CN109436310A - Rotor inclining rotary mechanism and unmanned plane - Google Patents
Rotor inclining rotary mechanism and unmanned plane Download PDFInfo
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- CN109436310A CN109436310A CN201811427354.9A CN201811427354A CN109436310A CN 109436310 A CN109436310 A CN 109436310A CN 201811427354 A CN201811427354 A CN 201811427354A CN 109436310 A CN109436310 A CN 109436310A
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- connecting rod
- rotary mechanism
- rotor
- inclining rotary
- gear
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- 230000007246 mechanism Effects 0.000 title claims abstract description 43
- 230000033001 locomotion Effects 0.000 claims description 28
- 230000005540 biological transmission Effects 0.000 claims description 4
- 230000000712 assembly Effects 0.000 abstract description 9
- 238000000429 assembly Methods 0.000 abstract description 9
- 238000010586 diagram Methods 0.000 description 4
- 230000001360 synchronised effect Effects 0.000 description 4
- 230000004992 fission Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Aviation & Aerospace Engineering (AREA)
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Abstract
This disclosure relates to a kind of rotor inclining rotary mechanism and unmanned plane, wherein rotor inclining rotary mechanism includes: connecting rod (100)；Mounting base (200) can be connected to the both ends of the connecting rod (100) for installing rotor assembly in which vert along the extending direction of the connecting rod (100)；And driving device (300), for driving the connecting rod (100) to move along the extending direction of the connecting rod (100), to drive the rotor assembly to vert along the extending direction of the connecting rod (100).Through the above technical solution, when unmanned plane verts, driving device drive link is moved along its own extending direction, and connecting rod is axially moved and then the mounting base that its both ends is arranged in is driven to vert towards connecting rod extending direction, rotor assembly is fixed in mounting base, is verted so as to synchronize with mounting base.In this course, verting for two rotor assemblies, save the cost are controlled by a driving device, and is able to ascend the synchronism of two rotor assemblies.
Description
Technical field
This disclosure relates to air vehicle technique field, and in particular, to a kind of rotor inclining rotary mechanism and unmanned plane.
Background technique
Unmanned plane during flying device generally includes Fixed Wing AirVehicle and multi-rotor aerocraft, for multi-rotor aerocraft,
Rotor can not only be supplied to the vertical lift of unmanned plane VTOL, hovering, when unmanned plane flight in the horizontal plane,
Rotor can also vert, with being supplied to unmanned plane is maintained at the lift of certain altitude and the power of horizontal movement simultaneously.It is existing
Have in technology, rotor realization is needed to vert under some cases, is respectively provided with the steering engine that verts at each rotor usually with logical
It crosses each rotor of independent steering engine control to vert, this just needs accurately to control the synchronism of multiple steering engines, and uses multiple steering engines
Higher cost.
Summary of the invention
One purpose of the embodiment of the present disclosure is to provide a kind of rotor inclining rotary mechanism, which can be driven by one
Dynamic device controls two rotors and verts, save the cost, and is able to ascend the synchronism of two rotors.
Another purpose of the embodiment of the present disclosure is to provide a kind of unmanned plane, which is configured with the rotation that the disclosure provides
Wing inclining rotary mechanism.
To achieve the goals above, the embodiment of the present disclosure provides a kind of rotor inclining rotary mechanism, comprising: connecting rod；Mounting base is used
In installation rotor assembly, the both ends of the connecting rod can be connected to along the extending direction of the connecting rod with verting；And driving device,
For driving the connecting rod to move along the extending direction of the connecting rod, to drive the rotor assembly along the extension side of the connecting rod
To verting.
Optionally, the driving device includes driving portion and driving section, and the driving section includes linear motion part, described straight
The direction of motion of line movement parts is identical as the extending direction of the connecting rod, and the connecting rod is fixed on the linear motion part.
Optionally, the linear motion part is rack gear, and the driving section further includes the gear with rack gear cooperation, described
Driving portion includes steering engine, and the output shaft of the steering engine is fixedly connected with the gear.
Optionally, the gear has ring gear, and the output shaft of the steering engine is formed as gear shaft, the ring gear and institute
State gear shaft engaged transmission.
Optionally, the inclining rotary mechanism further includes the gear-box for accommodating the rack gear and the gear, on the gear-box
It is provided with steering engine seat, the steering engine is mounted on the steering engine seat.
