CN205652349U - Unmanned aerial vehicle with thrust mechanism of amplification and fixing device - Google Patents

Abstract

The utility model discloses an unmanned aerial vehicle with thrust mechanism of amplification and fixing device, including fuselage, main rotor, the tailspin wing, steering wheel, engine and reducing gear box, the reducing gear box with the engine is connected, unmanned aerial vehicle with thrust mechanism of amplification and fixing device still includes: the thrust mechanism of amplification, the thrust mechanism of amplification with the steering wheel is connected, in order to enlarge the thrust that the steering wheel produced, a fixing device, the fixing device cover is established on the tail transmission shaft, and with fuselage fixed connection is in order to incite somebody to action the tail transmission shaft with fuselage relatively fixed. The utility model provides a prior art centered rudder mechanic have the technical defect that the energy resource consumption is big as the in -process.

Description

There is the unmanned plane of thrust amplifying mechanism and fixing device

Technical field

This utility model relates to unmanned air vehicle technique field, particularly to having thrust amplifying mechanism and fixing The unmanned plane of device.

Background technology

UAV is called for short " unmanned plane ", is to utilize radio robot and the program provided for oneself Control the most manned aircraft that device is handled.Without driving cabin on machine, but automatic pilot, program are installed Control the equipment such as device, signal pickup assembly.On ground, naval vessels or machine tool remote control station personnel pass through thunder The equipment such as reach, it be tracked, position, remote control, remote measurement and Digital Transmission.Can be distant at radio Take off as conventional airplane under control or launch with booster rocket, it is possible to being taken to aerial throwing by machine tool Let row fly away.

In prior art, the change of depopulated helicopter main rotor pitch, drive often by steering wheel The rotor face of main rotor swings up and down, and then realizes the change of rotor face with respect to the horizontal plane angle.So And, it is fixed on the steering wheel of fuselage interior, often and there is a segment distance between main rotor, pass through steering wheel When going to drive the rotor face of main rotor to swing up and down, generally require the biggest kinetic energy of consumption and just can overcome master Rotor self gravitation and realize rotor face and swing up and down, this allows for having the energy in steering wheel work process Consume big technological deficiency.

Utility model content

This utility model provides a kind of unmanned plane with thrust amplifying mechanism and fixing device, solves Prior art has in steering wheel work process the technological deficiency that energy resource consumption is big.

For solving above-mentioned technical problem, this utility model provides one and has thrust amplifying mechanism with solid Determine the unmanned plane of device, including fuselage, main rotor, tail rotor, steering wheel, electromotor and reduction box, Described reduction box is connected with described electromotor, and wherein, described main rotor is by final drive shaft and described machine Body is rotatably fixed connection；Described tail rotor is fixedly installed on the afterbody of described fuselage, and passes through tail Power transmission shaft is rotatably fixed with described fuselage and is connected；Described electromotor and described main rotor and described tail Rotor connects, and is used for driving described main rotor and described tail rotor to rotate, and described steering wheel is fixed on described The inside of fuselage；The described unmanned plane with thrust amplifying mechanism and fixing device also includes: thrust is put Great institutions, described thrust amplifying mechanism is connected with described steering wheel, to amplify the thrust that described steering wheel produces； Fixing device, described fixing device is set on described tail transmission shaft, and fixing with described fuselage is connected, So that described tail transmission shaft and described fuselage are relatively fixed.

Optionally, described thrust amplifying mechanism includes:

First drive link, one end of described first drive link is fixed on described fuselage；

Second drive link, one end of described second drive link is fixed on described steering wheel；And

Driver plate, described driver plate respectively with the other end of described first drive link and described second transmission The other end of bar is rotationally connected, and described driver plate is rotationally connected with described fuselage；Make described steering wheel The active force of described second drive link is passed through described driver plate, is transferred to described first drive link.

Optionally, described driver plate includes:

First point；

Second point；And

Thirdly；Wherein, the other end of described first drive link and described driver plate are at described first point Place is rotationally connected so that described first drive link can the most described first drive link at described first Rotate；The other end of described second drive link and described driver plate company of rotation at described second point Connect so that described second drive link can rotate relative to described second drive link at described second point； Described driver plate thirdly place be rotationally connected with described fuselage, and described driver plate described thirdly Place can rotate relative to described fuselage.

Optionally, described first drive link with described driver plate being rotationally connected at described first is Hinged；

And/or,

Described second drive link is hinged with described driver plate being rotationally connected at described second point；

And/or,

Described driver plate and described fuselage described thirdly locate to be rotationally connected be hinged.

