CN205652373U - Tail transmission shaft is unmanned aerial vehicle equipment of fixed - Google Patents
Tail transmission shaft is unmanned aerial vehicle equipment of fixed Download PDFInfo
- Publication number
- CN205652373U CN205652373U CN201620283240.1U CN201620283240U CN205652373U CN 205652373 U CN205652373 U CN 205652373U CN 201620283240 U CN201620283240 U CN 201620283240U CN 205652373 U CN205652373 U CN 205652373U
- Authority
- CN
- China
- Prior art keywords
- transmission shaft
- fixed
- fuselage
- tail transmission
- bar
- 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.)
- Withdrawn - After Issue
Links
Landscapes
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
Abstract
The utility model discloses a tail transmission shaft is unmanned aerial vehicle equipment of fixed, including fuselage, main rotor, the tailspin wing, steering wheel, engine and reducing gear box, the reducing gear box with the engine is connected, tail transmission shaft is unmanned aerial vehicle equipment of fixed still includes: the supporting component, the supporting component sets up in the fuselage, landing gear, landing gear is fixed in the bottom of fuselage, the thrust mechanism of amplification, the thrust mechanism of amplification with the steering wheel is connected, a fixing device, the fixing device cover is established on the tail transmission shaft, and with fuselage fixed connection. The utility model provides a because there is one section longer axle body distance in the tail transmission shaft in that tail transmission shaft is unmanned aerial vehicle equipment of fixed's fuselage is inside among the prior art, and producing very easily at flight in -process tail transmission shaft of causing is beated, is unfavorable for the technical defect of tail transmission shaft is unmanned aerial vehicle equipment of fixed's smooth flight.
Description
Technical field
This utility model relates to unmanned air vehicle technique field, is the unmanned of fixed pattern particularly to tail transmission shaft
Flight equipment.
Background technology
UAV is called for short " unmanned flight's equipment ", is to utilize radio robot and provide for oneself
Presetting apparatus handle the most manned aircraft.Without driving cabin on machine, but be provided with automatic pilot,
The equipment such as presetting apparatus, signal pickup assembly.On ground, naval vessels or machine tool remote control station personnel lead to
Cross the equipment such as radar, it be tracked, position, remote control, remote measurement and Digital Transmission.Can be wireless
Take off as conventional airplane under electrical remote control or launch with booster rocket, it is possible to being taken to sky by machine tool
Middle input is flown.
In prior art, the tail transmission shaft within depopulated helicopter is for being passed by the driving force of electromotor
Move in tail rotor, then drive tail rotor to rotate.But due to tail rotor distance electromotor away from
From farther out, this allows for tail transmission shaft in the fuselage of unmanned flight's equipment that tail transmission shaft is fixed pattern
There is the axle body distance of a section longer in portion, is very easy to generation and beats, be unfavorable for tail in flight course
Power transmission shaft is the smooth flight of unmanned flight's equipment of fixed pattern.
Utility model content
This utility model a kind of tail transmission shaft of offer is unmanned flight's equipment of fixed pattern, solves existing
The axle body distance of one section longer is there is in fuselage interior in technology due to tail transmission shaft, and flying of causing
During row, tail transmission shaft is very easy to generation and beats, and is unfavorable for the skill of the smooth flight of depopulated helicopter
Art defect.
For solving above-mentioned technical problem, this utility model provides the nothing that a kind of tail transmission shaft is fixed pattern
People's flight equipment, 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 can by final drive shaft and described fuselage
Fixing connection rotatably；Described tail rotor is fixedly installed on the afterbody of described fuselage, and by tail transmission
Axle is rotatably fixed with described fuselage and is connected；Described electromotor and described main rotor and described tail rotor
Connecting, be used for driving described main rotor and described tail rotor to rotate, described steering wheel is fixed on described fuselage
Inside；Described tail transmission shaft is that unmanned flight's equipment of fixed pattern also includes: a support component, described
Prop up support component to be arranged in described fuselage, be used for supporting and fix described final drive shaft；Take-off and landing device,
Described take-off and landing device is fixed on the bottom of described fuselage, to described tail transmission shaft to be the unmanned of fixed pattern
It is supported during flight equipment landing；Thrust amplifying mechanism, described thrust amplifying mechanism and described steering wheel
Connect, to amplify the thrust that described steering wheel produces；Fixing device, described fixing device is set in described
On tail transmission shaft, and fixing with described fuselage it is connected, so that described tail transmission shaft is relative with described fuselage
Fixing.
