CN105752349A - Unmanned helicopter - Google Patents
Unmanned helicopter Download PDFInfo
- Publication number
- CN105752349A CN105752349A CN201610211880.6A CN201610211880A CN105752349A CN 105752349 A CN105752349 A CN 105752349A CN 201610211880 A CN201610211880 A CN 201610211880A CN 105752349 A CN105752349 A CN 105752349A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- drive link
- bar
- fixing
- depopulated helicopter
- 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.)
- Granted
Links
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
Abstract
The invention discloses an unmanned helicopter. The unmanned helicopter comprises a body, a main rotor, a tail rotor, a steering engine, an engine, a reduction gearbox, a support component, a landing gear, a thrust amplification mechanism, a cooling device and a fixing device, wherein the reduction gearbox is connected with the engine, the support component is arranged in the body, the landing gear is fixed at the bottom of the body, the thrust amplification mechanism is connected with the steering engine, the cooling device is connected with the reduction gearbox, and the fixing device sleeves a tail transmission shaft and is fixedly connected with the body. By the unmanned helicopter, the technical defect that due to the fact that the tail transmission shaft has a long shaft body distance inside the body of the unmanned helicopter, the tail transmission shaft bounces quite easily, and the smooth flight of the unmanned helicopter is affected unfavorably in the prior art is overcome.
Description
Technical field
The present invention relates to depopulated helicopter technical field, particularly to depopulated helicopter.
Background technology
UAV is called for short " depopulated helicopter ", is the not manned aircraft of the presetting apparatus manipulation utilizing radio robot with providing for oneself.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 by the equipment such as radar, it be tracked, position, remote control, remote measurement and Digital Transmission.Can take off as conventional airplane under wireless remotecontrol or launch with booster rocket, it is possible to be taken to by machine tool and throw in flight in the air.
In prior art, the tail transmission shaft within depopulated helicopter is for being transferred in tail rotor by the driving force of electromotor, then drives tail rotor to rotate.But distant due to tail rotor distance electromotor, this allows for tail transmission shaft and there is one section longer axle body distance in the fuselage interior of depopulated helicopter, is very easy to generation and beats, be unfavorable for the smooth flight of depopulated helicopter in flight course.
Summary of the invention
The present invention provides a kind of depopulated helicopter, solve in prior art owing to tail transmission shaft exists axle body distance one section longer in the fuselage interior of depopulated helicopter, and the tail transmission shaft in flight course caused is very easy to generation and beats, it is unfavorable for the technological deficiency of the smooth flight of depopulated helicopter.
For solving above-mentioned technical problem, the invention provides a kind of depopulated helicopter, including fuselage, main rotor, tail rotor, steering wheel, electromotor and reduction box, described reduction box is connected with described electromotor, wherein, described main rotor is rotatably fixed with described fuselage by final drive shaft and is connected；Described tail rotor is fixedly installed on the afterbody of described fuselage, and is rotatably fixed with described fuselage by tail transmission shaft and is connected；Described electromotor is connected with described main rotor and described tail rotor, is used for driving described main rotor and described tail rotor to rotate, and described steering wheel is fixed on the inside of described fuselage；Described depopulated helicopter also includes: a support component, and described support component is arranged in described fuselage, is used for supporting and fixing described final drive shaft；Take-off and landing device, described take-off and landing device is fixed on the bottom of described fuselage, is supported during so that described depopulated helicopter to be landed；Thrust amplifying mechanism, described thrust amplifying mechanism is connected with described steering wheel, to amplify the thrust that described steering wheel produces；Chiller, described chiller is connected with described reduction box；Fixing device, described fixing device is set on described tail transmission shaft, and fixing with described fuselage is connected, described tail transmission shaft and described fuselage to be relatively fixed.
Optionally, described support component includes: the first bar；Second bar；And positioning seat；Wherein, one end of described first bar is removably secured with described final drive shaft and is connected, and the other end of described first bar offers a groove；One end of described second bar is set in described groove, in the end of one end of described second bar and the inwall of described groove, puts and is provided with one or more elastic ball so that the stress between described first bar and described second bar is cushioned；The other end of described second bar and one end of described positioning seat are rotationally connected so that described second bar is rotatable relative to described positioning seat.
