CN105836116B - Cooling type unmanned plane - Google Patents
Cooling type unmanned plane Download PDFInfo
- Publication number
- CN105836116B CN105836116B CN201610212402.7A CN201610212402A CN105836116B CN 105836116 B CN105836116 B CN 105836116B CN 201610212402 A CN201610212402 A CN 201610212402A CN 105836116 B CN105836116 B CN 105836116B
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- Prior art keywords
- fuselage
- fixed
- drive rod
- unmanned plane
- bar
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- 238000001816 cooling Methods 0.000 title claims abstract description 73
- 230000005540 biological transmission Effects 0.000 claims abstract description 33
- 230000007246 mechanism Effects 0.000 claims abstract description 11
- 239000007788 liquid Substances 0.000 claims description 8
- 230000002093 peripheral effect Effects 0.000 claims description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 238000010009 beating Methods 0.000 claims description 2
- 230000003139 buffering effect Effects 0.000 claims 1
- 230000008450 motivation Effects 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 10
- 230000017525 heat dissipation Effects 0.000 abstract description 8
- 230000007812 deficiency Effects 0.000 abstract description 6
- 239000003921 oil Substances 0.000 description 40
- 238000010586 diagram Methods 0.000 description 6
- 230000035939 shock Effects 0.000 description 5
- 239000012208 gear oil Substances 0.000 description 4
- 208000032369 Primary transmission Diseases 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 3
- 238000004891 communication Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 241000237858 Gastropoda Species 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- General Details Of Gearings (AREA)
Abstract
The invention discloses a kind of cooling type unmanned planes, including fuselage, main rotor, tail rotor, steering engine, engine and reduction gearbox, the reduction gearbox is connected with the engine, the cooling type unmanned plane further include: support component, the support component are arranged in the fuselage；Thrust amplifying mechanism, the thrust amplifying mechanism are connect with the steering engine；Cooling device, the cooling device are connect with the reduction gearbox；Fixed device, the fixed device is set on the tail transmission shaft, and is fixedly connected with the fuselage.Present application addresses the bad technological deficiencies of unmanned helicopter fuselage interior heat dissipation effect in the prior art.
Description
Technical field
The present invention relates to air vehicle technique fields, in particular to cooling type unmanned plane.
Background technique
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Without cockpit 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, are tracked, positioned to it, is remotely controlled, telemetering and number pass
It is defeated.It can take off as conventional airplane under wireless remotecontrol or be launched with booster rocket, can also be taken to by machine tool in the air
Launch flight.
It is cooling for the fuselage interior of unmanned plane in the prior art, it is all usually the Local cooling used, by adding gear
Oil, and radiate by the gear-box surface of reduction gearbox in unmanned helicopter, but type of cooling heat dissipation is slow, and only
Can the surface of part such as reduction gearbox to unmanned plane radiate, good heat dissipation effect can not be obtained.
Summary of the invention
The present invention provides a kind of cooling type unmanned plane, solves unmanned helicopter fuselage interior heat dissipation effect in the prior art
Bad technological deficiency.
In order to solve the above technical problems, the present invention provides a kind of cooling type unmanned plane, including fuselage, main rotor, tailspin
The wing, steering engine, engine and reduction gearbox, the reduction gearbox are connected with the engine, wherein the main rotor passes through main shaft
It is rotatably fixed and connect with the fuselage；The tail rotor is fixed at the tail portion of the fuselage, and passes through tail transmission shaft
It is rotatably fixed and connect with the fuselage；The engine is connect with the main rotor and the tail rotor, for driving
Main rotor and tail rotor rotation are stated, the steering engine is fixed on the inside of the fuselage；The cooling type unmanned plane further include:
Support component, the support component are arranged in the fuselage, are used to support and fix the main shaft；Thrust enlarger
Structure, the thrust amplifying mechanism are connect with the steering engine, to amplify the thrust that the steering engine generates；Cooling device, the cooling
Device is connect with the reduction gearbox；Fixed device, the fixed device are set on the tail transmission shaft, and solid with the fuselage
Fixed connection, the tail transmission shaft and the fuselage is relatively fixed.
