CN107719661A - A kind of unmanned plane rotor pulp distance varying mechanism - Google Patents
A kind of unmanned plane rotor pulp distance varying mechanism Download PDFInfo
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- CN107719661A CN107719661A CN201711089263.4A CN201711089263A CN107719661A CN 107719661 A CN107719661 A CN 107719661A CN 201711089263 A CN201711089263 A CN 201711089263A CN 107719661 A CN107719661 A CN 107719661A
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- unmanned plane
- rotor
- control bar
- pitch control
- hollow spindle
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- 230000007246 mechanism Effects 0.000 title claims abstract description 38
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- 210000004209 hair Anatomy 0.000 description 5
- 238000005183 dynamical system Methods 0.000 description 4
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- 239000003921 oil Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
Abstract
This application provides a kind of unmanned plane rotor pulp distance varying mechanism, and it has a hollow spindle, and the rotor of unmanned plane is fixedly mounted on the upper end of the hollow spindle and drives the rotor rotational to produce lift by the hollow spindle；The hollow spindle is internally provided with a pitch control bar, the upper end of pitch control bar is connected with a power transmission arm bearing that can be moved up and down with the pitch control bar in which can rotate to it, and the power transmission arm bearing drives the eccentric arm of the rotor to drive the rotor to be rotated around its mounting axis to change the angle of attack of the rotor by power transmission arm.The application is by the way that pitch control bar is arranged on inside hollow spindle, so that the space of installation pitch-changing mechanism need not be reserved between rotor and cantilever, the height that main shaft stretches out upwards from cantilever can diminish as far as possible, construction weight is significantly reduced, the payload for improving the unmanned plane of the application carries ability.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, more particularly to a kind of unmanned plane of more rotors, more particularly to it is a kind of nobody
Machine rotor pulp distance varying mechanism.
Background technology
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Unmanned plane presses application field, can be divided into it is military with it is civilian.Military aspect, unmanned plane are divided into reconnaissance plane and target
Machine.Civilian unmanned plane take photo by plane, agricultural, plant protection, miniature self-timer, express transportation, disaster relief, observation wild animal, monitoring pass
Catch an illness, survey and draw, news report, electric inspection process, the disaster relief, the field such as movies-making are widely used.
Existing multi-rotor unmanned aerial vehicle is usually electronic unmanned plane.The structure of more electronic unmanned planes of rotor is simply easily fabricated,
Motor is in light weight, stability of rotation, and dynamical system is easy to standardize, thus complete machine is relatively easy to manipulate, and flight noise is low,
Develop in short voyage civil area more active.Yet with battery energy density well below fuel oil, electronic unmanned plane by
To the limitation of battery, voyage is shorter, and load level is relatively low, can not be applied to military big load scout-attack field.It is and existing
The fuel oil unmanned plane generally use of long voyage fixes wing structure, and landing of taking off is limited by airport, can not hover, and cost is high,
Manipulate cumbersome, the flexible property used is inadequate.
CN 106697278A disclose that a kind of direct-drive type oil is dynamic determine rotating speed feather multi-rotor unmanned aerial vehicle, including fuselage, move
Force system, undercarriage and avionics system, described fuselage are the integrated fuselage of full material again, and described dynamical system is by engine
System, pitch-variable system, oil supply system and rotor system composition.Six rotors of the unmanned plane of above-mentioned prior art angularly between
Being set every ground around body, the application load for causing to carry on body can only be arranged at immediately below body, and due to all directions all
Stopped by rotor, the load of carrying can only carry out operation downwards, weapon delivery or can not be observed, deposit obliquely upward
Low in load level, topology layout is unreasonable, it is difficult to the defects of playing control and the security advantages of unmanned plane, limit rotor without
People's aircraft is in military and monitoring field development and application.
CN 205998123U disclose a kind of vertical layout rotor flying platform of fuel power four, its form include frame,
Dynamical system, navigation and control system, electrical system and task platform.Four identical horns, which are docked to be connected with two-by-two, to rise and fall
Frame is formed on the monocogue of frame；Dynamical system is arranged on the end of each horn, and power and energy are provided for flying platform
Source；Navigation and control system perceive and controlled posture, height and the position of flying platform；Electrical system have charging, power supply and
Indicator function；Task platform is used to install different task devices.The unmanned plane of the prior art is provided with four independent hairs
Motivation, the mutual interference in air flow of adjacent rotor are difficult to mediate, and the spacing of greater engine can further increase volume and again
Amount.