Optional: the other end of described positioning seat is by flexible being fixed on described fuselage of a resilient sleeve, so that described positioning seat and described fuselage flexibly connect.
Optionally, described take-off and landing device includes: undercarriage, and described undercarriage is fixedly installed on the bottom of described fuselage；And described undercarriage offers the first fixing hole；Brake wheel, described brake wheel and described undercarriage are removably secured at described first fixing hole place and are connected, so that described depopulated helicopter is directly contacted with ground by brake wheel in descent.
Optionally, described brake wheel includes: swiveling wheel, and described swiveling wheel is connected to a rotating shaft, and described swiveling wheel can rotate around the centrage of described rotating shaft；Connecting plate, one end of described connecting plate is fixing with described rotating shaft to be connected；Controlling bar, described control bar is removably secured with the other end of described connecting plate and is connected；Wherein, described control bar moves up or down, and regulates the described swiveling wheel height relative to described undercarriage to drive described connecting plate to rotate.
Optionally, described thrust amplifying mechanism includes: the first drive link, and one end of described first drive link is fixed on described fuselage；Second drive link, one end of described second drive link is fixed on the steering wheel of described fuselage interior；And driver plate, described driver plate is rotationally connected with the other end of the other end of described first drive link and described second drive link respectively, and described driver plate is rotationally connected with described fuselage；Make described steering wheel that the active force of described second drive link is passed through described driver plate, be transferred to described first drive link.
Optionally, described driver plate includes: the first point；Second point；And thirdly；Wherein, the other end of described first drive link and described driver plate are rotationally connected at described first place so that described first drive link can rotate by relatively described first drive link at described first place；The other end of described second drive link and described driver plate are rotationally connected at described second point place so that described second drive link can rotate by relatively described second drive link at described second point place；Described driver plate is rotationally connected at thirdly place and described fuselage, and described driver plate can rotate by relatively described fuselage at described thirdly place.
Optionally, described chiller includes: cooler bin；Return duct；Wherein, described cooler bin is connected with described reduction box by described return duct so that fluid is circulated between described reduction box and described cooler bin by described return duct, to increase the described fluid travelling distance in fuselage interior；And the peripheral position of described cooler bin and described reduction box is pasted with fin.
Optionally, described fixing device includes: the first sleeve；And fixing plate；Wherein, described first set jacket casing is located on described tail transmission shaft, described fixing sleeve-board is located on described first sleeve, and the outside of described fixing plate is fixing with described fuselage is connected, with the inside being fixed on described fuselage described tail transmission shaft consolidated by described first sleeve and described fixing plate, to prevent described tail transmission shaft from beating.
Optionally, described fixing device also includes: limiting plate, and wherein, described fixing plate offers the first hole, location, and the aperture in described first hole, location, more than the excircle diameter of described first sleeve, makes described first sleeve be located in described first hole, location；Described limiting plate offers the second hole, location, and the aperture in described second hole, location, more than the excircle diameter of described first sleeve, makes described first sleeve be located in described second hole, location；Described limiting plate is connected by fixing with described fixing plate.
The application has the beneficial effect that:
(1) the application reduces the abrasion of described undercarriage when described depopulated helicopter rises and falls by arranging brake wheel, and described brake wheel is manually controllable, simple in construction and conveniently dismounting.
(2) the application adopts described first bar and described second bar by being socketed, and it is provided with elastic ball between described first bar and described second bar, ensure that the reliability and stability of connection, improve the shock resistance of a described support component on the one hand, on the other hand, the cushion effect after member stress is added, it is to avoid described support component was subject to large impact, improve the life-span of a described support component, the safety and firmness of the final final drive shaft realized runs.