Optionally,

Described first point, described second point and the described thirdly position on described driver plate can be with shapes Become a triangle.

Optionally, described fixing device includes:

First sleeve；And

Fixed plate；Wherein, described first set jacket casing is located on described tail transmission shaft, described fixing sleeve-board It is located on described first sleeve, and the outside of described fixed plate is fixed with described fuselage and is connected, to pass through Described first sleeve and described fixed plate are by firm being fixed in described fuselage of described tail transmission shaft Portion, to prevent described tail transmission shaft from beating.

Optionally, described fixing device also includes:

Limiting plate, wherein,

Described fixed plate offers the first hole, location, and the aperture in described first hole, location is more than described first The excircle diameter of sleeve, makes described first sleeve be located in described first hole, location；

Described limiting plate offers the second hole, location, and the aperture in described second hole, location is more than described first The excircle diameter of sleeve, makes described first sleeve be located in described second hole, location；

Described limiting plate is connected by fixing with described fixed plate.

Optionally,

All offering screwed hole in described limiting plate and described fixed plate, described limiting plate is fixing with described Fixing connection between plate is threaded.

Optionally, the rounded shape of described fixed plate.

The application has the beneficial effect that:

(1) the application is by arranging thrust amplifying mechanism, is connected by steering wheel and the second drive link, the Two drive links are connected with driver plate, and driver plate and the first drive link connect, and such steering wheel acts on second The power of drive link, passes sequentially through driver plate, the first drive link is ultimately applied to main rotor so that by One drive link, the second drive link and driver plate constitute primary transmission and amplify the thrust of described steering wheel, subtract Lack the loss of energy.

Accompanying drawing explanation

In order to be illustrated more clearly that this utility model embodiment or technical scheme of the prior art, below will In describing embodiment, the required accompanying drawing used is briefly described, it should be apparent that, in describing below Accompanying drawing be only embodiments more of the present utility model.

Fig. 1 is in the application one better embodiment, has the nothing of thrust amplifying mechanism and fixing device Man-machine structural representation；

Fig. 2 is in the another better embodiment of the application, has thrust amplifying mechanism and fixing device The structural representation of unmanned plane；

Fig. 3 is the structural representation of fixing device in Fig. 1；

Fig. 4 is the structural representation of the application chiller；

Fig. 5 is the structural representation of the application reduction box；

Fig. 6 is the partial view of a support component in Fig. 2；

Fig. 7 be in Fig. 1 brake wheel structural representation；

Fig. 8 is the right view of brake wheel in Fig. 7.

Detailed description of the invention

In order to be better understood from technique scheme, below in conjunction with Figure of description and concrete enforcement Technique scheme is described in detail by mode.

Referring to Fig. 1 and Fig. 2, the one that the application provides has thrust amplifying mechanism and fixing device Unmanned plane 100, described in there is the unmanned plane of thrust amplifying mechanism and fixing device at least include fuselage 1, main rotor 2, tail rotor 3 and electromotor 4, described main rotor 2 rotates to provide lifting force, institute State tail rotor 3 to rotate to offset the moment of torsion produced when described main rotor 2 rotates, have described in ensureing Unmanned plane 100 smooth flight of thrust amplifying mechanism and fixing device.

Concrete, referring to Fig. 3, tail transmission shaft 7 is for being transferred to by the driving force of electromotor 4 Tail rotor 3.Due to distant apart from described electromotor 4 of described tail rotor 3, described tail transmission Axle 7 easily produces in-flight at the unmanned plane 100 with thrust amplifying mechanism and fixing device beats. And tail transmission shaft 7 is connected, with fixing tail transmission shaft by the fixing device 8 that the application provides with fuselage 1 7, reduce the amplitude of beating of described tail transmission shaft 7.Described fixing device 8 include the first sleeve 82, Fixed plate 81 and limiting plate 83, described first sleeve 82 is set on described tail transmission shaft 7, described The outside of fixed plate 81 is fixing with described fuselage 1 to be connected, and described fixed plate 81 offers the first location Hole, the aperture in described first hole, location, more than the excircle diameter of described first sleeve 82, makes described the One sleeve 82 is located in described first hole, location.Described limiting plate 83 offers the second hole, location, The aperture in described second hole, location, more than the excircle diameter of described first sleeve 82, makes described first set Cylinder 82 is located in described second hole, location.Described limiting plate 83 passes through bolt with described fixed plate 81 Connect, and by being provided with surplus between bolt and screwed hole, reduce beating of tail transmission shaft 7, And it is hardly damaged described tail transmission shaft 7.Concrete, on described limiting plate 83 and described fixed plate 81 All offer screwed hole, and use and leave the bolt of surplus with described screwed hole and be located in described screwed hole In with fixing described fixed plate 81 and described limiting plate 83, reduce beating of described tail transmission shaft 7, And it is hardly damaged described tail transmission shaft 7.By arranging the first sleeve 82, described first sleeve 82 is sheathed In described tail transmission shaft 7, to avoid described tail transmission shaft 7 and described limiting plate 83 or described fixing The direct friction of plate 81 and wear and tear, improve the life-span of described tail transmission shaft 7.

