CN105752350B - Tail transmission shaft is in unmanned flight's equipment of fixed - Google Patents
Tail transmission shaft is in unmanned flight's equipment of fixed Download PDFInfo
- Publication number
- CN105752350B CN105752350B CN201610212335.9A CN201610212335A CN105752350B CN 105752350 B CN105752350 B CN 105752350B CN 201610212335 A CN201610212335 A CN 201610212335A CN 105752350 B CN105752350 B CN 105752350B
- Authority
- CN
- China
- Prior art keywords
- fixed
- transmission shaft
- fuselage
- tail
- tail transmission
- 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.)
- Expired - Fee Related
Links
- 230000005540 biological transmission Effects 0.000 title claims abstract description 88
- 238000010009 beating Methods 0.000 claims description 2
- 230000003321 amplification Effects 0.000 claims 1
- 230000003139 buffering effect Effects 0.000 claims 1
- 238000003199 nucleic acid amplification method Methods 0.000 claims 1
- 230000007812 deficiency Effects 0.000 abstract description 5
- 239000003921 oil Substances 0.000 description 14
- 238000001816 cooling Methods 0.000 description 13
- 230000000694 effects Effects 0.000 description 6
- 238000010276 construction Methods 0.000 description 5
- 230000035939 shock Effects 0.000 description 5
- 238000005299 abrasion Methods 0.000 description 4
- 239000012530 fluid Substances 0.000 description 4
- 208000032369 Primary transmission Diseases 0.000 description 3
- 239000012208 gear oil Substances 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
Abstract
The invention discloses unmanned flight's equipment that a kind of tail transmission shaft is in fixed, including fuselage, main rotor, tail rotor, steering wheel, engine and reduction box, the reduction box is connected with the engine, and the tail transmission shaft also includes in unmanned flight's equipment of fixed：Support component, the support component are arranged in the fuselage；Take-off and landing device, the take-off and landing device are fixed on the bottom of the fuselage；Thrust amplifying mechanism, the thrust amplifying mechanism are connected with the steering wheel；Fixing device, the fixing device are set on the tail transmission shaft, and are fixedly connected with the fuselage.The present invention is solved in the prior art because tail transmission shaft in tail transmission shaft has one section longer of axle body distance in the fuselage interior of unmanned flight's equipment of fixed, tail transmission shaft is very easy to produce bounce in flight course caused by and, is unfavorable for the technological deficiency of smooth flight of the tail transmission shaft in unmanned flight's equipment of fixed.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, and more particularly to tail transmission shaft is in unmanned flight's equipment of fixed.
Background technology
UAV referred to as " unmanned flight's equipment ", is filled using radio robot and the programme-control provided for oneself
Put the not manned aircraft of manipulation.Without driving cabin on machine, but automatic pilot, presetting apparatus, signal pickup assembly are installed
Etc. equipment.On ground, naval vessels or machine tool remote control station personnel are by equipment such as radars, and it is tracked, positioned, is remotely controlled, remote measurement
And Digital Transmission.It can take off as conventional airplane or be launched with booster rocket under wireless remotecontrol, also can be by machine tool
Aerial launch is taken to fly.
In the prior art, the tail transmission shaft inside depopulated helicopter is for the driving force of engine to be transferred into tail rotor
In, then drive tail rotor to be rotated.But because tail rotor is apart from the distant of engine, this allows for tail transmission shaft and existed
There is one section longer of axle body distance in the fuselage interior of unmanned flight's equipment of fixed in tail transmission shaft, non-in flight course
Chang Rongyi produces bounce, is unfavorable for smooth flight of the tail transmission shaft in unmanned flight's equipment of fixed.
The content of the invention
The present invention provides unmanned flight's equipment that a kind of tail transmission shaft is in fixed, solves in the prior art because tail passes
One section longer of axle body distance be present in fuselage interior in moving axis, and caused by flight course tail transmission shaft be very easy to produce
Bounce, it is unfavorable for the technological deficiency of the smooth flight of depopulated helicopter.