The unmanned plane of above-mentioned prior art, an oil is configured on each cantilever and moves engine, exposed engine adds
The noise of rotor, unmanned plane is caused almost to be used in city spatial domain, using also disguised without what under military environment.
CN 106184740A disclose it is a kind of for unmanned plane rotary wing changing away from device, wherein also disclose one kind four
The unmanned plane of rotor, the unmanned plane are entered by being arranged on the dynamic engine of oil that two axles of fuselage interior export to front and rear two pairs of rotors
Row driving, but its special engine technology used is immature, power output is limited, can not be applied to the arms nothing of big load
It is man-machine.In addition, used by the prior art rotary wing changing away from device, the upper sliding block being set in by servo driving on main shaft
Slided up and down, to drive the transmission arm being connected with upper sliding block to be acted, and then rotor rotational driven by transmission arm,
To change the angle of attack of rotor, to realize rotary wing changing away from purpose.But in the prior art, due to needing to be arranged on main shaft
Sliding block, the height for causing main shaft to be stretched out upwards from cantilever is too big, the higher intensity of main shaft needs, bigger weight, and main shaft is straight
Footpath is also very big.The sliding block of the various hollow-core constructions set around main shaft, become big as the change of major axis diameter is big, in addition, with
The elongated of main axis length, manipulating the stroke of the connecting rod of displacement can also become big, and steering wheel needs bigger angle to be manipulated, thus
The situation of locking easily occurs, and because the connecting rod for connecting steering wheel is too remote apart from manipulating objects, causes linkage very multiple
Miscellaneous, its reliability can undoubtedly reduce a lot, and construction weight also becomes very big.
The content of the invention
The technical problem to be solved in the present invention is to provide a kind of unmanned plane rotor pulp distance varying mechanism, before being reduced or avoided
The problem of being previously mentioned.
In order to solve the above technical problems, the present invention proposes a kind of unmanned plane rotor pulp distance varying mechanism, for passing through steering wheel
The rotor of unmanned plane is driven to be rotated around its mounting axis to change the angle of attack of the rotor, wherein, the unmanned plane rotary wing changing oar
Spacing mechanism has a hollow spindle, and the rotor is fixedly mounted on the upper end of the hollow spindle and by the hollow spindle band
The rotor rotational is moved to produce lift；The hollow spindle is internally provided with one can be along the length direction of the hollow spindle
The pitch control bar of up and down motion, the upper end of the pitch control bar is connected with one in which can rotate to it can be with the displacement
The power transmission arm bearing that control stick moves up and down, the power transmission arm bearing drive the eccentric arm of the rotor to drive institute by power transmission arm
Rotor is stated to rotate around its mounting axis；The steering wheel is connected with the lower end of the pitch control bar by connecting rod and manipulates the change
Moved up and down away from control stick.
Preferably, the upper end of the pitch control bar passes at the top of the hollow spindle, and passes through the power transmission arm
The centre bore of bearing is fixedly connected with a locking cap.
Preferably, the diameter that the pitch control bar is passed after the top of the hollow spindle is less than positioned at described hollow
The diameter of the inside of main shaft, so as to form a step positioned at the upper end of the pitch control bar.
Preferably, supporting bearing, the outer ring of the supporting bearing and institute are provided with the centre bore of the power transmission arm bearing
State centre bore interference fit.
Preferably, the bottom of the inner ring of the supporting bearing is located on the step, the inner ring of the supporting bearing
Top withstands on the lower section of the locking cap by a stop collar.
Preferably, the step is stretched out outside the top of the hollow spindle.
Preferably, the lower openings of the centre bore of the power transmission arm bearing are open greatly to its upper.
Preferably, the hollow spindle is set protruding from the inside of a retainer, the bottom tool of the retainer
There is the port that the lower end for the pitch control bar passes.
Preferably, the steering wheel is arranged on the outside of the retainer, and by being arranged on the lower section of the retainer
Connecting rod is connected with the lower end of the pitch control bar.
Preferably, the bottom of the retainer is provided with link supports seat.