Optionally, the outer cover of the connecting rod is equipped with support arm, and one end of the support arm is fixed on fuselage, other end setting
There is support base, the mounting base is hinged by the first tiliting axis and the connecting rod, and passes through the second tiliting axis and the support base
Hingedly.
Optionally, the mounting base includes top plate and the side plate that extends vertically downward from the top plate both ends, the rotor
Assembly is mounted on the top of the top plate, and the bottom of the top plate is formed with two pieces of first otic placodes being oppositely arranged, the connecting rod
End protrude between two pieces of first otic placodes and hinged by first tiliting axis and first otic placode.
Optionally, one end of the support base is formed as the pipe clamp for being fixedly connected with the support arm, and the other end has
Two pieces of second otic placodes being oppositely arranged, the extending direction of second otic placode is identical as the extending direction of the connecting rod, and described
Two otic placodes are hinged by second tiliting axis and the side plate.
Optionally, return spring is provided at least one described second tiliting axis.
According to the second aspect of the embodiment of the present disclosure, a kind of unmanned plane, including fuselage and rotor inclining rotary mechanism, institute are provided
Stating rotor inclining rotary mechanism is according to above-described rotor inclining rotary mechanism.
Through the above technical solutions, driving device drive link is moved along its own extending direction when unmanned plane verts, even
Bar is axially moved and then the mounting base that its both ends is arranged in is driven to vert towards connecting rod extending direction, and rotor assembly is fixed on installation
On seat, vert so as to be synchronized with mounting base.In this course, two rotor assemblies are controlled by a driving device
It verts, save the cost, and it is able to ascend the synchronism of two rotor assemblies.
Other feature and advantage of the embodiment of the present disclosure will the following detailed description will be given in the detailed implementation section.
Detailed description of the invention
Attached drawing is to further understand for providing to the embodiment of the present disclosure, and constitute part of specification, under
The specific embodiment in face is used to explain the embodiment of the present disclosure together, but does not constitute the limitation to the embodiment of the present disclosure.Attached
In figure:
Fig. 1 is the structural schematic diagram for the rotor inclining rotary mechanism that a kind of illustrative embodiments of the disclosure provide；
Fig. 2 is the structural schematic diagram of driving device in rotor inclining rotary mechanism shown in fig. 1；
Fig. 3 is mounting base in rotor inclining rotary mechanism shown in fig. 1, the assembling schematic diagram of support base and connecting rod；
Fig. 4 is the structural schematic diagram of support base in rotor inclining rotary mechanism shown in fig. 1.
Description of symbols
100- connecting rod, 200- mounting base, 210- top plate, 220- side plate, the first otic placode of 230-, 300- driving device, 310-
Driving portion, 311- steering engine, 312- steering engine seat, the driving section 320-, 321- linear motion part, 322- gear, 323- gear-box, 410-
Motor, 420- blade, 500- support arm, 600- support base, 610- pipe clamp, the second otic placode of 620-, 700- return spring, 810- first
Tiliting axis, the second tiliting axis of 820-.
Specific embodiment
It is described in detail below in conjunction with specific embodiment of the attached drawing to the embodiment of the present disclosure.It should be understood that this
Locate described specific embodiment and be only used for describing and explaining the embodiment of the present disclosure, is not limited to the embodiment of the present disclosure.
In the embodiments of the present disclosure, in the absence of explanation to the contrary, the noun of locality used such as "upper", "lower" refers to nothing
Upper and lower when man-machine flat winged state, "inner", "outside" are usually for profile of corresponding components itself.In addition, this
Term " first ", " second " used in open embodiment etc. is that do not have suitable to distinguish an element and another element
Sequence and importance.In the following description when referring to the accompanying drawings, unless otherwise indicated, the same numbers in different attached drawings indicate it is identical or
Similar element.