In order to solve the above technical problems, the invention provides unmanned flight's equipment that a kind of tail transmission shaft is in fixed, bag
Fuselage, main rotor, tail rotor, steering wheel, engine and reduction box are included, the reduction box is connected with the engine, wherein, it is described
Main rotor is rotatably fixed with the fuselage by final drive shaft and is connected；The tail rotor is fixedly installed on the tail of the fuselage
Portion, and be rotatably fixed and be connected with the fuselage by tail transmission shaft；The engine and the main rotor and the tailspin
The wing connects, and for driving the main rotor and the tail rotor to rotate, the steering wheel is fixed on the inside of the fuselage；The tail
Power transmission shaft also includes in unmanned flight's equipment of fixed：Support component, the support component are arranged in the fuselage, are used for
Support and the fixed final drive shaft；Take-off and landing device, the take-off and landing device are fixed on the bottom of the fuselage, to be passed to the tail
Moving axis is supported when landing in unmanned flight's equipment of fixed；Thrust amplifying mechanism, the thrust amplifying mechanism with it is described
Steering wheel connects, to amplify thrust caused by the steering wheel；Fixing device, the fixing device are set on the tail transmission shaft,
And be fixedly connected with the fuselage, the tail transmission shaft and the fuselage are relatively fixed.
Optionally, the support component includes：First bar；Second bar；And positioning seat；Wherein, one end of first bar
It is removably secured and is connected with the final drive shaft, the other end of first bar offers a groove；The one of second bar
End is set in the groove, and the end of one end of second bar is with the inwall of the groove, putting provided with one or more
Elastic ball so that the stress between first bar and second bar is buffered；The other end of second bar with it is described
One end rotation connection of positioning seat so that second bar is rotatable relative to the positioning seat.
Optionally：The other end of the positioning seat is fixed on the fuselage by the way that a resilient sleeve is flexible, so that described
Positioning seat is flexibly connected with the fuselage.
Optionally, the take-off and landing device includes：Undercarriage, the undercarriage are fixedly installed on the bottom of the fuselage；And
The first fixing hole is offered on the undercarriage；Brake wheel, the brake wheel is with the undercarriage at first fixing hole
Connection is removably secured, so that the tail transmission shaft passes through brake wheel in unmanned flight's equipment of fixed in descent
Directly contacted with ground.
Optionally, the brake wheel includes：Rotating wheel, the rotating wheel is connected with a rotary shaft, and the rotating wheel can
Center line around the rotary shaft rotates；Connecting plate, one end of the connecting plate are fixedly connected with the rotary shaft；Control-rod,
The control-rod is removably secured with the other end of the connecting plate and is connected；Wherein, the control-rod moves up or down,
To drive the connecting plate rotation to adjust height of the rotating wheel relative to the undercarriage.
Optionally, the thrust amplifying mechanism includes：First drive link, one end of first drive link are fixed on described
On fuselage；Second drive link, one end of second drive link are fixed on the steering wheel of the fuselage interior；And driver plate, institute
Driver plate is stated to be rotatablely connected with the other end of first drive link and the other end of second drive link respectively, and the biography
Dynamic plate is rotatablely connected with the fuselage；So that the steering wheel passes through the driver plate, biography to the active force of second drive link
It is handed to first drive link.
Optionally, the driver plate includes：First point；Second point；And thirdly；Wherein, first drive link is another
One end is rotatablely connected with the driver plate at described first point so that first drive link can be relative at described first point
First drive link is rotated；The other end of second drive link and driver plate company of rotation at the second point
Connect so that second drive link can be rotated at the second point relative to second drive link；The driver plate exists
Thirdly place is rotatablely connected with the fuselage, and the driver plate can be rotated at the thirdly place relative to the fuselage.
Optionally, the fixing device includes：First sleeve；And fixed plate；Wherein, the first set jacket casing is located at described
On tail transmission shaft, the fixed plate is set on first sleeve, and the outside of the fixed plate is fixed with the fuselage and connected
Connect, with the inside for being fixed on the fuselage for being consolidated the tail transmission shaft by first sleeve and the fixed plate, with
Prevent the tail transmission shaft from beating.
Optionally, the fixing device also includes：Limiting plate, wherein, the fixed plate offers the first positioning hole, described
The aperture of first positioning hole is more than the excircle diameter of first sleeve, first sleeve is located in first positioning
Kong Zhong；The limiting plate offers the second positioning hole, and the aperture of second positioning hole is more than the excircle of first sleeve
Diameter, first sleeve is set to be located in second positioning hole；The limiting plate is with the fixed plate by being fixedly connected.
Optionally, the limiting plate is with offering screwed hole, the limiting plate and the fixed plate in the fixed plate
Between be fixedly connected be threaded connection；The fixed plate is in rounded shape.
The application has the beneficial effect that：
(1) when the application is risen and fallen by setting brake wheel to reduce the tail transmission shaft in unmanned flight's equipment of fixed
The abrasion of the undercarriage, and the brake wheel is manually controllable, simple in construction and convenient dismounting.