The unmanned plane rotor pulp distance varying mechanism of the application by by for manipulate the pitch control bar of displacement be arranged on it is hollow
Inside main shaft so that the space of installation pitch-changing mechanism need not be reserved between rotor and cantilever, for the master for driving cantilever to rotate
The height that axle stretches out upwards from cantilever can diminish as far as possible, can substantially be compressed to below the limiting altitude of structure, significantly
Alleviate construction weight.And moved up and down because steering wheel can manipulate pitch control bar by connecting rod from the bottom of main shaft, rudder
The corner stroke of machine can become very small, greatly reduce the manipulation distance of connecting rod, completely eliminate connecting rod and locking occurs
Possibility.Diminish simultaneously because connecting rod manipulates distance, the structure of connecting rod becomes very simple and compact, improves the present invention's
Structural reliability, while simple compact structure can further reduce construction weight, the unmanned plane for improving the application have
Imitate load and carry ability.
Brief description of the drawings
The following drawings is only intended to, in doing schematic illustration and explanation to the present invention, not delimit the scope of the invention.Wherein,
The dimensional structure diagram of the unmanned plane of a specific embodiment according to the present invention is shown in Fig. 1；
Structural representation after the part-structure removal of unmanned plane shown in Fig. 1 that Fig. 2 is shown；
The drive mechanism that the fuselage interior of the unmanned plane of another specific embodiment according to the application is shown in Fig. 3 shows
It is intended to；
The external structure of the unmanned plane rotor pulp distance varying mechanism of a specific embodiment according to the application is shown in Fig. 4
Schematic diagram；
The internal drive feature schematic diagram of the pulp distance varying mechanism of unmanned plane rotor shown in Fig. 4 is shown in Fig. 5；
The partial cutaway of the unmanned plane rotor pulp distance varying mechanism according to another specific embodiment of the application is shown in Fig. 6
Depending on decomposing schematic representation.
Embodiment
In order to which technical characteristic, purpose and the effect of the present invention is more clearly understood, now control illustrates this hair
Bright embodiment.Wherein, identical part uses identical label.
Just it has been observed that existing unmanned plane is laid out using holohedral symmetry mostly, position of centre of gravity is caused to converge, load layout
It is extremely limited, and because the rotor of holohedral symmetry layout all blocks all directions of unmanned plane, causes the load carried
Lotus weapon delivery or can not be observed obliquely upward, limit the application of existing unmanned plane.Other adjacent rotor phase
Interference in air flow between mutually be present, main screw lift can be increased by extending jib-length, and the ability for carrying payload is greatly limited
System.
To solve drawbacks described above, this application provides a kind of unmanned plane, as shown in Figure 1-2, wherein, root is shown in Fig. 1
According to the dimensional structure diagram of the unmanned plane of the specific embodiment of the present invention；The part of unmanned plane shown in Fig. 1 that Fig. 2 is shown
Structural representation after structure removal.
Referring to Fig. 1-2, the unmanned plane of the application includes fuselage 1,2, four cantilevers 3 of undercarriage and four rotors 5, fuselage
1 four cantilevers 3 of connection, each cantilever 3 are supported by the rotor 5 of a same diameter.Unlike existing multiaxis unmanned plane,
The fuselage 1 of the unmanned plane of the application is the strip of bilateral symmetry, and fuselage 1 has a longitudinal asymmetric axis 6, fuselage 1
It is generally elongated to be set parallel to the axis of symmetry 6.The head and tail of unmanned plane are each provided with two and are symmetrical with institute
State the rotor 5 of the arrangement of the axis of symmetry 6.The basic conception of the application is, is strip in the fuselage 1 of unmanned plane, and fuselage 1 has pair
Claim axis 6, four rotors 5 are respectively arranged at the both sides of the axis of symmetry 6, so as to be longitudinally formed a nothing below fuselage 1
The passage blocked, in favor of setting the load such as photoelectric nacelle 7 and arm discharge cylinder (not shown), avoid observation and weapon hair
Interfered when penetrating with cantilever 3 and rotor 5 etc., influence to use and fighting efficiency, improve the application of unmanned plane.Separately
Outside, due to there is provided the axis of symmetry 6, then on the longitudinal direction of unmanned plane there will be no lift structure, cantilever 3 and rotor 5 thereon
Etc. the both sides that structure can only be distributed in the axis of symmetry 6, it is possible thereby to longitudinally obtain larger range of load mount point in fuselage, easily
In extension load layout.
