CN104229136A - Transmission mechanism and multi-rotor aircraft - Google Patents
Transmission mechanism and multi-rotor aircraft Download PDFInfo
- Publication number
- CN104229136A CN104229136A CN201410128637.9A CN201410128637A CN104229136A CN 104229136 A CN104229136 A CN 104229136A CN 201410128637 A CN201410128637 A CN 201410128637A CN 104229136 A CN104229136 A CN 104229136A
- Authority
- CN
- China
- Prior art keywords
- transmission shaft
- rotor
- shaft
- bearing
- mouth
- 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; 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
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/16—Flying platforms with five or more distinct rotor axes, e.g. octocopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/20—Transmission of mechanical power to rotors or propellers
-
- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C23/00—Bearings for exclusively rotary movement adjustable for aligning or positioning
- F16C23/02—Sliding-contact bearings
- F16C23/04—Sliding-contact bearings self-adjusting
- F16C23/043—Sliding-contact bearings self-adjusting with spherical surfaces, e.g. spherical plain bearings
- F16C23/045—Sliding-contact bearings self-adjusting with spherical surfaces, e.g. spherical plain bearings for radial load mainly, e.g. radial spherical plain bearings
-
- 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2326/00—Articles relating to transporting
- F16C2326/43—Aeroplanes; Helicopters
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Support Of The Bearing (AREA)
- Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The embodiment of the invention provides a transmission mechanism and a multi-rotor aircraft. The transmission mechanism comprises a support rack, a transmission shaft and a bearing assembly, wherein the transmission shaft is mounted on the support rack; the power generated by a power part is transmitted to a driven part by virtue of the transmission shaft; the bearing assembly is mounted on the transmission shaft and comprises a flexible bearing and a support bearing; the flexible bearing comprises an outer ring and an inner ring; the inner surface of the outer ring is a spherical surface; the inner ring is rotatably mounted on the outer ring along the spherical center of the spherical surface; the outer ring is fixed on the inner wall of the support rack; the inner ring is mounted on the support bearing; the support bearing is mounted on the transmission shaft. According to the transmission mechanism, the support rack bends and drives the bearing assembly which is used for supporting the transmission shaft to deflect; as the outer ring and the inner ring of the flexible bearing in the bearing assembly are rotatably connected with each other, the support rack is prevented from transmitting the bending stress generated by bending to the transmission shaft, and then the damage to the transmission shaft is avoided.
Description
Technical field
The present invention relates to transmission field, and more specifically, relate to a kind of transmission device and multi-rotor aerocraft.
Background technology
Multi-rotor aerocraft obtains accreditation and the popularization in market with its good stability and control, at present, multi-rotor aerocraft mostly in the world is electronic multi-rotor aerocraft, modal is electronic four rotors and electronic six rotorcraft, the key character of this type of aircraft uses battery as the energy, motor is as power, and motor is directly connected with rotor.
Owing to being subject to the restriction of capacity of cell, during the boat of electronic multi-rotor aerocraft, (flight time) is short, is generally no more than 1 hour.Similarly, owing to being subject to the restriction of capacity of cell, the load that electronic multi-rotor aerocraft can bear is also relatively little, and its gross weight General Requirements is less than 30kg.Above-mentioned restriction when load and boat causes the application scenarios of multi-rotor aerocraft limited.
At present, a kind of possible settling mode adopts the dynamic driving engine of oil to replace motor as propulsion source.Because oil is liquid, lighter in weight and can provide sufficient power source, when greatly can increase the boat of multi-rotor aerocraft and capacity weight.
But compared with motor, the dynamic driving engine speed of response of oil is slow, course of reaction nonlinearity.Move driving engine if special for each rotor configures one with the oil that it is directly connected, multi-rotor aerocraft cost not only can be made high, and the problem of multi-rotor aerocraft cooperation control difficulty can be faced.A kind of feasible solution of the problems referred to above moves between driving engine and each rotor at oil to utilize transmission shaft to carry out transmission, makes the dynamic transmitting set unification of oil provide power for each rotor.
In above-mentioned solution, the dynamic driving engine of oil and rotor lay respectively at the two ends of the bracing frame supporting this transmission shaft.Inevitably bend under the effect of the moment of flexure that bracing frame is formed in external force (gravity etc. that the pulling force, the gravity of rotor part or the supported member that produce as rotor produce).The bending flexure stress caused of this bracing frame can be passed to this transmission shaft by the backup bearing of bracing frame inside, thus causes transmission shaft to deform, and causes the damage of transmission shaft.
Summary of the invention
The embodiment of the present invention provides a kind of transmission device and multi-rotor aerocraft, to avoid the problem on deformation of transmission shaft under flexure stress effect.
