CN105752350A - Unmanned aerial equipment with fixed tail transmission shaft - Google Patents
Unmanned aerial equipment with fixed tail transmission shaft Download PDFInfo
- Publication number
- CN105752350A CN105752350A CN201610212335.9A CN201610212335A CN105752350A CN 105752350 A CN105752350 A CN 105752350A CN 201610212335 A CN201610212335 A CN 201610212335A CN 105752350 A CN105752350 A CN 105752350A
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- Prior art keywords
- transmission shaft
- tail transmission
- fuselage
- fixing
- drive link
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 90
- 238000010009 beating Methods 0.000 claims description 7
- 230000003321 amplification Effects 0.000 abstract 2
- 238000003199 nucleic acid amplification method Methods 0.000 abstract 2
- 230000007547 defect Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 7
- 238000010276 construction Methods 0.000 description 5
- 230000035939 shock Effects 0.000 description 5
- 238000005299 abrasion Methods 0.000 description 4
- 238000001816 cooling Methods 0.000 description 4
- 230000007812 deficiency Effects 0.000 description 4
- 208000032369 Primary transmission Diseases 0.000 description 3
- 230000001276 controlling effect Effects 0.000 description 3
- 239000012208 gear oil Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 210000001138 tear Anatomy 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
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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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
Abstract
The invention discloses unmanned aerial equipment with a fixed tail transmission shaft. The unmanned aerial equipment 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 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, and the fixing device sleeves the tail transmission shaft and is fixedly connected with the body. By the unmanned aerial equipment with the fixed tail transmission shaft, 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 aerial equipment, the tail transmission shaft bounces quite easily, and the smooth flight of the unmanned aerial equipment is affected unfavorably in the prior art is overcome.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, be unmanned flight's equipment of fixed pattern particularly to tail transmission shaft.
Background technology
UAV is called for short " unmanned flight's equipment ", 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 due to tail rotor distance electromotor distant, this allows for the fuselage interior of unmanned flight's equipment that tail transmission shaft is fixed pattern at tail transmission shaft and there is one section longer axle body distance, flight course is very easy to generation beat, is unfavorable for that tail transmission shaft is the smooth flight of unmanned flight's equipment of fixed pattern.
Summary of the invention
The present invention provides a kind of tail transmission shaft to be unmanned flight's equipment of fixed pattern, solve in prior art owing to tail transmission shaft exists axle body distance one section longer in fuselage interior, 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 unmanned flight's equipment that a kind of tail transmission shaft is fixed pattern, 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;Unmanned flight's equipment that described tail transmission shaft is fixed pattern 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, with to described tail transmission shaft be fixed pattern unmanned flight's equipment landing time be supported;Thrust amplifying mechanism, described thrust amplifying mechanism is connected with described steering wheel, to amplify the thrust that described steering wheel produces;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, and are directly contacted with ground by brake wheel in descent so that described tail transmission shaft is unmanned flight's equipment of fixed pattern.
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 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.
Optionally, described limiting plate and described fixing plate all offering screwed hole, the fixing connection between described limiting plate with described fixing plate is threaded;The described rounded shape of fixing plate.
The application has the beneficial effect that:
(1) the application reduces the abrasion of described undercarriage when unmanned flight's equipment that described tail transmission shaft is fixed pattern 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 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 unmanned flight's equipment that tail transmission shaft is fixed pattern 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, and tail transmission shaft is unmanned flight's device structure schematic diagram of fixed pattern;
Fig. 2 is in the another better embodiment of the application, and tail transmission shaft is the structural representation of unmanned flight's equipment of fixed pattern;
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 tail transmission shaft that the application provides is unmanned flight's equipment 100 of fixed pattern, unmanned flight's equipment that described tail transmission shaft is fixed pattern 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 that described tail transmission shaft is unmanned flight's equipment 100 smooth flight of fixed pattern.
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 unmanned flight's equipment 100 that tail transmission shaft is fixed pattern 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, when described worm structure is rotated, the gear oil in described reduction box 12 is pressed onto in described cooler bin 13, make described tail transmission shaft be fixed pattern unmanned flight's equipment 100 fuselage interior structure cooling 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 the tail rotor 3 structure division setting of unmanned flight's equipment 100 of fixed pattern at described tail transmission shaft is also equipped with a chiller, it is common that to be applied to that the chiller 100 of unmanned flight's equipment that tail transmission shaft is fixed pattern cools down be all often the Local cooling adopted, by adding gear oil, and be applied to described in relying on tail transmission shaft be fixed pattern unmanned flight's equipment chiller 100 in the gear-box surface of reduction box 12 dispel the heat, the heat radiation of this type of cooling is slow, and be only capable of to described be applied to tail transmission shaft be fixed pattern unmanned flight's equipment chiller 100 in local dispel the heat, good radiating effect can not be obtained.What the application provided be applied to the chiller 100 of unmanned flight's equipment that tail transmission shaft is fixed pattern 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.Described being applied to the chiller 100 of unmanned flight's equipment that tail transmission shaft is fixed pattern and also include at least one cooler bin 13, 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, when described worm structure is rotated, the gear oil in described reduction box 12 is pressed onto in described cooler bin 13, make tail transmission shaft be fixed pattern unmanned flight's equipment 100 fuselage interior structure cooling 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 for controlling unmanned flight's equipment 100 flight attitude and the track that tail transmission shaft is fixed pattern.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, refer to Fig. 6, present invention also provides a kind of support component 11, be applied to unmanned flight's equipment 100 that tail transmission shaft is fixed pattern, 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 by adopting supported at three point, supporting construction stable and to described tail transmission shaft be fixed pattern unmanned flight's equipment 100 flight course in can play the effect of damping.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 to be fastened on described tail transmission shaft be on the fuselage 1 of unmanned flight's equipment 100 of fixed pattern be 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 unmanned flight's equipment 100 that described tail transmission shaft is fixed pattern 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 that described tail transmission shaft is unmanned flight's equipment 100 of fixed pattern.