Further, as illustrated, the fusiformis structure of the fuselage of the unmanned plane of the application substantially strip, head and
The width constriction of tail, middle part width maximum are easy to set engine.The fuselage of fusiformis structure can also move forward and backward
Flight resistance is reduced in journey, improves the voyage of unmanned plane.In addition, the fuselage of fusiformis structure can also be the maximization of rotor diameter
Provide space.
Further, as shown in figure 1, the unmanned plane of the application in a specific embodiment, the front end of fuselage 1 is provided with
Can carry photoelectric nacelle 7 gondola hanging structure (not shown).In another specific embodiment, the bottom of fuselage 1 can
To set the attachment structure (not shown) of carry arm discharge cylinder, for example, parallel can be set along the length direction of the axis of symmetry 6
Two or more arm discharge cylinders are put, wherein the arm discharge cylinder can be specially launch canister or rocket projectile hair
Shooting cylinder, because this kind of arm discharge cylinder needs to provide the elevation angle obliquely, it is difficult to send out if its front there are the barriers such as rotor
Boosted missile or rocket projectile (unmanned plane just crashes in the case of interference being present), therefore arranged for ease of load, head and machine
The rotor 5 of tail is with the axis of symmetry 6 apart from equal configuration, then arm discharge cylinder can be intuitively by parallel to load path 6
The mode that sets of length direction realize the load gravity center balance of unmanned plane, in order to the manipulation of unmanned plane, simplify flying-controlled box
Design difficulty.
The problem of in order to overcome adjacent rotor interference in air flow, each rotor 5 in the application is around being provided with a shape
The kuppe 4 of shape identical annular.The setting of kuppe 4 allows the diameter of rotor 5 to be maximumlly extended, as long as
Do not interfere with fuselage 1, so as in the case where the length of cantilever 3 need not be extended, effectively improve nobody as far as possible
The lift of machine, thus the carrying ability of unmanned plane can be improved.In order to see more clearly, the part-structure of the unmanned plane in Fig. 2
It is removed.
The drive mechanism that the fuselage interior of the unmanned plane of another specific embodiment according to the application is shown in Fig. 3 shows
It is intended to, from Fig. 2-3, the cantilever 3 of the unmanned plane of the application is hollow-core construction, and it is internally provided with drive link 9.The application
Unmanned plane fuselage 1 in engine 99 is installed, the power of engine can pass to drive 90 by structures such as belts,
Drive 90 further imparts power to each rotor 5 by the drive link 9 being attached thereto.
In drive mechanism shown in Fig. 3, a main shaft 8 is set in parallel between the head of unmanned plane and the cantilever 3 of tail,
81, first power output wheels 82 of a power input wheel and second power output wheel are installed with main shaft 8
83, power input wheel 81 is driven by engine 99 by dynamo belt 84, the first power output wheel 82 and the second power output
Wheel 83 drives the drive link 9 set in the cantilever 3 of unmanned plane to rotate by the first belt 85 and the second belt 86 respectively, and will hair
The power of motivation 99 passes to each rotor 5.
The drive mechanism of the unmanned plane of the application only needs to utilize belt (dynamo belt 84, the first belt 85 and the
Two belts 86) and a main shaft 8, it is possible to the power of the engine 99 of fuselage interior installation is delivered separately to head and tail
Four rotors 5, simple in construction, in light weight, technology maturation, implement in the absence of any risk, and engine 99 can be adopted
With ordinary internal combustion engine or commercially available existing aero-engine, it is not necessary to be specifically designed special engine.Started using existing
Machine can also select the engine of different capacity as needed, can meet the needs of the unmanned plane of various magnitudes of load.In addition
Main shaft 8 is set parallel to cantilever 3, and three be arranged on main shaft 8 wheel is parallel to each other, thus the drive link 9 of head and tail
Receiving the mode of power need not be commutated by bevel gear, it is possible to reduce the weight of mechanical commutation device.
Also as before, referring to the drawings, in the specific embodiment of the application, the middle part of drive link 9 is fixedly connected with one
Individual drive 90, drive 90 impart power to drive link 9, and drive two rotors 5 that the both ends of drive link 9 connect towards phase
Anti- direction rotates.The arrangement of the axis of symmetry 6 is symmetrical with because the head and tail of the unmanned plane of the application are each provided with two
Cantilever 3, two cantilevers 3 of head are located along the same line, wherein a drive link 9 can be set；Two cantilevers 3 of tail
It is located along the same line, wherein a drive link 9 can also be set, the two drive links 9 of head and tail are led simultaneously
The driving of axle 8 rotates in the same direction, thus two rotors 5 of two rotors 5 of head and tail are in the same side of fuselage 1
Rotation situation be identical.Then, drive link 9, respectively to both sides passing power, is passed by the driving of the drive 90 at middle part
Direction of transfer of the power that lever 9 is transmitted at its both ends by the mechanism switching kinetics of such as bevel gear 87 etc, same biography
The rotor 5 at the both ends of lever 9 is rotated in the opposite direction by bevel gear driving, thus can offset mutual torque, so as to
To avoid the rotation of unmanned plane.