Optionally, the support component includes: the first bar；Second bar；And positioning seat；Wherein, one end of first bar
It is removably secured and connect with the main shaft, the other end of first bar offers a groove；The one of second bar
End cap is set in the groove, in the end of one end of second bar and the inner wall of the groove, is put and is equipped 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 of positioning seat is rotatablely connected, so that second bar can be rotated relative to the positioning seat.
Optional: 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 and the fuselage are flexibly connected.
Optionally, the thrust amplifying mechanism includes: the first drive rod, and one end of first drive rod is fixed on described
On fuselage；One end of second drive rod, second drive rod is fixed on the steering engine of the fuselage interior；And driver plate, institute
It states driver plate to be rotatablely connected with the other end of the other end of first drive rod and second drive rod respectively, and the biography
Movable plate and the fuselage are rotatablely connected；So that the steering engine passes through the driver plate, biography to the active force of second drive rod
It is handed to first drive rod.
Optionally, the driver plate includes: first point；Second point；And thirdly；Wherein, first drive rod is another
One end and the driver plate are rotatablely connected at described first point, so that first drive rod can be opposite at described first point
First drive rod is rotated；The other end of second drive rod and driver plate company of rotation at the second point
It connects, so that second drive rod can be rotated at the second point relative to second drive rod；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 pipe；Wherein, the cooler bin by the return pipe with
The reduction gearbox connection, so that oil liquid is circulated between the reduction gearbox and the cooler bin by the return pipe, with
Increase the oil liquid in the travelling distance of fuselage interior；And the peripheral position of the cooler bin and the reduction gearbox is pasted with heat dissipation
Piece.
Optionally, the fixed device includes: first sleeve；And fixed plate；Wherein, the first sleeve is set in described
On tail transmission shaft, the fixed plate is set in the first sleeve, and the outside of the fixed plate and the fixed company of the fuselage
It connects, with the inside for being fixed on the fuselage for being consolidated the tail transmission shaft by the first sleeve and the fixed plate, with
Prevent the tail transmission shaft from beating.
Optionally, the fixed device further include: limit plate, wherein the fixed plate offers first positioning hole, described
The aperture of first positioning hole is greater than the excircle diameter of the first sleeve, and the first sleeve is made to be threaded through first positioning
Kong Zhong；The limit plate offers second location hole, and the aperture of the second location hole is greater than the excircle of the first sleeve
Diameter is threaded through the first sleeve in the second location hole；The limit plate is with the fixed plate by being fixedly connected.
Optional: the return pipe includes: the first hose and the second hose；The cooler bin include the first oil inlet and with
Corresponding first oil outlet of first oil inlet；The reduction gearbox include the second oil inlet and with the second oil inlet phase
Corresponding second oil outlet；Wherein, first oil inlet is connected to by first hose with second oil outlet；It is described
First oil outlet is connected to by second hose with second oil inlet.
Optional: the cooling fin is aluminium flake.
The application has the beneficial effect that:
(1) the application passes through socket, and first bar and second bar using 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 increasing member stress avoids the support component by large impact, improves the support
The service life of component, the safety and firmness operation for the main shaft finally realized.
(2) the application is connected by the first drive rod of setting, the second drive rod and driver plate by steering engine and the second drive rod
It connects, the second drive rod is connect with driver plate, and driver plate is connect with the first drive rod, and such steering engine acts on the second drive rod
Power, passes sequentially through driver plate, the first drive rod is ultimately applied to main rotor, so that by the first drive rod, the second drive rod and biography
Movable plate constitutes primary transmission to amplify the thrust of the steering engine, reduces the loss of energy.
(3) the application is by adding cooler bin and return pipe, so that the oil liquid of reduction gearbox is in fuselage interior, by returning
Flow tube circulates in cooler bin and reduction gearbox, increases oil liquid in the travelling distance of fuselage interior, meanwhile, in reduction gearbox and
The peripheral position of cooler bin is provided with cooling fin, further to radiate to reduction gearbox and cooler bin, solves in the prior art
The bad technological deficiency of cooling type unmanned aerial vehicle body internal heat dissipating effect.