Referring to Fig.1, the embodiment of the present disclosure provides a kind of rotor inclining rotary mechanism, including connecting rod 100, mounting base 200 and driving
Device 300.Wherein, mounting base 200 can be connected to the both ends of connecting rod 100 in which vert along the extending direction of connecting rod 100, for pacifying
Fill rotor assembly.In the embodiments of the present disclosure, as shown in Figure 1, rotor assembly may include blade 420 and for driving blade
The motors 410 of 420 rotations, motor 410 is fixedly mounted in mounting base 200, so as to realize blade 420 and motor 410 with
Synchronizing for mounting base 200 is verted.Mounting base 200 can vert along the extending direction of connecting rod 100 refers to that the first of mounting base 200 connects
Connecing end can rotate around with the fixed certain point of unmanned aerial vehicle body, and second connection end is connected with connecting rod 100, moves when connecting rod 100 is axial
When dynamic, second connection end can be driven to rotate around the first connecting pin.Driving device 300 is for drive link 100 along connecting rod 100
Extending direction movement, to drive rotor assembly to vert along the extending direction of connecting rod 100, driving device 300 be can be set at nobody
The fuselage interior of machine.In this way, 300 drive link 100 of driving device is moved along its own extending direction when unmanned plane verts, even
Bar 100 is axially moved and then the mounting base 200 that its both ends is arranged in is driven to vert towards 100 extending direction of connecting rod, rotor assembly
It is fixed in mounting base 200, verts so as to be synchronized with mounting base 200.In this course, pass through a driving device
300 two rotor assemblies of control vert, save the cost, and are able to ascend the synchronism of two rotor assemblies.
It should be noted that " verting " described in the embodiment of the present disclosure refers to that mounting base 200 is initial perpendicular relative to it
Straight state carries out tilt rotation around the certain point being connected with fuselage.I.e. unmanned plane normal flight when, mounting base 200 is in vertical shape
State (i.e. the axis of blade 420), the blade 420 being disposed there above correspondingly are in horizontality, are hung down with being supplied to unmanned plane
Lift needed for straight landing, hovering etc..When unmanned plane needs vertical or horizontal in the horizontal plane of a certain height in the sky fly
When row, mounting base 200 drives blade 420 to vert, and is maintained at the lift of certain altitude and in level to be supplied to unmanned plane
The power of vertical or horizontal flight, avoids fuselage from tilting in face, reduces the flight resistance of unmanned plane.Wherein, machine is longitudinally referred to
The front-rear direction of body laterally refers to the left and right directions of fuselage.Therefore, arranged direction of the embodiment of the present disclosure to connecting rod 100
It is not specifically limited, such as connecting rod 100 can be arranged along the front-rear direction of fuselage, can also be arranged along the left and right directions of fuselage,
Can also with the angled setting in direction all around, to be respectively supplied to the direction of motion needed for unmanned plane according to actual needs
On power.For example, it is same that driving device 300 can control former and later two rotor assemblies when connecting rod 100 is arranged along the longitudinal direction
Step is verted before and after ground；When connecting rod 100 is arranged in left-right direction, it is same that driving device 300 can control the two rotor assemblies in left and right
It laterally verts on step ground.In the embodiments of the present disclosure, the arranged direction of connecting rod 100 is the extending direction namely connecting rod of connecting rod 100
100 axial direction.For other beneficial effects for further describing rotor inclining rotary mechanism, below only with connecting rod 100 along the left and right of fuselage
Direction is described in detail for laying.
Specifically, referring to Figures 1 and 2, driving device 300 may include driving portion 310 and driving section 320, driving portion 310
For providing the power output of the movement of connecting rod 100, driving section 320 is between driving portion 310 and connecting rod 100, by the power
Output is transferred to connecting rod 100.Driving section 320 may include linear motion part 321, the direction of motion for the part 321 that moves along a straight line and company
The extending direction of bar 100 is identical, and connecting rod 100 is fixed on linear motion part 321, thus by linear motion part 321 along connecting rod
The linear motion of 100 extending directions drives the synchronous axial movement of connecting rod 100.Wherein, connecting rod 100 can be designed as separate structure,
And it is connected to opposite side of the linear motion part 321 in the direction of motion, when the part 321 that moves along a straight line is moved towards side,
The separate structure of its two sides can be driven to move simultaneously, and then the blade 420 of two sides is made to vert in the same direction, realized through a driving
The two-way linear output for the linear motion part 321 that device 300 triggers, save the cost reduce the load of unmanned plane.Certainly, connecting rod
100 may be overall structure, and is fastenedly connected by fastener and linear motion part 321.