First aspect, provide a kind of transmission device, comprising: bracing frame, one end is connected with power pack section, and the other end is connected with secondary part, and at the mode of operation of described transmission device, the moment of flexure that the bonding force of support frame as described above produces is greater than 0; Be arranged on the transmission shaft on support frame as described above, the transmission of power produced by described power pack section by described transmission shaft is to described secondary part; Be assemblied in the bearing assembly on described transmission shaft, comprise flexible bearing and backup bearing, described flexible bearing comprises outer shroud and inner ring, the inside face of described outer shroud is sphere, described inner ring is rotatably installed in described outer shroud along the centre of sphere of described sphere, described outer shroud is fixed on the inwall of support frame as described above, and described inner ring is arranged on described backup bearing, and described backup bearing is assemblied on described transmission shaft.
In conjunction with first aspect, in a kind of implementation of first aspect, described transmission shaft comprises: the input end be connected with described power pack section; The mouth be connected with described secondary part; Axle unit between described input end and described mouth, described axle unit comprises shaft part and is arranged on the described bearing assembly on described shaft part; Wherein, described input end, be connected successively by coupler between described axle unit and described mouth.
In conjunction with any one of first aspect or its above-mentioned implementation, in the another kind of implementation of first aspect, the described axle unit of N section is comprised between described input end and described mouth, be connected successively by coupler between the described axle unit of N section, wherein, N is determined by the angle compensation amount of the degree of crook of support frame as described above under Moment and the coupler on described transmission shaft.
In conjunction with any one of first aspect or its above-mentioned implementation, in the another kind of implementation of first aspect, described power pack section comprises the dynamic driving engine of oil, and the rotating shaft that described oil moves driving engine is connected with one end of described transmission shaft; Described secondary part comprises rotor, and the rotating shaft of described rotor is connected with the other end of described transmission shaft.
Second aspect, provides a kind of multi-rotor aerocraft, comprising: body, is provided with the dynamic driving engine of oil; Along at least three rotor parts of the circle distribution being the center of circle with described body center, described rotor part and described body are arranged on the two ends of bracing frame respectively, and described oil moves driving engine by being arranged on transmission shaft on support frame as described above by power transmission to described rotor part; Be assemblied in the bearing assembly on described transmission shaft, comprise flexible bearing and backup bearing, described flexible bearing comprises outer shroud and inner ring, the inside face of described outer shroud is sphere, described inner ring is rotatably installed in described outer shroud along the centre of sphere of described sphere, described outer shroud is fixed on the inwall of support frame as described above, and described inner ring is arranged on described backup bearing, and described backup bearing is assemblied on described transmission shaft.
In conjunction with second aspect, in a kind of implementation of second aspect, described transmission shaft comprises: move with described oil the input end that driving engine is connected; The mouth be connected is divided with the Rotary-Wing Department being positioned at this transmission shaft other end; Axle unit between described input end and described mouth, described axle unit comprises shaft part and is arranged on the described bearing assembly on described shaft part; Wherein, described input end, be connected successively by coupler between described axle unit and described mouth.
In conjunction with any one of second aspect or its above-mentioned implementation, in the another kind of implementation of second aspect, the described axle unit of N section is comprised between described input end and described mouth, be connected successively by coupler between the described axle unit of N section, wherein, N is determined by the angle compensation amount of the degree of crook of support frame as described above under Moment and the coupler on described transmission shaft.
In conjunction with any one of second aspect or its above-mentioned implementation, in the another kind of implementation of second aspect, described Rotary-Wing Department divides and comprises: the rotor shaft be connected with the mouth of described transmission shaft; Be assemblied in the inclinator in described rotor shaft, inner ring and the described rotor shaft of described inclinator are fitted.
In conjunction with any one of second aspect or its above-mentioned implementation, in the another kind of implementation of second aspect, described at least three Rotary-Wing Departments are divided into four rotor parts.
In conjunction with any one of second aspect or its above-mentioned implementation, in the another kind of implementation of second aspect, described at least three Rotary-Wing Departments are divided into six rotor parts.
In the embodiment of the present invention, be connected because bracing frame divides with Rotary-Wing Department, the pulling force of vertical direction can be produced during rotor some work, cause bracing frame flexural deformation.The bearing assembly of supporting shaft can be driven after bracing frame bends to deflect.Owing to being rotatably connected between the outer shroud of the flexible bearing in bearing assembly and inner ring, avoiding bracing frame and the flexure stress of bending generation is passed on transmission shaft, and then avoid the damage of transmission shaft.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme of the embodiment of the present invention, be briefly described to the accompanying drawing used required in the embodiment of the present invention below, apparently, accompanying drawing described is below only some embodiments of the present invention, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is the section-drawing of the transmission device of one embodiment of the invention.
Fig. 2 is the section-drawing of the transmission device under the case of bending of one embodiment of the invention.
Fig. 3 is the section-drawing of the transmission device of one embodiment of the invention.
Fig. 4 is the section-drawing of the transmission device of one embodiment of the invention.
Fig. 5 is the section-drawing of the transmission device of one embodiment of the invention.
Fig. 6 is the constructional drawing of the flexible bearing of one embodiment of the invention.
Fig. 7 is the birds-eye view of the quadrotor of one embodiment of the invention.
