CN113460298A - Motor tilting mechanism and tilting rotor aerocar - Google Patents
Motor tilting mechanism and tilting rotor aerocar Download PDFInfo
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- CN113460298A CN113460298A CN202110825393.XA CN202110825393A CN113460298A CN 113460298 A CN113460298 A CN 113460298A CN 202110825393 A CN202110825393 A CN 202110825393A CN 113460298 A CN113460298 A CN 113460298A
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- Aviation & Aerospace Engineering (AREA)
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- Chemical & Material Sciences (AREA)
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- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The embodiment of the application provides a motor tilting mechanism and a tilting rotor aerocar, and relates to the technical field of aerocars. The motor tilting mechanism comprises a wing assembly, a tilting driving assembly and a power assembly. The wing subassembly includes that frame and rotor tilt the axle, and the drive assembly that verts includes actuator and link mechanism, and the actuator is connected in the frame, and link mechanism's output fixed connection is in the rotor shaft that verts to make the actuator drive the rotor through link mechanism and vert the axle around self axis at default angle internal rotation. The rotor verts the output and the power component fixed connection of axle, and drives power component and rotate under the effect of driving assembly that verts to make the motor mechanism of verting can change between rotor mode and stationary vane mode. This mechanism that verts of motor simple structure can accurate control the angle of verting through the drive assembly that verts, and only at rotor mode and stationary vane mode conversion in-process circular telegram action, is favorable to energy-conservation and promotes the flight performance of verting rotor hovercar.
Description
Technical Field
The application belongs to the technical field of aerocars, and more specifically relates to a motor tilting mechanism and a tilting rotor aerocar.
Background
The rotor hovercar verts is a novel hovercar which integrates fixed wing hovercars and helicopters.
The rotor shaft of the aerocar can be switched between a vertical state and a horizontal state, and the aerocar is in a flight mode of a transverse helicopter when the rotor shaft is in a state vertical to the ground. When the rotor wing is inclined forwards in the axial direction and rotates by 90 degrees to be in a horizontal state, the rotor wing can be used as a tension propeller, and the aerocar is in a flight mode of a fixed wing.
Because present rotor hovercar verts and adopts gear steering wheel drive more for the steering wheel all is in the state of atress circular telegram at whole flight in-process, is unfavorable for energy-conservation, and influences flight performance.
Disclosure of Invention
Objects of the present application include, for example, providing a motor tilt mechanism and tilt rotor flying vehicle that ameliorates at least some of the problems described above.
The embodiment of the application can be realized as follows:
in a first aspect, a motor tilting mechanism is provided and includes a wing assembly, a tilting drive assembly and a power assembly. The wing assembly includes a frame and a rotor tilt shaft rotatably coupled to the frame. The tilting drive assembly comprises an actuator and a connecting rod mechanism which are connected in a transmission mode, the actuator is connected to the rack, and the output end of the connecting rod mechanism is fixedly connected to a tilting shaft of the rotor wing, so that the actuator drives the tilting shaft of the rotor wing to rotate around the axis of the actuator at a preset angle through the connecting rod mechanism. The rotor verts the output and the power component fixed connection of axle, and drives power component and rotate under the effect of driving assembly that verts to make the motor mechanism of verting can change between rotor mode and stationary vane mode.
Further, link mechanism includes first rotation piece, connecting rod and second rotation piece, and first rotation piece includes first connecting portion and second connecting portion, and the second rotation piece includes third connecting portion and fourth connecting portion, and first connecting portion are connected with the output of actuator, and the second connecting portion are articulated with the first end of connecting rod, and the third connecting portion with the rotor axle of verting, the fourth connecting portion hold with the second of connecting rod and articulate.
Furthermore, the output shaft of the actuator is located to first connecting portion cover, and the rotor axle that verts is located to the third connecting portion cover, all through articulated shaft rotatable coupling between second connecting portion and the connecting rod, between fourth connecting portion and the connecting rod. The distance between the second connecting part and the first connecting part is equal to the distance between the fourth connecting part and the third connecting part, so that the rotating angle of the first rotating part is the same as that of the second rotating part.
Further, the tilting drive assembly further comprises a fixing seat and a bearing seat, the actuator is fixedly connected to the frame through the fixing seat, the first rotating part is rotatably connected to the bearing seat, and the bearing seat is fixedly connected to the frame.