Further, incorporated by reference to Fig. 1-2 in the lump refering to 4-5, the embodiment of the present application additionally provides one Chiller.Reduction box 12 is connected with described electromotor 4, for the power to the output of described electromotor 4 Carry out regulator drive.Described chiller includes that at least one cooler bin 13, described cooler bin 13 wrap Include the first oil-in and first oil-out corresponding with described first oil-in；Described reduction box 12 Including the second oil-in and second oil-out corresponding with described second oil-in；Described first oil-feed Mouth connects with described second oil-out, it is preferred that described first oil-in leads to described second oil-out Cross first hose connection and connect；Described first oil-out connects with described second oil-in, it is preferred that Described first oil-out and described second oil-in are hose connection and connect by second.And the application is logical Cross a sheathed worm structure on the gear shaft in described reduction box 12 so that described worm structure rotates Time the gear oil in described reduction box 12 is pressed onto in described cooler bin 13, make described in there is thrust put The fuselage interior structure cooling of the unmanned plane 100 of great institutions and fixing device is more abundant.Certainly, this Shen In please, the peripheral position of reduction box 12 and cooler bin 13 be also respectively provided with fin, to add further Strong radiating effect.As preferably, this fin can be aluminium flake.

Based on same utility model design, the application has thrust amplifying mechanism and fixing dress described A cooling dress it is also equipped with at the reduction box 12 that tail rotor 3 structure division of the unmanned plane 100 put is arranged Put, the common chiller 100 being applied to there is the unmanned plane of thrust amplifying mechanism and fixing device Cooling is the most all the Local cooling used, and by adding gear oil, and is applied to have and pushes away described in relying on The gear-box surface of reduction box 12 in the chiller 100 of the unmanned plane of force amplificatory structure and fixing device Dispelling the heat, the heat radiation of this type of cooling is slow, and is only capable of that described being applied to is had thrust amplifying mechanism Dispel the heat with the local in the chiller 100 of the unmanned plane of fixing device, can not obtain very well Radiating effect.The unmanned plane being applied to there is thrust amplifying mechanism and fixing device that the application provides Chiller 100 also include afterbody reduction box 12 and chiller.Concrete, described reduction box 12 are connected with described electromotor 4, for the power of described electromotor 4 output is carried out regulator drive.Institute State the chiller 100 being applied to that there is the unmanned plane of thrust amplifying mechanism and fixing device also include to A few cooler bin 13, described cooler bin 13 include the first oil-in and with described first oil-in phase The first corresponding oil-out；Described reduction box 12 include the second oil-in and with described second oil-in phase The second corresponding oil-out；Described first oil-in connects with described second oil-out, it is preferred that institute State the first oil-in pass through hose connection with described second oil-out and connect；Described first oil-out with Described second oil-in connection, it is preferred that described first oil-out and described second oil-in are by soft Pipe connects and connects.And the application is tied by a worm screw sheathed on the gear shaft in described reduction box 12 Structure so that the gear oil in described reduction box 12 is pressed onto described cooler bin when rotating by described worm structure In 13, make the fuselage interior structure cooling with the unmanned plane 100 of thrust amplifying mechanism and fixing device More abundant.