Fig. 8 is the birds-eye view of the quadrotor of one embodiment of the invention.
Fig. 9 is the birds-eye view of the quadrotor of one embodiment of the invention.
Figure 10 is the birds-eye view of the six rotorcraft of one embodiment of the invention.
Figure 11 is the birds-eye view of the six rotorcraft of one embodiment of the invention.
Figure 12 is the birds-eye view of the six rotorcraft of one embodiment of the invention.
Figure 13 is the cutaway view of the quadrotor A-A along the line of Fig. 6.
Figure 14 is the cutaway view of the quadrotor B-B along the line of Fig. 6.
Figure 15 is the cutaway view of the quadrotor A-A along the line of Fig. 8.
Figure 16 is the cutaway view of the quadrotor B-B along the line of Fig. 8.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, be clearly and completely described the technical scheme in the embodiment of the present invention, obviously, described embodiment is a part of embodiment of the present invention, instead of whole embodiment.Based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under the prerequisite not making creative work, all should belong to the scope of protection of the invention.
Referring to figs. 1 through Fig. 5, transmission device 1 comprises:
Bracing frame 11.Bracing frame 11 one end is connected with power pack section 4, and the other end is connected with secondary part 6.At the mode of operation of transmission device 1, the moment of flexure that the bonding force of bracing frame 11 produces is greater than 0.
Be arranged on the transmission shaft 12 on bracing frame 11, the transmission of power produced by power pack section 4 by transmission shaft 12 is to secondary part 6.
Be assemblied in the bearing assembly 13 on transmission shaft 12.Bearing assembly 13 comprises flexible bearing 14 and backup bearing 15.Flexible bearing 14 comprises outer shroud 16 and inner ring 17, the inside face of outer shroud 16 is sphere, and inner ring 17 is rotatably installed in outer shroud 16 along the centre of sphere of this sphere, and outer shroud 16 is fixed on the inwall of bracing frame 11, inner ring 17 is arranged on backup bearing 15, and backup bearing 15 is assemblied on transmission shaft 12.
In the embodiment of the present invention, the moment of flexure that the bonding force due to bracing frame produces is greater than 0, and bracing frame can bend under Moment.The bearing assembly of supporting shaft can be driven after bracing frame bends to deflect.Owing to being rotatably connected between the outer shroud of the flexible bearing in bearing assembly and inner ring, avoiding bracing frame and the flexure stress of bending generation is passed on transmission shaft, and then avoid the damage of transmission shaft.
Flexible bearing 14 can adopt the structure shown in Fig. 6.As can be seen from Figure 6, the inside face of outer shroud 16 is sphere, and the outside face of inner ring 17 is also sphere, and inner ring 17 can do spheric motion along the inside face of outer shroud 16.
Should be understood that the effect of the backup bearing 15 in bearing assembly 13 is supporting shafts 15.The particular type of the embodiment of the present invention to backup bearing 15 is not construed as limiting, and such as, can be self-aligning ball bearing, deep groove ball bearing etc.In addition, the number of the backup bearing 15 that bearing assembly 13 comprises can be 1, also can be multiple, specifically can look and support and the demand of location, and the factor such as the size of inner ring 17 is determined.
Should be understood that above-mentioned bracing frame 11 can be framework, truss or tubular form etc.
In embodiments of the present invention, transmission shaft 12 can be an integrated axis, and this axis distributes one or more bearing assembly 13.
Alternatively, as an embodiment, transmission shaft 12 can comprise: the input end 18 be connected with power pack section 4, the mouth 19 be connected with secondary part 6, and the axle unit 20 between input end 18 and mouth 19.The bearing assembly 13 that axle unit 20 can comprise shaft part 21 and be arranged on shaft part 21; Wherein, input end 18, be connected successively by coupler 22 between axle unit 20 and mouth 19.
In the embodiment of the present invention, transmission shaft inside adopts coupler to connect.Coupler not only plays connection function, also plays the effect compensating the axis angle deflection caused because bracing frame bends.
