CN105752323B - Land wear-resistance unmanned plane - Google Patents
Land wear-resistance unmanned plane Download PDFInfo
- Publication number
- CN105752323B CN105752323B CN201610211879.3A CN201610211879A CN105752323B CN 105752323 B CN105752323 B CN 105752323B CN 201610211879 A CN201610211879 A CN 201610211879A CN 105752323 B CN105752323 B CN 105752323B
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- CN
- China
- Prior art keywords
- fuselage
- drive link
- unmanned plane
- landing
- 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.)
- Expired - Fee Related
Links
- 238000001816 cooling Methods 0.000 claims abstract description 22
- 230000005540 biological transmission Effects 0.000 claims description 23
- 239000012530 fluid Substances 0.000 claims description 11
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 230000003139 buffering effect Effects 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 9
- 238000005299 abrasion Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 abstract description 4
- 239000003921 oil Substances 0.000 description 12
- 238000010276 construction Methods 0.000 description 5
- 230000035939 shock Effects 0.000 description 5
- 208000032369 Primary transmission Diseases 0.000 description 3
- 230000007812 deficiency Effects 0.000 description 3
- 239000012208 gear oil Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000010009 beating Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- 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
-
- 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
-
- 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)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Braking Arrangements (AREA)
Abstract
The invention discloses one kind landing wear-resistance unmanned plane, including fuselage, main rotor, tail rotor, steering wheel, engine and reduction box, the reduction box to be connected with the engine, and the landing wear-resistance unmanned plane also includes：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；Cooling device, the cooling device are connected with the reduction box.The present invention solves answers undercarriage to wear the big, technical problem of short life in the prior art, has reached the technique effect for reducing the abrasion of alighting gear undercarriage, improving the undercarriage life-span.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, and more particularly to land wear-resistance unmanned plane.
Background technology
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Without driving cabin on machine, but the equipment such as automatic pilot, presetting apparatus, signal pickup assembly are installed.
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 numeral pass
It is defeated.It can take off as conventional airplane or be launched with booster rocket under wireless remotecontrol, can also be taken to by machine tool in the air
Launch flight.
Unmanned plane is always directly contacted, this just makes by undercarriage with ground first in descent in the prior art
Undercarriage abrasion is larger in contact process, highly shortened the life-span of undercarriage.
The content of the invention
The present invention provides a kind of landing wear-resistance unmanned plane, solves and answers undercarriage to wear big, short life in the prior art
Technical problem, reached the technique effect for reducing the abrasion of alighting gear undercarriage, improving the undercarriage life-span.
In order to solve the above technical problems, the invention provides one kind land wear-resistance unmanned plane, including fuselage, main rotor,
Tail rotor, steering wheel, engine and reduction box, the reduction box are connected with the engine, wherein, the main rotor passes through main biography
Moving axis is rotatably fixed with the fuselage and is connected；The tail rotor is fixedly installed on the afterbody of the fuselage, and is passed by tail
Moving axis is rotatably fixed with the fuselage and is connected；The engine is connected with the main rotor and the tail rotor, for driving
The main rotor and tail rotor rotation are moved, the steering wheel is fixed on the inside of the fuselage；It is described landing wear-resistance nobody
Machine also includes：Support component, the support component are arranged in the fuselage, for supporting and fixing the final drive shaft；Rise
Dropping control device, the take-off and landing device are fixed on the bottom of the fuselage, with to being propped up during the landing wear-resistance unmanned plane landing
Support；Thrust amplifying mechanism, the thrust amplifying mechanism are connected with the steering wheel, to amplify thrust caused by the steering wheel；Cooling
Device, the cooling device are connected with the reduction box；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 landing wear-resistance unmanned plane is directly connect in descent by brake wheel with ground
Touch.
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 cooling device includes：Cooler bin；Return duct；Wherein, the cooler bin by the return duct with
The reduction box connection so that fluid is circulated by the return duct between the reduction box and the cooler bin, with
Increase travelling distance of the fluid in fuselage interior；And the peripheral position of the cooler bin and the reduction box is pasted with radiating
Piece.
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.
The application has the beneficial effect that：
(1) the application is by setting brake wheel to reduce the mill of the undercarriage when landing wear-resistance unmanned plane rises and falls
Damage, 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 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
The bad technological deficiency of wear-resistance unmanned aerial vehicle body internal heat dissipating effect of landing.
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 land wear-resistance unmanned plane structural representation；
Fig. 2 is the structural representation for the wear-resistance unmanned plane that lands in the another better embodiment of the application；
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.
Refer to Fig. 1 and Fig. 2, a kind of landing wear-resistance unmanned plane 100 that the application provides, the landing wear-resistance nobody
Machine 100 comprises at least fuselage 1, main rotor 2, tail rotor 3 and engine 4, and the main rotor 2 is rotated to provide lifting force, described
Tail rotor 3 rotates rotates caused moment of torsion to offset the main rotor 2, to ensure that the landing wear-resistance unmanned plane 100 is flat
Steady flight.