Optionally, described support component includes: the first bar；Second bar；And positioning seat；Wherein, institute
State one end of the first bar to be removably secured with described final drive shaft and be connected, the other end of described first bar
Offer a groove；One end of described second bar is set in described groove, one end of described second bar
End and described groove inwall in, put and be provided with one or more elastic ball so that described first bar
And the stress between described second bar is buffered；The other end of described second bar and described positioning seat
One end is rotationally connected so that described second bar is rotatable relative to described positioning seat.
It is optional: the other end of described positioning seat is fixed on described fuselage by a resilient sleeve flexibility,
So that described positioning seat flexibly connects with described fuselage.
Optionally, described take-off and landing device includes: undercarriage, and described undercarriage is fixedly installed on described machine
The bottom of body；And offer the first fixing hole on described undercarriage；Brake wheel, described brake wheel and institute
State undercarriage and be removably secured connection at described first fixing hole, so that described tail transmission shaft is in solid
Unmanned flight's equipment of sizing is directly contacted with ground by brake wheel in descent.
Optionally, described brake wheel includes: rotate wheel, and described rotation wheel connection has a rotary shaft, and
The described wheel that rotates can rotate around the centrage of described rotary shaft；Connecting plate, one end of described connecting plate with
Described rotary shaft is fixing to be connected；Controlling bar, described control bar is detachable with the other end of described connecting plate
Fix connection；Wherein, described control bar moves up or down, to drive described connecting plate to rotate
Regulate described rotation and take turns the height relative to described undercarriage.
Optionally, described thrust amplifying mechanism includes: the first drive link, the one of described first drive link
End is fixed on described fuselage；Second drive link, described machine is fixed in one end of described second drive link
On steering wheel within body；And driver plate, described driver plate respectively with the other end of described first drive link
It is rotationally connected with the other end of described second drive link, and described driver plate is rotationally connected with described fuselage；
Make described steering wheel to the active force of described second drive link by described driver plate, be transferred to described the
One drive link.
Optionally, described driver plate includes: the first point；Second point；And thirdly；Wherein, described
The other end of the first drive link is rotationally connected at described first with described driver plate so that described
One drive link can rotate relative to described first drive link at described first；Described second transmission
The other end of bar 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 thirdly being located
It is rotationally connected with described fuselage, and described driver plate can be carried out by the most described fuselage at described thirdly place
Rotate.
Optionally, described fixing device includes: the first sleeve；And fixed plate；Wherein, described first
Sleeve is set on described tail transmission shaft, and described fixed plate is set on described first sleeve, and described
The outside of fixed plate is fixing with described fuselage to be connected, to be incited somebody to action by described first sleeve and described fixed plate
The inside being fixed on described fuselage that described tail transmission shaft is firm, to prevent described tail transmission shaft from jumping
Dynamic.
Optionally, described fixing device also includes: limiting plate, and wherein, described fixed plate offers
One hole, location, the aperture in described first hole, location, more than the excircle diameter of described first sleeve, makes institute
State the first sleeve to be located in described first hole, location；Described limiting plate offers the second hole, location, institute
State the aperture excircle diameter more than described first sleeve in the second hole, location, make described first sleeve wear
It is located in described second hole, location；Described limiting plate is connected by fixing with described fixed plate.
Optionally, described limiting plate and described fixed plate all offer screwed hole, described limiting plate with
Fixing connection between described fixed plate is threaded；The rounded shape of described fixed plate.
The application has the beneficial effect that:
(1) the application reduces the unmanned flight that described tail transmission shaft is fixed pattern set by arranging brake wheel
The standby abrasion of described undercarriage when rising and falling, and described brake wheel is manually controllable, simple in construction and conveniently tearing open
Unload.
(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
The shock resistance of described support component, on the other hand, adds the cushion effect after member stress, it is to avoid described
Support component, by crossing large impact, improves the life-span of described support component, the final final drive shaft realized
Safety and firmness run.
(3) the application is by arranging the first drive link, the second drive link and driver plate, by steering wheel and
Two drive links connect, 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 is ultimately applied to main rotation
The wing so that be made up of primary transmission the first drive link, the second drive link and driver plate to amplify described steering wheel
Thrust, decrease the loss of energy.
(4) the application sets up the first sleeve and fixed plate by setting, and first set jacket casing is located at tail transmission shaft
Outside, fixed plate is set in the outside of the first sleeve so that by tail transmission shaft and the fuselage of fuselage interior
Be relatively fixed, be effectively prevented unmanned flight's equipment that tail transmission shaft is fixed pattern in flight course by
And the technological deficiency easily beated that cause long in tail transmission shaft.