(2) the application uses first bar with second bar by being socketed, and first bar and second bar
Between be provided with elastic ball, ensure that the reliability and stability of connection, on the one hand improve the shock resistance of the support component,
On the other hand, the cushion effect after member stress is added, avoids the support component from improving the support by large impact
The life-span of component, the safety and firmness operation for the final drive shaft finally realized.
(3) the application is connected by setting the first drive link, the second drive link and driver plate by steering wheel and the second drive link
Connect, the second drive link is connected with driver plate, and driver plate is connected with the first drive link, and such steering wheel acts on the second drive link
Power, pass sequentially through driver plate, the first drive link is ultimately applied to main rotor so that by the first drive link, the second drive link and biography
Dynamic plate forms primary transmission to amplify the thrust of the steering wheel, reduces 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 the outside of tail transmission shaft, Gu
Fixed board is set in the outside of the first sleeve so that the tail transmission shaft of fuselage interior is relatively fixed with fuselage, is effectively prevented
Tail transmission shaft is easily jumped in unmanned flight's equipment of fixed in flight course caused by tail transmission shaft is long
Dynamic technological deficiency.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, embodiment will be described below
In the required accompanying drawing used be briefly described, it should be apparent that, drawings in the following description be only the present invention some
Embodiment.
Fig. 1 is in the better embodiment of the application one, and tail transmission shaft is in unmanned flight's device structure schematic diagram of fixed；
Fig. 2 is in the another better embodiment of the application, and tail transmission shaft shows in the structure of unmanned flight's equipment of fixed
It is intended to；
Fig. 3 is the structural representation of fixing device in Fig. 1；
Fig. 4 is the structural representation of the application cooling device；
Fig. 5 is the structural representation of the application reduction box；
Fig. 6 is the partial view of support component in Fig. 2；
Fig. 7 is the structural representation of brake wheel in Fig. 1；
Fig. 8 is the right view of brake wheel in Fig. 7.
Embodiment
In order to be better understood from above-mentioned technical proposal, below in conjunction with Figure of description and specific embodiment to upper
Technical scheme is stated to be described in detail.
Fig. 1 and Fig. 2 are referred to, a kind of tail transmission shaft that the application provides is in unmanned flight's equipment 100 of fixed, described
Tail transmission shaft comprises at least fuselage 1, main rotor 2, tail rotor 3 and engine 4, the main rotation in unmanned flight's equipment of fixed
The wing 2 is rotated to provide lifting force, and the tail rotor 3 rotates rotates caused moment of torsion to offset the main rotor 2, to ensure
State the smooth flight of unmanned flight's equipment 100 that tail transmission shaft is in fixed.
Specifically, referring to Fig. 3, tail transmission shaft 7 is for the driving force of engine 4 to be transferred into tail rotor 3.By institute
Tail rotor 3 is stated apart from the distant of the engine 4, the tail transmission shaft 7 is in the unmanned flight that tail transmission shaft is in fixed
Equipment 100 in-flight easily produces bounce.And tail transmission shaft 7 is connected by the fixing device 8 that the application provides with fuselage 1, with solid
Determine tail transmission shaft 7, reduce the bounce amplitude of the tail transmission shaft 7.The fixing device 8 includes the first sleeve 82, fixed plate 81
And limiting plate 83, first sleeve 82 are set on the tail transmission shaft 7, the outside of the fixed plate 81 and the fuselage 1
It is fixedly connected, the fixed plate 81 offers the first positioning hole, and the aperture of first positioning hole is more than first sleeve 82
Excircle diameter, first sleeve 82 is located in first positioning hole.It is fixed that the limiting plate 83 offers second
Position hole, the aperture of second positioning hole are more than the excircle diameter of first sleeve 82, wear first sleeve 82
In second positioning hole.The limiting plate 83 is bolted with the fixed plate 81, and by bolt and screw thread
Surplus is provided between hole, reduces the bounce of tail transmission shaft 7, and is hardly damaged the tail transmission shaft 7.It is specifically, described spacing
Offer screwed hole on plate 83 and the fixed plate 81, and be located in using the bolt that surplus is left with the screwed hole described
With the fixation fixed plate 81 and the limiting plate 83 in screwed hole, the bounce of the tail transmission shaft 7 is reduced, and be hardly damaged
The tail transmission shaft 7.By setting the first sleeve 82, first sleeve 82 is set in the tail transmission shaft 7, to avoid
State tail transmission shaft 7 to wear with the direct friction of the limiting plate 83 or the fixed plate 81, improve the tail transmission shaft 7
Life-span.