Further, the tilting drive assembly further comprises a coupler, the actuator comprises an output shaft, the first rotating part comprises a rotating shaft, and the output shaft is in transmission connection with the rotating shaft through the coupler.
Furthermore, a limiting structure is arranged between the second connecting part of the first rotating part and the first end of the connecting rod; or a limiting structure is arranged between the fourth connecting part of the second rotating part and the second end of the connecting rod, and the limiting structure is used for limiting the rotating angle of the first rotating part to be a preset angle.
Furthermore, the actuator comprises a worm and gear speed reduction steering engine, and an output shaft of the worm and gear speed reduction steering engine is parallel to a rotor tilting shaft.
Further, the output that the rotor verts the axle still is provided with the flange, and power component includes the installation department, and the rotor verts the axle and passes through flange and installation department fixed connection, and makes the rotor vert the central axis of axle and power component's the central axis and be located the coplanar.
Furthermore, the wing assembly further comprises a covering coated on the rack, the covering encloses a containing cavity, and the tilting drive assembly and the rotor tilting shaft are embedded in the containing cavity.
In a second aspect, a tilt rotor flying vehicle is provided, comprising a motor tilt mechanism.
The motor mechanism that verts that this application embodiment provided drives link mechanism through the actuator to make link mechanism drive the rotor of wing subassembly and vert the axle and at predetermineeing the angle internal rotation. The rotor verts the output and power component fixed connection of axle, and drives power component's rotor axle when the pivoted and rotates in vertical face.
This motor tilting mechanism can change between rotor mode and fixed wing mode through tilting drive assembly's action. And the power is applied when the rotor wing mode and the fixed wing mode are switched, so that the energy and the electricity of the system are saved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained from the drawings without inventive effort.
Fig. 1 is a schematic structural diagram illustrating a rotor shaft in a motor tilting mechanism according to an embodiment of the present disclosure in a vertical state;
fig. 2 is a schematic structural diagram of a rotor shaft in a motor tilting mechanism according to an embodiment of the present disclosure in a horizontal state;
fig. 3 is a schematic structural diagram of a wing assembly and a tilt driving assembly of a motor tilt mechanism according to an embodiment of the present disclosure;
fig. 4 is a schematic structural diagram of a link mechanism in a motor tilting mechanism provided in an embodiment of the present application in different states.
Icon: 100-a motor tilting mechanism; 110-a wing assembly; 112-a rack; 1120-a rib plate; 1122-main beam; 114-bearing holders; 116-rotor tilt axis; 118-a flange; 120-a tilt drive assembly; 1202-fixed seat; 1204-bearing seat; 121-an actuator; 122-a coupling; 124-linkage mechanism; 1242-first rotating member; 1244-connecting rod; 1246-second turning piece; 130-a power assembly; 131-rotor shaft.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations.
It should be noted that the features of the embodiments of the present application may be combined with each other without conflict.
The flying automobile can fly in the air and can run on the land, and can be changed into an airplane from a road automobile. The tilt rotor aerocar is a novel aerocar which can fuse the aerocar of fixed wings and the aerocar of helicopters.
The rotor aerocar that verts is through the two wing point departments at similar fixed wing, respectively installs one set of rotor subassembly that verts, and this rotor subassembly that verts can drive the rotor axle and convert between horizontal position and vertical position.
When this rotor hovercar verts and lands perpendicularly, through the rotor subassembly drive rotor shaft that verts be in the state perpendicular to ground to this rotor hovercar that verts can present the flight state of tandem helicopter. And the tilt rotor aerocar in the state can hover in the air, fly forwards and backwards and fly sideways.
After this rotor hovercar verts just reaching certain steady speed after taking off, vert the subassembly through the rotor and drive the rotor shaft and convert the horizontality into, be about to the rotor shaft 90 that verts forward. This rotor that verts rotor hovercar's rotor can regard as the pulling force screw this moment to make the rotor that verts hovercar can regard as the hovercar of fixed wing class, carry out long-range flight with higher speed.
The rotor subassembly that verts at present adopts the gear steering wheel as the motor to vert the drive mostly, and the gear steering wheel is in atress, the state of circular telegram all the time at hovercar's flight in-process, and it is great to have led to the power consumption of system, and the weight of flight system is great, is unfavorable for the product energy-conservation. In addition, the tilting process of the motor not only needs larger torque, but also does not have a self-locking function so that the safety and reliability of the motor during tilting are reduced. The rotor subassembly of verting of current includes the rotation axis, because the rotation axis is installed in the bottom of motor, the partial mass that verts of rotation axis is great for hovercar's gyroscopic effect is great, and the security is not enough.