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, and tail transmission shaft is unmanned flight's equipment of fixed pattern
Structural representation；
Fig. 2 is in the another better embodiment of the application, and tail transmission shaft is that the unmanned flight of fixed pattern sets
Standby structural representation；
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, a kind of tail transmission shaft that the application provides is the unmanned flight of fixed pattern
Equipment 100, described tail transmission shaft is that unmanned flight's equipment of fixed pattern at least includes fuselage 1, main rotor
2, tail rotor 3 and electromotor 4, described main rotor 2 rotates to provide lifting force, described tail rotor 3
Rotate to offset the moment of torsion produced when described main rotor 2 rotates, to ensure that described tail transmission shaft is in fixing
Unmanned flight's equipment 100 smooth flight of type.
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 unmanned flight's equipment 100 that tail transmission shaft is fixed pattern beats.And this
Tail transmission shaft 7 is connected by the fixing device 8 that application provides with fuselage 1, with fixing tail transmission shaft 7,
Reduce the amplitude of beating of described tail transmission shaft 7.Described fixing device 8 includes the first sleeve 82, fixes
Plate 81 and limiting plate 83, described first sleeve 82 is set on described tail transmission shaft 7, described fixing
The outside of plate 81 is fixing with described fuselage 1 to be connected, and described fixed plate 81 offers the first hole, location,
The aperture in described first hole, location, more than the excircle diameter of described first sleeve 82, makes described first set
Cylinder 82 is located in described first hole, location.Described limiting plate 83 offers the second hole, location, described
The aperture of the second hole, location, more than the excircle diameter of described first sleeve 82, makes described first sleeve
82 are located in described second hole, location.Described limiting plate 83 is with described fixed plate 81 by bolt even
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
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 tail transmission shaft in
The fuselage interior structure cooling of unmanned flight's equipment 100 of fixed pattern is more abundant.Certainly, in the application
The peripheral position of reduction box 12 and cooler bin 13 is also respectively provided with fin, dissipates with further reinforcement
Thermal effect.As preferably, this fin can be aluminium flake.
Based on same utility model design, the application is that nobody of fixed pattern flies at described tail transmission shaft
It is also equipped with a chiller at the reduction box 12 that tail rotor 3 structure division of row equipment 100 is arranged,
Common it be applied to the chiller 100 of unmanned flight's equipment that tail transmission shaft is fixed pattern and often cool down
It is all the Local cooling used, by adding gear oil, and is applied to tail transmission shaft described in dependence in fixing
In the chiller 100 of unmanned flight's equipment of type, dispel the heat in the gear-box surface of reduction box 12, should
Type of cooling heat radiation is slow, and is only capable of being applied to the unmanned flight that tail transmission shaft is fixed pattern set described
Dispelling the heat in the standby local in chiller 100, can not obtain good radiating effect.This Shen
The chiller 100 of unmanned flight's equipment that tail transmission shaft is fixed pattern that is applied to that please provide also includes
Afterbody reduction box 12 and chiller.Concrete, described reduction box 12 is connected with described electromotor 4,
Power for exporting described electromotor 4 carries out regulator drive.The described tail transmission shaft that is applied to is in fixing
The chiller 100 of unmanned flight's equipment of type also includes at least one cooler bin 13, described cooler bin
13 include the first oil-in and first oil-out corresponding with described first oil-in；Described reduction box
12 include the second oil-in and second oil-out corresponding with described second oil-in；Described first enters
Hydraulic fluid port connects with described second oil-out, it is preferred that described first oil-in and described second oil-out
By hose connection and connect；Described first oil-out connects with described second oil-in, it is preferred that
Described first oil-out passes through hose connection with described second oil-in and connects.And the application passes through
A sheathed worm structure on gear shaft in described reduction box 12 so that will when described worm structure rotates
Gear oil in described reduction box 12 is pressed onto in described cooler bin 13, and making tail transmission shaft is fixed pattern
The fuselage interior structure cooling of unmanned flight's equipment 100 is 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 flies for controlling unmanned flight's equipment 100 that tail transmission shaft is fixed pattern
Attitude and track.Described thrust amplifying mechanism 9 increases the one-level transmission with described steering wheel to amplify steering wheel
The thrust produced, reduces energy loss.Concrete, described thrust amplifying mechanism 9 includes the first transmission
Bar 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 described
Two drive links 93 connect；One end of described first drive link 91 is force side, described first drive link
One end of 91 is fixing with described fuselage 1 to be connected, the other end of described first drive link 91 and described biography
Dynamic plate 92 is fixing at described 1: 921 to be connected, and described first drive link 91 can be relatively described
1: 921 rotates.One end of described second drive link 93 and described driver plate 92 are described second
Fix at point 923 and connect, and described second drive link 93 can rotate relative to described second point 923, institute
The other end stating the 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 tail
Power transmission shaft is unmanned flight's equipment 100 of fixed pattern, and the support component 11 that the application provides is arranged on institute
State in fuselage 1, for supporting and fix the spacing collar of described final drive shaft 10.Described support component
11 by using supported at three point, and supporting construction is stable and be that nobody of fixed pattern flies to described tail transmission shaft
Row equipment 100 flight course can play the effect of damping.Concrete, described support component 11 includes
First bar the 111, second bar 113 and positioning seat 114；One end of described first bar 111 and described fuselage
1 is removably secured connection, and the other end of described first bar 111 offers a groove；Described second
One end of bar 113 is set in described groove, and the end of one end of described second bar 113 is recessed with described
Put in the inwall of groove and be provided with one or more elastic ball 112 so that described first bar 111 and described the
Stress between two bars 113 is buffered, and reduces 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
Tail transmission shaft is on the fuselage 1 of unmanned flight's equipment 100 of fixed pattern, so that described positioning seat 114
Fix with described fuselage 1 and be 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 reduces the unmanned flight that described tail transmission shaft is fixed pattern and sets
The abrasion of described undercarriage 5 when rising and falling for 100, and described brake wheel 6 is manually controllable, structure letter
Single and convenient dismounting.