(3) the application is by arranging the first drive link, the second drive link and driver plate, connected by steering wheel and the second drive link, second drive link is connected with driver plate, driver plate and the first drive link connect, such steering wheel acts on the power of the second drive link, pass sequentially through driver plate, the first drive link is ultimately applied to main rotor so that is made up of primary transmission the first drive link, the second drive link and driver plate to amplify the thrust of described steering wheel, decreases the loss of energy.
(4) the application is by setting up cooler bin and return duct, make to be in the fluid of reduction box in fuselage interior, circulated in cooler bin and reduction box by return duct, increase the fluid travelling distance in fuselage interior, simultaneously, it is provided with fin at the peripheral position of reduction box and cooler bin, so that reduction box and cooler bin to be dispelled the heat further, solves the technological deficiency that in prior art, depopulated helicopter fuselage interior radiating effect is bad.
(5) the application sets up the first sleeve and fixing plate by setting, first set jacket casing is located at the outside of tail transmission shaft, fixing sleeve-board is located at the outside of the first sleeve, make to be relatively fixed the tail transmission shaft of fuselage interior and fuselage, be effectively prevented depopulated helicopter and technological deficiency of very easily beating of causing long due to tail transmission shaft in flight course.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below the accompanying drawing used required during embodiment is described is briefly described, it should be apparent that, the accompanying drawing in the following describes is only some embodiments of the present invention.
Fig. 1 is in the application one better embodiment, depopulated helicopter structural representation；
Fig. 2 is in the another better embodiment of the application, the structural representation of depopulated helicopter；
Fig. 3 is the structural representation fixing device in Fig. 1；
Fig. 4 is the structural representation of the application chiller；
Fig. 5 is the structural representation of the application reduction box；
Fig. 6 is the partial view of a support component in Fig. 2；
Fig. 7 be in Fig. 1 brake wheel structural representation；
Fig. 8 is the right view of brake wheel in Fig. 7.
Detailed description of the invention
In order to be better understood from technique scheme, below in conjunction with Figure of description and specific embodiment, technique scheme is described in detail.
Refer to Fig. 1 and Fig. 2, a kind of depopulated helicopter 100 that the application provides, described depopulated helicopter at least includes fuselage 1, main rotor 2, tail rotor 3 and electromotor 4, described main rotor 2 rotates to provide lifting force, described tail rotor 3 rotates to offset the moment of torsion produced when described main rotor 2 rotates, to ensure the smooth flight of described depopulated helicopter 100.
Concrete, referring to Fig. 3, tail transmission shaft 7 is for the driving force of electromotor 4 is transferred to tail rotor 3.Due to distant apart from described electromotor 4 of described tail rotor 3, described tail transmission shaft 7 easily produces to beat at depopulated helicopter 100 in-flight.And tail transmission shaft 7 is connected by the fixing device 8 that the application provides with fuselage 1, with fixing tail transmission shaft 7, reduce the amplitude of beating of described tail transmission shaft 7.Described fixing device 8 includes the first sleeve 82, fixing plate 81 and limiting plate 83, described first sleeve 82 is set on described tail transmission shaft 7, the outside of described fixing plate 81 is fixing with described fuselage 1 to be connected, described fixing plate 81 offers the first hole, location, the aperture in described first hole, location, more than the excircle diameter of described first sleeve 82, makes described first sleeve 82 be located in described first hole, location.Described limiting plate 83 offers the second hole, location, and the aperture in described second hole, location, more than the excircle diameter of described first sleeve 82, makes described first sleeve 82 be located in described second hole, location.Described limiting plate 83 is bolted with described fixing plate 81, and by being provided with surplus between bolt and screwed hole, reduces beating of tail transmission shaft 7, and be hardly damaged described tail transmission shaft 7.Concrete, described limiting plate 83 and described fixing plate 81 all offer screwed hole, and adopt and leave the bolt of surplus with described screwed hole and be located in described screwed hole to fix described fixing plate 81 and described limiting plate 83, reduce beating of described tail transmission shaft 7, and be hardly damaged described tail transmission shaft 7.By arranging the first sleeve 82, described first sleeve 82 is set in described tail transmission shaft 7, weares and teares to avoid the direct friction of described tail transmission shaft 7 and described limiting plate 83 or described fixing plate 81, improves the life-span of described tail transmission shaft 7.