Based on the above problem, the embodiment of the present application provides a motor tilting mechanism 100.
Referring to fig. 1, the motor tilting mechanism 100 is installed at the wing tip of the wing and may include a wing assembly 110, a tilting drive assembly 120 and a power assembly 130.
Wherein, wing subassembly 110 can install the motor rotor as the installing support, still can provide lift for verting rotor hovercar when the fixed wing mode flight. Tilt drive assembly 120 installs in wing assembly 110's inside, can incline the axle 116 through wing assembly 110 and drive power assembly 130 and rotate in the vertical plane to make this rotor shaft 131 of rotor hovercar that verts change between horizontal state and vertical state, and then change this rotor hovercar's flight state that verts. Power assembly 130 is used for driving the rotor blade to rotate to make the tilt rotor hovercar that installs this motor tilt mechanism 100 can produce lift when rotor mode state, can produce thrust when fixed wing mode state.
Specifically, as shown in fig. 1, wing assembly 110 may include a frame 112 and a rotor tilt shaft 116, rotor tilt shaft 116 being rotatably coupled to frame 112.
Referring to fig. 1 and 2 together, fig. 1 is a schematic structural view illustrating a rotor shaft 131 of the power assembly 130 in a vertical state, and fig. 2 is a schematic structural view illustrating the rotor shaft 131 of the power assembly 130 in a horizontal state.
The rotor shaft 131 is rotated within a predetermined angle, thereby realizing switching between the two modes.
Wherein, predetermine the angle and can be 90, through rotor tilting shaft 116 drive power assembly 130's rotor axle 131 rotate 90, can adjust rotor axle 131 and be in horizontality and vertical state, also can change between horizontality and vertical state.
Referring to fig. 3, the frame 112 may include rib plates 1120 and a main beam 1122, the frame 112 is used as a wing bearing structure, the number of the rib plates 1120 includes at least two, at least two rib plates 1120 are arranged at intervals, the main beam 1122 is fixedly connected between two rib plates 1120, and an included angle is formed between the main beam 1122 and the rib plates 1120.
Alternatively, the included angle may be substantially a right angle, meaning that the main beam 1122 may be perpendicular or substantially perpendicular to the rib plate 1120. Rib 1120 may be configured to support rotor tilt shaft 116 such that rotor tilt shaft 116 is rotatably coupled to rib 1120, and spar 1122 may be configured to secure mounting block 1202 of tilt drive assembly 120 to provide structural support for tilt drive assembly 120.
To reduce friction as rotor tilt shaft 116 is rotated relative to airframe 112 by tilt drive assembly 120. Further, the wing assembly 110 may further include a bearing mount 114.
The mounting groove has been seted up to two at least corresponding positions of floor 1120 that the interval set up, and bearing fixing base 114 fixed connection installs the bearing in the mounting groove in the bearing fixing base 114 to make rotor tilt axle 116 pass through bearing and bearing fixing base 114 rotatable coupling, thereby can install rotor tilt axle 116 on floor 1120. When installed, the rotor tilt shaft 116 is axially fixed in position with only rotational freedom to rotate about its central axis.
Optionally, in this embodiment, the number of the ribs 1120 is two, the two ribs 1120 are arranged in parallel, and the rotor tilting shaft 116 is disposed through the ribs 1120 and is rotatably connected. Wherein the central axis of rotor tilt shaft 116 is perpendicular to rib 1120.
To facilitate the secure connection of the output end of rotor tilt shaft 116 to power assembly 130, wing assembly 110 may optionally further include a flange 118.
Further, the wing assembly 110 may further include a skin that covers the outer periphery of the frame 112 and may enclose the receiving cavity. The tilting drive assembly 120 and the rotor tilting shaft 116 are embedded in the accommodating cavity, so that the motor tilting mechanism 100 does not affect the aerodynamic layout of the whole wing.
With continued reference to fig. 3, in particular, the tilting drive assembly 120 includes an actuator 121 and a linkage 124 that are connected in a transmission manner, and the actuator 121 can drive the linkage 124 to move as a power source.