Further, please continue to refer to Fig. 4, present invention also provides a kind of thrust amplifying mechanism 9, with Steering wheel connects；Described steering wheel is for controlling the unmanned plane 100 with thrust amplifying mechanism and fixing device Flight attitude and track.Described thrust amplifying mechanism 9 increases the one-level transmission with described steering wheel to amplify The thrust that steering wheel produces, reduces energy loss.Concrete, described thrust amplifying mechanism 9 includes first Drive link the 91, second drive link 93 and driver plate 92, described driver plate 92 includes 1: 921, Second point 923 and thirdly 922.Described driver plate 92 respectively with described first drive link 91 and institute State the second drive link 93 to connect；One end of described first drive link 91 is force side, and described first passes One end of lever 91 is fixing with described fuselage 1 to be connected, the other end of described first drive link 91 and institute State driver plate 92 fixing connection at described 1: 921, and described first drive link 91 can be relative Described 1: 921 rotates.One end of described second drive link 93 and described driver plate 92 are described Fix at second point 923 and connect, and described second drive link 93 can rotate relative to described second point 923, The other end of described second drive link 93 is connected with described steering wheel.Described driver plate 92 is thirdly 922 Place is connected with described fuselage 1, and described driver plate 92 can relative to described in thirdly 922 rotate.Pass through First drive link the 91, second drive link 93 is set and driver plate 92 increases primary transmission and amplifies described The thrust of steering wheel, reduces energy loss.

Preferably, described first drive link 91 and described driver plate 92 are hinged at 1: 921； Described second drive link 93 and described driver plate 92 are hinged at second point 923；Described driver plate 92 With described fuselage 1 at thirdly 922 hinged.

Preferably, described 1: 921, second point 923 and thirdly 922 position triangular in shape.

Further, refer to Fig. 6, present invention also provides a kind of support component 11, be applied to tool Having the unmanned plane 100 of thrust amplifying mechanism and fixing device, the support component 11 that the application provides is arranged In described fuselage 1, for supporting and fix the spacing collar of described final drive shaft 10.Described support Assembly 11 is by using supported at three point, and supporting construction is stable and has thrust amplifying mechanism with solid to described Determine unmanned plane 100 flight course of device can play the effect of damping.Concrete, described support group Part 11 includes the first bar the 111, second bar 113 and positioning seat 114；One end of described first bar 111 Being removably secured with described fuselage 1 and be connected, the other end of described first bar 111 offers a groove； One end of described second bar 113 is set in described groove, the end of one end of described second bar 113 It is provided with one or more elastic ball 112 so that described first bar 111 with putting in the inwall of described groove And the stress between described second bar 113 is buffered, reduce vibrations.

In the present embodiment, described elastic ball 112 is baton round；Another of described second bar 113 End is provided with the first lug, and described first lug offers the first through hole, the one of described positioning seat 114 End is provided with the second lug, and described second lug offers the second through hole mated with described first through hole, Described first through hole is bolted with described second through hole, makes described second bar 113 energy institute relatively State positioning seat 114 to rotate.In order to reduce the vibrations of described support component 11, described positioning seat further The other end of 114 is also arranged with a resilient sleeve, and described resilient sleeve is I-shaped, described resilient sleeve It is set on described positioning seat 114, and the groove of the I-shaped of described resilient sleeve is fastened on described On the fuselage 1 of the unmanned plane 100 with thrust amplifying mechanism and fixing device, so that described positioning seat 114 fixing with described fuselage 1 are connected.

In the present embodiment, described resilient sleeve is rubber sleeve.Improve further by arranging resilient sleeve The shock resistance of a support component 11 described in.Described first bar 111 passes through socket with described second bar 113, And it is provided with elastic ball 112 between described first bar 111 and described second bar 113, also improve institute State the shock resistance of a support component 11.The application uses described first bar 111 and described second bar 113 By socket, and it is provided with elastic ball 112 between described first bar 111 and described second bar 113, Instead of the hinged etc. of routine, described first bar 111 and described second bar 113 are ensured by pretightning force The reliability and stability connected, on the one hand improves the shock resistance of described support component 11, another Aspect, adds the cushion effect after member stress, it is to avoid described support component 11 by crossing large impact, Improve the life-span of described support component 11.

Further, incorporated by reference to Fig. 1-2 in the lump refering to Fig. 7-8, the present embodiment additionally provides one and rises and falls Device, for take-off and landing device, including a undercarriage 5 and brake wheel 6, described undercarriage 5 is solid Surely the bottom of described fuselage 1 it is arranged on.Described brake wheel 6 is removably secured with described undercarriage 5 Connect.Being provided for of described brake wheel 6 has thrust amplifying mechanism and fixing device described in reducing Unmanned plane 100 is the abrasion of described undercarriage 5 when rising and falling, and described brake wheel 6 is manually controllable, knot Structure is simple and conveniently dismantles.

