CN103381885A - Multi-rotor wing aircraft - Google Patents
Multi-rotor wing aircraft Download PDFInfo
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- CN103381885A CN103381885A CN2012101343372A CN201210134337A CN103381885A CN 103381885 A CN103381885 A CN 103381885A CN 2012101343372 A CN2012101343372 A CN 2012101343372A CN 201210134337 A CN201210134337 A CN 201210134337A CN 103381885 A CN103381885 A CN 103381885A
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Abstract
The invention discloses a multi-rotor wing aircraft. The multi-rotor wing aircraft comprises a power system and a distance change system. The power system comprises a main rotatable part, multiple driving parts and rotor wings connected respectively to the driving parts. The main rotatable part is provided with a rotatable end. The driving parts are driven by the rotatable end and transmit rotation to the rotor wings so that the rotor wings rotate synchronously. The distance change system comprises multiple distance change units. The distance change units are used respectively for changing incidence angles of the rotor wings. The driving parts are driven by the same rotatable end and the driving parts transmit rotation to the rotor wings so that the rotor wings rotate synchronously. Through distance change of the rotor wings, the multi-rotor wing aircraft can turn over, fly reversely or swing.
Description
Technical field
The present invention relates to the electronic toy field, particularly a kind of multi-rotor aerocraft.
Background technology
Along with the development of science and technology and improving constantly of people's living standard, the kind of electronic toy is more and more abundanter, and function also from strength to strength.In these electronic toys, aircraft also is subjected to liking of numerous airplane hobbyists deeply as a kind of electronic toy of top grade.These aircraft can wireless distance control, and according to the difference of its purposes and performance, these aircraft can be divided into several classes such as toy, model plane, civil and military.According to the difference of the fuel that uses, it is moving and electronic that these aircraft can be divided into again oil.The moving largest benefit of oil is that cruise duration is long, and needing only timely oiling can fly, and horsepower is powerful.But the danger coefficient of servomotor is higher, safeguards relative complex, and price comparison is high, and therefore electronic model plane become the universal dominant role of model plane.
The at present domestic and international existing multi-rotor aerocraft of model circle adopts a plurality of motors to control respectively separately many group rotors.As shown in Figure 1, existing aircraft 1 comprises an inner support 11, four pipe links 12, four motors 13 and four rotors 14, and the two ends of each pipe link 12 are individually fixed on inner support 11 and brushless motor 13, and each brushless motor 13 is used for driving a rotor 14.The rotating speed of organizing rotor by electronic circuit control more realize aircraft stable elevation, seesaw or side-to-side movement.
There is following problem in existing multi-rotor aerocraft: the first, a plurality of motor performance is variant, thereby causes and be difficult to synchronous (rotating speed and speed of response are all inconsistent), causes and hovers, lifting, the problem such as left-right and front-back flight is accurate not, and control response is accurate not; The second, rotor can not displacement, because the rotor of existing aircraft adopts fixing form, can not displacement, and so can not do the stunts such as upset, inverted flight or pendulum.
Therefore study and develop that a kind of each gyroplane rotate speed is synchronous and aircraft can bending moment is particularly necessary.
Summary of the invention
The technical problem to be solved in the present invention is to be difficult to defective synchronous and can not bending moment for each gyroplane rotate speed that overcomes multi-rotor aerocraft of the prior art, a kind of multi-rotor aerocraft is provided, and each rotor of this multi-rotor aerocraft can synchronous rotary and can bending moment.
The present invention solves above-mentioned technical matters by following technical proposals:
A kind of multi-rotor aerocraft, its characteristics are, this multi-rotor aerocraft comprises a power system and a displacement system, this power system comprises main rotatable parts, a plurality of drive disk assembly and is connected in rotor on each drive disk assembly, these main rotatable parts have a round end, those drive disk assemblies drive and transmission of rotation to those rotors are made its synchronous rotation by this round end, and this displacement system comprises a plurality of displacements unit, and each displacement unit is used for changing the angle of attack of those rotor one rotors.
better, these main rotatable parts comprise an actuating device and one first finishing bevel gear cuter, this the first finishing bevel gear cuter is connected in the end of the rotor of this actuating device, each drive disk assembly comprises a drive link and a rotor shaft, drive link in each drive disk assembly is mutually vertical with rotor shaft, the two ends of each drive link are connected with respectively one second finishing bevel gear cuter and a third hand tap gear, be provided with the rotor in one the 4th finishing bevel gear cuter and those rotors on each rotor shaft, those second finishing bevel gear cuters all mesh with this first finishing bevel gear cuter, one the 4th finishing bevel gear cuter engagement in each third hand tap gear and those the 4th finishing bevel gear cuters.