According to one embodiment, as shown in Fig. 2, linear motion part 321 can be rack gear, driving section 320 can also be wrapped
The gear 322 with rack gear cooperation is included, driving portion 310 includes steering engine 311, and the output shaft of steering engine 311 is fixedly connected with gear 322,
To convert straight line output by gear and rack teeth mechanism for the rotation of steering engine 311 output.In this way, when rotor assembly is respectively arranged
In the left and right sides of fuselage, connecting rod 100 can be integrally formed with rack gear, i.e., connecting rod 100 and rack gear can be formed as an entirety,
For example formed as a root long bar, rack gear is processed at the intermediate position of shaft, and both ends are polished rod, in order to manufacture, the company of fully ensuring that
The bonding strength of bar 100 and rack gear.Certainly, driving portion 310 is not limited in a kind of embodiment of steering engine 311, other can have
The power source for having rotation to export is applied equally to the disclosure.Linear motion part 321 is also not limited to the embodiment of rack gear,
Such as the component that drive link 100 is axially moved can also be the movement mechanisms such as feed screw nut, guide rail slide block, corresponding power source
Adaptation setting.
Further, referring to Fig. 2, gear 322 can have ring gear, the output shaft of steering engine 311 can be correspondingly formed for
Gear shaft, ring gear and gear shaft engaged transmission rotate coaxially the external tooth of gear 322 with ring gear in turn, external tooth drive rack
It is moved along 100 extending direction of connecting rod, the rotation output of steering engine 311 is steadily transferred to gear 322.In other embodiments
In, the output shaft of steering engine 311 may be common polished rod axis, be connected by key with the centre bore of gear 322 to be moved
Power transmitting.
In addition, as shown in Fig. 2, inclining rotary mechanism can also include the gear-box 323 for accommodating above-mentioned rack and pinion 322, with
Rack-and-pinion is formed and is protected, prevents impurity from entering and influencing transmission and service life.Steering engine can be set on gear-box 323
Seat 312, steering engine 311 is mounted on steering engine seat 312, to realize the fixation of steering engine 311.
According to the embodiment of the present disclosure, referring to Figure 1 and Figure 3, it is contemplated that unmanned plane itself load-carrying and each component are on fuselage
Arrange the factors such as orientation, connecting rod 100 can be specially to be horizontally through the elongate rod of fuselage, and two rotor assemblies at its both ends
Longitudinal central axis line about fuselage is symmetrically laid to avoid machine gravity offset, is equipped between fuselage and each rotor assembly certain
Distance to guarantee the flying power of unmanned plane, to avoid connecting rod 100 during unmanned plane during flying by the shock of exotic and
Damage, the outside of connecting rod 100 can be arranged with support arm 500, and one end of support arm 500 is fixed on fuselage, can referring for example to Fig. 2
To be fixedly connected with the said gear case 323 of fuselage interior.Specifically, support arm 500 can be designed as cannulated sleeve structure, end
Mounting hole is circumferentially offered on the outer wall in portion, the both ends of gear-box 323 may be designed in tubular construction, the tubular construction
Internal diameter allows connecting rod 100 to pass through and supports to be less than support arm with radial limit, outer diameter slightly larger than the diameter of connecting rod 100
500 internal diameter is fixedly connected by mounting hole with support arm 500 with can extend into support arm 500.In addition, in rotor assembly
The electric wire of motor 410, with connection circuit, the same of space utilization rate can also be improved from the internal stretch of support arm 500 to fuselage
When guarantee unmanned plane appearance terseness and aesthetics.As shown in figure 3, support base has can be set in the other end of support arm 500
600, support base 600 is fixedly connected with fuselage, and mounting base 200 is hinged with connecting rod 100 by the first tiliting axis 810, and passes through the
Two tiliting axis 820 and support base 600 are hinged.First tiliting axis 810 and the second tiliting axis 820 be parallel to each other and with connecting rod 100
Extending direction is vertical.When connecting rod 100 is axially moved, mounting base 200 can be driven to make to install by the first tiliting axis 810
The opposite support base 600 of seat 200 verts around the second tiliting axis 820.