The application has the beneficial effect that:
1, the application reduces the abrasion of described undercarriage when unmanned flight's equipment that described tail transmission shaft is fixed pattern 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, being 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, solving tail transmission shaft in prior art is the bad technological deficiency of unmanned flight's device body internal heat dissipating effect of fixed pattern.
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 unmanned flight's equipment that tail transmission shaft is fixed pattern 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 tail transmission shaft is unmanned flight's equipment of fixed pattern, 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, unmanned flight's equipment that described tail transmission shaft is fixed pattern 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, with to described tail transmission shaft be fixed pattern unmanned flight's equipment landing time be supported;
Thrust amplifying mechanism, described thrust amplifying mechanism is connected with described steering wheel, to amplify the thrust that described steering wheel produces;
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. tail transmission shaft as claimed in claim 1 is unmanned flight's equipment of fixed pattern, 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. tail transmission shaft as claimed in claim 2 is unmanned flight's equipment of fixed pattern, 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. tail transmission shaft as claimed in claim 1 is unmanned flight's equipment of fixed pattern, 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, and are directly contacted with ground by brake wheel in descent so that described tail transmission shaft is unmanned flight's equipment of fixed pattern.
5. tail transmission shaft as claimed in claim 4 is unmanned flight's equipment of fixed pattern, 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. tail transmission shaft as claimed in claim 1 is unmanned flight's equipment of fixed pattern, 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. tail transmission shaft as claimed in claim 6 is unmanned flight's equipment of fixed pattern, 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. tail transmission shaft as claimed in claim 1 is unmanned flight's equipment of fixed pattern, 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.
9. tail transmission shaft as claimed in claim 8 is unmanned flight's equipment of fixed pattern, 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.
10. tail transmission shaft as claimed in claim 9 is unmanned flight's equipment of fixed pattern, it is characterised in that
All offering screwed hole on described limiting plate and described fixing plate, the fixing connection between described limiting plate with described fixing plate is threaded;
The described rounded shape of fixing plate.
Priority Applications (1)
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CN201610212335.9A CN105752350B (en) | 2016-04-07 | 2016-04-07 | Tail transmission shaft is in unmanned flight's equipment of fixed |
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CN201610212335.9A CN105752350B (en) | 2016-04-07 | 2016-04-07 | Tail transmission shaft is in unmanned flight's equipment of fixed |
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CN105752350A true CN105752350A (en) | 2016-07-13 |
CN105752350B CN105752350B (en) | 2018-03-02 |
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CN201610212335.9A Expired - Fee Related CN105752350B (en) | 2016-04-07 | 2016-04-07 | Tail transmission shaft is in unmanned flight's equipment of fixed |
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
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CN111306255A (en) * | 2020-02-24 | 2020-06-19 | 北京中航智科技有限公司 | Transmission system |
CN112238948A (en) * | 2020-10-16 | 2021-01-19 | 中国直升机设计研究所 | Quick-release helicopter tail transmission shaft assembly |
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CN201526610U (en) * | 2009-08-14 | 2010-07-14 | 江苏达胜加速器制造有限公司 | Accelerator transmission shaft |
FR2976553A1 (en) * | 2011-06-20 | 2012-12-21 | Cassidian | SYSTEM FOR INTEGRATING A DIESEL ENGINE IN A DRONE |
CN203727646U (en) * | 2014-03-13 | 2014-07-23 | 中国科学院沈阳自动化研究所 | Unmanned helicopter |
CN205652373U (en) * | 2016-04-07 | 2016-10-19 | 易瓦特科技股份公司 | Tail transmission shaft is unmanned aerial vehicle equipment of fixed |
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- 2016-04-07 CN CN201610212335.9A patent/CN105752350B/en not_active Expired - Fee Related
Patent Citations (5)
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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 |
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Publication number | Priority date | Publication date | Assignee | Title |
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CN111306255A (en) * | 2020-02-24 | 2020-06-19 | 北京中航智科技有限公司 | Transmission system |
CN112238948A (en) * | 2020-10-16 | 2021-01-19 | 中国直升机设计研究所 | Quick-release helicopter tail transmission shaft assembly |
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