Particularly, N section axle unit 20 can be comprised between input end 18 and mouth 19, be connected successively by coupler 22 between N section axle unit 20, wherein, N is determined by the angle compensation amount of the degree of crook of bracing frame 11 under Moment and the coupler 22 on transmission shaft 12.Bracing frame 11 in external force (such as, by the gravity of the gravity of strut member, secondary part 6, or secondary part 6(such as rotor) pulling force etc. that produces) effect under can bend, the axis between input end 18 and mouth 19 can produce certain deflection angle (depending on external force size).Now, the number of axle unit 20 can be decided by the degree of crook of the length of transmission distance and bracing frame 11, the foundation determined can be: in input end 18, each shaft part 21 and mouth 19, angle between adjacent two parts is all less than the coupler that is attached thereto angle compensation amount allowable, if this angle is greater than coupler angle compensation amount allowable, then increase the number of axle unit 20.Casehistory, see Fig. 1 to Fig. 3, supposes under the effect of external force, and the maximum deflection angle that bracing frame 11 produces is 2 degree, and the angle compensation amount allowable of each coupler 22 is 1 degree, so can arrange 1 axle unit 20 between input end 18 and mouth 19.Input end 18, between mouth 19 and axle unit 20 successively by coupler 22, totally 2 coupler, be connected.Because each coupler 22 can compensate the deflection angle of 1 degree, 2 maximum deflection angles compensating 2 degree of coupler, can meet the compensation demand of maximum deflection angle.Casehistory again, see Fig. 4 to Fig. 5, suppose under the effect of external force, the maximum deflection angle that bracing frame 11 produces is 3 degree, and the angle compensation amount allowable of each coupler 22 is 1 degree, so can 2 axle units 20 be set between input end 18 and mouth 19.Input end 18, between mouth 19 and axle unit 20 successively by coupler 22, totally 2 coupler, be connected.Because each coupler 22 can compensate the deflection angle of 1 degree, 3 maximum deflection angles compensating 3 degree of coupler, can meet the compensation demand of maximum deflection angle.
Should be understood that in axle unit 20, the bearing assembly 13 be enclosed within shaft part 21 can be 1, also can be multiple.The distributing position of bearing assembly 13 on shaft part 21 also can be varied, and the embodiment of the present invention does not do concrete restriction to this.Such as, see Fig. 3 and Fig. 4,1 axle unit 20 comprises 1 bearing assembly 13, and this bearing assembly 13 is arranged on the middle part of shaft part 21.And for example, see Fig. 1, Fig. 2 and Fig. 5,1 axle unit 20 comprises 2 bearing assemblies 13, and these 2 bearing assemblies 13 are separately positioned on the two ends of shaft part 21.Certainly, the number of the bearing assembly 13 in 1 axle unit 20 can also be 3, even more, the arrangement of bearing assembly 13 on shaft part 21 also can adopt other arrangement, specifically can arrange according to the length of shaft part 21 and actual location requirement.
Should be understood that the particular type of the embodiment of the present invention to power pack section 4 and secondary part 6 is not construed as limiting, such as, power pack section 4 can comprise the dynamic driving engine of oil, and the rotating shaft of the dynamic driving engine of oil is connected with one end of transmission shaft 12; Secondary part 6 comprises rotor, and the rotating shaft of rotor is connected with the other end of transmission shaft 12.Transmission device operationally, rotor can produce very large pulling force, under the effect of this pulling force, bracing frame can be driven to produce bending, the bearing assembly of the embodiment of the present invention effectively can avoid bracing frame by this bending Stress transmit produced on transmission shaft, thus avoids the distortion of transmission shaft.
It should be noted that, above is only an example of application scenarios to the embodiment of the present invention, and the embodiment of the present invention is not limited to this scene.As long as when transmission device works; under the External Force Acting of the bracing frame of supporting shaft; the scene that the moment of flexure produced is greater than 0, all can use the transmission device of the embodiment of the present invention to avoid the problem on deformation of above-mentioned transmission shaft, therefore all should fall in the protection domain of the embodiment of the present invention.
Composition graphs 1-Fig. 6 describes the transmission device of the embodiment of the present invention in detail above.Hereafter composition graphs 7 to Figure 16 describes the multi-rotor aerocraft of the embodiment of the present invention in detail.It should be noted that, the transmission device 1 that the multi-rotor aerocraft hereinafter described can adopt Fig. 1 to Fig. 6 to describe, for avoiding repetition, suitably omitting the description repeated.
See Fig. 7 to Figure 16, multi-rotor aerocraft 7 can comprise: body 41, is provided with the dynamic driving engine 42 of oil.Along at least three rotor parts 6 of the circle distribution being the center of circle with the center of body 41, rotor part 6 and body 41 are arranged on the two ends of bracing frame 11 respectively.The dynamic driving engine 42 of oil is by being arranged on transmission shaft 12 on bracing frame 11 by power transmission to rotor part 6.Be assemblied in the bearing assembly 13 on transmission shaft 12, comprise flexible bearing 14 and backup bearing 15, flexible bearing 14 comprises outer shroud 16 and inner ring 17, the inside face of outer shroud 16 is sphere, inner ring 17 centre of sphere is globally rotatably installed in outer shroud 16, outer shroud 16 is fixed on the inwall of bracing frame 11, and inner ring 17 is arranged on backup bearing 15, and backup bearing 15 is assemblied on transmission shaft 12.
In the embodiment of the present invention, be connected because bracing frame divides with Rotary-Wing Department, the pulling force of vertical direction can be produced during rotor some work, cause bracing frame flexural deformation.The bearing assembly of supporting shaft can be driven after bracing frame bends to deflect.Owing to being rotatably connected between the outer shroud of the flexible bearing in bearing assembly and inner ring, avoiding bracing frame and the flexure stress of bending generation is passed on transmission shaft, and then avoid the damage of transmission shaft.