Better, this actuating device is a fuel engines or an electrical motor.Fuel engines and electrical motor can both drive the first finishing bevel gear cuter rotation, and using fuel engines is also the multi-rotor aerocraft that can make the rotor synchronous rotary and have the stunt functions such as upset, inverted flight or pendulum.In addition, fuel engines has the advantages that cruise duration is long and horsepower is powerful, can make use in military or model plane competition.
Better, this electrical motor is the external rotor brushless electrical motor.The multi-rotor aerocraft that uses brushless motor to make has advantages of that friction is little, heating power is low, noise is low and long service life.In addition, outer rotor brushless motor has larger moment and lower rotating speed than the inner-rotor brushless motor, so can reduce the requirement to the gear change ratio.
Better, the end of the rotor of this actuating device is provided with at least one first groove milling, be penetrated with one first connecting bore on this first finishing bevel gear cuter, this first finishing bevel gear cuter is socketed on the end of this rotor by this first connecting bore, and captives joint with this rotor by this first groove milling.Socket connects and the groove milling fixed form makes the loading and unloading of rotor tip of the first finishing bevel gear cuter and actuating device easier.
Better, this multi-rotor aerocraft also comprises internal stent and a cross mounting bracket on one, and four hold-down arms of this cross mounting bracket all have first tapped bore, and this actuating device is anchored on this on internal stent by those first tapped bore.As the bracing frame of multi-rotor aerocraft, upper internal stent plays and connects the also key role of the numerous mechanical parts of load-bearing.That the making of bracing frame will have is frivolous, pressure-bearing and joint space-efficient characteristics.
Better, having a storage tank on those on internal stent, those second finishing bevel gear cuters and this first finishing bevel gear cuter all are positioned at this storage tank.By those second finishing bevel gear cuters and this first finishing bevel gear cuter are arranged at pollution and the damage of not only having saved the space in this storage tank but also having prevented the gear teeth.
Better, this multi-rotor aerocraft also comprises four lower internal stent, those lower internal stent all have one group of the first half position-limited trough, be provided with four groups of the second half position-limited troughs on should upper internal stent, those lower internal stent all are connected on this on internal stent, and those the first half position-limited troughs all mutually engage with those the second half position-limited troughs and are used for spacing those drive links.
Better, the number of those drive links, those rotor shaft, those second finishing bevel gear cuters, those third hand tap gears, those the 4th finishing bevel gear cuters and those rotors is four groups, six groups or eight groups.
Better, the number of those drive links, those rotor shaft, those second finishing bevel gear cuters, those third hand tap gears, those the 4th finishing bevel gear cuters and those rotors is four groups, and those drive links are in the same plane, and the angle of two adjacent drive links is 90 °.
Better, the gear teeth opposite direction of two the 4th finishing bevel gear cuters that two adjacent drive links connect is so that the hand of rotation of two adjacent rotors is opposite.This engaging structure can be so that when two the 4th finishing bevel gear cuter clickwises, two other the 4th finishing bevel gear cuter left-hand revolution, thereby offset anti-twisted power between rotor, the flight of multi-rotor aerocraft is more steady.
Better, the two ends of each drive link are provided with at least one second groove milling and at least one the 3rd groove milling respectively, all be penetrated with one second connecting bore on those second finishing bevel gear cuters, all be penetrated with one the 3rd connecting bore on those third hand tap gears, those second finishing bevel gear cuters and those third hand tap gears socket-connect by the two ends of those second connecting bores and those the 3rd connecting bores and those drive links respectively, and fix by the two ends of those second groove millings and those the 3rd groove millings and those drive links.
Better, each drive link comprises that one has connecting rod and a S. A. of the first axis hole, and this second finishing bevel gear cuter and this third hand tap gear are arranged at respectively the two ends of this S. A., and this S. A. is placed through in this first axis hole.
Better, the two ends of each S. A. are provided with a clutch shaft bearing, those clutch shaft bearings and those S. A.s are articulated and be used for those S. A.s of carrying.By the use clutch shaft bearing, the friction force decrease between the internal face of those S. A.s rotations and those the first axis holes, the engagement between gear is more tight, and the rotation of S. A. is more smooth.