The specific feature of the unmanned plane rotor pulp distance varying mechanism of the application is further described referring to Fig. 4-6, its
In, the external structure signal of the unmanned plane rotor pulp distance varying mechanism of a specific embodiment according to the application is shown in Fig. 4
Figure；The internal drive feature schematic diagram of the pulp distance varying mechanism of unmanned plane rotor shown in Fig. 4 is shown in Fig. 5；Basis is shown in Fig. 6
The broken section decomposing schematic representation of the unmanned plane rotor pulp distance varying mechanism of another specific embodiment of the application.
As schemed, just it has been observed that the unmanned plane of the application includes fuselage 1, undercarriage 2 and the fuselage 1 installed in unmanned plane
Internal engine 99, fuselage 1 have a longitudinal asymmetric axis 6, and the head and tail of unmanned plane are each provided with two symmetrically
In the cantilever 3 that the axis of symmetry 6 is arranged, each cantilever 3 is supported by a rotor 5.Wherein cantilever 3 is hollow-core construction, inside it
It is provided with drive link 9.The middle part of drive link 9 is fixedly connected with a drive 90, and drive link 9 is since drive 90 along machine
Two cantilevers 3 of body both sides stretch out.
Such as figure, the end of each cantilever 3 is supported by a retainer 69, travelling gear is provided with retainer 69, uses
In the power of drive link 9 is passed into rotor 5 by travelling gear.Specifically, it is illustrated that retainer 69 substantially one is vertical
The box of cube, the end of cantilever 3 is fixedly connected with a lateral wall of retainer 69, while the lateral wall is connected with cantilever 3
The position connect has a hole stretched into for the end of drive link 9, and the end of drive link 9 is stretched into positioned at retainer by this hole
69 inside, and one first bevel gear 91 is connected with by spline in the end of drive link 9, as shown in Figure 5.First bevel gear
91 are meshed with a second bevel gear 92, the hollow master that second bevel gear 92 is connected to drive rotor 5 to rotate by spline
Axle 68.
Wherein, hollow spindle 68 is a key structure of the unmanned plane rotor pulp distance varying mechanism of the application, below will be right
This is described in detail.As shown in fig. 6, this application provides a kind of unmanned plane rotor pulp distance varying mechanism, it has hollow spindle 68, rotation
The wing 5 is fixedly mounted on the upper end of hollow spindle 68 and drives rotor 5 to rotate to produce lift by hollow spindle 68.Hollow spindle 68
A pitch control bar 65 that can be moved up and down along the length direction of hollow spindle 68 is internally provided with, pitch control bar 65 passes through
Steering wheel 67 manipulates its up and down motion.
The upper end of pitch control bar 65 is connected with one in which can rotate to it can be as pitch control bar 65 moves up and down
Power transmission arm bearing 64, power transmission arm bearing 64 by power transmission arm 641 drive rotor 5 eccentric arm 59 drive rotor 5 around its install
Axis rotates, so as to change the angle of attack of rotor 5.
More specifically, steering wheel 67 is connected with the lower end of pitch control bar 65 by connecting rod and manipulates pitch control bar about 65
Motion.Further, steering wheel 67 is arranged on the outside of retainer 69, and by be arranged on retainer 69 lower section connecting rod with
The lower end connection of pitch control bar 65.
In general, the unmanned plane rotor pulp distance varying mechanism of the application can be used for the rotor that unmanned plane is driven by steering wheel 67
5 rotate to change the angle of attack of rotor 5 around its mounting axis, so as to reach the purpose of the pitch for the rotor for changing unmanned plane.