Should be understood that above-mentioned at least three rotor parts 6 can distribute along the even circumferential being the center of circle with the center of body 41, also can non-uniform Distribution.
Alternatively, as an embodiment, see Fig. 7 to Fig. 9, multi-rotor aerocraft 7 can comprise four rotor parts, 6, four rotor parts 6 centered by body 41, in cross shape or X-shaped shape be distributed in its surrounding.Or see Figure 10 to Figure 12, multi-rotor aerocraft 7 can comprise six rotor parts, 6, six rotor parts 6 centered by body 41, is evenly distributed on its surrounding.
Should be understood that the embodiment of the present invention moves the number of driving engine 42 to oil and concrete restriction is not done in position.Such as, multi-rotor aerocraft 7 can comprise 1 oil and move driving engine 42, and the dynamic driving engine 42 of this oil is arranged on the position as shown in Fig. 7 or Figure 10.And for example, multi-rotor aerocraft 7 comprises 2 oil and moves driving engine 42, and these 2 oil move driving engine 42 and arrange and combine installation according to the mode such as shown in Fig. 8 or Figure 11.And for example, multi-rotor aerocraft 7 comprises 4 oil and moves driving engine 42, and these 4 oil move driving engine 42 and arrange and combine installation according to the mode such as shown in Fig. 9 or Figure 12.Certainly, the oil that multi-rotor aerocraft 7 can also comprise 3 or other numbers moves driving engine, and the number of the dynamic driving engine of oil can determine factors such as the power that the demand of power and each driving engine can provide according to aircraft.
Alternatively, as an embodiment, transmission shaft 12 can comprise: move with oil the input end 18 that driving engine 42 is connected; The mouth 19 be connected with the rotor part 6 being positioned at transmission shaft 12 other end; Axle unit 20 between input end 18 and mouth 19, the bearing assembly 13 that axle unit 20 can comprise shaft part 21 and be arranged on shaft part 21; Wherein, input end 18, be connected successively by coupler 22 between axle unit 20 and mouth 19.
In the embodiment of the present invention, transmission shaft inside adopts coupler to connect.Coupler not only plays connection function, also plays the effect compensating the axis angle deflection caused because bracing frame bends.
Alternatively, as an embodiment, comprise between input end 18 and mouth 19 between N section axle unit 20, N section axle unit 20 and being connected successively by coupler 22, wherein, N is determined by the angle compensation amount of the degree of crook of bracing frame 11 under Moment and the coupler 22 on transmission shaft 12.
Alternatively, as an embodiment, see Figure 13 to Figure 16, rotor part 6 can comprise: the rotor shaft 61 be connected with the mouth 18 of transmission shaft 12; Be assemblied in the inclinator 62 in rotor shaft 61, inner ring 63 and the rotor shaft 61 of inclinator 62 are fitted.In prior art, the inner ring 63 of inclinator 62 is arranged in rotor shaft 61 by ball-bearing casing, make the too complicated with the structure of rotor shaft 61 of inclinator 62, add the difficulty of assembling, reliability reduces, inner ring and the rotor shaft 61 of embodiment of the present invention medium dip device 62 are directly fitted, and enormously simplify the structure between inclinator and rotor shaft 61, improve reliability.
Particularly, inclinator 62 is that this manipulation assembly from up to down connects distance-variable rocker arm, distance-variable rocker arm connecting rod, inclinator outer shroud, inclinator inner ring, inclinator inner ring toggle, clip, inclinator outer shroud toggle, steering wheel connecting rod and steering wheel successively to the part in the total manipulation assembly apart from handling of rotor.Inclinator 62 forms primarily of inclinator outer shroud, inclinator inner ring 63 and the bearing be connected to therebetween, this inclinator 62 is assemblied in rotor shaft 61, and can sliding axially along rotor shaft 61, inclinator outer shroud does not rotate with rotor shaft 61 under the effect of inclinator outer shroud toggle, inner ring 63 under the effect of inclinator inner ring toggle along with rotor shaft 61 is rotated.Rotor part 6 comprises steering wheel, inclinator 62 is driven to slide along rotor shaft 61 by the steering wheel connecting rod be connected with this steering wheel, and then drive the distance-variable rocker arm connecting rod be connected with inclinator 62 to move up and down, thus drive distance-variable rocker arm to rotate around the propeller hub pitch change axes of screw propeller, reach the object handling the total distance of rotor.
Should be understood that the embodiment of the present invention does not do concrete restriction to the structure that oil moves between the mouth 19 of the input end 18 of driving engine 42 and transmission shaft 12, transmission shaft 12, the form of transmission is varied, provides the example of concrete type of belt drive below.