Better, this displacement system comprises four displacement unit, each displacement unit comprises a steering wheel, one first expansion link and a transmission component, those steering wheels, those first expansion links, those transmission components and the rotor of being connected connect successively, those steering wheels are used for driving those first expansion links and do fore and aft motion, those first expansion links are used for those transmission components of interlock, and those transmission components are used for changing the angle of attack of those rotors.
Better, this multi-rotor aerocraft also comprises a dash receiver, and this dash receiver is captiveed joint with those lower internal stent, and those steering wheels are threaded with this dash receiver.
Better, those steering wheels are straight line steering wheel or rocking arm steering wheel.
Better, this multi-rotor aerocraft also comprises four rotor supports, those transmission components include a distance-variable rocker arm, several second expansion links, one updip swash plate, one second bearing and tilting frame once, this updip swash plate, this second bearing and this swash plate that has a down dip are placed through on this rotor shaft and interlock mutually successively, the two ends of each distance-variable rocker arm respectively with those first expansion links in one first expansion link and this swash plate that has a down dip mutually link, those updip swash plates change the angle of attack of those rotors by those second expansion links.
Better, each transmission component includes two the second expansion links, each rotor comprises two fins, two oar chucks, two the 3rd bearings, a sail shaft and rotor heads, each rotor head is fixedly connected on this sail shaft and has one second axis hole, those sail shaft are plugged in this second axis hole, in each rotor, those the 3rd bearings are connected in the two ends of this sail shaft, and those the 3rd bearings all connect a fin by an oar chuck.
Better, the rotating speed that described synchronous rotation is those rotors is identical.
Positive progressive effect of the present invention is:
The invention provides a kind of multi-rotor aerocraft.Drive by same round end due to those drive disk assemblies and with transmission of rotation to those rotors, so each rotor can synchronous rotary, in addition, those rotors can also be realized by bending moment the stunts such as upset, inverted flight or pendulum.
Description of drawings
Fig. 1 is the block diagram of existing aircraft.
Fig. 2 is the block diagram of the multi-rotor aerocraft of preferred embodiment of the present invention.
Fig. 3 is the exploded view of the multi-rotor aerocraft of preferred embodiment of the present invention.
Fig. 4 is the block diagram of actuating device of the multi-rotor aerocraft of preferred embodiment of the present invention.
The first partial perspective view of the multi-rotor aerocraft of Fig. 5 preferred embodiment of the present invention.
Fig. 6 is the block diagram of upper internal stent of the multi-rotor aerocraft of preferred embodiment of the present invention.
Fig. 7 is the second partial perspective view of the multi-rotor aerocraft of preferred embodiment of the present invention.
Fig. 8 is the block diagram of lower internal stent of the multi-rotor aerocraft of preferred embodiment of the present invention.
Fig. 9 is the 3rd partial exploded view of the multi-rotor aerocraft of preferred embodiment of the present invention.
Figure 10 is the 4th partial perspective view of the multi-rotor aerocraft of preferred embodiment of the present invention.
Figure 11 is the 5th partial exploded view of the multi-rotor aerocraft of preferred embodiment of the present invention.
Figure 12 is the 6th partial perspective view of the multi-rotor aerocraft of preferred embodiment of the present invention.
Figure 13 is the block diagram of steering wheel of the multi-rotor aerocraft of preferred embodiment of the present invention.
Figure 14 is the 7th partial exploded view of the multi-rotor aerocraft of preferred embodiment of the present invention.
Figure 15 is the 8th partial perspective view of the multi-rotor aerocraft of preferred embodiment of the present invention.
Figure 16 is the enlarged drawing of the multi-rotor aerocraft in the B boost line in Figure 15.
Figure 17 is the use principle figure of the multi-rotor aerocraft of preferred embodiment of the present invention.
Block diagram when Figure 18 is the inverted flight of multi-rotor aerocraft of preferred embodiment of the present invention.