Further, 4-5 is referred in the lump incorporated by reference to Fig. 1-2, the embodiment of the present application additionally provides a kind of cooling device.Slow down
Case 12 is connected with the engine 4, and the power for being exported to the engine 4 carries out regulator drive.The cooling device includes
At least one cooler bin 13, the cooler bin 13 are fuel-displaced including the first oil inlet and corresponding with first oil inlet first
Mouthful；The reduction box 12 includes the second oil inlet and second oil-out corresponding with second oil inlet；Described first enters
Hydraulic fluid port is connected with second oil-out, it is preferred that first oil inlet is connected with second oil-out by the first flexible pipe
Connect and connect；First oil-out connects with second oil inlet, it is preferred that first oil-out enters with described second
Hydraulic fluid port is connected and connected by the second flexible pipe.And the application on the gear shaft in the reduction box 12 by being arranged a worm screw knot
Structure so that the gear oil in the reduction box 12 is pressed onto in the cooler bin 13 during the worm structure rotation, makes the tail
Power transmission shaft is more abundant in the fuselage interior structure cooling of unmanned flight's equipment 100 of fixed.Certainly, reduction box 12 in the application
Fin is also respectively provided with the peripheral position of cooler bin 13, further to strengthen radiating effect.Preferably, the fin
It can be aluminium flake.
Based on same inventive concept, tail of the application in the tail transmission shaft in unmanned flight's equipment 100 of fixed
A cooling device is also equipped with the reduction box 12 that the structure division of rotor 3 is set, and common applied to tail transmission shaft is in fixed
The cooling device 100 of unmanned flight's equipment to cool down all be often the Local cooling used, by adding gear oil, and described in relying on
Dissipated applied to tail transmission shaft in the gear-box surface of reduction box 12 in the cooling device 100 of unmanned flight's equipment of fixed
Heat, type of cooling radiating is slow, and is only capable of to the cooling applied to tail transmission shaft in unmanned flight's equipment of fixed
Part in device 100 is radiated, and can not obtain good radiating effect.The application provide be in applied to tail transmission shaft
The cooling device 100 of unmanned flight's equipment of fixed also includes afterbody reduction box 12 and cooling device.Specifically, the deceleration
Case 12 is connected with the engine 4, and the power for being exported to the engine 4 carries out regulator drive.The tail that is applied to is driven
Axle also includes at least one cooler bin 13 in the cooling device 100 of unmanned flight's equipment of fixed, and the cooler bin 13 includes
First oil inlet and first oil-out corresponding with first oil inlet；The reduction box 12 include the second oil inlet and with
The second corresponding oil-out of second oil inlet；First oil inlet connects with second oil-out, it is preferred that institute
The first oil inlet is stated to be connected and connect by flexible pipe with second oil-out；First oil-out and second oil inlet
Connection, it is preferred that first oil-out is connected and connected by flexible pipe with second oil inlet.And the application passes through in institute
State and a worm structure is arranged on the gear shaft in reduction box 12 so that by the reduction box 12 during the worm structure rotation
Gear oil is pressed onto in the cooler bin 13, makes tail transmission shaft cold in the fuselage interior structure of unmanned flight's equipment 100 of fixed
It is more abundant.
Further, please continue to refer to Fig. 4, present invention also provides a kind of thrust amplifying mechanism 9, it is connected with steering wheel；Institute
State the flight attitude of unmanned flight's equipment 100 and track that steering wheel is used to control tail transmission shaft in fixed.The thrust enlarger
Structure 9 increases transmission of the one-level with the steering wheel to amplify thrust caused by steering wheel, reduces energy loss.Specifically, the thrust
Enlarger 9 includes the first drive link 91, the second drive link 93 and driver plate 92, and the driver plate 92 includes 1: 921, the
2: 923 and thirdly 922.The driver plate 92 is connected with first drive link 91 and second drive link 93 respectively；
One end of first drive link 91 is force side, and one end of first drive link 91 is fixedly connected with the fuselage 1, described
The other end of first drive link 91 is fixedly connected with the driver plate 92 at described 1: 921, and first drive link
91 can rotate relative to described 1: 921.One end of second drive link 93 is with the driver plate 92 in the second point 923
Place is fixedly connected, and second drive link 93 can rotate relative to the second point 923, the other end of second drive link 93
It is connected with the steering wheel.The driver plate 92 is connected at thirdly 922 with the fuselage 1, and the driver plate 92 can be relative
Thirdly 922 rotation.By setting the first drive link 91, the second drive link 93 and driver plate 92 to increase primary transmission to put
The thrust of the big steering wheel, reduces energy loss.