In a specific embodiment, hollow spindle 68 sets, hollow spindle 68 protruding from the inside of retainer 69
Stretch out and be fixedly connected in the end outside retainer 69 by way of spline connection with the mounting seat 651 of rotor 5, to avoid pacifying
Dress seat 651 is come off from the end of hollow spindle 68, and a hold-doun nut 652, hold-doun nut are provided with the top of mounting seat 651
652 modes that can be connected through a screw thread are screwed in the outside of the end of hollow spindle 68.To cause the lower end of pitch control bar 65
It can be operated by steering wheel 67, the bottom of retainer 69, which sets to have, is available for the end that the lower end of pitch control bar 65 passes
Mouthful.In addition, the one end for being arranged on the connecting rod of the lower section of retainer 69 is connected with steering wheel 67, under the other end and pitch control bar 65
End connection, the bottom of retainer 69 are provided with the link supports seat 691 for providing connecting rod support.
In another specific embodiment, the upper end of pitch control bar 65 passes from the top of hollow spindle 68, and passes through
The centre bore 642 of power transmission arm bearing 64 is fixedly connected with a locking cap 63, and the main function of locking cap 63 is to prevent power transmission
Arm bearing 64 comes off from the upper end of pitch control bar 65.
Quantity on power transmission arm bearing 64 corresponding to rotor 5 is connected with multiple power transmission arms 641, the other end of power transmission arm 641
Connect the eccentric arm 59 of rotor 5.In specific embodiment is illustrated, the quantity for the rotor 5 that each cantilever 3 connects is three.
When rotor 5 rotates with mounting seat 651 under the drive of hollow spindle 68, the power transmission that is connected with rotor 5
Arm bearing 64 can rotate together with rotor 5.And the lower end of the pitch control bar 65 through the centre bore 642 of power transmission arm bearing 64
It is connected with steering wheel 67, thus pitch control bar 65 is non-rotatable.In this case, pitch control bar 65 and power transmission arm bearing
Need to set a kind of special structural relation between 64 so that the one side of power transmission arm bearing 64 can be 65 turns with respect to pitch control bar
It is dynamic, on the other hand can also be when pitch control bar 65 move up and down, power transmission arm bearing 64 can be with pitch control bar
65 move up and down together.
To realize above-mentioned special function, this application provides such a structure, the i.e. center in power transmission arm bearing 64
Supporting bearing 621 is set in hole 642 so that power transmission arm bearing 64 can be by supporting bearing 621 around 65 turns of pitch control bar
It is dynamic.Meanwhile try the inner ring of supporting bearing 621 being stuck on pitch control bar 65, when pitch control bar 65 moves up and down
Wait, the inner ring of the supporting bearing 621 being stuck on pitch control bar 65 moves with pitch control bar 65, so as to drive supporting bearing
621 outer ring is also moved together, and the outer ring of supporting bearing 621 and the centre bore 642 of power transmission arm bearing 64 are interference fitted, thus
By the outer ring of supporting bearing 621 power transmission arm bearing 64 can be driven to move up and down.
To realize the function being stuck in the inner ring of supporting bearing 621 on pitch control bar 65, in specific embodiment is illustrated,
The diameter that pitch control bar 65 is passed after the top of hollow spindle 68 is less than the diameter positioned at the inside of hollow spindle 68, so as to
Form a step 62 positioned at the upper end of pitch control bar 65.Bearing is provided with the centre bore 642 of power transmission arm bearing 64
Bearing 621, outer ring and the centre bore 642 of supporting bearing 621 are interference fitted.Platform is located in the bottom of the inner ring of supporting bearing 621
On rank 62, the top of the inner ring of supporting bearing 621 withstands on the lower section of locking cap 63 by a stop collar 61.Therefore, lock herein
Cap 63 is determined except can prevent power transmission arm bearing 64 from being come off from the upper end of pitch control bar 65, can also limit stop collar 61,
For the inner ring of supporting bearing 621 to be pressed in into step 62 by stop collar 61.
That is, the inner ring of supporting bearing 621 is stuck in displacement by the present embodiment by the collective effect of step 62 and stop collar 61
On control stick 65, so as to which the inner ring of supporting bearing 621 when pitch control bar 65 moves up and down, can be driven to transport up and down
It is dynamic, finally it can both drive power transmission arm bearing 64 to move up and down, it is also possible that power transmission arm bearing 64 can be around pitch control
Bar 65 rotates.
In the preferred embodiment of the application, step 62 is stretched out outside the top of hollow spindle 68, thus can be with
The entirety of power transmission arm bearing 64 is limited in the top of step 62 by step 62, power transmission arm bearing 64 will not be with hollow master when rotating
The problem of top contact of axle 68 is not in constructive interference.