Description of reference numerals:
Existing aircraft: 1
Inner support: 11 pipe links: 12
Motor: 13 rotors: 14
Multi-rotor aerocraft: A
Upper internal stent: 2 storage tanks: 21
The second half position-limited troughs: 22 cross mounting brackets: 3
Hold-down arm: 31 first tapped bore: 311
Lower internal stent: 4 the first half position-limited troughs: 41
Power system: 5 main rotatable parts: 51
Actuating device: 511 first groove millings: 5111
The first finishing bevel gear cuter: 512 first connecting bores: 5121
Drive disk assembly: 52 drive links: 520
S. A.: 521 second finishing bevel gear cuters: 5211
The second connecting bore: 52111 third hand tap gears: 5212
The 3rd connecting bore: 52,121 second groove millings: 5213
The 3rd groove milling: 5214 clutch shaft bearings: 5215
Connecting rod: 522 first axis holes: 5221
Rotor shaft: 523 the 4th finishing bevel gear cuters: 5231
Rotor: 53 fins: 531
Oar chuck: 532 the 3rd bearings: 533
Sail shaft: 534 rotor heads: 535
Pad: 536 packing rings: 537
Displacement system: 6 steering wheels: 61
The first expansion link: 62 transmission components: 63
Distance-variable rocker arm: 631 second expansion links: 632
Updip swash plate: 633 second bearings: 634
Swash plate has a down dip: 635 dash receivers: 7
Rotor support: 8 alighting gears: 9
The specific embodiment
Provide preferred embodiment of the present invention below in conjunction with accompanying drawing, to describe technical scheme of the present invention in detail.
As shown in Fig. 2-16, the multi-rotor aerocraft A of the present embodiment comprises a power system 5, this power system 5 comprises main rotatable parts 51, a plurality of drive disk assembly 52 and is connected in rotor 53 on each drive disk assembly 52, as shown in Figure 3-4, these main rotatable parts 51 comprise an actuating device 511 and one first finishing bevel gear cuter 512, and this first finishing bevel gear cuter 512 is connected in the end of the rotor of this actuating device 511.
As Fig. 5 and shown in Figure 7, this actuating device 511 is the external rotor brushless electrical motor.As Fig. 4 and shown in Figure 7, the end of the rotor of this actuating device 511 is provided with first groove milling 5111, be penetrated with one first connecting bore 5121 on this first finishing bevel gear cuter 512, this first finishing bevel gear cuter 512 is socketed on the end of this rotor by this first connecting bore 5121, and captives joint with this rotor by this first groove milling 5111.
As Fig. 4 and shown in Figure 6, this multi-rotor aerocraft comprises that also one has internal stent 2 and a cross mounting bracket 3 on a storage tank 21, four hold-down arms 31 of this cross mounting bracket 3 all have first tapped bore 311, and this actuating device 511 is anchored on this on internal stent 2 by those first tapped bore 311.As Fig. 7 and shown in Figure 12, those the second finishing bevel gear cuters 5211 and this first finishing bevel gear cuter 512 all are positioned at this storage tank 21.
As shown in Fig. 7-9, also be provided with four groups of the second half position-limited troughs 22 on should upper internal stent 2, this multi-rotor aerocraft also comprises four lower internal stent 4, those lower internal stent 4 all have one group of the first half position-limited trough 41, those lower internal stent 4 all are connected in this on internal stent 2, and those the first half position-limited troughs 41 all engage and are used for spacing those drive links 520 with those the second half position-limited troughs 22 are mutual.
As shown in Figure 9, each drive link 520 comprises that one has connecting rod 522 and a S. A. 521 of the first axis hole 5221, this the second finishing bevel gear cuter 5211 and this third hand tap gear 5212 are arranged at respectively the two ends of this S. A. 521, and this S. A. 521 is placed through in this first axis hole 5221.the two ends of each S. A. 521 are provided with at least one second groove milling 5213 and at least one the 3rd groove milling 5214 respectively, all be penetrated with one second connecting bore 52111 on those second finishing bevel gear cuters 5211, all be penetrated with one the 3rd connecting bore 52121 on those third hand tap gears 5212, those the second finishing bevel gear cuters 5211 and those third hand tap gears 5212 socket-connect by the two ends of those second connecting bores 52111 and those the 3rd connecting bores 52121 and those S. A.s 521 respectively, and fix by the two ends of those second groove millings 5213 and those the 3rd groove millings 5214 and those S. A.s 521.The two ends of each S. A. 521 are provided with a clutch shaft bearing 5215, and those clutch shaft bearings 5215 carry those S. A.s 521 when those S. A.s 521 rotate on those first axis holes 5221.