Preferably, first drive link 91 is hinged with the driver plate 92 at 1: 921；Second drive link
93 are hinged with the driver plate 92 at second point 923；The driver plate 92 is hinged with the fuselage 1 at thirdly 922.
Preferably, described 1: 921, second point 923 and thirdly 922 position it is triangular in shape.
Further, referring to Fig. 6, present invention also provides a kind of support component 11, applied to tail transmission shaft in fixation
Unmanned flight's equipment 100 of type, the support component 11 that the application provides are arranged in the fuselage 1, for supporting and fixing institute
State the spacing collar of final drive shaft 10.The support component 11 is stable and to the tail by using supported at three point, supporting construction
Power transmission shaft is in that can play a part of damping in the flight course of unmanned flight's equipment 100 of fixed.Specifically, the support component
11 include the first bar 111, the second bar 113 and positioning seat 114；One end of first bar 111 is removably solid with the fuselage 1
Fixed connection, the other end of first bar 111 offer a groove；One end of second bar 113 is set in the groove,
The end of one end of second bar 113 in the inwall of the groove with putting provided with one or more elastic balls 112 so that described
Stress between first bar 111 and second bar 113 is buffered, and reduces vibrations.
In the present embodiment, the elastic ball 112 is baton round；It is convex that the other end of second bar 113 is provided with first
Ear, first through hole is offered in the first lug, one end of the positioning seat 114 is provided with the second lug, second lug
On offer the second through hole matched with the first through hole, the first through hole is bolted with second through hole,
Second bar 113 is set to be rotated relative to the positioning seat 114.In order to further reduce the vibrations of the support component 11, institute
The other end for stating positioning seat 114 is also arranged with a resilient sleeve, and the resilient sleeve is I-shaped, and the resilient sleeve is set in described
On positioning seat 114, and the groove of the I-shaped of the resilient sleeve is fastened on the unmanned flight that the tail transmission shaft is in fixed
On the fuselage 1 of equipment 100, so that the positioning seat 114 is fixedly connected with the fuselage 1.
In the present embodiment, the resilient sleeve is rubber sleeve.By setting resilient sleeve to further increase the support
The shock resistance of component 11.First bar 111 and second bar 113 are by being socketed, and first bar 111 and described second
Elastic ball 112 is provided between bar 113, also improves the shock resistance of the support component 11.The application uses first bar
111 with second bar 113 by socket, and be provided with elastic ball 112 between first bar 111 and second bar 113,
Instead of it is conventional be hinged etc., first bar 111 and second bar 113 by pretightning force ensure that the reliability of connection with
Stability, the shock resistance of the support component 11 is on the one hand improved, on the other hand, adds the cushion effect after member stress,
The support component 11 is avoided by large impact, improves the life-span of the support component 11.
Further, Fig. 7-8 are referred in the lump incorporated by reference to Fig. 1-2, the present embodiment additionally provides a kind of take-off and landing device, for rising and falling
For device, including a undercarriage 5 and brake wheel 6, the undercarriage 5 are fixedly installed on the bottom of the fuselage 1.The brake
Wheel 6 is removably secured with the undercarriage 5 to be connected.The brake wheel 6 is provided for reducing the tail transmission shaft in fixation
The abrasion of unmanned flight's equipment 100 of type undercarriage 5 when rising and falling, and the brake wheel 6 is manually controllable, it is simple in construction and
Convenient dismounting.
Specifically, offering the first fixing hole on the undercarriage 5, first fixing hole is used for and the brake wheel 6
Be used cooperatively, to be plugged in by fixture in first fixing hole and the brake wheel 6, make the brake wheel 6 with it is described
Undercarriage 5 is fixedly connected.In the present embodiment, the fixture is specially latch.
