CN105752349B - Depopulated helicopter - Google Patents
Depopulated helicopter Download PDFInfo
- Publication number
- CN105752349B CN105752349B CN201610211880.6A CN201610211880A CN105752349B CN 105752349 B CN105752349 B CN 105752349B CN 201610211880 A CN201610211880 A CN 201610211880A CN 105752349 B CN105752349 B CN 105752349B
- Authority
- CN
- China
- Prior art keywords
- fuselage
- drive link
- depopulated helicopter
- bar
- plate
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
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- 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
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- 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
Abstract
The invention discloses a kind of depopulated helicopter, including fuselage, main rotor, tail rotor, steering wheel, engine and reduction box, the reduction box is connected with the engine, and the depopulated helicopter 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；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 fuselage interior of the tail transmission shaft in depopulated helicopter has one section longer of axle body distance, tail transmission shaft is very easy to produce bounce in flight course caused by and, is unfavorable for the technological deficiency of the smooth flight of depopulated helicopter.
Description
Technical field
The present invention relates to depopulated helicopter technical field, more particularly to depopulated helicopter.
Background technology
UAV is to utilize radio robot and the presetting apparatus provided for oneself referred to as " depopulated helicopter "
The not manned aircraft manipulated.Without driving cabin on machine, but automatic pilot, presetting apparatus, signal pickup assembly etc. are installed
Equipment.On ground, naval vessels or machine tool remote control station personnel are by equipment such as radars, 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 band
Flight is launched to aerial.
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 depopulated helicopter, be very easy to produce bounce in flight course, unfavorable
In the smooth flight of depopulated helicopter.
The content of the invention
The present invention provides a kind of depopulated helicopter, solves in the prior art because tail transmission shaft is in the machine of depopulated helicopter
One section longer of axle body distance inside body be present, and caused by flight course tail transmission shaft be very easy to produce bounce, no
Beneficial to the technological deficiency of the smooth flight of depopulated helicopter.
In order to solve the above technical problems, the invention provides a kind of depopulated helicopter, including fuselage, main rotor, tail rotor,
Steering wheel, engine and reduction box, the reduction box are connected with the engine, wherein, the main rotor by final drive shaft with
The fuselage is rotatably fixed connection；The tail rotor is fixedly installed on the afterbody of the fuselage, and by tail transmission shaft with
The fuselage is rotatably fixed connection；The engine is connected with the main rotor and the tail rotor, described for driving
Main rotor and tail rotor rotation, the steering wheel are fixed on the inside of the fuselage；The depopulated helicopter 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, described
Dropping control device is fixed on the bottom of the fuselage, to be supported when landing to the depopulated helicopter；Thrust amplifying mechanism, it is described
Thrust amplifying mechanism is connected with the steering wheel, to amplify thrust caused by the steering wheel；Cooling device, the cooling device and institute
State reduction box connection；Fixing device, the fixing device are set on the tail transmission shaft, and are fixedly connected with the fuselage,
So that the tail transmission shaft and the fuselage to be 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 depopulated helicopter is directly contacted in descent by brake wheel 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 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 abrasion of the undercarriage when depopulated helicopter rises and falls, 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 depopulated helicopter fuselage interior radiating effect.
(5) 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 depopulated helicopter is easily beated in flight course caused by tail transmission shaft is long.
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 depopulated helicopter structural representation in the better embodiment of the application one；
Fig. 2 is the structural representation of depopulated helicopter 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.
Fig. 1 and Fig. 2, a kind of depopulated helicopter 100 that the application provides are referred to, the depopulated helicopter comprises at least machine
Body 1, main rotor 2, tail rotor 3 and engine 4, the main rotor 2 are rotated to provide lifting force, the tail rotor 3 rotate with to
The main rotor 2 that disappears rotates caused moment of torsion, to ensure the smooth flight of depopulated helicopter 100.
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 in-flight easily to produce in depopulated helicopter 100 apart from the distant of the engine 4, the tail transmission shaft 7
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 tail
The bounce amplitude of power 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, and the outside of the fixed plate 81 is fixedly connected with the fuselage 1, and the fixed plate 81 is opened
Provided with the first positioning hole, the aperture of first positioning hole is more than the excircle diameter of first sleeve 82, makes described first
Sleeve 82 is located in first positioning hole.The limiting plate 83 offers the second positioning hole, the hole of second positioning hole
Footpath is more than the excircle diameter of first sleeve 82, first sleeve 82 is located in second positioning hole.It is described
Limiting plate 83 is bolted with the fixed plate 81, and by being provided with surplus between bolt and screwed hole, reduces tail
The bounce of power transmission shaft 7, and it is hardly damaged the tail transmission shaft 7.Specifically, opened in the limiting plate 83 and the fixed plate 81
Provided with screwed hole, and the bolt for leaving surplus with the screwed hole is used to be located in the screwed hole with the fixation fixed plate
81 and the limiting plate 83, the bounce of the tail transmission shaft 7 is reduced, and be hardly damaged the tail transmission shaft 7.By setting the
One sleeve 82, first sleeve 82 are set in the tail transmission shaft 7, to avoid the tail transmission shaft 7 and the limiting plate
The direct friction of 83 or described fixed plates 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 nothing
The fuselage interior structure cooling of people's helicopter 100 is more abundant.Certainly, the peripheral position of reduction box 12 and cooler bin 13 in the application
Fin is also respectively provided with, further to strengthen radiating effect.Preferably, the fin can be aluminium flake.