The actuator 121 is fixedly connected to the main beam 1122 of the wing assembly 110, and the connecting rod mechanism 124 can drive the rotor tilting shaft 116 to rotate, so as to drive the rotor shaft 131 of the power assembly 130 to rotate relative to the fixed wing, thereby changing the flight state of the hovercar.
In order to realize the self-locking function of the tilting drive assembly 120, the control precision can be improved. Alternatively, actuator 121 may include a worm gear reduction steering engine, and the output shaft of the worm gear reduction steering engine may be parallel to rotor tilt shaft 116. The worm and gear speed reduction steering engine has the advantages of small volume, accurate control and large torsion, and can realize self-locking.
In alternative embodiments, other types of actuators can be used for the actuator 121, such as: reciprocating plunger type steering engines, rotating vane type steering engines and the like. The embodiment of the present application does not limit the specific type of the actuator 121, as long as the actuator can provide the same rotation mode as the output shaft of the worm and gear reduction steering engine.
The link mechanism 124 may include a first rotating member 1242, a link 1244 and a second rotating member 1246. The first rotating member 1242 and the second rotating member 1246 are rotatably connected to two ends of the connecting rod 1244 respectively, the first rotating member 1242 is connected to an output end of the actuator 121, and the second rotating member 1246 is connected to the rotor tilting shaft 116, so that the actuator 121 drives the rotor tilting shaft 116 to rotate through the connecting rod mechanism 124. The first rotating member 1242 is driven by the actuator 121 to rotate, and then transmits the torque to the second rotating member 1246 through the connecting rod 1244, so as to drive the rotor tilting shaft 116 and the power assembly 130 to rotate.
Referring to fig. 4a, 4b and 4c, in the process of rotating the first rotating member 1242, an included angle between a connecting line between the hinge point of the second end of the connecting rod 1244 and the center point of the second rotating member 1246 and the horizontal plane, that is, the angle is changed from a1 to a2, and then to A3, so as to achieve the purpose of controlling the tilting angle of the rotor shaft 131 of the power assembly 130.
Specifically, the first rotating member 1242 may include a first connecting portion and a second connecting portion, the second rotating member 1246 may include a third connecting portion and a fourth connecting portion, and the connecting rod 1244 includes opposite first and second ends. The output end of the actuator 121 is connected to the first connecting portion of the first rotating member 1242, the second connecting portion is hinged to the first end of the connecting rod 1244, the second end of the connecting rod 1244 is hinged to the fourth connecting portion of the second rotating member 1246, and the third connecting portion is connected to the rotor tilting shaft 116.
In order to allow the angle of rotation of actuator 121 to be equal to the angle of rotation of rotor tilt shaft 116 to facilitate accurate control of the angle of rotation of rotor shaft 131 of power assembly 130. Optionally, the rotation deviation axis of the first rotating member 1242 is parallel to the rotation deviation axis of the second rotating member 1246, so that the actuator 121 does not need to output a complicated control angle conversion formula during control, which is beneficial to reducing calculation errors.
Alternatively, the first connecting portion is connected to the output shaft of the actuator 121, and fixedly connects the first rotating member 1242 with the output shaft of the actuator 121. The mounting hole has been seted up to the third connecting portion, and the rotor axle 116 that verts is located to the third connecting portion cover, and makes the second rotate 1246 and rotor axle 116 fixed connection that verts. And the second connecting part and the connecting rod 1244 and the fourth connecting part and the connecting rod 1244 are rotatably connected through a hinge shaft. When the output shaft of the rotator 121 drives the first rotating member 1242 to rotate, the first rotating member 1242 drives the second rotating member 1246 to rotate synchronously through the connecting rod 1244, and the second rotating member 1246 drives the rotor tilting shaft 116 to rotate synchronously.
In the embodiment of the present application, the distance between the center of the second connecting portion and the center of the first connecting portion in the link mechanism 124 is equal to the distance between the center of the fourth connecting portion and the center of the third connecting portion. In other words, the link mechanism 124 is a double-rocker mechanism, and the first rotating member 1242 is parallel to the second rotating member 1246 during the movement process, so that the rotation angle of the first rotating member 1242 is the same as the rotation angle of the second rotating member 1246, and the rotation angle of the output shaft of the actuator 121 is equal to the rotation angle of the rotor tilting shaft 116.