See Figure 13 to Figure 16, the dynamic driving engine 42 of oil is arranged on the first drop-gear box 44 by engine bed 43.Power input shaft 45 and oil move driving engine 42 and are connected, and move driving engine 42 drive it to rotate by oil.Power input shaft 45 is supported on the first drop-gear box 44 by the first backup bearing 46.The end of power input shaft 45 connects the first conical gear 47.First conical gear 47 is meshed with the second conical gear 23, and the second conical gear 23 is connected with input end 18.Input end 18 is supported on the first drop-gear box 44 by the second backup bearing 24.Mouth 19 is supported on the second drop-gear box 64 by the 3rd backup bearing 25.Mouth 19 end connects the 3rd conical gear the 26, three conical gear 26 and is meshed with the 4th conical gear 65.4th conical gear 65 is connected with rotor shaft 61, and rotor shaft 61 is supported on the second drop-gear box 64 by the 4th backup bearing 66.Rotor shaft 61 is connected with rotor 67, thus drives rotor 67 to rotate.
In addition, the dynamic driving engine 42 of oil receives the signal from flight control system by engine control wire 48, to control the power of the dynamic driving engine 42 of oil.Multi-rotor aerocraft 7 can also comprise user equipment, parachute etc.
In several embodiments that the application provides, should be understood that disclosed system, apparatus and method can realize by another way.Such as, device embodiment described above is only schematic, such as, the division of described unit, be only a kind of logic function to divide, actual can have other dividing mode when realizing, such as multiple unit or assembly can in conjunction with or another system can be integrated into, or some features can be ignored, or do not perform.Another point, shown or discussed coupling each other or direct-coupling or communication connection can be by some interfaces, and the indirect coupling of device or unit or communication connection can be electrical, machinery or other form.
The described unit illustrated as separating component or can may not be and physically separates, and the parts as unit display can be or may not be physical location, namely can be positioned at a place, or also can be distributed on multiple network element.Some or all of unit wherein can be selected according to the actual needs to realize the object of the present embodiment scheme.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; change can be expected easily or replace, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should described be as the criterion with the protection domain of claim.
Claims (10)
1. a transmission device, is characterized in that, comprising:
Bracing frame, one end is connected with power pack section, and the other end is connected with secondary part, and at the mode of operation of described transmission device, the moment of flexure that the bonding force of support frame as described above produces is greater than 0;
Be arranged on the transmission shaft on support frame as described above, the transmission of power produced by described power pack section by described transmission shaft is to described secondary part;
Be assemblied in the bearing assembly on described transmission shaft, comprise flexible bearing and backup bearing, described flexible bearing comprises outer shroud and inner ring, the inside face of described outer shroud is sphere, described inner ring is rotatably installed in described outer shroud along the centre of sphere of described sphere, described outer shroud is fixed on the inwall of support frame as described above, and described inner ring is arranged on described backup bearing, and described backup bearing is assemblied on described transmission shaft.
2. transmission device as claimed in claim 1, it is characterized in that, described transmission shaft comprises:
The input end be connected with described power pack section;
The mouth be connected with described secondary part;
Axle unit between described input end and described mouth, described axle unit comprises shaft part and is arranged on the described bearing assembly on described shaft part;
Wherein, described input end, be connected successively by coupler between described axle unit and described mouth.
3. transmission device as claimed in claim 2, it is characterized in that, the described axle unit of N section is comprised between described input end and described mouth, be connected successively by coupler between the described axle unit of N section, wherein, N is determined by the angle compensation amount of the degree of crook of support frame as described above under Moment and the coupler on described transmission shaft.
4. transmission device as claimed any one in claims 1 to 3, is characterized in that, described power pack section comprises the dynamic driving engine of oil, and the rotating shaft that described oil moves driving engine is connected with one end of described transmission shaft; Described secondary part comprises rotor, and the rotating shaft of described rotor is connected with the other end of described transmission shaft.
5. a multi-rotor aerocraft, is characterized in that, comprising:
Body, is provided with the dynamic driving engine of oil;
Along at least three rotor parts of the circle distribution being the center of circle with described body center, described rotor part and described body are arranged on the two ends of bracing frame respectively, and described oil moves driving engine by being arranged on transmission shaft on support frame as described above by power transmission to described rotor part;
Be assemblied in the bearing assembly on described transmission shaft, comprise flexible bearing and backup bearing, described flexible bearing comprises outer shroud and inner ring, the inside face of described outer shroud is sphere, described inner ring is rotatably installed in described outer shroud along the centre of sphere of described sphere, described outer shroud is fixed on the inwall of support frame as described above, and described inner ring is arranged on described backup bearing, and described backup bearing is assemblied on described transmission shaft.
6. multi-rotor aerocraft as claimed in claim 5, it is characterized in that, described transmission shaft comprises:
The input end that driving engine is connected is moved with described oil;
The mouth be connected is divided with the Rotary-Wing Department being positioned at this transmission shaft other end;
Axle unit between described input end and described mouth, described axle unit comprises shaft part and is arranged on the described bearing assembly on described shaft part;
Wherein, described input end, be connected successively by coupler between described axle unit and described mouth.