Additionally, it is preferred that the centre bore 642 of power transmission arm bearing 64 is a stepped hole, its underpart opening is opened greatly to its upper
Mouthful, supporting bearing 621 can be arranged in lower openings, because the upper opening of centre bore 642 is smaller, thus supporting bearing
621 can be limited in the lower section of upper opening, be made so as to avoid supporting bearing 621 from being spun off from the top of centre bore 642
Into accident.
The unmanned plane rotor pulp distance varying mechanism of the application by by for manipulate the pitch control bar of displacement be arranged on it is hollow
Inside main shaft so that the space of installation pitch-changing mechanism need not be reserved between rotor and cantilever, for the master for driving cantilever to rotate
The height that axle stretches out upwards from cantilever can diminish as far as possible, can substantially be compressed to below the limiting altitude of structure, significantly
Alleviate construction weight.And moved up and down because steering wheel can manipulate pitch control bar by connecting rod from the bottom of main shaft, rudder
The corner stroke of machine can become very small, greatly reduce the manipulation distance of connecting rod, completely eliminate connecting rod and locking occurs
Possibility.Diminish simultaneously because connecting rod manipulates distance, the structure of connecting rod becomes very simple and compact, improves the present invention's
Structural reliability, while simple compact structure can further reduce construction weight, the unmanned plane for improving the application have
Imitate load and carry ability.
It will be appreciated by those skilled in the art that although the present invention is described in the way of multiple embodiments,
It is that not each embodiment only includes an independent technical scheme.So narration is used for the purpose of for the sake of understanding in specification,
The skilled in the art should refer to the specification as a whole is understood, and by technical scheme involved in each embodiment
The modes of different embodiments can be mutually combined into understand protection scope of the present invention by regarding as.
The schematical embodiment of the present invention is the foregoing is only, is not limited to the scope of the present invention.It is any
Those skilled in the art, equivalent variations, modification and the combination made on the premise of the design of the present invention and principle is not departed from,
The scope of protection of the invention all should be belonged to.
Claims (10)
- A kind of 1. unmanned plane rotor pulp distance varying mechanism, for driving the rotor (5) of unmanned plane by steering wheel (67) around its installation axle Line is rotated to change the angle of attack of the rotor (5), it is characterised in that the unmanned plane rotor pulp distance varying mechanism is hollow with one Main shaft (68), the rotor (5) are fixedly mounted on the upper end of the hollow spindle (68) and driven by the hollow spindle (68) The rotor (5) is rotated to produce lift；The hollow spindle (68) is internally provided with one can be along the hollow spindle (68) Length direction move up and down pitch control bar (65), the upper end of the pitch control bar (65) connects in which can rotate to it There is a power transmission arm bearing (64) that can be moved up and down with the pitch control bar (65), the power transmission arm bearing (64) passes through biography The arm of force (641) drives the eccentric arm (59) of the rotor (5) to drive the rotor (5) to be rotated around its mounting axis；The steering wheel (67) it is connected by connecting rod with the lower end of the pitch control bar (65) and manipulates the pitch control bar (65) and is moved up and down.
- 2. unmanned plane rotor pulp distance varying mechanism as claimed in claim 1, it is characterised in that the pitch control bar (65) it is upper End passes at the top of the hollow spindle (68), and is locked through the centre bore (642) of the power transmission arm bearing (64) with one Determine cap (63) to be fixedly connected.
- 3. unmanned plane rotor pulp distance varying mechanism as claimed in claim 2, it is characterised in that the pitch control bar (65) passes Diameter after the top of the hollow spindle (68) is less than the diameter positioned at the inside of the hollow spindle (68), so as to be formed One step (62) positioned at the upper end of the pitch control bar (65).
- 4. unmanned plane rotor pulp distance varying mechanism as claimed in claim 3, it is characterised in that in the power transmission arm bearing (64) Supporting bearing (621) is provided with heart hole (642), outer ring and the centre bore (642) interference of the supporting bearing (621) are matched somebody with somebody Close.
- 5. unmanned plane rotor pulp distance varying mechanism as claimed in claim 4, it is characterised in that the supporting bearing (621) it is interior The bottom of circle is located on the step (62), and the top of the inner ring of the supporting bearing (621) passes through a stop collar (61) Withstand on the lower section of the locking cap (63).