Further, consulting 4-5 in the lump incorporated by reference to Fig. 1-2, the embodiment of the present application additionally provides a kind of chiller.Reduction box 12 is connected with described electromotor 4, for the power of described electromotor 4 output is carried out regulator drive.Described chiller includes at least one cooler bin 13, and described cooler bin 13 includes the first oil-in and first oil-out corresponding with described first oil-in；Described reduction box 12 includes the second oil-in and second oil-out corresponding with described second oil-in；Described first oil-in connects with described second oil-out, it is preferred that described first oil-in and described second oil-out are hose connection and connect by first；Described first oil-out connects with described second oil-in, it is preferred that described first oil-out and described second oil-in are hose connection and connect by second.And the application is by a sheathed worm structure on the gear shaft in described reduction box 12, being pressed onto in described cooler bin 13 by gear oil in described reduction box 12 when described worm structure is rotated, the fuselage interior structure cooling making described depopulated helicopter 100 is more abundant.Certainly, in the application, the peripheral position of reduction box 12 and cooler bin 13 is also respectively provided with fin, to strengthen radiating effect further.As preferably, this fin can be aluminium flake.
Based on same inventive concept, reduction box 12 place that the application is arranged at tail rotor 3 structure division of described depopulated helicopter 100 is also equipped with a chiller, it is all often the Local cooling adopted that the common chiller 100 being applied to depopulated helicopter cools down, by adding gear oil, and be applied to the gear-box surface of reduction box 12 in the chiller 100 of depopulated helicopter described in relying on and dispel the heat, the heat radiation of this type of cooling is slow, and be only capable of being dispelled the heat in the local in the described chiller 100 being applied to depopulated helicopter, good radiating effect can not be obtained.The chiller 100 being applied to depopulated helicopter that the application provides also includes afterbody reduction box 12 and chiller.Concrete, described reduction box 12 is connected with described electromotor 4, for the power of described electromotor 4 output is carried out regulator drive.The described chiller 100 being applied to depopulated helicopter also includes at least one cooler bin 13, and described cooler bin 13 includes the first oil-in and first oil-out corresponding with described first oil-in；Described reduction box 12 includes the second oil-in and second oil-out corresponding with described second oil-in；Described first oil-in connects with described second oil-out, it is preferred that described first oil-in passes through hose connection with described second oil-out and connects；Described first oil-out connects with described second oil-in, it is preferred that described first oil-out passes through hose connection with described second oil-in and connects.And the application is by a sheathed worm structure on the gear shaft in described reduction box 12 so that the gear oil in described reduction box 12 is pressed onto in described cooler bin 13 when rotating by described worm structure, the fuselage interior structure cooling making depopulated helicopter 100 is more abundant.
Further, please continue to refer to Fig. 4, present invention also provides a kind of thrust amplifying mechanism 9, be connected with steering wheel；Described steering wheel is used for controlling depopulated helicopter 100 flight attitude and track.Described thrust amplifying mechanism 9 increases the one-level transmission with described steering wheel to amplify the thrust that steering wheel produces, and reduces energy loss.Concrete, described thrust amplifying mechanism 9 includes the first drive link the 91, second drive link 93 and driver plate 92, and described driver plate 92 includes 1: 921, second point 923 and thirdly 922.Described driver plate 92 is connected with described first drive link 91 and described second drive link 93 respectively；One end of described first drive link 91 is force side, one end of described first drive link 91 is fixing with described fuselage 1 to be connected, the other end of described first drive link 91 is fixing at described 1: 921 place with described driver plate 92 to be connected, and described first drive link 91 can rotate relative to described 1: 921.One end of described second drive link 93 is fixing at described second point 923 place with described driver plate 92 to be connected, and described second drive link 93 can rotate relative to described second point 923, and the other end of described second drive link 93 is connected with described steering wheel.Described driver plate 92 is connected with described fuselage 1 at thirdly 922 places, and described driver plate 92 can relative to described in thirdly 922 rotate.Increase primary transmission amplify the thrust of described steering wheel by arranging first drive link the 91, second drive link 93 and driver plate 92, reduce energy loss.