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 in landing wear-resistance unmanned plane 100 in-flight to hold
It is also easy to produce bounce.And tail transmission shaft 7 is connected by the fixing device 8 that the application provides with fuselage 1, to fix 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, and described
One sleeve 82 is set on the tail transmission shaft 7, and the outside of the fixed plate 81 is fixedly connected with the fuselage 1, the fixation
Plate 81 offers the first positioning hole, and the aperture of first positioning hole is more than the excircle diameter of first sleeve 82, makes institute
The first sleeve 82 is stated to be located in first positioning hole.The limiting plate 83 offers the second positioning hole, second positioning
The aperture in hole is more than the excircle diameter of first sleeve 82, first sleeve 82 is located in second positioning hole
In.The limiting plate 83 is bolted with the fixed plate 81, and by being provided with surplus between bolt and screwed hole,
Reduce the bounce of tail transmission shaft 7, and be hardly damaged the tail transmission shaft 7.Specifically, the limiting plate 83 and the fixed plate 81
On offer screwed hole, and use the bolt for leaving surplus with the screwed hole to be located in the screwed hole with described in fixation
Fixed plate 81 and the limiting plate 83, reduce the bounce of the tail transmission shaft 7, and are hardly damaged the tail transmission shaft 7.Pass through
First sleeve 82 is set, first sleeve 82 is set in the tail transmission shaft 7, with avoid the tail transmission shaft 7 with it is described
The direct friction of limiting plate 83 or the fixed plate 81 and wear, improve the life-span of the tail transmission shaft 7.
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 drop
The fuselage interior structure cooling for falling wear-resistance unmanned plane 100 is more abundant.Certainly, in the application reduction box 12 and cooler bin 13 it is outer
Enclose position and be also respectively provided with fin, further to strengthen radiating effect.Preferably, the fin can be aluminium flake.
Based on same inventive concept, the application sets up separately in the structural portion of tail rotor 3 of the landing wear-resistance unmanned plane 100
A cooling device is also equipped with the reduction box 12 put, the common cooling device 100 applied to landing wear-resistance unmanned plane is cold
But all it is often the Local cooling used, by adding gear oil, and relies on the cooling for being applied to landing wear-resistance unmanned plane
The gear-box surface of reduction box 12 is radiated in device 100, and type of cooling radiating is slow, and is only capable of being applied to drop to described
The part fallen in the cooling device 100 of wear-resistance unmanned plane is radiated, and can not obtain good radiating effect.The application carries
The cooling device 100 for being applied to landing wear-resistance unmanned plane supplied also includes afterbody reduction box 12 and cooling device.Specifically, institute
State reduction box 12 to be connected with the engine 4, the power for exporting the engine 4 carries out regulator drive.It is described to be applied to
The cooling device 100 of landing wear-resistance unmanned plane also includes at least one cooler bin 13, and the cooler bin 13 includes the first oil-feed
Mouth and first oil-out corresponding with first oil inlet；The reduction box 12 includes the second oil inlet and with described second
The second corresponding oil-out of oil inlet；First oil inlet connects with second oil-out, it is preferred that described first enters
Hydraulic fluid port is connected and connected by flexible pipe with second oil-out；First oil-out connects with second oil inlet, excellent
Choosing, first oil-out is connected and connected by flexible pipe with second oil inlet.And the application passes through in the deceleration
A worm structure is arranged on gear shaft in case 12 so that by the gear oil in the reduction box 12 during the worm structure rotation
It is pressed onto in the cooler bin 13, makes the fuselage interior structure cooling of landing wear-resistance unmanned plane 100 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 steering wheel be used for control land the flight attitude of wear-resistance unmanned plane 100 and track.The thrust amplifying mechanism 9 increases one-level and institute
The transmission of steering wheel is stated to amplify thrust caused by steering wheel, reduces energy loss.Specifically, the thrust amplifying mechanism 9 includes the
One drive link 91, the second drive link 93 and driver plate 92, the driver plate 92 is including 1: 921, second point 923 and thirdly
922.The driver plate 92 is connected with first drive link 91 and second drive link 93 respectively；First drive link 91
One end be force side, one end of first drive link 91 is fixedly connected with the fuselage 1, first drive link 91 it is another
One end is fixedly connected with the driver plate 92 at described 1: 921, and first drive link 91 can relatively described first
The rotation of point 921.One end of second drive link 93 is fixedly connected with the driver plate 92 at the second point 923, and institute
Stating the second drive link 93 can be rotated relative to the second point 923, and the other end of second drive link 93 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 relatively described thirdly 922 rotation
Turn.By setting the first drive link 91, the second drive link 93 and driver plate 92 to increase primary transmission to amplify pushing away for the steering wheel
Power, reduce 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 landing wear-resistance nobody
Machine 100, the support component 11 that the application provides are arranged in the fuselage 1, for supporting and fixing the final drive shaft 10
Spacing collar.The support component 11 is stable and to the landing wear-resistance unmanned plane by using supported at three point, supporting construction
Damping can be played a part of in 100 flight courses.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 secured with the fuselage 1 and is connected, first bar 111 it is another
End offers a groove；One end of second bar 113 is set in the groove, the end of one end of second bar 113
With being put in the inwall of the groove provided with one or more elastic balls 112 so that first bar 111 and second bar 113
Between stress buffered, reduce 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 fuselage 1 of the landing wear-resistance unmanned plane 100
On, 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, present embodiments provide a kind of take-off and landing device, for the dress that rises and falls
For putting, 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 are removably secured with the undercarriage 5 and are connected.The brake wheel 6 is provided for reducing the landing wear-resistance unmanned plane
The abrasion of 100 undercarriages 5 when rising and falling, and the brake wheel 6 is manually controllable, 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 the life-span of the landing wear-resistance unmanned plane 100.