- 6. unmanned plane rotor pulp distance varying mechanism as claimed in claim 5, it is characterised in that the step (62) is stretched out described Outside the top of hollow spindle (68).
- 7. unmanned plane rotor pulp distance varying mechanism as claimed in claim 6, it is characterised in that in the power transmission arm bearing (64) The lower openings in heart hole (642) are open greatly to its upper.
- 8. the unmanned plane rotor pulp distance varying mechanism as described in one of claim 1-7, it is characterised in that the hollow spindle (68) Setting is protruding from the inside of a retainer (69), and the bottom of the retainer (69), which has, supplies the pitch control bar (65) port that lower end passes.
- 9. unmanned plane rotor pulp distance varying mechanism as claimed in claim 8, it is characterised in that the steering wheel (67) is arranged on described The outside of retainer (69), and the connecting rod of the lower section by being arranged on the retainer (69) and the pitch control bar (65) Lower end connects.
- 10. unmanned plane rotor pulp distance varying mechanism as claimed in claim 9, it is characterised in that the bottom of the retainer (69) It is provided with link supports seat (691).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711089263.4A CN107719661A (en) | 2017-11-08 | 2017-11-08 | A kind of unmanned plane rotor pulp distance varying mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711089263.4A CN107719661A (en) | 2017-11-08 | 2017-11-08 | A kind of unmanned plane rotor pulp distance varying mechanism |
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| Publication Number | Publication Date |
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| CN107719661A true CN107719661A (en) | 2018-02-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711089263.4A Pending CN107719661A (en) | 2017-11-08 | 2017-11-08 | A kind of unmanned plane rotor pulp distance varying mechanism |
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| CN (1) | CN107719661A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108860629A (en) * | 2018-06-25 | 2018-11-23 | 云南优航无人机科技有限公司 | A kind of rotary-wing transmission mechanism of unmanned plane |
| CN113928541A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Helicopter control system motion control law design method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002316699A (en) * | 2001-04-18 | 2002-10-29 | Techno Link Co Ltd | Coaxial reverse rotation type helicopter |
| CN101723091A (en) * | 2009-12-16 | 2010-06-09 | 李游 | Rotor wing pitch change control device of heligyro |
| CN102658865A (en) * | 2012-05-17 | 2012-09-12 | 李游 | Coaxial drive and control structure for coaxial contrarotation rotor helicopter |
| CN105292465A (en) * | 2015-11-04 | 2016-02-03 | 中航维拓（北京）科技有限责任公司 | Rigid rotor system for helicopter |
| CN105539832A (en) * | 2015-12-24 | 2016-05-04 | 上海埃威航空电子有限公司 | Variable-pitch power device for multi-rotor-wing unmanned aerial vehicle |
| CN207450249U (en) * | 2017-11-08 | 2018-06-05 | 沈阳旋飞航空技术有限公司 | A kind of unmanned plane rotor pulp distance varying mechanism |
-
2017
- 2017-11-08 CN CN201711089263.4A patent/CN107719661A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002316699A (en) * | 2001-04-18 | 2002-10-29 | Techno Link Co Ltd | Coaxial reverse rotation type helicopter |
| CN101723091A (en) * | 2009-12-16 | 2010-06-09 | 李游 | Rotor wing pitch change control device of heligyro |
| CN102658865A (en) * | 2012-05-17 | 2012-09-12 | 李游 | Coaxial drive and control structure for coaxial contrarotation rotor helicopter |
| CN105292465A (en) * | 2015-11-04 | 2016-02-03 | 中航维拓（北京）科技有限责任公司 | Rigid rotor system for helicopter |
| CN105539832A (en) * | 2015-12-24 | 2016-05-04 | 上海埃威航空电子有限公司 | Variable-pitch power device for multi-rotor-wing unmanned aerial vehicle |
| CN207450249U (en) * | 2017-11-08 | 2018-06-05 | 沈阳旋飞航空技术有限公司 | A kind of unmanned plane rotor pulp distance varying mechanism |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108860629A (en) * | 2018-06-25 | 2018-11-23 | 云南优航无人机科技有限公司 | A kind of rotary-wing transmission mechanism of unmanned plane |
| CN113928541A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Helicopter control system motion control law design method |
| CN113928541B (en) * | 2021-11-19 | 2023-04-25 | 中国直升机设计研究所 | Helicopter control system motion control law design method |
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