Preferably, described first drive link 91 is hinged at the 1: 921 place with described driver plate 92；Described second drive link 93 is hinged at second point 923 place with described driver plate 92；Described driver plate 92 is hinged at thirdly 922 places with described fuselage 1.
Preferably, described 1: 921, second point 923 and thirdly 922 position triangular in shape.
Further, referring to Fig. 6, present invention also provides one support component 11, be applied to depopulated helicopter 100, the support component 11 that the application provides is arranged in described fuselage 1, for supporting and fix the spacing collar of described final drive shaft 10.Described support component 11 is by adopting supported at three point, and supporting construction is stablized and to the effect that can play damping in described depopulated helicopter 100 flight course.Concrete, described support component 11 includes the first bar the 111, second bar 113 and positioning seat 114；One end of described first bar 111 is removably secured with described fuselage 1 and is connected, and the other end of described first bar 111 offers a groove；One end of described second bar 113 is set in described groove, put in the end of one end of described second bar 113 and the inwall of described groove and be provided with one or more elastic ball 112, stress between described first bar 111 and described second bar 113 is cushioned, reduces vibrations.
In the present embodiment, described elastic ball 112 is baton round；The other end of described second bar 113 is provided with the first lug, described first lug offers the first through hole, one end of described positioning seat 114 is provided with the second lug, described second lug offers the second through hole mated with described first through hole, described first through hole and described second through hole are bolted, and make described second bar 113 can rotate relative to described positioning seat 114.In order to reduce the vibrations of a described support component 11 further, the other end of described positioning seat 114 is also arranged with a resilient sleeve, described resilient sleeve is I-shaped, described resilient sleeve is set on described positioning seat 114, and the groove of the I-shaped of described resilient sleeve is fastened on the fuselage 1 of described depopulated helicopter 100, it is connected so that described positioning seat 114 is fixing with described fuselage 1.
In the present embodiment, described resilient sleeve is rubber sleeve.The shock resistance of a described support component 11 is further increased by arranging resilient sleeve.Described first bar 111 and described second bar 113 are by being socketed, and are provided with elastic ball 112 between described first bar 111 and described second bar 113, also improve the shock resistance of a described support component 11.The application adopts described first bar 111 and described second bar 113 by being socketed, and it is provided with elastic ball 112 between described first bar 111 and described second bar 113, instead of the hinged etc. of routine, described first bar 111 and described second bar 113 are subject to pretightning force and ensure that the reliability and stability of connection, improve the shock resistance of a described support component 11 on the one hand, on the other hand, add the cushion effect after member stress, avoid a described support component 11 to be subject to large impact, improve the life-span of a described support component 11.
Further, consulting Fig. 7-8 in the lump incorporated by reference to Fig. 1-2, the present embodiment additionally provides a kind of take-off and landing device, and for take-off and landing device, including a undercarriage 5 and brake wheel 6, described undercarriage 5 is fixedly installed on the bottom of described fuselage 1.Described brake wheel 6 is removably secured with described undercarriage 5 and is connected.Described brake wheel 6 be arranged to reduce the abrasion of described undercarriage 5 when described depopulated helicopter 100 rises and falls, and described brake wheel 6 is manually controllable, simple in construction and convenient dismounting.
Concrete, described undercarriage 5 offers the first fixing hole, described first fixing hole for described brake wheel 6 with the use of, to be plugged in described first fixing hole by fixture and in described brake wheel 6, to make described brake wheel 6 fix with described undercarriage 5 and be connected.In the present embodiment, described fixture is specially latch.