The application's has the beneficial effect that：
1st, the application is by setting brake wheel to reduce the mill of the undercarriage when landing wear-resistance unmanned plane rises and falls
Damage, 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
The bad technological deficiency of wear-resistance unmanned aerial vehicle body internal heat dissipating effect of landing.
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
The technological deficiency that landing wear-resistance unmanned plane is easily beated in flight course caused by tail transmission shaft is long.
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. one kind landing wear-resistance unmanned plane, including fuselage, main rotor, tail rotor, steering wheel, engine and reduction box, described to subtract
Fast case is connected with the engine, wherein, the main rotor is rotatably fixed with the fuselage by final drive shaft and is connected；Institute
The afterbody that tail rotor is fixedly installed on the fuselage is stated, and is rotatably fixed and is connected with the fuselage by tail transmission shaft；Institute
Engine is stated to be connected with the main rotor and the tail rotor, it is described for driving the main rotor and the tail rotor to rotate
Steering wheel is fixed on the inside of the fuselage；Characterized in that, the landing wear-resistance unmanned plane 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, during with to the landing wear-resistance unmanned plane landing
It is supported；
Thrust amplifying mechanism, the thrust amplifying mechanism are connected with the steering wheel, to amplify thrust caused by the steering wheel；
Cooling device, the cooling device are connected with the reduction box；
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. landing wear-resistance unmanned plane as claimed in claim 1, 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. landing wear-resistance unmanned plane as claimed in claim 1, it is characterised in that 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 removably secured at first fixing hole with the undercarriage and is connected, so that described
Landing wear-resistance unmanned plane is directly contacted in descent by brake wheel with ground.
4. landing wear-resistance unmanned plane as claimed in claim 3, it is characterised in that the brake wheel includes：
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. landing wear-resistance unmanned plane as claimed in claim 1, it is characterised in that the thrust amplifying 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. landing wear-resistance unmanned plane as claimed in claim 5, it is characterised in that the driver plate includes：
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. landing wear-resistance unmanned plane as claimed in claim 1, it is characterised in that the cooling device includes：
Cooler bin；
Return duct；
Wherein, the cooler bin is connected by the return duct with the reduction box so that fluid is by the return duct in institute
State and circulated between reduction box and the cooler bin, to increase travelling distance of the fluid in fuselage interior；It is and described cold
But the peripheral position of case and the reduction box is pasted with fin.
8. landing wear-resistance unmanned plane as claimed in claim 4, it is characterised in that
The first connecting hole, the second connecting hole and the second fixing hole are offered on the connecting plate；
Between first connecting hole and second connecting hole, the rotary shaft is located in described second fixed hole position
In first connecting hole；
One end of the control-rod is provided with a fixed part, and the fixed part is located in second connecting hole.
9. landing wear-resistance unmanned plane as claimed in claim 8, it is characterised in that
The control-rod is fixedly connected by latch or clip with the connecting plate in second connection hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610211879.3A CN105752323B (en) | 2016-04-07 | 2016-04-07 | Land wear-resistance unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610211879.3A CN105752323B (en) | 2016-04-07 | 2016-04-07 | Land wear-resistance unmanned plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105752323A CN105752323A (en) | 2016-07-13 |
| CN105752323B true CN105752323B (en) | 2018-03-27 |
Family
ID=56334398
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610211879.3A Expired - Fee Related CN105752323B (en) | 2016-04-07 | 2016-04-07 | Land wear-resistance unmanned plane |
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| Country | Link |
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| CN (1) | CN105752323B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109484628B (en) * | 2018-12-24 | 2020-09-25 | 沈阳旋飞航空技术有限公司 | Oil moves unmanned aerial vehicle's simple and easy transport mechanism |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101238033A (en) * | 2005-08-04 | 2008-08-06 | 雅马哈发动机株式会社 | Unmanned helicopter |
| 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 |
| CN203318678U (en) * | 2013-06-05 | 2013-12-04 | 王开林 | Discrete control system of coaxial type double-rotor unmanned helicopter control system |
| CN203727646U (en) * | 2014-03-13 | 2014-07-23 | 中国科学院沈阳自动化研究所 | Unmanned helicopter |
| CN205707307U (en) * | 2016-04-07 | 2016-11-23 | 易瓦特科技股份公司 | Landing wear-resistance unmanned plane |
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2016
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| Publication number | Publication date |
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| CN105752323A (en) | 2016-07-13 |
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