(4) the application adds first sleeve and fixed plate by setting, and first sleeve is set in the outside of tail transmission shaft, Gu
Fixed board is set in the outside of first sleeve, so that the tail transmission shaft of fuselage interior is relatively fixed with fuselage, it effectively prevents
Cooling type unmanned plane in flight course due to tail transmission shaft it is too long caused by the technological deficiency easily beated.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, embodiment will be described below
Needed in attached drawing be briefly described, it should be apparent that, the accompanying drawings in the following description is only of the invention some
Embodiment.
Fig. 1 is cooling type unmanned plane structural schematic diagram in one better embodiment of the application；
Fig. 2 is the structural schematic diagram of cooling type unmanned plane in the another better embodiment of the application；
Fig. 3 is the structural schematic diagram that device is fixed in Fig. 1；
Fig. 4 is the structural schematic diagram of the application cooling device；
Fig. 5 is the structural schematic diagram of the application reduction gearbox；
Fig. 6 is the partial view of support component in Fig. 2；
Fig. 7 is the structural schematic diagram of brake wheel in Fig. 1；
Fig. 8 is the right view of brake wheel in Fig. 7.
Specific embodiment
In order to better understand the above technical scheme, in conjunction with appended figures and specific embodiments to upper
Technical solution is stated to be described in detail.
Fig. 1 and Fig. 2, a kind of cooling type unmanned plane 100 provided by the present application are please referred to, the cooling type unmanned plane at least wraps
Fuselage 1, main rotor 2, tail rotor 3 and engine 4 are included, to provide lifting force, the tail rotor 3 rotates for the rotation of main rotor 2
To offset the torque generated when the main rotor 2 rotation, to guarantee 100 smooth flight of cooling type unmanned plane.
Specifically, referring to Fig. 3, tail transmission shaft 7 is for the driving force of engine 4 to be transferred to tail rotor 3.By institute
State distance of the tail rotor 3 apart from the engine 4 farther out, the tail transmission shaft 7 is in-flight easy to produce in cooling type unmanned plane 100
Raw bounce.And tail transmission shaft 7 is connect by fixed device 8 provided by the present application with fuselage 1, to fix tail transmission shaft 7, described in reduction
The bounce amplitude of tail transmission shaft 7.The fixed device 8 includes first sleeve 82, fixed plate 81 and limit plate 83, the first set
Cylinder 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 fixed plate 81
Offer first positioning hole, the aperture of the first positioning hole is greater than the excircle diameter of the first sleeve 82, makes described the
One sleeve 82 is threaded through in the first positioning hole.The limit plate 83 offers second location hole, the second location hole
Aperture is greater than the excircle diameter of the first sleeve 82, is threaded through the first sleeve 82 in the second location hole.Institute
It states limit plate 83 to be bolted with the fixed plate 81, and is had a margin by being arranged between bolt and threaded hole, reduced
The bounce of tail transmission shaft 7, and it is hardly damaged the tail transmission shaft 7.Specifically, in the limit plate 83 and the fixed plate 81
Threaded hole is offered, and uses that there are the bolts of surplus to be threaded through in the threaded hole with the fixation fixation with the threaded hole
Plate 81 and the limit plate 83, reduce the bounce of the tail transmission shaft 7, and are hardly damaged the tail transmission shaft 7.Pass through setting
First sleeve 82, the first sleeve 82 are set in the tail transmission shaft 7, to avoid the tail transmission shaft 7 and the limit
The direct friction of plate 83 or the fixed plate 81 and wear, improve the service life of the tail transmission shaft 7.
Further, incorporated by reference to Fig. 1-2 together refering to 4-5, the embodiment of the present application also provides a kind of cooling devices.Slow down
Case 12 is connect with the engine 4, and the power for exporting to the engine 4 carries out regulator drive.The cooling device includes
At least one cooler bin 13, the cooler bin 13 include the first oil inlet and corresponding with first oil inlet first fuel-displaced
Mouthful；The reduction gearbox 12 includes the second oil inlet and the second oil outlet corresponding with second oil inlet；Described first into
Hydraulic fluid port is connected to second oil outlet, it is preferred that first oil inlet and second oil outlet are connected by the first hose
It connects and is connected to；First oil outlet is connected to second oil inlet, it is preferred that first oil outlet with described second into
Hydraulic fluid port is connected to and in communication with by the second hose.And the application on the gear shaft in the reduction gearbox 12 by being arranged a worm screw knot
Structure makes described cold so that the gear oil in the reduction gearbox 12 is pressed onto the cooler bin 13 by the worm structure when rotating
But the fuselage interior structure cooling of type unmanned plane 100 is more abundant.Certainly, in the application reduction gearbox 12 and cooler bin 13 outer part
Position is also respectively provided with cooling fin, to further strengthen heat dissipation effect.Preferably, the cooling fin can be aluminium flake.