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, improves the life-span that described tail transmission shaft is unmanned flight's equipment 100 of fixed pattern.
The application has the beneficial effect that:
1, the application reduces, by arranging brake wheel, the unmanned flight that described tail transmission shaft is fixed pattern
The abrasion of described undercarriage when equipment rises and falls, and described brake wheel is manually controllable, simple in construction and side
Just dismantle.
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 the unmanned flight that tail transmission shaft in prior art is fixed pattern and set
The technological deficiency that standby host 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 unmanned flight's equipment that tail transmission shaft is fixed pattern and was flying
And the technological deficiency easily beated that cause long due to tail transmission shaft in journey.
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 (10)
1. tail transmission shaft is unmanned flight's equipment of fixed pattern, including fuselage, main rotor, tailspin
The wing, steering wheel, electromotor and reduction box, described reduction box is connected with described electromotor, wherein, described
Main rotor is rotatably fixed with described fuselage by final drive shaft and is connected；Described tail rotor is fixedly installed
At the afterbody of described fuselage, and it 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 tailspin
The wing rotates, and described steering wheel is fixed on the inside of described fuselage；It is characterized in that, described tail transmission shaft in
Unmanned flight's equipment of fixed pattern also includes:
Propping up support component, described support component is arranged in described fuselage, is used for supporting and fix described master
Power transmission shaft；
Take-off and landing device, described take-off and landing device is fixed on the bottom of described fuselage, with to described tail transmission shaft
Unmanned flight's equipment in fixed pattern is supported when landing；
Thrust amplifying mechanism, described thrust amplifying mechanism is connected with described steering wheel, to amplify described steering wheel
The thrust produced；
Fixing device, described fixing device is set on described tail transmission shaft, and fixes with described fuselage
Connect, so that described tail transmission shaft and described fuselage are relatively fixed.
2. tail transmission shaft as claimed in claim 1 is unmanned flight's equipment of fixed pattern, and its feature exists
In, described support component includes:
First bar；
Second bar；And
Positioning seat；Wherein, one end of described first bar is removably secured with described final drive shaft and is connected,
The other end of described first bar offers a groove；One end of described second bar is set in described groove,
The end of one end of described second bar, with the inwall of described groove, is put and is provided with one or more elastic ball,
Stress between described first bar and described second bar is buffered；The other end of described second bar
It is rotationally connected with one end of described positioning seat so that described second bar is rotatable relative to described positioning seat.
3. tail transmission shaft as claimed in claim 2 is unmanned flight's equipment of fixed pattern, and its feature exists
In:
The other end of described positioning seat is by flexible being fixed on described fuselage of a resilient sleeve, so that institute
State positioning seat to flexibly connect with described fuselage.
4. tail transmission shaft as claimed in claim 1 is unmanned flight's equipment of fixed pattern, and its feature exists
In, described take-off and landing device includes:
Undercarriage, described undercarriage is fixedly installed on the bottom of described fuselage；And open on described undercarriage
It is provided with the first fixing hole；
Brake wheel, described brake wheel is removably secured at described first fixing hole with described undercarriage
Connect, so that described tail transmission shaft is unmanned flight's equipment of fixed pattern passes through brake in descent
Wheel directly contacts with ground.