7. multi-rotor aerocraft as claimed in claim 6, it is characterized in that, the described axle unit of N section is comprised between described input end and described mouth, be connected successively by coupler between the described axle unit of N section, wherein, N is determined by the angle compensation amount of the degree of crook of support frame as described above under Moment and the coupler on described transmission shaft.
8. the multi-rotor aerocraft according to any one of claim 5-7, is characterized in that, described Rotary-Wing Department divides and comprises:
The rotor shaft be connected with the mouth of described transmission shaft;
Be assemblied in the inclinator in described rotor shaft, inner ring and the described rotor shaft of described inclinator are fitted.
9. the multi-rotor aerocraft according to any one of claim 5-8, is characterized in that, described at least three Rotary-Wing Departments are divided into four rotor parts.
10. the multi-rotor aerocraft according to any one of claim 5-8, is characterized in that, described at least three Rotary-Wing Departments are divided into six rotor parts.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410128637.9A CN104229136B (en) | 2014-04-01 | 2014-04-01 | Transmission mechanism and multi-rotor aerocraft |
| PCT/CN2015/074193 WO2015149615A1 (en) | 2014-04-01 | 2015-03-13 | Transmission mechanism and multi-rotor aircraft |
| HK15103194.1A HK1201014A2 (en) | 2014-04-01 | 2015-03-30 | Driving mechanism and multi-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410128637.9A CN104229136B (en) | 2014-04-01 | 2014-04-01 | Transmission mechanism and multi-rotor aerocraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104229136A true CN104229136A (en) | 2014-12-24 |
| CN104229136B CN104229136B (en) | 2016-08-24 |
Family
ID=52218224
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410128637.9A Expired - Fee Related CN104229136B (en) | 2014-04-01 | 2014-04-01 | Transmission mechanism and multi-rotor aerocraft |
Country Status (3)
| Country | Link |
|---|---|
| CN (1) | CN104229136B (en) |
| HK (1) | HK1201014A2 (en) |
| WO (1) | WO2015149615A1 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015149615A1 (en) * | 2014-04-01 | 2015-10-08 | 嘉兴深远世宁航空技术有限公司 | Transmission mechanism and multi-rotor aircraft |
| JP2020100387A (en) * | 2018-12-21 | 2020-07-02 | 株式会社プロドローン | Unmanned aircraft |
| JP2020147258A (en) * | 2019-03-16 | 2020-09-17 | 矢継 正信 | Rotary wing flight body for every module |
| CN115258171A (en) * | 2022-08-04 | 2022-11-01 | 杨熙 | Design method and mechanism of aero-engine lengthened shaft and rotating mechanism |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11027836B2 (en) * | 2018-07-13 | 2021-06-08 | The Boeing Company | Rotorcraft with canted coaxial rotors |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2119876C1 (en) * | 1997-11-20 | 1998-10-10 | Назаров Николай Андреевич | Helicopter main rotor hub |
| EP1961997A2 (en) * | 2007-02-23 | 2008-08-27 | Jtekt Corporation | Strain wave reduction gear and variable transmission ratio steering apparatus |
| US20100285920A1 (en) * | 2008-02-19 | 2010-11-11 | Mitsubishi Heavy Industries, Ltd. | Planetary gear system |
| CN203318679U (en) * | 2012-09-13 | 2013-12-04 | 吴松 | Co-engine multi-shaft multi-rotor craft |
| CN203753402U (en) * | 2014-04-01 | 2014-08-06 | 王晨帆 | Transmission mechanism and multi-rotor craft |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2508518B2 (en) * | 1986-12-27 | 1996-06-19 | ソニー株式会社 | Paint applicator |
| JPH1110209A (en) * | 1997-06-25 | 1999-01-19 | Mitsubishi Heavy Ind Ltd | Rolling mill |
| JP5191700B2 (en) * | 2007-07-12 | 2013-05-08 | 富士フイルム株式会社 | Bearing structure of coating roll, coating device, and coating method |
| CN201148210Y (en) * | 2007-12-26 | 2008-11-12 | 朱家乐 | Semi-flexible type shaft driven system for small-sized unmanned helicopter tail rotor |
| CN203362819U (en) * | 2013-06-27 | 2013-12-25 | 神华集团有限责任公司 | Bearing device |
| CN104229136B (en) * | 2014-04-01 | 2016-08-24 | 北京深远世宁科技有限公司 | Transmission mechanism and multi-rotor aerocraft |
-
2014
- 2014-04-01 CN CN201410128637.9A patent/CN104229136B/en not_active Expired - Fee Related
-
2015
- 2015-03-13 WO PCT/CN2015/074193 patent/WO2015149615A1/en active Application Filing
- 2015-03-30 HK HK15103194.1A patent/HK1201014A2/en not_active IP Right Cessation
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2119876C1 (en) * | 1997-11-20 | 1998-10-10 | Назаров Николай Андреевич | Helicopter main rotor hub |
| EP1961997A2 (en) * | 2007-02-23 | 2008-08-27 | Jtekt Corporation | Strain wave reduction gear and variable transmission ratio steering apparatus |