Concrete, described undercarriage 5 offers the first fixing hole, described first fixing hole for Described brake wheel 6 with the use of, to be plugged in described first fixing hole and described brake by fixture In wheel 6, make described brake wheel 6 fix with described undercarriage 5 and be connected.In the present embodiment, institute State fixture and be specially latch.

Further, described brake wheel 6 includes rotating wheel 61, connecting plate 62 and controlling bar 63.Institute State rotation wheel 61 and include that a rotary shaft, described rotation wheel 61 can be revolved around the centrage of described rotary shaft Turn.One end of described connecting plate 62 is fixing with described rotary shaft to be connected；Control bar, with described connecting plate The other end of 62 is removably secured connection；Described control bar 63 moves up or down, and makes described Connecting plate 62 rotates and regulates the described height rotating wheel 61.Concrete, the one of described connecting plate 62 End offers the first connecting hole, and the other end of described connecting plate 62 offers the second connecting hole, described company Being further opened with the second fixing hole on fishplate bar 62, described second fixed hole position is in described first connecting hole and institute State between the second connecting hole.Described control bar 63 is removably secured with described connecting plate 62 and is connected, Preferably, one end of described control bar 63 is provided with a fixed part, and described fixed part is located in described In two connecting holes, and it is connected by latch or clip are fixing with described connecting plate 62.Described rotary shaft is worn Being located in described first connecting hole, described rotary shaft is at described first connection hole and described connecting plate 62 Fixing connection so that rotate the height of wheel 61 when described connecting plate 62 rotates described in adjustable.This Shen Connecting plate 62, rotary shaft and control bar 63 please be use to form a linkage, and combine control bar 63 The position of mobile adjustment brake wheel 6, simple in construction and convenient dismounting.

During operation, manually make described control bar 63 move up or down, make described rotation wheel 61 Move down, when the described minimum altitude minimum altitude less than described undercarriage 5 rotating wheel 61, and The difference in height of the described minimum altitude and the minimum altitude of described undercarriage 5 rotating wheel 61 equals to or more than During preset value, in described first fixing hole and described second fixing hole, plug fixture, with fixing institute State brake wheel 6.The brake wheel 6 that the application is arranged, Non-follow control and readily accessible, reduce described rising Fall the abrasion of frame 5, improve described in there is the unmanned plane 100 of thrust amplifying mechanism and fixing device Life-span.

The application has the beneficial effect that:

1, the application by arrange brake wheel reduce described in there is thrust amplifying mechanism and fixing device Unmanned plane abrasion of described undercarriage when rising and falling, and described brake wheel is manually controllable, simple in construction And conveniently dismounting.

2, the application use described first bar and described second bar by socket, and described first bar and institute State and be provided with elastic ball between the second bar, it is ensured that the reliability and stability of connection, on the one hand improve Described in, the shock resistance of a support component, on the other hand, adds the cushion effect after member stress, it is to avoid institute State support component by crossing large impact, improve the life-span of described support component, the final main transmission realized The safety and firmness of axle runs.

3, the application is by arranging the first drive link, the second drive link and driver plate, by steering wheel with Second drive link connects, and the second drive link is connected with driver plate, and driver plate and the first drive link connect, So steering wheel acts on the power of the second drive link, passes sequentially through driver plate, the first drive link finally acts on In main rotor so that constituted primary transmission by the first drive link, the second drive link and driver plate and amplify The thrust of described steering wheel, decreases the loss of energy.

4, the application is by setting up cooler bin and return duct so that be in the oil of reduction box in fuselage interior Liquid, is circulated in cooler bin and reduction box by return duct, increases the fluid trip in fuselage interior Dynamic distance, meanwhile, is provided with fin at the peripheral position of reduction box and cooler bin, with to reduction box Dispel the heat further with cooler bin, solve and prior art has thrust amplifying mechanism and fixing device The technological deficiency that unmanned aerial vehicle body internal heat dissipating effect is bad.

5, the application sets up the first sleeve and fixed plate by setting, and first set jacket casing is located at tail transmission The outside of axle, fixed plate is set in the outside of the first sleeve so that by the tail transmission shaft of fuselage interior with Fuselage is relatively fixed, and is effectively prevented the unmanned plane with thrust amplifying mechanism and fixing device and is flying And the technological deficiency easily beated that cause long due to tail transmission shaft during row.