5. tail transmission shaft as claimed in claim 4 is unmanned flight's equipment of fixed pattern, and its feature exists
In, described brake wheel includes:
Rotating wheel, described rotation wheel connection has a rotary shaft, and described rotation wheel can be around described rotary shaft
Centrage rotate；
Connecting plate, one end of described connecting plate is fixing with described rotary shaft to be connected；
Controlling bar, described control bar is removably secured with the other end of described connecting plate and is connected；
Wherein, described control bar moves up or down, and regulates institute to drive described connecting plate to rotate
State the height rotating wheel relative to described undercarriage.
6. tail transmission shaft as claimed in claim 1 is unmanned flight's equipment of fixed pattern, and its feature exists
In, 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 the steering wheel of described fuselage interior；
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.
7. tail transmission shaft as claimed in claim 6 is unmanned flight's equipment of fixed pattern, and its feature exists
In, 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.
8. tail transmission shaft as claimed in claim 1 is unmanned flight's equipment of fixed pattern, and its feature exists
In, 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.
9. tail transmission shaft as claimed in claim 8 is unmanned flight's equipment of fixed pattern, and its feature exists
In, 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.
10. tail transmission shaft as claimed in claim 9 is unmanned flight's equipment of fixed pattern, its feature
It is,
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；
The rounded shape of described fixed plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620283240.1U CN205652373U (en) | 2016-04-07 | 2016-04-07 | Tail transmission shaft is unmanned aerial vehicle equipment of fixed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620283240.1U CN205652373U (en) | 2016-04-07 | 2016-04-07 | Tail transmission shaft is unmanned aerial vehicle equipment of fixed |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205652373U true CN205652373U (en) | 2016-10-19 |
Family
ID=57390799
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620283240.1U Withdrawn - After Issue CN205652373U (en) | 2016-04-07 | 2016-04-07 | Tail transmission shaft is unmanned aerial vehicle equipment of fixed |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205652373U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105752350A (en) * | 2016-04-07 | 2016-07-13 | 湖北易瓦特科技股份有限公司 | Unmanned aerial equipment with fixed tail transmission shaft |
-
2016
- 2016-04-07 CN CN201620283240.1U patent/CN205652373U/en not_active Withdrawn - After Issue
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105752350A (en) * | 2016-04-07 | 2016-07-13 | 湖北易瓦特科技股份有限公司 | Unmanned aerial equipment with fixed tail transmission shaft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111003166A (en) | Tandem electric double-rotor helicopter and control system thereof | |
| CN105836116A (en) | Cooled unmanned plane | |
| US3254725A (en) | Aircraft propulsion system | |
| CN205652347U (en) | Cooling type unmanned aerial vehicle | |
| US3185408A (en) | Aircraft propulsion system | |
| CN205652373U (en) | Tail transmission shaft is unmanned aerial vehicle equipment of fixed | |
| CN105752321A (en) | Unmanned aerial vehicle landing device and unmanned aerial vehicle | |
| CN205652342U (en) | Unmanned aerial vehicle with landing gear and cooling device | |
| CN205652375U (en) | Unmanned aerial vehicle with supporting component and fixing device | |
| CN205652359U (en) | Type unmanned aerial vehicle takes precautions against earthquakes | |
| CN205652345U (en) | Unmanned aerial vehicle equipment | |
| CN205707383U (en) | Depopulated helicopter | |
| CN105752350B (en) | Tail transmission shaft is in unmanned flight's equipment of fixed | |
| CN205707307U (en) | Landing wear-resistance unmanned plane | |
| CN206766338U (en) | One kind stops stable unmanned plane | |
| CN205652343U (en) | Unmanned aerial vehicle with landing gear and fixing device | |
| CN205652344U (en) | Unmanned aerial vehicle with landing gear and supporting component | |
| CN205652353U (en) | Unmanned aerial vehicle with cooling device and fixing device | |
| CN205872450U (en) | Unmanned aerial vehicle landing gear and unmanned aerial vehicle | |
| CN205652374U (en) | Unmanned aerial vehicle with supporting component and cooling device | |
| CN205652340U (en) | Unmanned aerial vehicle with supporting component and thrust mechanism of amplification | |
| CN205652349U (en) | Unmanned aerial vehicle with thrust mechanism of amplification and fixing device | |
| CN205707347U (en) | It is applied to the fixing device of depopulated helicopter | |
| CN205707308U (en) | There is the unmanned plane of take-off and landing device and thrust amplifying mechanism | |
| CN205652357U (en) | Unmanned aerial vehicle with thrust mechanism of amplification and cooling device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20161019 Effective date of abandoning: 20180302 |
|
| AV01 | Patent right actively abandoned |