Based on same inventive concept, the application is arranged in 3 structure division of tail rotor of the cooling type unmanned plane 100
A cooling device is also equipped at reduction gearbox 12, the common cooling device 100 applied to cooling type unmanned plane cools down often all
It is the Local cooling used, by adding gear oil, and is applied in the cooling device 100 of cooling type unmanned plane slow down described in
The gear-box surface of case 12 is radiated, and type of cooling heat dissipation is slow, and be only capable of to described applied to cooling type unmanned plane
Part in cooling device 100 is radiated, and good heat dissipation effect can not be obtained.It is provided by the present application to be applied to cooling type
The cooling device 100 of unmanned plane further includes tail portion reduction gearbox 12 and cooling device.Specifically, the reduction gearbox 12 starts with described
Machine 4 connects, and the power for exporting to the engine 4 carries out regulator drive.The cooling dress applied to cooling type unmanned plane
Setting 100 further includes at least one cooler bin 13, and the cooler bin 13 includes the first oil inlet and opposite with first oil inlet
The first oil outlet answered；The reduction gearbox 12 includes the second oil inlet and corresponding with second oil inlet second fuel-displaced
Mouthful；First oil inlet is connected to second oil outlet, it is preferred that first oil inlet and second oil outlet are logical
Hose is crossed to be connected to and in communication with；First oil outlet is connected to second oil inlet, it is preferred that first oil outlet and institute
The second oil inlet is stated to be connected to and in communication with by hose.And the application is by being arranged a snail on the gear shaft in the reduction gearbox 12
Rod structure makes cold so that the gear oil in the reduction gearbox 12 is pressed onto the cooler bin 13 by the worm structure when rotating
But the fuselage interior structure cooling of type unmanned plane 100 is more abundant.
Further, please continue to refer to Fig. 4, present invention also provides a kind of thrust amplifying mechanisms 9, connect with steering engine；Institute
Steering engine is stated for controlling 100 flight attitude of cooling type unmanned plane and track.The thrust amplifying mechanism 9 increases level-one and the rudder
The transmission of machine reduces energy loss to amplify the thrust that steering engine generates.Specifically, the thrust amplifying mechanism 9 includes the first biography
Lever 91, the second drive rod 93 and driver plate 92, the driver plate 92 is 922 including 1: 921, second point 923 and thirdly.
The driver plate 92 is connect with first drive rod 91 and second drive rod 93 respectively；The one of first drive rod 91
End is force side, and one end of first drive rod 91 is fixedly connected with the fuselage 1, the other end of first drive rod 91
It is fixedly connected at described 1: 921 with the driver plate 92, and first drive rod 91 can relatively described 1: 921
Rotation.One end of second drive rod 93 is fixedly connected at the second point 923 with the driver plate 92, and described second
Drive rod 93 can be rotated relative to the second point 923, and the other end of second drive rod 93 is connect with the steering engine.The biography
Movable plate 92 is connect at thirdly 922 with the fuselage 1, and the driver plate 92 can be relative to thirdly 922 rotation.Pass through
First drive rod 91, the second drive rod 93 and driver plate 92 are set and increase primary transmission to amplify the thrust of the steering engine, is reduced
Energy loss.
Preferably, first drive rod 91 and the driver plate 92 are hinged at 1: 921；Second drive rod
93 is hinged at second point 923 with the driver plate 92；The driver plate 92 and the fuselage 1 are hinged 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, it is applied to cooling type unmanned plane
100, support component 11 provided by the present application is arranged in the fuselage 1, is used to support and fixes the limit of the main shaft 10
Position sleeve.For the support component 11 by using supported at three point, support construction is stable and flies to the cooling type unmanned plane 100
It can play the role of damping in the process.Specifically, the support component 11 includes 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 connect, and the other end of first bar 111 opens up
There is a groove；One end of second bar 113 is arranged in the groove, the end of one end of second bar 113 with it is described
It is put in the inner wall of groove and is equipped with one or more elastic balls 112, so that between first bar 111 and second bar 113
Stress is buffered, and vibration is reduced.