Further, referring to Fig. 3, according to some embodiments, mounting base 200 may include top plate 210 and from 210 liang of top plate
The side plate 220 extended vertically downward is held, the motor 410 of rotor assembly is mounted on the top of top plate 210, the bottom shape of top plate 210
At there is two pieces of first otic placodes 230 being oppositely arranged, the first otic placode 230 is parallel to each other with side plate 220, and the end of connecting rod 100 is protruded into
It is between two piece of first otic placode 230 and hinged by the first tiliting axis 810 and the first otic placode 230.First tiliting axis 810 is radially worn
The end for crossing connecting rod 100,230 one side of the first otic placode being oppositely arranged are capable of the radial displacement of limiting rod 100, on the other hand
The space that connecting rod 100 can also be kept for be axially moved.When mounting base 200 is in plumbness, connecting rod 100 and the first otic placode
230 are mutually perpendicular to, and angle is 90 °；When mounting base 200 is verted, connecting rod 100 drops the first tiliting axis 810 axially movable, makes
One otic placode 230 is rotated around the first tiliting axis 810, and the angle between connecting rod 100 and the first otic placode 230 is more than or less than 90 °.
Further, as shown in figures 1 and 3, one end of support base 600 can be formed as connecting for fixing with support arm 500
The pipe clamp 610 connect, the outer diameter that the internal diameter of pipe clamp 610 is greater than support arm 500 are clamped with the outer wall to support arm 500.Pipe clamp 610
The other end has two pieces of second otic placodes 620 being oppositely arranged, the extending direction of the second otic placode 620 and the extending direction of connecting rod 100
Identical and be located between two blocks of side plates 220, two piece of second otic placode 620 passes through two the second tiliting axis 820 and two blocks of side plates respectively
220 is hinged.For convenient for manufacturing and assembling, referring to Fig. 4, support base 600 can be that first is seperated and second is seperated along axial design,
One of fission can be integrally formed with the second otic placode 620, and the first fission and the second fission may finally pass through fastener
It is fastenedly connected.In this way, can make side plate 220 relative to the second otic placode 620 around the second tiliting axis when the rotation of the first otic placode 230
820 rotate synchronously, and then realize verting for mounting base 200.Second otic placode 620 hingedly can also limiting rod 100 with side plate 220
When initial position is without axial displacement, the first otic placode 230 is freely rotated around the first tiliting axis 810.In this embodiment, side plate
220 are formed as the first connecting pin of above-mentioned mounting base 200, and the first otic placode 230 is formed as the second company of above-mentioned mounting base 200
Connect end.It should be noted that the flight attitude of unmanned plane is controlled by blade 420 completely in the embodiment of the present disclosure, by mounting base
200 can tilt angle control in a certain range, it can be ensured that the dynamic property and stability of unmanned plane so that unmanned plane has
Enough lift stops in the sky.Wherein, to avoid blade 420 towards collision support arm 500 when verting close to the direction of fuselage or
Support base 600, when being in initial vertical state as shown in Figure 3 based on mounting base 200, the height of top plate 210 can be appropriate
Higher than the outer wall highest point of the pipe clamp 610 of support base 600.When connecting rod 100 be specifically described below being moved along the left and right directions of fuselage
The direction of verting of mounting base 200.
311 drive rack of steering engine moves downward, and the connecting rod 100 on the left of rack gear moves downward, and the mounting base 200 in left side is therewith
It verts to the right, the connecting rod 100 on the right side of rack gear moves downward, and the mounting base 200 on right side is verted to the right therewith, realizes fuselage or so two
The blade 420 of side verts to the right simultaneously；311 drive rack of steering engine moves right, and the connecting rod 100 on the left of rack gear moves right, left
The mounting base 200 of side is verted to the left therewith, and the connecting rod 100 on the right side of rack gear moves right, and the mounting base 200 on right side inclines to the left therewith
Turn, realizes that the blade 420 at left and right sides of fuselage verts to the left simultaneously.
In addition, return spring 700 can be set at least one the second above-mentioned tiliting axis 820 referring to Fig. 3 and Fig. 4.
In this way, when steering engine 311 work normally when, realized by the work or locking of steering engine 311 mounting base 200 vert and angle
Positioning；When steering engine 311 fails, the restoring force of return spring 700 can be axially moved so that in verting with drive link 100
The mounting base 200 of state returns to initial vertical state, and inclining rotary mechanism is made to keep avoiding unmanned plane disequilibrium and generating from steady
It crashes, it is ensured that flight safety.