For example, in order to allow the rotor shaft 131 of the power assembly 130 to rotate 90 ° in the vertical plane, the rotor tilt shaft 116 is rotated 90 ° by controlling the output shaft of the actuator 121 to rotate 90 °, thereby achieving the transition between the horizontal state and the vertical state.
Optionally, a limiting structure (not shown) may be further disposed in the link mechanism 124, and after the link mechanism 124 rotates in place, the link mechanism 124 is limited by the limiting structure to continue rotating, so that the rotating angle of the first rotating member 1242 is just the preset angle.
The limiting structure may be disposed between the second connecting portion of the first rotating member 1242 and the first end of the connecting rod 1244, or the limiting structure may be disposed between the fourth connecting portion of the second rotating member 1246 and the second end of the connecting rod 1244. Wherein, limit structure can set up to protruding class structure.
For example, a protrusion may be provided at a suitable location on the contact surface of the second connector portion near the first end of the link 1244. When the actuator 121 drives the first rotating member 1242 to rotate by a predetermined angle, the protrusion abuts against the first end of the connecting rod 1244 to prevent the first rotating member 1242 from driving the connecting rod 1244 to rotate continuously. The protrusions can be used as physical limiting structures and are used for being matched with a worm and gear speed reduction steering engine to achieve accurate control of the rotation angle.
To facilitate the connection between the actuator 121 and the linkage 124. With continued reference to fig. 3, tilt drive assembly 120 may optionally further include a coupling 122. The actuator 121 comprises an output shaft and the first rotating member 1242 comprises an input shaft, and the output shaft of the actuator 121 and the input shaft of the first rotating member 1242 are fixedly connected through a coupling 122. Because the coupling 122 is a rigid coupling 122, the use of the coupling 122 can reduce the vibration of the power assembly 130 during operation.
In addition, tilt drive assembly 120 is connected for convenience. Optionally, tilt drive assembly 120 may further include a fixed mount 1202 and a bearing housing 1204.
The fixing base 1202 may be fixedly connected to the main beam 1122, and the actuator 121 is connected to the fixing base 1202, so as to be fixedly connected to the frame 112 through the fixing base 1202, so as to ensure that the actuator 121 can stably operate.
The number of the bearing seats 1204 can be two, and both the two bearing seats 1204 can be fixedly connected to the main beam 1122 and are respectively located at two sides of the first rotating member 1242. The input shaft of the first rotating member 1242 is rotatably connected to the bearing seat 1204 through a bearing, and further can rotate around the bearing center of the bearing seat 1204, so as to be rotatably connected to the frame 112 through the bearing seats 1204 at both sides.
Alternatively, the number of tilt drive assemblies 120 may be at least one. When there is one tilt drive assembly 120, the motor tilt mechanism 100 is a single drive. In other alternative embodiments, the number of tilting drive assemblies 120 may be two or more, and when the number of tilting drive assemblies 120 is multiple, the motor tilting mechanism 100 is in a multi-drive mode. The present application is not limited to a specific number of tilt drive assemblies 120, as may be desired.
With continued reference to fig. 1, the power assembly 130 may include a motor, a rotor, and a hub. The outer peripheral wall of power assembly 130 is provided with the installation department, and the installation department is located the coplanar with the central axis of rotor shaft 131. During installation, rotor tilt shaft 116 is fixedly coupled to the mounting portion of power assembly 130 via flange 118. And after the fixed connection, the central axis of the rotor tilt shaft 116 and the central axis of the power assembly 130 are located on the same plane, so that the flange 118 is located on the center axis of the power assembly 130. The driving torque of the tilting driving assembly 120 is reduced, the whole weight of the driving assembly is reduced, the gyro effect can be reduced, the safety is enhanced, and the system reliability is improved.
It will be appreciated that in the motor tilt mechanism 100, the specific location at which the actuator 121 is mounted on the spar 1122 via the mounting block 1202 is not limited, and the actuator 121 may be fixed to the frame 112 of the wing assembly 110 via other structural fasteners. In alternative embodiments, the installation position and the installation manner of the actuator 121 are not limited, and the actuator may also be installed on other parts of the frame 112, such as the rib 1120, etc., through the fixing seat 1202. This application is to actuator 121's mounted position and mounting means, as long as satisfy and realize that actuator 121 provides drive power for link mechanism 124, and actuator 121's turned angle and rotor tilt shaft 116's turned angle the same can.