Further, described brake wheel 6 includes swiveling wheel 61, connecting plate 62 and controls bar 63.Described swiveling wheel 61 includes a rotating shaft, and described swiveling wheel 61 can rotate around the centrage of described rotating shaft.One end of described connecting plate 62 is fixing with described rotating shaft to be connected；Control bar, be removably secured with the other end of described connecting plate 62 and be connected；Described control bar 63 moves up or down, and makes described connecting plate 62 rotate the height regulating described swiveling wheel 61.Concrete, one end of described connecting plate 62 offers the first connecting hole, the other end of described connecting plate 62 offers the second connecting hole, and described connecting plate 62 is further opened with the second fixing hole, and described second fixed hole position is between described first connecting hole and described second connecting hole.Described control bar 63 is removably secured with described connecting plate 62 and is connected, it is preferred that one end of described control bar 63 is provided with a fixed part, and described fixed part is located in described second connecting hole, and is connected by latch or clip are fixing with described connecting plate 62.Described rotating shaft is located in described first connecting hole, and described rotating shaft is fixing with described connecting plate 62 in described first connection hole to be connected so that the height of swiveling wheel 61 described in adjustable when described connecting plate 62 rotates.The application adopts connecting plate 62, rotating shaft and controls bar 63 and form a linkage, and combines the position of the mobile adjustment brake wheel 6 controlling bar 63, simple in construction and convenient dismounting.
During operation, described control bar 63 is manually made to move up or down, described swiveling wheel 61 is made to move down, when the minimum altitude of described swiveling wheel 61 is lower than the minimum altitude of described undercarriage 5, and the difference in height of the minimum altitude of described swiveling wheel 61 and the minimum altitude of described undercarriage 5 equal to or more than preset value time, described first fixing hole and described second fixing hole plug fixture, with fixing described brake wheel 6.The brake wheel 6 that the application is arranged, Non-follow control and readily accessible, reduce the abrasion of described undercarriage 5, improve the life-span of described depopulated helicopter 100.
The application has the beneficial effect that:
1, the application reduces the abrasion of described undercarriage when described depopulated helicopter rises and falls by arranging brake wheel, and described brake wheel is manually controllable, simple in construction and conveniently dismounting.
2, the application adopts described first bar and described second bar by being socketed, and it is provided with elastic ball between described first bar and described second bar, ensure that the reliability and stability of connection, improve the shock resistance of a described support component on the one hand, on the other hand, the cushion effect after member stress is added, it is to avoid described support component was subject to large impact, improve the life-span of a described support component, the safety and firmness of the final final drive shaft realized runs.
3, the application is by arranging the first drive link, the second drive link and driver plate, connected by steering wheel and the second drive link, second drive link is connected with driver plate, driver plate and the first drive link connect, such steering wheel acts on the power of the second drive link, pass sequentially through driver plate, the first drive link is ultimately applied to main rotor so that is made up of primary transmission the first drive link, the second drive link and driver plate to amplify the thrust of described steering wheel, decreases the loss of energy.
4, the application is by setting up cooler bin and return duct, make to be in the fluid of reduction box in fuselage interior, circulated in cooler bin and reduction box by return duct, increase the fluid travelling distance in fuselage interior, simultaneously, it is provided with fin at the peripheral position of reduction box and cooler bin, so that reduction box and cooler bin to be dispelled the heat further, solves the technological deficiency that in prior art, depopulated helicopter fuselage interior radiating effect is bad.
5, the application sets up the first sleeve and fixing plate by setting, first set jacket casing is located at the outside of tail transmission shaft, fixing sleeve-board is located at the outside of the first sleeve, make to be relatively fixed the tail transmission shaft of fuselage interior and fuselage, be effectively prevented depopulated helicopter and technological deficiency of very easily beating of causing long due to tail transmission shaft in flight course.
It should be noted last that, above detailed description of the invention is only in order to illustrate technical scheme and unrestricted, although the present invention being described in detail with reference to example, it will be understood by those within the art that, technical scheme can be modified or equivalent replacement, without deviating from the spirit and scope of technical solution of the present invention, it all should be encompassed in the middle of scope of the presently claimed invention.