Further, the brake wheel 6 includes rotating wheel 61, connecting plate 62 and control-rod 63.The rotating wheel 61 includes
One rotary shaft, the center line that the rotating wheel 61 can surround the rotary shaft rotate.One end of the connecting plate 62 and the rotation
Rotating shaft is fixedly connected；Control-rod, it is removably secured and is connected with the other end of the connecting plate 62；The control-rod 63 upwards or
Move down, the rotation of connecting plate 62 is adjusted the height of the rotating wheel 61.Specifically, one end of the connecting plate 62
The first connecting hole is offered, the other end of the connecting plate 62 offers the second connecting hole, is further opened with the connecting plate 62
Second fixing hole, second fixed hole position is between first connecting hole and second connecting hole.The control-rod 63
It is removably secured and is connected with the connecting plate 62, it is preferred that one end of the control-rod 63 is provided with a fixed part, described solid
Determine portion to be located in second connecting hole, and be fixedly connected by latch or clip with the connecting plate 62.The rotary shaft
It is located in first connecting hole, the rotary shaft is fixedly connected in first connection hole with the connecting plate 62, is made
Obtain the height that the rotating wheel 61 is can adjust when the connecting plate 62 rotates.The application uses connecting plate 62, rotary shaft and control
Bar 63 forms a linkage, and combines the position of the mobile adjustment brake wheel 6 of control-rod 63, simple in construction and convenient dismounting.
During operation, manually move up or down the control-rod 63, move down the rotating wheel 61, when described
The minimum altitude of rotating wheel 61 is less than the minimum altitude of the undercarriage 5, and the minimum altitude of the rotating wheel 61 and described
When falling the difference in height of the minimum altitude of frame 5 and being equal to or more than preset value, in first fixing hole and second fixing hole
Fixture is plugged, with the fixation brake wheel 6.The brake wheel 6 that the application is set, control manually and easy to disassemble, reduce institute
The abrasion of undercarriage 5 is stated, improves life-span of the tail transmission shaft in unmanned flight's equipment 100 of fixed.
The application's has the beneficial effect that：
1st, when the application is risen and fallen by setting brake wheel to reduce the tail transmission shaft in unmanned flight's equipment of fixed
The abrasion of the undercarriage, and the brake wheel is manually controllable, simple in construction and convenient dismounting.
2nd, the application using first bar and second bar by socket, and first bar and second bar it
Between be provided with elastic ball, ensure that the reliability and stability of connection, on the one hand improve the shock resistance of the support component, separately
On the one hand, the cushion effect after member stress is added, avoids the support component from improving the support group by large impact
The life-span of part, the safety and firmness operation for the final drive shaft finally realized.
3rd, the application is connected by setting the first drive link, the second drive link and driver plate by steering wheel and the second drive link
Connect, the second drive link is connected with driver plate, and driver plate is connected with the first drive link, and such steering wheel acts on the second drive link
Power, pass sequentially through driver plate, the first drive link is ultimately applied to main rotor so that by the first drive link, the second drive link and biography
Dynamic plate forms primary transmission to amplify the thrust of the steering wheel, reduces the loss of energy.
4th, the application is by setting up cooler bin and return duct so that the fluid of reduction box is in fuselage interior, by returning
Flow tube circulates in cooler bin and reduction box, increases travelling distance of the fluid in fuselage interior, meanwhile, in reduction box and
The peripheral position of cooler bin is provided with fin, further to be radiated to reduction box and cooler bin, solves in the prior art
Tail transmission shaft is in the bad technological deficiency of unmanned flight's device body internal heat dissipating effect of fixed.
5th, the application sets up the first sleeve and fixed plate by setting, and first set jacket casing is located at the outside of tail transmission shaft, Gu
Fixed board is set in the outside of the first sleeve so that the tail transmission shaft of fuselage interior is relatively fixed with fuselage, is effectively prevented
Tail transmission shaft is easily jumped in unmanned flight's equipment of fixed in flight course caused by tail transmission shaft is long
Dynamic technological deficiency.
It should be noted last that above embodiment is merely illustrative of the technical solution of the present invention and unrestricted,
Although the present invention is described in detail with reference to example, it will be understood by those within the art that, can be to the present invention
Technical scheme modify or equivalent substitution, without departing from the spirit and scope of technical solution of the present invention, it all should cover
Among scope of the presently claimed invention.