| US20100285920A1 (en) * | 2008-02-19 | 2010-11-11 | Mitsubishi Heavy Industries, Ltd. | Planetary gear system |
| CN203318679U (en) * | 2012-09-13 | 2013-12-04 | 吴松 | Co-engine multi-shaft multi-rotor craft |
| CN203753402U (en) * | 2014-04-01 | 2014-08-06 | 王晨帆 | Transmission mechanism and multi-rotor craft |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015149615A1 (en) * | 2014-04-01 | 2015-10-08 | 嘉兴深远世宁航空技术有限公司 | Transmission mechanism and multi-rotor aircraft |
| JP2020100387A (en) * | 2018-12-21 | 2020-07-02 | 株式会社プロドローン | Unmanned aircraft |
| JP2020147258A (en) * | 2019-03-16 | 2020-09-17 | 矢継 正信 | Rotary wing flight body for every module |
| CN115258171A (en) * | 2022-08-04 | 2022-11-01 | 杨熙 | Design method and mechanism of aero-engine lengthened shaft and rotating mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104229136B (en) | 2016-08-24 |
| WO2015149615A1 (en) | 2015-10-08 |
| HK1201014A2 (en) | 2015-08-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104229136A (en) | Transmission mechanism and multi-rotor aircraft | |
| CN102658865B (en) | Coaxial drive and control structure for coaxial contrarotation rotor helicopter | |
| CN104029197B (en) | A kind of vector propulsion mechanism of underwater robot | |
| RU2108267C1 (en) | Toroidal fuselage of unmanned flying vehicle | |
| US9499262B2 (en) | Composite flexure for tiltrotor rotor system | |
| CN102787983B (en) | Wind turbine nacelle | |
| CN106525404B (en) | A kind of tail-rotor platform | |
| US10640199B2 (en) | Wheel and gear assembly | |
| KR20160101120A (en) | Bidirectional bearing, drive train, planetary gear and wind generator | |
| CN101850851A (en) | Layout structure of SPORT clock scanning satellite | |
| CN103466087A (en) | Nacelle tilting mechanism for tilt rotor aircraft | |
| CN101614615A (en) | Simulative loader of tail reducer of helicopter | |
| CN102777545A (en) | Aircraft and long-service-life electric steering engine thereof | |
| CN204536862U (en) | The electromechanical servo system of thruster vector control | |
| CN203753402U (en) | Transmission mechanism and multi-rotor craft | |
| EP2935881B1 (en) | Flexible drive shaft | |
| CN102765475B (en) | Air vehicle and electric steering engine capable of resisting large bending torque thereof | |
| CN201148210Y (en) | Semi-flexible type shaft driven system for small-sized unmanned helicopter tail rotor | |
| CN107614932B (en) | Planetary gear train comprising bevel gears and force balancing device | |
| CN103466088A (en) | Nacelle gear tilting mechanism for tilt rotor aircraft | |
| CN108100267B (en) | Motor cluster power system | |
| CN209650533U (en) | Unmanned plane | |
| KR102050132B1 (en) | Drone | |
| US20240092493A1 (en) | Propulsion System for Electric Aircraft | |
| CN104698984B (en) | The electromechanical servo system of thruster vector control |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| ASS | Succession or assignment of patent right |
Owner name: JIAXING SHENYUAN SHINING AVIATION TECHNOLOGY CO., Free format text: FORMER OWNER: WANG CHENFAN Effective date: 20150109 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 102200 CHANGPING, BEIJING TO: 314000 JIAXING, ZHEJIANG PROVINCE |
|
| TA01 | Transfer of patent application right |
Effective date of registration: 20150109 Address after: Jiaxing City, Zhejiang province 314000 Nanhu District Ling Gong Tang Road No. 3339 (Jiaxing city) building 1, room 329 Applicant after: Jiaxing far reaching Aviation Technology Co.,Ltd. Address before: 102200 Beijing City, Changping District Agricultural College Road WITHUB District Lingxiu Jiu A5-1-902 Applicant before: Wang Chenfan |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20160302 Address after: 100085 Beijing, Haidian District, No. ten on the ground floor, No. 1, building 14, floor 1402, 4 Applicant after: BEIJING SHENYUAN SHINING TECHNOLOGY Co.,Ltd. Address before: Jiaxing City, Zhejiang province 314000 Nanhu District Ling Gong Tang Road No. 3339 (Jiaxing city) building 1, room 329 Applicant before: Jiaxing far reaching Aviation Technology Co.,Ltd. |
|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20181206 Address after: 646000 No. 347 South Zhangjiaci Road, Shidong Street, Longmatan District, Luzhou City, Sichuan Province Patentee after: Southwest UAV Technology Co.,Ltd. Address before: 100085 Floor 1402, Building 4, No. 1 Hospital, Shangdi Tenth Street, Haidian District, Beijing Patentee before: BEIJING SHENYUAN SHINING TECHNOLOGY Co.,Ltd. |
|
| 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: 20160824 |