Claims (10)
1. a depopulated helicopter, including fuselage, main rotor, tail rotor, steering wheel, electromotor and reduction box, described reduction box is connected with described electromotor, and wherein, described main rotor is rotatably fixed with described fuselage by final drive shaft and is connected；Described tail rotor is fixedly installed on the afterbody of described fuselage, and is rotatably fixed with described fuselage by tail transmission shaft and is connected；Described electromotor is connected with described main rotor and described tail rotor, is used for driving described main rotor and described tail rotor to rotate, and described steering wheel is fixed on the inside of described fuselage；It is characterized in that, described depopulated helicopter also includes:
Propping up support component, described support component is arranged in described fuselage, is used for supporting and fixing described final drive shaft；
Take-off and landing device, described take-off and landing device is fixed on the bottom of described fuselage, is supported during so that described depopulated helicopter to be landed；
Thrust amplifying mechanism, described thrust amplifying mechanism is connected with described steering wheel, to amplify the thrust that described steering wheel produces；
Chiller, described chiller is connected with described reduction box；
Fixing device, described fixing device is set on described tail transmission shaft, and fixing with described fuselage is connected, described tail transmission shaft and described fuselage to be relatively fixed.
2. depopulated helicopter as claimed in claim 1, it is characterised in that described support component includes:
First bar；
Second bar；And
Positioning seat；Wherein, one end of described first bar is removably secured with described final drive shaft and is connected, and the other end of described first bar offers a groove；One end of described second bar is set in described groove, in the end of one end of described second bar and the inwall of described groove, puts and is provided with one or more elastic ball so that the stress between described first bar and described second bar is cushioned；The other end of described second bar and one end of described positioning seat are rotationally connected so that described second bar is rotatable relative to described positioning seat.
3. depopulated helicopter as claimed in claim 2, it is characterised in that:
The other end of described positioning seat is by flexible being fixed on described fuselage of a resilient sleeve, so that described positioning seat and described fuselage flexibly connect.
4. depopulated helicopter as claimed in claim 1, it is characterised in that described take-off and landing device includes:
Undercarriage, described undercarriage is fixedly installed on the bottom of described fuselage；And described undercarriage offers the first fixing hole；
Brake wheel, described brake wheel and described undercarriage are removably secured at described first fixing hole place and are connected, so that described depopulated helicopter is directly contacted with ground by brake wheel in descent.
5. depopulated helicopter as claimed in claim 4, it is characterised in that described brake wheel includes:
Swiveling wheel, described swiveling wheel is connected to a rotating shaft, and described swiveling wheel can rotate around the centrage of described rotating shaft；
Connecting plate, one end of described connecting plate is fixing with described rotating shaft to be connected；
Controlling bar, described control bar is removably secured with the other end of described connecting plate and is connected；
Wherein, described control bar moves up or down, and regulates the described swiveling wheel height relative to described undercarriage to drive described connecting plate to rotate.
6. depopulated helicopter as claimed in claim 1, it is characterised in that described thrust amplifying mechanism includes:
First drive link, one end of described first drive link is fixed on described fuselage；
Second drive link, one end of described second drive link is fixed on the steering wheel of described fuselage interior；And
Driver plate, described driver plate is rotationally connected with the other end of the other end of described first drive link and described second drive link respectively, and described driver plate is rotationally connected with described fuselage；Make described steering wheel that the active force of described second drive link is passed through described driver plate, be transferred to described first drive link.
7. depopulated helicopter as claimed in claim 6, it is characterised in that described driver plate includes:
First point；
Second point；And
Thirdly；Wherein, the other end of described first drive link and described driver plate are rotationally connected at described first place so that described first drive link can rotate by relatively described first drive link at described first place；The other end of described second drive link and described driver plate are rotationally connected at described second point place so that described second drive link can rotate by relatively described second drive link at described second point place；Described driver plate is rotationally connected at thirdly place and described fuselage, and described driver plate can rotate by relatively described fuselage at described thirdly place.