Specifically, when mounting base 200 needs to vert, simultaneously drive link 100 is axially moved to realize peace the rotation of steering engine 311
Dress seat 200 verts；When mounting base 200 is not verted or tilt angle is fixed, steering engine 311 is lockup state to mounting base 200
The state carry out locking, gear and rack teeth mechanism is maintained at some meshing state at this time, and the first otic placode 230 and side plate 220 are located
In nonrotating state.When steering engine 311 fails, the azimuth caging of mounting base 200 is released, the movement of gear and rack teeth mechanism not by
Steering engine 311 limits, and side plate 220 is under the active force of return spring 700 around the second tiliting axis 820 towards the initial of mounting base 200
Vertical state rotation, while the first otic placode 230 being driven to rotate around the first tiliting axis 810,810 drive link 100 of the first tiliting axis
It being axially moved, connecting rod 100 drives rack gear synchronous linear connected to it to move, and so that mounting base 200 is turned to vertical state,
So that the fuselage of unmanned plane is kept some skyborne height and position with certain lift level, avoids fuselage stress unbalance and fall
It ruins.
The embodiment of the present disclosure also provides a kind of unmanned plane, including fuselage and rotor inclining rotary mechanism, wherein rotor inclining rotary mechanism
For above-mentioned rotor inclining rotary mechanism.Unmanned plane has whole beneficial effects of above-mentioned rotor inclining rotary mechanism, and details are not described herein again.
Further, rotor inclining rotary mechanism can also be multiple to lay along the longitudinal gap of fuselage, such as can be along machine
The longitudinally disposed two rotor inclining rotary mechanisms of body improve the firm of unmanned aerial vehicle body structure to form common quadrotor drone
Property.
The preferred embodiment of the embodiment of the present disclosure is described in detail in conjunction with attached drawing above, still, the embodiment of the present disclosure is simultaneously
The detail being not limited in above embodiment can be to disclosure reality in the range of the technology design of the embodiment of the present disclosure
The technical solution for applying example carries out a variety of simple variants, these simple variants belong to the protection scope of the embodiment of the present disclosure.
It is further to note that specific technical features described in the above specific embodiments, in not lance
In the case where shield, it can be combined in any appropriate way, in order to avoid unnecessary repetition, the embodiment of the present disclosure pair
No further explanation will be given for various combinations of possible ways.
In addition, any combination can also be carried out between a variety of different embodiments of the embodiment of the present disclosure, as long as it is not
The thought of the embodiment of the present disclosure is violated, equally should be considered as embodiment of the present disclosure disclosure of that.
Claims (10)
1. a kind of rotor inclining rotary mechanism characterized by comprising
Connecting rod (100)；
Mounting base (200) can be connected to described in which vert for installing rotor assembly along the extending direction of the connecting rod (100)
The both ends of connecting rod (100)；And
Driving device (300), for driving the connecting rod (100) to move along the extending direction of the connecting rod (100), to drive
The extending direction that rotor assembly is stated along the connecting rod (100) verts.
2. rotor inclining rotary mechanism according to claim 1, which is characterized in that the driving device (300) includes driving portion
(310) and driving section (320), the driving section (320) include linear motion part (321), the fortune of linear motion part (321)
Dynamic direction is identical as the extending direction of the connecting rod (100), and the connecting rod (100) is fixed on the linear motion part (321).
3. rotor inclining rotary mechanism according to claim 2, which is characterized in that the linear motion part (321) is rack gear, institute
Stating driving section (320) further includes the gear (322) with rack gear cooperation, and the driving portion (310) includes steering engine (311), institute
The output shaft for stating steering engine (311) is fixedly connected with the gear (322).
4. rotor inclining rotary mechanism according to claim 3, which is characterized in that the gear (322) has ring gear, described
The output shaft of steering engine (311) is formed as gear shaft, the ring gear and gear shaft engaged transmission.
5. rotor inclining rotary mechanism according to claim 3, which is characterized in that the inclining rotary mechanism further includes accommodating the tooth
The gear-box (323) of item and the gear (322) is provided with steering engine seat (312), the steering engine on the gear-box (323)
(311) it is mounted on the steering engine seat (312).