In the present embodiment, the elastic ball 112 is baton round；It is convex that the other end of second bar 113 is equipped with first
Ear, first through hole is offered in the first lug, and one end of the positioning seat 114 is equipped with the second lug, second lug
On offer and be bolted with matched second through-hole of the first through hole, the first through hole with second through-hole,
Second bar 113 is set to rotate relative to the positioning seat 114.In order to further decrease the vibration 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 cooling type unmanned plane 100, with
It is fixedly connected with the positioning seat 114 with the fuselage 1.
In the present embodiment, the resilient sleeve is rubber sleeve.The support is further improved by the way that resilient sleeve is arranged
The shock resistance of component 11.First bar 111 passes through socket, and first bar 111 and described second with second bar 113
It is provided with elastic ball 112 between bar 113, also improves the shock resistance of the support component 11.The application uses first bar
111 pass through socket with second bar 113, and are provided with elastic ball 112 between first bar 111 and second bar 113,
Instead of conventional hinged etc., first bar 111 and second bar 113 by pretightning force ensure that the reliability of connection with
On the one hand stability improves the shock resistance of the support component 11, on the other hand, the cushion effect after increasing member stress,
It avoids the support component 11 by large impact, improves the service life of the support component 11.
Further, incorporated by reference to Fig. 1-2 together refering to Fig. 7-8, 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 fixed at the bottom of the fuselage 1.The brake
Wheel 6 is removably secured with the undercarriage 5 to be connect.The setting of the brake wheel 6 is for reducing the cooling type unmanned plane 100
The abrasion of the undercarriage 5 when rising and falling, and the brake wheel 6 is manually controllable, structure is simple and easy to disassemble.
Specifically, offering the first fixation hole on the undercarriage 5, first fixation hole is used for and the brake wheel 6
Be used cooperatively, to be plugged in first fixation hole and the brake wheel 6 by fixing piece, make the brake wheel 6 with it is described
Undercarriage 5 is fixedly connected.In the present embodiment, the fixing piece is specially bolt.
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 rotating wheel 61 can be rotated around the center line of the rotary shaft.One end of the connecting plate 62 and the rotation
Shaft is fixedly connected；Control-rod is removably secured with the other end of the connecting plate 62 and connect；The control-rod 63 upwards or
It moves down, makes the rotation of connecting plate 62 to adjust 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 also provided on the connecting plate 62
Second fixation hole, second fixed hole position is between first connecting hole and second connecting hole.The control-rod 63
It is removably secured and connect 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 threaded through in second connecting hole, and is fixedly connected by bolt or clip with the connecting plate 62.The rotary shaft
It is threaded through 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 can adjust the rotating wheel 61 when the connecting plate 62 rotation.The application uses connecting plate 62, rotary shaft and control
Bar 63 forms a link mechanism, and combines the position of the mobile adjustment brake wheel 6 of control-rod 63, and structure is simple and easy to disassemble.
It when operation, manually moves up or down the control-rod 63, moves down the rotating wheel 61, when described
The minimum altitude of rotating wheel 61 is lower 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 equal to or more than preset value, in first fixation hole and second fixation hole
Fixing piece is plugged, with the fixation brake wheel 6.The brake wheel 6 of the application setting, manually controls and easy to disassemble, reduces institute
The abrasion for stating undercarriage 5 improves the service life of the cooling type unmanned plane 100.
The application's has the beneficial effect that:
1, the application reduces the abrasion of the undercarriage when cooling type unmanned plane rises and falls by the way that brake wheel is arranged, and
The brake wheel is manually controllable, and structure is simple and easy to disassemble.
2, 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 increasing member stress avoids the support component by large impact, improves the support group
The service life of part, the safety and firmness operation for the main shaft finally realized.
3, the application is connected by the first drive rod of setting, the second drive rod and driver plate by steering engine and the second drive rod
It connects, the second drive rod is connect with driver plate, and driver plate is connect with the first drive rod, and such steering engine acts on the second drive rod
Power, passes sequentially through driver plate, the first drive rod is ultimately applied to main rotor, so that by the first drive rod, the second drive rod and biography
Movable plate constitutes primary transmission to amplify the thrust of the steering engine, reduces the loss of energy.