Claims (9)
1. a kind of tail transmission shaft be in fixed unmanned flight's equipment, including fuselage, main rotor, tail rotor, steering wheel, engine and
Reduction box, the reduction box are connected with the engine, wherein, the main rotor is rotatable by final drive shaft and the fuselage
Ground is fixedly connected；The tail rotor is fixedly installed on the afterbody of the fuselage, and rotatable by tail transmission shaft and the fuselage
Ground is fixedly connected；The engine is connected with the main rotor and the tail rotor, for driving the main rotor and the tail
Rotor wing rotation, the steering wheel are fixed on the inside of the fuselage；Characterized in that, the tail transmission shaft in fixed nobody fly
Row equipment also includes：
Support component, the support component are arranged in the fuselage, for supporting and fixing the final drive shaft；
Take-off and landing device, the take-off and landing device are fixed on the bottom of the fuselage, with to the tail transmission shaft be in fixed nobody
Flight equipment is supported when landing；
Thrust amplifying mechanism, the thrust amplifying mechanism are connected with the steering wheel, to amplify thrust caused by the steering wheel；
Fixing device, the fixing device are set on the tail transmission shaft, and are fixedly connected with the fuselage, by the tail
Power transmission shaft and the fuselage are relatively fixed；
The support component includes：
First bar；
Second bar；And
Positioning seat；Wherein, one end of first bar is removably secured with the final drive shaft is connected, first bar it is another
One end offers a groove；One end of second bar is set in the groove, the end of one end of second bar and institute
In the inwall for stating groove, put provided with one or more elastic balls so that the stress between first bar and second bar obtains
To buffering；The other end of second bar is rotatablely connected with one end of the positioning seat so that second bar is relative to described
Positioning seat is rotatable.
2. tail transmission shaft as claimed in claim 1 is in unmanned flight's equipment of fixed, it is characterised in that：
The other end of the positioning seat is fixed on the fuselage by the way that a resilient sleeve is flexible so that the positioning seat with it is described
Fuselage is flexibly connected.
3. tail transmission shaft as claimed in claim 1 is in unmanned flight's equipment of fixed, it is characterised in that the take-off and landing device
Including：
Undercarriage, the undercarriage are fixedly installed on the bottom of the fuselage；And the first fixing hole is offered on the undercarriage；
Brake wheel, the brake wheel is removably secured at first fixing hole with the undercarriage and is connected, so that described
Tail transmission shaft is directly contacted in descent in unmanned flight's equipment of fixed by brake wheel with ground.
4. tail transmission shaft as claimed in claim 3 is in unmanned flight's equipment of fixed, it is characterised in that the brake wheel bag
Include：
Rotating wheel, the rotating wheel is connected with a rotary shaft, and the rotating wheel can rotate around the center line of the rotary shaft；
Connecting plate, one end of the connecting plate are fixedly connected with the rotary shaft；
Control-rod, the control-rod are removably secured with the other end of the connecting plate and are connected；
Wherein, the control-rod moves up or down, with drive connecting plate rotation adjust the rotating wheel relative to
The height of the undercarriage.
5. tail transmission shaft as claimed in claim 1 is in unmanned flight's equipment of fixed, it is characterised in that the thrust amplification
Mechanism includes：
First drive link, one end of first drive link are fixed on the fuselage；
Second drive link, one end of second drive link are fixed on the steering wheel of the fuselage interior；And
Driver plate, the driver plate rotate with the other end of first drive link and the other end of second drive link respectively
Connection, and the driver plate is rotatablely connected with the fuselage；So that the steering wheel passes through to the active force of second drive link
The driver plate, it is transferred to first drive link.
6. tail transmission shaft as claimed in claim 5 is in unmanned flight's equipment of fixed, it is characterised in that the driver plate bag
Include：
First point；
Second point；And
Thirdly；Wherein, the other end of first drive link is rotatablely connected with the driver plate at described first point so that
First drive link can be rotated at described first point relative to first drive link；Second drive link it is another
End is rotatablely connected with the driver plate at the second point so that second drive link can relative institute at the second point
The second drive link is stated to be rotated；The driver plate is rotatablely connected at thirdly place with the fuselage, and the driver plate is in institute
Stating thirdly place can be rotated relative to the fuselage.
7. tail transmission shaft as claimed in claim 1 is in unmanned flight's equipment of fixed, it is characterised in that the fixing device
Including：
First sleeve；And
Fixed plate；Wherein, the first set jacket casing is located on the tail transmission shaft, and the fixed plate is set in first sleeve
On, and the outside of the fixed plate is fixedly connected with the fuselage, described in being incited somebody to action by first sleeve and the fixed plate
The firm inside for being fixed on the fuselage of tail transmission shaft, to prevent the tail transmission shaft from beating.
8. tail transmission shaft as claimed in claim 7 is in unmanned flight's equipment of fixed, it is characterised in that the fixing device
Also include：
Limiting plate, wherein,
The fixed plate offers the first positioning hole, and the aperture of first positioning hole is straight more than the excircle of first sleeve
Footpath, first sleeve is set to be located in first positioning hole；
The limiting plate offers the second positioning hole, and the aperture of second positioning hole is straight more than the excircle of first sleeve
Footpath, first sleeve is set to be located in second positioning hole；
The limiting plate is with the fixed plate by being fixedly connected.