As Fig. 9 and shown in Figure 12, each drive disk assembly 52 comprises a drive link 520 and a rotor shaft 523, drive link 520 in each drive disk assembly 52 is mutually vertical with rotor shaft 523, the two ends of each drive link 520 are connected with respectively one second finishing bevel gear cuter 5211 and a third hand tap gear 5212, be provided with the rotor in one the 4th finishing bevel gear cuter 5231 and those rotors 53 on each rotor shaft 523, those second finishing bevel gear cuters 5211 all mesh with this first finishing bevel gear cuter 512, one the 4th finishing bevel gear cuter 5231 engagements in each third hand tap gear 5212 and those the 4th finishing bevel gear cuters 5231.
As Fig. 3 and shown in Figure 10, the number of those drive links 520, those rotor shaft 523, those second finishing bevel gear cuters 5211, those third hand tap gears 5212, those the 4th finishing bevel gear cuters 5231 and those rotors 53 is four groups, those drive links 520 are in the same plane, and the angle of two adjacent drive links 520 is 90 °.Shown in Figure 10, the gear teeth opposite direction of two the 4th finishing bevel gear cuters 5231 that two adjacent drive links 520 connect.By using four the 4th finishing bevel gear cuters of forward and reverse installation, adjacent the 4th finishing bevel gear cuter in twos can be realized respectively cw and left-hand revolution function.
As shown in figure 11, this multi-rotor aerocraft also comprises four rotor supports 8, and those the 4th finishing bevel gear cuters 5231 can drive those rotor shaft 523 rotations, and the top of those rotor shaft 523 is fixed with rotor 53.
during use, as shown in figure 12, these actuating device 511 High Rotation Speeds drive the first corresponding rotation of finishing bevel gear cuter 512, identical and even the first finishing bevel gear cuter 512 engagements due to those the second finishing bevel gear cuter 5211 models, therefore those second finishing bevel gear cuters 5211 can synchronous rotary, be that rotating speed is identical, and then those second finishing bevel gear cuters 5211 by those S. A.s 521 with transmission of rotation to the identical third hand tap gear 5212 of those models, then, those third hand tap gears 5212 with transmission of rotation to the 4th identical finishing bevel gear cuter 5231 of those models, at last, those rotor shaft 523 drive rotor 53 rotations on its top.At this moment, airborne aerodynamic loading will provide lift, form the most basic dipping and heaving of aircraft, so each rotor in power system can provide the most basic power for this multi-rotor aerocraft.If realize moving forward and backward, the functions such as sway, left rotation and right rotation, upset, inverted flight and pendulum, also need a system that controls the direction of each rotor power, namely the displacement system 6.
As shown in Fig. 2 and Figure 13-17, the multi-rotor aerocraft A of the present embodiment also comprises a displacement system 6 and a dash receiver 7, and this dash receiver 7 is captiveed joint with those lower internal stent 4, and those steering wheels 61 are threaded with this dash receiver 7.This displacement system 6 comprises four displacement unit, each displacement unit comprises a steering wheel 61, one first expansion link 62 and a transmission component 63, those steering wheels 61, those first expansion links 62, those transmission components 63 and the rotor 53 of being connected connect successively, those steering wheels 61 are used for driving those first expansion links 62 and do fore and aft motion, those first expansion links 62 are used for those transmission components 63 of interlock, and those transmission components 63 are used for changing the angle of attack of those rotors 53.
As shown in figure 14, those transmission components 63 include a distance-variable rocker arm 631, two the second expansion links 632, one updip swash plate 633, one second bearing 634 and tilting frame 635 once, this updip swash plate 633, this second bearing 634 and this swash plate 635 that has a down dip are placed through on this rotor shaft 523 and interlock mutually successively, the two ends of each distance-variable rocker arm 631 respectively with those first expansion links 62 in one first expansion link 62 and this swash plate 635 that has a down dip mutually link, those updip swash plates 633 are by the angle of attack of those second expansion links, 632 those rotors 53 of change.
As Figure 14 and shown in Figure 16, each rotor 53 comprises two fins 531, two oar chucks 532, two the 3rd bearings, a sail shaft 534, a rotor head 535, a pad 536 and packing rings 537, each rotor head 535 is fixedly connected on this sail shaft 534 and has one second axis hole, those sail shaft 534 are plugged in this second axis hole, in each rotor, those the 3rd bearings are connected in the two ends of this sail shaft 534, and those the 3rd bearings all connect a fin 531 by an oar chuck 532.