Based on same inventive concept, the application subtracts what the structure division of tail rotor 3 of the depopulated helicopter 100 was set
A cooling device is also equipped with fast case 12, the common cooling device 100 applied to depopulated helicopter, which cools down, often all to be adopted
Local cooling, by adding gear oil, and rely on reduction box 12 in the cooling device 100 applied to depopulated helicopter
Gear-box surface is radiated, and type of cooling radiating is slow, and is only capable of to the cooling device applied to depopulated helicopter
Part in 100 is radiated, and can not obtain good radiating effect.What the application provided is applied to the cold of depopulated helicopter
But device 100 also includes afterbody reduction box 12 and cooling device.Specifically, the reduction box 12 is connected with the engine 4, use
Regulator drive is carried out in the power exported to the engine 4.The cooling device 100 applied to depopulated helicopter is also included extremely
A few 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 simultaneously with second oil-out by flexible pipe
Connection；First oil-out connects with second oil inlet, it is preferred that first oil-out and second oil inlet
Connected and connected by flexible pipe.And the application on the gear shaft in the reduction box 12 by being arranged a worm 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 depopulated helicopter 100
Fuselage interior structure cooling 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
Steering wheel is stated to be used to control the flight attitude of depopulated helicopter 100 and track.The thrust amplifying mechanism 9 increases one-level and the steering wheel
Transmission to amplify thrust caused by steering wheel, reduce energy loss.Specifically, the thrust amplifying mechanism 9 includes the first transmission
Bar 91, the second drive link 93 and driver plate 92, the driver plate 92 include 1: 921, second point 923 and thirdly 922.Institute
Driver plate 92 is stated to be connected with first drive link 91 and second drive link 93 respectively；One end of first drive link 91
For force side, one end of first drive link 91 is fixedly connected with the fuselage 1, the other end of first drive link 91 with
The driver plate 92 is fixedly connected at described 1: 921, and first drive link 91 relatively described 1: 921 can revolve
Turn.One end of second drive link 93 is fixedly connected with the driver plate 92 at the second point 923, and described second passes
Lever 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 transmission
Plate 92 is connected at thirdly 922 with the fuselage 1, and the driver plate 92 can be relative to thirdly 922 rotation.By setting
Putting the first drive link 91, the second drive link 93 and driver plate 92 increases primary transmission to amplify the thrust of the steering wheel, reduces energy
Amount 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 depopulated helicopter 100,
The support component 11 that the application provides is arranged in the fuselage 1, for supporting and fixing the stop collar of the final drive shaft 10
Cylinder.The support component 11 is stable and in the flight course of depopulated helicopter 100 by using supported at three point, supporting construction
Damping can be played a part of.Specifically, the support component 11 includes the first bar 111, the second bar 113 and positioning seat 114；It is described
One end of first bar 111 is removably secured with the fuselage 1 and is connected, and the other end of first bar 111 offers a groove；
One end of second bar 113 is set in the groove, the end of one end of second bar 113 and the inwall of the groove
Inside put provided with one or more elastic balls 112 so that the stress between first bar 111 and second bar 113 is delayed
Punching, 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 depopulated helicopter 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 depopulated helicopter 100 that is provided for reducing of the brake wheel 6 rises
The abrasion of the undercarriage 5 when 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 depopulated helicopter 100.
The application's has the beneficial effect that：
1st, the application is by setting brake wheel to reduce the abrasion of the undercarriage when depopulated helicopter rises and falls, and institute
It is manually controllable to state brake wheel, 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 depopulated helicopter fuselage interior radiating effect.
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 depopulated helicopter 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. a kind of depopulated helicopter, including fuselage, main rotor, tail rotor, steering wheel, engine and reduction box, the reduction box with
The engine connection, wherein, the main rotor is rotatably fixed with the fuselage by final drive shaft and is connected；The tailspin
The wing is fixedly installed on the afterbody of the fuselage, and is rotatably fixed and be connected with the fuselage by tail transmission shaft；It is described to start
Machine is connected with the main rotor and the tail rotor, and for driving the main rotor and the tail rotor to rotate, the steering wheel is consolidated
Due to the inside of the fuselage；Characterized in that, the depopulated helicopter 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, to be propped up when landing to the depopulated helicopter
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 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. depopulated helicopter 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. depopulated helicopter 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
Depopulated helicopter is directly contacted in descent by brake wheel with ground.
4. depopulated helicopter 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. depopulated helicopter 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. depopulated helicopter 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. depopulated helicopter 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. depopulated helicopter as claimed in claim 1, it is characterised in that the fixing device includes：
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.
9. depopulated helicopter as claimed in claim 8, it is characterised in that the fixing device also includes：
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610211880.6A CN105752349B (en) | 2016-04-07 | 2016-04-07 | Depopulated helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610211880.6A CN105752349B (en) | 2016-04-07 | 2016-04-07 | Depopulated helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105752349A CN105752349A (en) | 2016-07-13 |
| CN105752349B true CN105752349B (en) | 2017-12-26 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610211880.6A Expired - Fee Related CN105752349B (en) | 2016-04-07 | 2016-04-07 | Depopulated helicopter |
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| Country | Link |
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| CN (1) | CN105752349B (en) |
Citations (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 |
| CN205707383U (en) * | 2016-04-07 | 2016-11-23 | 易瓦特科技股份公司 | Depopulated helicopter |
-
2016
- 2016-04-07 CN CN201610211880.6A patent/CN105752349B/en not_active Expired - Fee Related
Patent Citations (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 |
| CN205707383U (en) * | 2016-04-07 | 2016-11-23 | 易瓦特科技股份公司 | Depopulated helicopter |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105752349A (en) | 2016-07-13 |
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Granted publication date: 20171226 Termination date: 20190407 |