9. tail transmission shaft as claimed in claim 8 is in unmanned flight's equipment of fixed, it is characterised in that
The limiting plate in the fixed plate with offering screwed hole, the fixed company between the limiting plate and the fixed plate
It is threaded connection to connect；
The fixed plate is in rounded shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610212335.9A CN105752350B (en) | 2016-04-07 | 2016-04-07 | Tail transmission shaft is in unmanned flight's equipment of fixed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610212335.9A CN105752350B (en) | 2016-04-07 | 2016-04-07 | Tail transmission shaft is in unmanned flight's equipment of fixed |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105752350A CN105752350A (en) | 2016-07-13 |
| CN105752350B true CN105752350B (en) | 2018-03-02 |
Family
ID=56334422
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610212335.9A Expired - Fee Related CN105752350B (en) | 2016-04-07 | 2016-04-07 | Tail transmission shaft is in unmanned flight's equipment of fixed |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105752350B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111306255B (en) * | 2020-02-24 | 2021-09-17 | 北京中航智科技有限公司 | Transmission system |
| CN112238948A (en) * | 2020-10-16 | 2021-01-19 | 中国直升机设计研究所 | Quick-release helicopter tail transmission shaft assembly |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201457735U (en) * | 2009-06-29 | 2010-05-12 | 佛山市安尔康姆航拍科技有限公司 | Wheel-ski mixing type undercarriage for unmanned aerial vehicle |
| CN201526610U (en) * | 2009-08-14 | 2010-07-14 | 江苏达胜加速器制造有限公司 | Accelerator transmission shaft |
| FR2976553A1 (en) * | 2011-06-20 | 2012-12-21 | Cassidian | SYSTEM FOR INTEGRATING A DIESEL ENGINE IN A DRONE |
| CN203727646U (en) * | 2014-03-13 | 2014-07-23 | 中国科学院沈阳自动化研究所 | Unmanned helicopter |
| CN205652373U (en) * | 2016-04-07 | 2016-10-19 | 易瓦特科技股份公司 | Tail transmission shaft is unmanned aerial vehicle equipment of fixed |
-
2016
- 2016-04-07 CN CN201610212335.9A patent/CN105752350B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN105752350A (en) | 2016-07-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US2318259A (en) | Direct-lift aircraft | |
| US10625846B2 (en) | Adaptable rotor control system for a variable number of blades | |
| CN105836116B (en) | Cooling type unmanned plane | |
| US10745120B2 (en) | Adaptable rotor control system for a variable number of blades | |
| CN105752350B (en) | Tail transmission shaft is in unmanned flight's equipment of fixed | |
| US20230356833A1 (en) | Aircraft propulsion and torque mitigation technologies | |
| CN105752321B (en) | Unmanned plane take-off and landing device and unmanned plane | |
| US3254725A (en) | Aircraft propulsion system | |
| US3185408A (en) | Aircraft propulsion system | |
| CN205652347U (en) | Cooling type unmanned aerial vehicle | |
| CN105752323B (en) | Land wear-resistance unmanned plane | |
| CN105752324B (en) | Unmanned flight's equipment | |
| CN105752349B (en) | Depopulated helicopter | |
| CN205652342U (en) | Unmanned aerial vehicle with landing gear and cooling device | |
| CN205652373U (en) | Tail transmission shaft is unmanned aerial vehicle equipment of fixed | |
| CN205652359U (en) | Type unmanned aerial vehicle takes precautions against earthquakes | |
| CN205707383U (en) | Depopulated helicopter | |
| CN205652345U (en) | Unmanned aerial vehicle equipment | |
| CN205652375U (en) | Unmanned aerial vehicle with supporting component and fixing device | |
| CN105857602B (en) | Shockproof unmanned plane | |
| CN205707307U (en) | Landing wear-resistance unmanned plane | |
| CN205872450U (en) | Unmanned aerial vehicle landing gear and unmanned aerial vehicle | |
| CN205707347U (en) | It is applied to the fixing device of depopulated helicopter | |
| CN205652357U (en) | Unmanned aerial vehicle with thrust mechanism of amplification and cooling device | |
| CN205707308U (en) | There is the unmanned plane of take-off and landing device and thrust amplifying mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information |
Address after: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Applicant after: Easy Technology Co Ltd Address before: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Applicant before: EWATT CO., LTD. |
|
| COR | Change of bibliographic data | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180302 Termination date: 20190407 |