During use, as shown in figure 17, this steering wheel 61 promotes (pulling) this first expansion link 62, this this distance-variable rocker arm 631 cws (conter clockwise) rotation of the first expansion link 62 interlocks, and link this updip swash plate 633 and this have a down dip swash plate 635 upwards (downwards) slowly move, this second expansion link 632 makes the thick end of those fins 531 upwards kick up (downward-sloping), makes this rotor 53 be in positive incidence (the negative angle of attack).Control because each rotor 53 carries out the angle of attack by a steering wheel 61, so four groups of rotors 53 in multi-rotor aerocraft A have multiple positive and negative angle of attack syntagmatic, in addition, two groups of relative rotors 53 can also realize that the angle of attack is poor.Control the angle of attack of those rotors 53 and the angle of attack between rotor 53 is poor in twos by those steering wheels 61, can realize that multi-rotor aerocraft moves forward and backward, the functions such as sway, left rotation and right rotation, upset, inverted flight and pendulum.Aircraft can carry out the adjusting of each rotor moment by the angle of attack that changes fin 531.
As shown in figure 18, before and after heading, the angle of attack of the sidespin wing 53 is constant, by the angle of attack of change of flight direction left and right sides rotor 53, can realize the upset of aircraft.Due to when the aircraft forward flies, all rotors all should keep positive incidence, so complete and during inverted flight, all rotors 53 should be all the negative angle of attack, to guarantee having lift force upwards in aircraft upset.
Although more than described the specific embodiment of the present invention, it will be understood by those of skill in the art that these are only casehistorys, protection scope of the present invention is limited by appended claims.Those skilled in the art can make various changes or modifications to these embodiments under the prerequisite that does not deviate from principle of the present invention and essence, but these changes and modification all fall into protection scope of the present invention.
Claims (20)
1. multi-rotor aerocraft, it is characterized in that, this multi-rotor aerocraft comprises a power system and a displacement system, this power system comprises main rotatable parts, a plurality of drive disk assembly and is connected in rotor on each drive disk assembly, these main rotatable parts have a round end, those drive disk assemblies drive and transmission of rotation to those rotors are made its synchronous rotation by this round end, and this displacement system comprises a plurality of displacements unit, and each displacement unit is used for changing the angle of attack of those rotor one rotors.
2. multi-rotor aerocraft as claimed in claim 1, it is characterized in that, these main rotatable parts comprise an actuating device and one first finishing bevel gear cuter, this the first finishing bevel gear cuter is connected in the end of the rotor of this actuating device, each drive disk assembly comprises a drive link and a rotor shaft, drive link in each drive disk assembly is mutually vertical with rotor shaft, the two ends of each drive link are connected with respectively one second finishing bevel gear cuter and a third hand tap gear, be provided with the rotor in one the 4th finishing bevel gear cuter and those rotors on each rotor shaft, those second finishing bevel gear cuters all mesh with this first finishing bevel gear cuter, one the 4th finishing bevel gear cuter engagement in each third hand tap gear and those the 4th finishing bevel gear cuters.
3. multi-rotor aerocraft as claimed in claim 2, is characterized in that, this actuating device is a fuel engines or an electrical motor.
4. multi-rotor aerocraft as claimed in claim 3, is characterized in that, this electrical motor is the external rotor brushless electrical motor.
5. multi-rotor aerocraft as claimed in claim 2, it is characterized in that, the end of the rotor of this actuating device is provided with at least one first groove milling, be penetrated with one first connecting bore on this first finishing bevel gear cuter, this first finishing bevel gear cuter is socketed on the end of this rotor by this first connecting bore, and captives joint with this rotor by this first groove milling.
6. multi-rotor aerocraft as claimed in claim 2, it is characterized in that, this multi-rotor aerocraft also comprises internal stent and a cross mounting bracket on one, four hold-down arms of this cross mounting bracket all have first tapped bore, and this actuating device is anchored on this on internal stent by those first tapped bore.
7. multi-rotor aerocraft as claimed in claim 6, is characterized in that, has a storage tank on those on internal stent, and those second finishing bevel gear cuters and this first finishing bevel gear cuter all are positioned at this storage tank.
8. multi-rotor aerocraft as claimed in claim 2, it is characterized in that, this multi-rotor aerocraft also comprises four lower internal stent, those lower internal stent all have one group of the first half position-limited trough, be provided with four groups of the second half position-limited troughs on should upper internal stent, those lower internal stent all are connected on this on internal stent, and those the first half position-limited troughs all mutually engage with those the second half position-limited troughs and are used for spacing those drive links.