8. depopulated helicopter as claimed in claim 1, it is characterised in that described chiller includes:
Cooler bin；
Return duct；
Wherein, described cooler bin is connected with described reduction box by described return duct so that fluid is circulated between described reduction box and described cooler bin by described return duct, to increase the described fluid travelling distance in fuselage interior；And the peripheral position of described cooler bin and described reduction box is pasted with fin.
9. depopulated helicopter as claimed in claim 1, it is characterised in that described fixing device includes:
First sleeve；And
Fixing plate；Wherein, described first set jacket casing is located on described tail transmission shaft, described fixing sleeve-board is located on described first sleeve, and the outside of described fixing plate is fixing with described fuselage is connected, with the inside being fixed on described fuselage described tail transmission shaft consolidated by described first sleeve and described fixing plate, to prevent described tail transmission shaft from beating.
10. depopulated helicopter as claimed in claim 9, it is characterised in that described fixing device also includes:
Limiting plate, wherein,
Described fixing plate offers the first hole, location, and the aperture in described first hole, location, more than the excircle diameter of described first sleeve, makes described first sleeve be located in described first hole, location；
Described limiting plate offers the second hole, location, and the aperture in described second hole, location, more than the excircle diameter of described first sleeve, makes described first sleeve be located in described second hole, location；
Described limiting plate is connected by fixing with described fixing plate.
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 true CN105752349A (en) | 2016-07-13 |
| CN105752349B CN105752349B (en) | 2017-12-26 |
Family
ID=56334384
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610211880.6A Expired - Fee Related CN105752349B (en) | 2016-04-07 | 2016-04-07 | Depopulated helicopter |
Country Status (1)
| Country | Link |
|---|---|
| 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 |
|---|---|
| CN105752349B (en) | 2017-12-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10183742B2 (en) | Direct orientation vector rotor | |
| CN105752321A (en) | Unmanned aerial vehicle landing device and unmanned aerial vehicle | |
| CN105836116B (en) | Cooling type unmanned plane | |
| CN105752350A (en) | Unmanned aerial equipment with fixed tail transmission shaft | |
| CN205652347U (en) | Cooling type unmanned aerial vehicle | |
| CN105752324A (en) | Unmanned flight equipment | |
| CN105752323B (en) | Land wear-resistance unmanned plane | |
| CN205652373U (en) | Tail transmission shaft is unmanned aerial vehicle equipment of fixed | |
| CN205652342U (en) | Unmanned aerial vehicle with landing gear and cooling device | |
| CN205652375U (en) | Unmanned aerial vehicle with supporting component and fixing device | |
| CN205652345U (en) | Unmanned aerial vehicle equipment | |
| CN205707383U (en) | Depopulated helicopter | |
| CN112424065A (en) | Aircraft propulsion and torque mitigation techniques | |
| CN205652359U (en) | Type unmanned aerial vehicle takes precautions against earthquakes | |
| CN205707307U (en) | Landing wear-resistance unmanned plane | |
| US20190256218A1 (en) | Transmission system for aircraft structure | |
| US2948489A (en) | Captive rotary wing aircraft and control system | |
| CN105752349A (en) | Unmanned helicopter | |
| CN205872450U (en) | Unmanned aerial vehicle landing gear and unmanned aerial vehicle | |
| CN205707347U (en) | It is applied to the fixing device of depopulated helicopter | |
| CN205652353U (en) | Unmanned aerial vehicle with cooling device and fixing device | |
| CN205652343U (en) | Unmanned aerial vehicle with landing gear and fixing device | |
| CN205652340U (en) | Unmanned aerial vehicle with supporting component and thrust mechanism of amplification | |
| CN205652374U (en) | Unmanned aerial vehicle with supporting component and cooling device | |
| CN205652372U (en) | Be applied to cooling device of unmanned helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information |
Address after: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Applicant after: Easy Technology Co Ltd Address before: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Applicant before: EWATT CO., LTD. |
|
| COR | Change of bibliographic data | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171226 Termination date: 20190407 |