4, the application is by adding cooler bin and return pipe, so that the oil liquid of reduction gearbox is in fuselage interior, by returning
Flow tube circulates in cooler bin and reduction gearbox, increases oil liquid in the travelling distance of fuselage interior, meanwhile, in reduction gearbox and
The peripheral position of cooler bin is provided with cooling fin, further to radiate to reduction gearbox and cooler bin, solves in the prior art
The bad technological deficiency of cooling type unmanned aerial vehicle body internal heat dissipating effect.
5, the application adds first sleeve and fixed plate by setting, and first sleeve is set in the outside of tail transmission shaft, Gu
Fixed board is set in the outside of first sleeve, so that the tail transmission shaft of fuselage interior is relatively fixed with fuselage, it effectively prevents
Cooling type unmanned plane in flight course due to tail transmission shaft it is too long caused by the technological deficiency easily beated.
It should be noted last that the above specific embodiment is only used to illustrate the technical scheme of the present invention and not to limit it,
Although being described the invention in detail referring to example, those skilled in the art should understand that, it can be to the present invention
Technical solution be modified or replaced equivalently, without departing from the spirit and scope of the technical solution of the present invention, should all cover
In the scope of the claims of the present invention.
Claims (9)
1. a kind of cooling type unmanned plane, including fuselage, main rotor, tail rotor, steering engine, engine and reduction gearbox, the reduction gearbox
It is connected with the engine, wherein the main rotor is rotatably fixed with the fuselage by main shaft and is connect；The tail
Rotor is fixed at the tail portion of the fuselage, and is rotatably fixed and is connect with the fuselage by tail transmission shaft；The hair
Motivation is connect with the main rotor and the tail rotor, for driving the main rotor and the tail rotor to rotate, the steering engine
It is fixed on the inside of the fuselage；It is characterized in that, the cooling type unmanned plane further include:
Support component, the support component are arranged in the fuselage, are used to support and fix the main shaft；
Thrust amplifying mechanism, the thrust amplifying mechanism are connect with the steering engine, to amplify the thrust that the steering engine generates；
Cooling device, the cooling device are connect with the reduction gearbox；
Fixed device, the fixed device is set on the tail transmission shaft, and is fixedly connected with the fuselage, by the tail
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 main shaft connect, first bar it is another
One end offers a groove；One end of second bar is arranged in the groove, the end of one end of second bar and institute
It states in the inner wall of groove, puts and be equipped 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 and one end of the positioning seat are rotatablely connected, so that second bar is relative to described
Positioning seat can be rotated.
2. cooling type unmanned plane as described 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 flexible connection.
3. cooling type unmanned plane as described in claim 1, which is characterized in that the thrust amplifying mechanism includes:
One end of first drive rod, first drive rod is fixed on the fuselage；
One end of second drive rod, second drive rod is fixed on the steering engine of the fuselage interior；And
Driver plate, the driver plate are rotated with the other end of the other end of first drive rod and second drive rod respectively
Connection, and the driver plate and the fuselage are rotatablely connected；So that the steering engine passes through the active force of second drive rod
The driver plate is transferred to first drive rod.
4. cooling type unmanned plane as claimed in claim 3, which is characterized in that the driver plate includes:
First point；
Second point；And
Thirdly；Wherein, the other end of first drive rod and the driver plate are rotatablely connected at described first point, so that
First drive rod can be rotated at described first point relative to the driver plate；The other end of second drive rod with
The driver plate is rotatablely connected at the second point, so that second drive rod can the relatively described biography at the second point
Movable plate is rotated；The driver plate thirdly place with the fuselage be rotatablely connected, and the driver plate it is described thirdly
Place can be rotated relative to the fuselage.
5. cooling type unmanned plane as described in claim 1, which is characterized in that the cooling device includes:
Cooler bin；
Return pipe；
Wherein, the cooler bin is connect by the return pipe with the reduction gearbox, so that oil liquid is by the return pipe in institute
It states and is circulated between reduction gearbox and the cooler bin, to increase the oil liquid in the travelling distance of fuselage interior；And it is described cold
But the peripheral position of case and the reduction gearbox is pasted with cooling fin.