9. multi-rotor aerocraft as claimed in claim 2, is characterized in that, the number of those drive links, those rotor shaft, those second finishing bevel gear cuters, those third hand tap gears, those the 4th finishing bevel gear cuters and those rotors is four groups, six groups or eight groups.
10. multi-rotor aerocraft as claimed in claim 9, it is characterized in that, the number of those drive links, those rotor shaft, those second finishing bevel gear cuters, those third hand tap gears, those the 4th finishing bevel gear cuters and those rotors is four groups, those drive links are in the same plane, and the angle of two adjacent drive links is 90 °.
11. multi-rotor aerocraft as claimed in claim 10 is characterized in that, the gear teeth opposite direction of two the 4th finishing bevel gear cuters that two adjacent drive links connect is so that the hand of rotation of two adjacent rotors is opposite.
12. multi-rotor aerocraft as claimed in claim 2, it is characterized in that, the two ends of each drive link are provided with at least one second groove milling and at least one the 3rd groove milling respectively, all be penetrated with one second connecting bore on those second finishing bevel gear cuters, all be penetrated with one the 3rd connecting bore on those third hand tap gears, those second finishing bevel gear cuters and those third hand tap gears socket-connect by the two ends of those second connecting bores and those the 3rd connecting bores and those drive links respectively, and fix by the two ends of those second groove millings and those the 3rd groove millings and those drive links.
13. multi-rotor aerocraft as claimed in claim 2, it is characterized in that, each drive link comprises that one has connecting rod and a S. A. of the first axis hole, and this second finishing bevel gear cuter and this third hand tap gear are arranged at respectively the two ends of this S. A., and this S. A. is placed through in this first axis hole.
14. multi-rotor aerocraft as claimed in claim 13 is characterized in that, the two ends of each S. A. are provided with a clutch shaft bearing, those clutch shaft bearings and those S. A.s are articulated and be used for those S. A.s of carrying.
15. multi-rotor aerocraft as claimed in claim 8, it is characterized in that, this displacement system comprises four displacement unit, each displacement unit comprises a steering wheel, one first expansion link and a transmission component, those steering wheels, those first expansion links, those transmission components and the rotor of being connected connect successively, those steering wheels are used for driving those first expansion links and do fore and aft motion, and those first expansion links are used for those transmission components of interlock, and those transmission components are used for changing the angle of attack of those rotors.
16. multi-rotor aerocraft as claimed in claim 15 is characterized in that, this multi-rotor aerocraft also comprises a dash receiver, and this dash receiver is captiveed joint with those lower internal stent, and those steering wheels are threaded with this dash receiver.
17. multi-rotor aerocraft as claimed in claim 15 is characterized in that, those steering wheels are straight line steering wheel or rocking arm steering wheel.
18. multi-rotor aerocraft as claimed in claim 15, it is characterized in that, this multi-rotor aerocraft also comprises four rotor supports, those transmission components include a distance-variable rocker arm, several second expansion links, one updip swash plate, one second bearing and tilting frame once, this updip swash plate, this second bearing and this swash plate that has a down dip are placed through on this rotor shaft and interlock mutually successively, the two ends of each distance-variable rocker arm respectively with those first expansion links in one first expansion link and this swash plate that has a down dip mutually link, those updip swash plates change the angle of attack of those rotors by those second expansion links.
19. multi-rotor aerocraft as claimed in claim 18, it is characterized in that, each transmission component includes two the second expansion links, each rotor comprises two fins, two oar chucks, two the 3rd bearings, a sail shaft and rotor heads, each rotor head is fixedly connected on this sail shaft and has one second axis hole, those sail shaft are plugged in this second axis hole, in each rotor, those the 3rd bearings are connected in the two ends of this sail shaft, and those the 3rd bearings all connect a fin by an oar chuck.
20. multi-rotor aerocraft as described in any one in claim 1-19 is characterized in that the rotating speed that described synchronous rotation is those rotors is identical.
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| CN201210134337.2A CN103381885B (en) | 2012-05-02 | 2012-05-02 | Multi-rotor aerocraft |
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| CN201210134337.2A CN103381885B (en) | 2012-05-02 | 2012-05-02 | Multi-rotor aerocraft |
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