6. rotor inclining rotary mechanism according to claim 1, which is characterized in that the outer cover of the connecting rod (100) is equipped with branch
One end of arm (500), the support arm (500) is fixed on fuselage, and the other end is provided with support base (600), the mounting base
(200) hingedly by the first tiliting axis (810) and the connecting rod (100), and pass through the second tiliting axis (820) and the support base
(600) hinged.
7. rotor inclining rotary mechanism according to claim 6, which is characterized in that the mounting base (200) includes top plate (210)
With the side plate (220) extended vertically downward from the top plate (210) both ends, the rotor assembly is mounted on the top plate (210)
Top, the bottom of the top plate (210) is formed with two pieces of first otic placodes (230) being oppositely arranged, the end of the connecting rod (100)
Portion protrudes between two pieces of first otic placodes (230) and is cut with scissors by first tiliting axis (810) and first otic placode (230)
It connects.
8. rotor inclining rotary mechanism according to claim 7, which is characterized in that one end of the support base (600) is formed as
Pipe clamp (610) for being fixedly connected with the support arm (500), the other end have two pieces of second otic placodes (620) being oppositely arranged,
The extending direction of second otic placode (620) is identical as the extending direction of the connecting rod (100), and second otic placode (620) is logical
It crosses second tiliting axis (820) and the side plate (220) is hinged.
9. rotor inclining rotary mechanism according to claim 8, which is characterized in that at least one described second tiliting axis (820)
On be provided with return spring (700).
10. a kind of unmanned plane, including fuselage and rotor inclining rotary mechanism, which is characterized in that the rotor inclining rotary mechanism is according to power
Benefit requires rotor inclining rotary mechanism described in any one of 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811427354.9A CN109436310A (en) | 2018-11-27 | 2018-11-27 | Rotor inclining rotary mechanism and unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811427354.9A CN109436310A (en) | 2018-11-27 | 2018-11-27 | Rotor inclining rotary mechanism and unmanned plane |
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| CN201811427354.9A Pending CN109436310A (en) | 2018-11-27 | 2018-11-27 | Rotor inclining rotary mechanism and unmanned plane |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111959765A (en) * | 2020-08-03 | 2020-11-20 | 南京航空航天大学 | Tilt rotor wing mechanism based on ultrasonic motor |
| CN112340010A (en) * | 2020-09-11 | 2021-02-09 | 广州极飞科技有限公司 | Unmanned plane |
| CN112340035A (en) * | 2020-09-11 | 2021-02-09 | 广州极飞科技有限公司 | Unmanned aerial vehicle's power unit and unmanned aerial vehicle |
| CN112478170A (en) * | 2020-12-15 | 2021-03-12 | 广州极飞科技有限公司 | Aircraft with a flight control device |
| CN113428360A (en) * | 2021-08-13 | 2021-09-24 | 复旦大学 | Water-air amphibious multi-rotor unmanned aerial vehicle |
| CN114476047A (en) * | 2021-12-03 | 2022-05-13 | 南昌三瑞智能科技有限公司 | Mechanism that verts of rotor unmanned aerial vehicle motor verts |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111959765A (en) * | 2020-08-03 | 2020-11-20 | 南京航空航天大学 | Tilt rotor wing mechanism based on ultrasonic motor |
| CN111959765B (en) * | 2020-08-03 | 2022-06-17 | 南京航空航天大学 | Tilt rotor wing mechanism based on ultrasonic motor |
| CN112340010A (en) * | 2020-09-11 | 2021-02-09 | 广州极飞科技有限公司 | Unmanned plane |
| CN112340035A (en) * | 2020-09-11 | 2021-02-09 | 广州极飞科技有限公司 | Unmanned aerial vehicle's power unit and unmanned aerial vehicle |
| CN112478170A (en) * | 2020-12-15 | 2021-03-12 | 广州极飞科技有限公司 | Aircraft with a flight control device |
| CN113428360A (en) * | 2021-08-13 | 2021-09-24 | 复旦大学 | Water-air amphibious multi-rotor unmanned aerial vehicle |
| CN114476047A (en) * | 2021-12-03 | 2022-05-13 | 南昌三瑞智能科技有限公司 | Mechanism that verts of rotor unmanned aerial vehicle motor verts |
| CN114476047B (en) * | 2021-12-03 | 2024-02-13 | 南昌三瑞智能科技有限公司 | Tilting mechanism of tilting rotor unmanned aerial vehicle motor |
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