6. cooling type unmanned plane as claimed in claim 5, it is characterised in that:
The return pipe includes: the first hose and the second hose；
The cooler bin includes the first oil inlet and the first oil outlet corresponding with first oil inlet；
The reduction gearbox includes the second oil inlet and the second oil outlet corresponding with second oil inlet；
Wherein, first oil inlet is connected to by first hose with second oil outlet；First oil outlet is logical
Second hose is crossed to be connected to second oil inlet.
7. cooling type unmanned plane as claimed in claim 5, it is characterised in that:
The cooling fin is aluminium flake.
8. cooling type unmanned plane as described in claim 1, which is characterized in that the fixed device includes:
First sleeve；And
Fixed plate；Wherein, the first sleeve is set on the tail transmission shaft, and the fixed plate is set in the first sleeve
On, and the outside of the fixed plate is fixedly connected with the fuselage, with will be described by the 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. cooling type unmanned plane as claimed in claim 8, which is characterized in that the fixed device further include:
Limit plate, wherein
The fixed plate offers first positioning hole, and the excircle that the aperture of the first positioning hole is greater than the first sleeve is straight
Diameter is threaded through the first sleeve in the first positioning hole；
The limit plate offers second location hole, and the excircle that the aperture of the second location hole is greater than the first sleeve is straight
Diameter is threaded through the first sleeve in the second location hole；
The limit plate is with the fixed plate by being fixedly connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610212402.7A CN105836116B (en) | 2016-04-07 | 2016-04-07 | Cooling type unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610212402.7A CN105836116B (en) | 2016-04-07 | 2016-04-07 | Cooling type unmanned plane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105836116A CN105836116A (en) | 2016-08-10 |
| CN105836116B true CN105836116B (en) | 2019-02-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610212402.7A Expired - Fee Related CN105836116B (en) | 2016-04-07 | 2016-04-07 | Cooling type unmanned plane |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107089342A (en) * | 2017-05-12 | 2017-08-25 | 常州银鹰航空科技有限公司 | A kind of unmanned plane liquid cooling system |
| CN107264816A (en) * | 2017-05-12 | 2017-10-20 | 上海寅翅智能科技有限公司 | A kind of unmanned plane liquid cooling system |
| CN211969749U (en) * | 2020-03-31 | 2020-11-20 | 南京达索航空科技有限公司 | Unmanned aerial vehicle cabin heat abstractor |
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| KR20110052370A (en) * | 2009-11-12 | 2011-05-18 | (주)한성티앤아이 | Air cooling engine cooling device of unmanned helicopter |
| CN203638091U (en) * | 2013-12-16 | 2014-06-11 | 大连浦州航空科技有限公司 | Unmanned helicopter transmission device |
| CN203727646U (en) * | 2014-03-13 | 2014-07-23 | 中国科学院沈阳自动化研究所 | Unmanned helicopter |
| EP2778048A1 (en) * | 2013-03-15 | 2014-09-17 | Bell Helicopter Textron Inc. | Autorotative enhancement system |
| CN205652347U (en) * | 2016-04-07 | 2016-10-19 | 易瓦特科技股份公司 | Cooling type unmanned aerial vehicle |
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- 2016-04-07 CN CN201610212402.7A patent/CN105836116B/en not_active Expired - Fee Related
Patent Citations (6)
| 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 |
| KR20110052370A (en) * | 2009-11-12 | 2011-05-18 | (주)한성티앤아이 | Air cooling engine cooling device of unmanned helicopter |
| EP2778048A1 (en) * | 2013-03-15 | 2014-09-17 | Bell Helicopter Textron Inc. | Autorotative enhancement system |
| CN203638091U (en) * | 2013-12-16 | 2014-06-11 | 大连浦州航空科技有限公司 | Unmanned helicopter transmission device |
| CN203727646U (en) * | 2014-03-13 | 2014-07-23 | 中国科学院沈阳自动化研究所 | Unmanned helicopter |
| CN205652347U (en) * | 2016-04-07 | 2016-10-19 | 易瓦特科技股份公司 | Cooling type unmanned aerial vehicle |
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| CN105836116A (en) | 2016-08-10 |
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