve combinations, straight line or straight line and curve Combination, it is more flexible changeable, it is suitble to diversified aircraft fuselage configuration demand.

5, blade running track is changeable, and pneumatic channel can avoid the isostructural obstruction of aircraft fuselage, realizes gas Efficiency of movement bigizationner.

6, it in some embodiments, drives the intermediate position of track hollow, can be used for placing aircraft fuselage, do not rotated The ejection escape of the influence of blade, unit is possibly realized.

Present invention also provides an alternative embodiments, and specifically, driving track includes that track framework and magnetic field occur Mechanism.Track box body is internally provided with toroidal cavity, and the inner wall of track framework is provided with groove.Magnetic field generating means are by several coils Around forming, coil setting forms the primary of line-like driving motor, generates magnetic after energization group in track framework inner wall trench ?.

Rotating mechanism is arranged in the toroidal cavity, including driving unit and flexible connector, driving unit and bullet Property connector interval be connected.The secondary of driving unit line-like driving motor, the magnetic field in track framework toroidal cavity are made With the circumferential driving force of lower generation.Flexible connector can produce deformation appropriate, and rotating mechanism is allowed to transport along the track of variable curvature It is dynamic.It is placed with magnet on driving unit, enables rotating mechanism suspended motion in the magnetic field in track cavity.

Blade is uniformly distributed, is mounted on the driving unit of the rotating mechanism, and the driving list of each blade spin rotation mechanism Extend at member, and is stretched out from the opening of toroidal cavity.Driving unit can drive rotating mechanism to move along driving track, and drive Blade movement, so that blade be made to generate aerodynamic force.

Using this structure there is the length of driving track and curvature shapes can design, significantly improve blade average length gas The advantages that efficiency of movement and reduction blade aerodynamic layout designs difficulty, another choosing also is provided for new configuration rotorcraft design It selects.

It is understood that the power supply with aircraft joined together by the aircraft rotor driver in the alternative embodiment supplies It can be alternating current to electric current provided by device, be also possible to direct current, according to the difference of powered types, coil windings mode And it also needs to carry out corresponding change with the rapport of driving unit.

Finally it is noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent Present invention has been described in detail with reference to the aforementioned embodiments for pipe, those skilled in the art should understand that: it is still It is possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is equally replaced It changes；And these are modified or replaceed, the essence for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution Mind and range.

Claims

1. a kind of aircraft rotor driver, which is characterized in that the aircraft includes: with rotor driver

It drives track (1), the driving track (1) includes force transmission mechanism and track framework (11), the track framework (11) On be provided with annular receiving groove (111), the opening of the annular receiving groove (111) is oriented back to annular center direction；

Rotating mechanism (2), the rotating mechanism (2) setting in the annular receiving groove (111), the rotating mechanism (2) with The force transmission mechanism transmission connection；

Blade (3), the quantity of the blade (3) is multiple, and is uniformly mounted on the rotating mechanism (2), and each blade (3) extend at spin rotation mechanism, and stretched out from the opening of annular receiving groove；Wherein,

The force transmission mechanism can drive the rotating mechanism (2) to move around the driving track (1)；The rotating mechanism (2) The blade (3) are driven to move, so that blade (3) be made to generate power；

The rotating mechanism (2) includes the driving unit (21) that multiple head and the tail are mutually connected, wherein setting on several driving units (21) Mounting portion (211) are equipped with, which is known as mounting portion driving unit, and it is single that other driving units are known as common driving Member, the mounting portion (211) on each mounting portion driving unit is for installing a blade (3)；The driving of any one mounting portion is single Member is equal with the quantity of ordinary drive units that its another immediate mounting portion driving unit is separated by；

It is connected between each driving unit (21) by elastic connection unit (22).

2. aircraft rotor driver as described in claim 1, which is characterized in that the driving track (1) be it is multiple, it is each Driving track (1) is overlapped mutually setting and is connected with each other, the number of the quantity of the rotating mechanism (2) and driving track (1) Measure it is equal, and each rotating mechanism (2) setting one it is described driving track (1) annular receiving groove (111) in；The blade (3) it is separately positioned on different rotating mechanisms (2).

3. aircraft rotor driver as described in claim 1, which is characterized in that the force transmission mechanism is electromagnetic coil (4), The electromagnetic coil (4) connect with the power supply unit of the aircraft, generates magnetic field when the electromagnetic coil is powered；

It is provided with conductor and magnet on the rotating mechanism (2), when the electromagnetic coil (4) generate magnetic field, the conductor Generating induced current moves rotating mechanism (2) around the driving track (1) to generate motoricity.

4. aircraft rotor driver as described in claim 1, which is characterized in that the driving unit (21) includes conductor sheet Body (212) and the magnet (213) that conductor body edge is set.

5. aircraft rotor driver as claimed in claim 4, which is characterized in that the conductor body (212) is cuboid Or square, and its inner hollow, the magnet (213) are arranged on the angle of the conductor body (212).

6. aircraft rotor driver as claimed in claim 1 or 2, which is characterized in that the aircraft rotor driver is into one Step includes:

Peripheral annular body (5), the peripheral annular body (5) is hollow, the driving track (1), rotating mechanism (2) and blade (3) be arranged at the hollow inside of the peripheral annular body (5), the shape that the inner wall of the peripheral annular body (5) is surrounded with When the blade moves the blade tip of the blade be formed by motion profile shape it is identical, and the peripheral annular body (5) There is gap, the gap between the inner wall and the blade tip of the blade (3) is formed between inner wall and the blade tip of the blade (3) Duct.

7. aircraft rotor driver as described in claim 1, which is characterized in that the force transmission mechanism include force transmission shaft and Connecting shaft, the input terminal of the force transmission shaft and the engine of aircraft connect；The input terminal of the connecting shaft and the force transmission shaft Output end connection, the output end of the connecting shaft connect with the rotating mechanism；Or

The force transmission mechanism includes driving motor and driving wheel, and the driving motor is integrated in driving unit (21)；It is described The output axis connection of driving wheel and the driving motor, under the driving of the driving motor, the rotating mechanism (2) is along driving Track (1) movement.

8. a kind of aircraft, which is characterized in that the aircraft includes aircraft fuselage and any one of such as claim 1 to 7 The aircraft rotor driver, the aircraft rotor driver are connect with the aircraft fuselage (6), the aircraft Fuselage (6) provides power with rotor driver for the aircraft, and the aircraft is made to be worked with rotor driver；The aircraft is used Rotor driver is for providing lift, to make the aircraft flight.

9. aircraft as claimed in claim 8, which is characterized in that the rail of the driving track in the aircraft rotor driver The generally circular framework of road framework or oval ring-type framework, and the middle part of the track framework is hollow；The aircraft fuselage (6) setting is connect at the middle part of the track framework (11), and with the track framework (11)；

The aircraft fuselage (6) is in UFO shape or strip, and when the aircraft fuselage is strip, the aircraft is filled with rotor Install the middle part in the aircraft fuselage (6), any end or the both ends that the aircraft fuselage is set.