The motor tilting mechanism 100 provided by the embodiment of the application has the advantages of simple structure and reasonable design, and not only can realize a self-locking function through the worm and gear reduction steering engine, but also can accurately control the tilting angle. The rotor shaft 131 of the power assembly 130 can be switched between a rotor mode and a fixed-wing mode, so that the rotor of the power assembly 130 can be tilted from a vertical state during takeoff to a horizontal state during high-speed flight, and the purpose of changing the flight state of the hovercar is achieved.
And the motor tilting mechanism 100 has light weight and compact structure. By being arranged in the wing skin, the aerodynamic layout of the whole wing cannot be influenced. Adopt link mechanism 124 to transmit for the rotation angle that power assembly 130's rotor shaft 131 verts the angle is unanimous with actuator 121's turned angle, is favorable to accurate control angle of verting. The installation part of the rotor wing tilting shaft 116 and the power assembly 130 is fixed, so that the gyro effect is reduced, and the safety and the reliability of the product are improved. So that the hovercar applying the motor tilting mechanism 100 has the advantages of stable overall operation, strong safety and strong practicability. The motor tilting mechanism 100 can also be applied to wing spar structures of other wing types, and is beneficial to expanding the application field.
The embodiment of the application also provides a tilt rotor aerocar, and the tilt rotor aerocar can comprise the motor tilt mechanism 100.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, and not to limit the same; although the present application has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not necessarily depart from the spirit and scope of the corresponding technical solutions in the embodiments of the present application.
Claims (10)
1. A motor tilting mechanism, comprising:
a wing assembly including a airframe and a rotor tilt shaft rotatably coupled to the airframe;
the tilting driving assembly comprises an actuator and a connecting rod mechanism which are in transmission connection, the actuator is connected to the rack, and the output end of the connecting rod mechanism is fixedly connected to the rotor tilting shaft, so that the actuator drives the rotor tilting shaft to rotate around the axis of the rotor tilting shaft within a preset angle through the connecting rod mechanism; and
power assembly, the rotor verts the output of axle with power assembly fixed connection, and is in drive assembly's the effect that verts drives down power assembly rotates, so that the motor mechanism of verting can change between rotor mode and stationary vane mode.
2. The motor tilt mechanism of claim 1, wherein the linkage mechanism includes a first rotating member, a connecting rod, and a second rotating member, the first rotating member including a first connecting portion and a second connecting portion, the second rotating member including a third connecting portion and a fourth connecting portion, the first connecting portion being connected to the output of the actuator, the second connecting portion being hinged to the first end of the connecting rod, the third connecting portion being connected to the rotor tilt shaft, and the fourth connecting portion being hinged to the second end of the connecting rod.
3. The motor tilt mechanism of claim 2, wherein the first connection is disposed about the output shaft of the actuator, the third connection is disposed about the rotor tilt shaft, and the second connection and the link, and the fourth connection and the link are rotatably coupled via hinge shafts;
the distance between the second connecting portion and the first connecting portion is equal to the distance between the fourth connecting portion and the third connecting portion, so that the rotating angle of the first rotating member is the same as the rotating angle of the second rotating member.
4. The motor tilt mechanism of claim 2, wherein the tilt drive assembly further comprises a fixed mount and a bearing mount, the actuator being fixedly coupled to the housing via the fixed mount, the first rotatable member being rotatably coupled to the bearing mount, the bearing mount being fixedly coupled to the housing.
5. The motor tilt mechanism of claim 2, wherein the tilt drive assembly further comprises a coupling, the actuator comprises an output shaft, and the first rotatable member comprises a shaft, the output shaft being drivingly connected to the shaft via the coupling.
6. The motor tilting mechanism according to claim 2, wherein a limit structure is provided between the second connecting portion of the first rotating member and the first end of the connecting rod; or
A limiting structure is arranged between the fourth connecting part of the second rotating part and the second end of the connecting rod, and the limiting structure is used for limiting the rotating angle of the first rotating part to be the preset angle.
7. The motor tilting mechanism according to claim 1, wherein the actuator comprises a worm and gear reduction steering engine, and an output shaft of the worm and gear reduction steering engine is parallel to the tilting shaft of the rotor.