It should be noted last that, above detailed description of the invention is only in order to illustrate technology of the present utility model Scheme and unrestricted, although this utility model being described in detail with reference to example, this area general Logical it will be appreciated by the skilled person that the technical solution of the utility model can be modified or be equal to and replace Changing, without deviating from the spirit and scope of technical solutions of the utility model, it all should contain in this practicality new In the middle of the right of type.

Claims (9)

1. a unmanned plane with thrust amplifying mechanism and fixing device, including fuselage, main rotor, tail rotor, steering wheel, electromotor and reduction box, described reduction box is connected with described electromotor, and wherein, described main rotor is rotatably fixed with described fuselage by final drive shaft and is connected；Described tail rotor is fixedly installed on the afterbody of described fuselage, and is rotatably fixed with described fuselage by tail transmission shaft and is connected；Described electromotor is connected with described main rotor and described tail rotor, is used for driving described main rotor and described tail rotor to rotate, and described steering wheel is fixed on the inside of described fuselage；It is characterized in that, described in there is the unmanned plane of thrust amplifying mechanism and fixing device also include:

Thrust amplifying mechanism, described thrust amplifying mechanism is connected with described steering wheel, to amplify the thrust that described steering wheel produces；

Fixing device, described fixing device is set on described tail transmission shaft, and fixing with described fuselage is connected, described tail transmission shaft and described fuselage to be relatively fixed.

There is the unmanned plane of thrust amplifying mechanism and fixing device the most as claimed in claim 1, it is characterised in that described thrust amplifying mechanism includes:

First drive link, one end of described first drive link is fixed on described fuselage；

Second drive link, one end of described second drive link is fixed on described steering wheel；And

Driver plate, the described driver plate other end with the other end of described first drive link and described second drive link respectively is rotationally connected, and described driver plate is rotationally connected with described fuselage；Make described steering wheel that the active force of described second drive link is passed through described driver plate, be transferred to described first drive link.

There is the unmanned plane of thrust amplifying mechanism and fixing device the most as claimed in claim 2, it is characterised in that described driver plate includes:

First point；

Second point；And

Thirdly；Wherein, the other end of described first drive link is rotationally connected at described first with described driver plate so that described first drive link can rotate relative to described first drive link at described first；The other end of described second drive link is rotationally connected at described second point with described driver plate so that described second drive link can rotate relative to described second drive link at described second point；Described driver plate is rotationally connected with described fuselage at thirdly place, and described driver plate can rotate relative to described fuselage at described thirdly place.

There is the unmanned plane of thrust amplifying mechanism and fixing device the most as claimed in claim 3, it is characterised in that

Described first drive link is hinged with described driver plate being rotationally connected at described first；

And/or,

Described second drive link is hinged with described driver plate being rotationally connected at described second point；

And/or,

Described driver plate and described fuselage described thirdly locate to be rotationally connected be hinged.

5. the unmanned plane with thrust amplifying mechanism and fixing device as described in claim 4 or 3, it is characterised in that

Described first point, described second point and the described thirdly position on described driver plate can form a triangle.

There is the unmanned plane of thrust amplifying mechanism and fixing device the most as claimed in claim 1, it is characterised in that described fixing device includes:

First sleeve；And

Fixed plate；Wherein, described first set jacket casing is located on described tail transmission shaft, described fixed plate is set on described first sleeve, and the outside of described fixed plate is fixing with described fuselage is connected, with the inside being fixed on described fuselage described tail transmission shaft consolidated by described first sleeve and described fixed plate, to prevent described tail transmission shaft from beating.

There is the unmanned plane of thrust amplifying mechanism and fixing device the most as claimed in claim 6, it is characterised in that described fixing device also includes:

Limiting plate, wherein,

Described fixed plate offers the first hole, location, and the aperture in described first hole, location, more than the excircle diameter of described first sleeve, makes described first sleeve be located in described first hole, location；

Described limiting plate offers the second hole, location, and the aperture in described second hole, location, more than the excircle diameter of described first sleeve, makes described first sleeve be located in described second hole, location；

Described limiting plate is connected by fixing with described fixed plate.

There is the unmanned plane of thrust amplifying mechanism and fixing device the most as claimed in claim 7, it is characterised in that

All offering screwed hole in described limiting plate and described fixed plate, the fixing connection between described limiting plate with described fixed plate is threaded.

There is the unmanned plane of thrust amplifying mechanism and fixing device the most as claimed in claim 8, it is characterised in that

The rounded shape of described fixed plate.