8. The motor tilting mechanism according to claim 1, wherein the output of the rotor tilting shaft is further provided with a flange, the power assembly comprises an installation part, the rotor tilting shaft passes through the flange and the installation part is fixedly connected, and the rotor tilting shaft is provided with a central axis which is located on the same plane as the central axis of the power assembly.
9. The motor tilt mechanism of any of claims 1-8, wherein the wing assembly further includes a skin that is wrapped around the frame, the skin enclosing a cavity in which the tilt drive assembly and the rotor tilt shaft are nested.
10. A tiltrotor flying vehicle comprising the motor tilting mechanism of any one of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202110825393.XA CN113460298A (en) | 2021-07-21 | 2021-07-21 | Motor tilting mechanism and tilting rotor aerocar |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110825393.XA CN113460298A (en) | 2021-07-21 | 2021-07-21 | Motor tilting mechanism and tilting rotor aerocar |
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| CN113460298A true CN113460298A (en) | 2021-10-01 |
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| CN202110825393.XA Pending CN113460298A (en) | 2021-07-21 | 2021-07-21 | Motor tilting mechanism and tilting rotor aerocar |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113955097A (en) * | 2021-11-01 | 2022-01-21 | 广东汇天航空航天科技有限公司 | Steering engine displacement processing method and device of rotor craft |
| CN114347738A (en) * | 2022-01-12 | 2022-04-15 | 广东汇天航空航天科技有限公司 | Arm mechanism and flight device |
| CN116853491A (en) * | 2023-09-01 | 2023-10-10 | 成都沃飞天驭科技有限公司 | Tilting device, design method thereof and aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030201362A1 (en) * | 2002-04-25 | 2003-10-30 | Fushun Yang | Helicarplane |
| CN209241317U (en) * | 2018-11-30 | 2019-08-13 | 深圳飞马机器人科技有限公司 | A kind of inclining rotary mechanism and fixed-wing unmanned plane |
| CN110154658A (en) * | 2019-05-29 | 2019-08-23 | 吉林大学 | Across the medium variant unmanned vehicles of assembled bionic based on kingfisher and predacious diving beetle shape |
| CN110654190A (en) * | 2019-10-31 | 2020-01-07 | 南京航空航天大学 | Tilting shaftless ducted rotor aerocar and working method thereof |
| CN111169631A (en) * | 2020-02-21 | 2020-05-19 | 山东蜂巢航空科技有限公司 | Rotor unmanned aerial vehicle verts |
-
2021
- 2021-07-21 CN CN202110825393.XA patent/CN113460298A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030201362A1 (en) * | 2002-04-25 | 2003-10-30 | Fushun Yang | Helicarplane |
| CN209241317U (en) * | 2018-11-30 | 2019-08-13 | 深圳飞马机器人科技有限公司 | A kind of inclining rotary mechanism and fixed-wing unmanned plane |
| CN110154658A (en) * | 2019-05-29 | 2019-08-23 | 吉林大学 | Across the medium variant unmanned vehicles of assembled bionic based on kingfisher and predacious diving beetle shape |
| CN110654190A (en) * | 2019-10-31 | 2020-01-07 | 南京航空航天大学 | Tilting shaftless ducted rotor aerocar and working method thereof |
| CN111169631A (en) * | 2020-02-21 | 2020-05-19 | 山东蜂巢航空科技有限公司 | Rotor unmanned aerial vehicle verts |
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|---|---|---|---|---|
| CN113955097A (en) * | 2021-11-01 | 2022-01-21 | 广东汇天航空航天科技有限公司 | Steering engine displacement processing method and device of rotor craft |
| CN113955097B (en) * | 2021-11-01 | 2023-03-24 | 广东汇天航空航天科技有限公司 | Steering engine displacement processing method and device of rotor craft |
| CN114347738A (en) * | 2022-01-12 | 2022-04-15 | 广东汇天航空航天科技有限公司 | Arm mechanism and flight device |
| CN114347738B (en) * | 2022-01-12 | 2023-06-02 | 广东汇天航空航天科技有限公司 | Arm mechanism and flight device |
| CN116853491A (en) * | 2023-09-01 | 2023-10-10 | 成都沃飞天驭科技有限公司 | Tilting device, design method thereof and aircraft |
| CN116853491B (en) * | 2023-09-01 | 2023-11-07 | 成都沃飞天驭科技有限公司 | Tilting device, design method thereof and aircraft |
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