CN214649017U - Power system and aircraft - Google Patents
Power system and aircraft Download PDFInfo
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- CN214649017U CN214649017U CN202022620974.3U CN202022620974U CN214649017U CN 214649017 U CN214649017 U CN 214649017U CN 202022620974 U CN202022620974 U CN 202022620974U CN 214649017 U CN214649017 U CN 214649017U
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Abstract
The application discloses driving system and aircraft, driving system includes: a propeller assembly; the power assembly comprises a magnetic piece and a hollow magnetic generation device; the magnetic piece is fixedly connected with the propeller assembly, at least part of the magnetic piece is positioned in the magnetic generation device, and a gap is formed between the magnetic piece and the inner wall of the magnetic generation device; the magnetic part moves along the vertical direction under the action of the magnetic generation device so as to drive the propeller assembly to move. Through the power system, a contact torque transmission mode is cancelled, the structure of the power system is simplified, the maintenance cost is reduced, the use reliability of the aircraft is enhanced, and the service life of the aircraft is prolonged.
Description
Technical Field
The application relates to the technical field of aircrafts, in particular to a power system and an aircraft.
Background
The attitude change of pitching and tilting flight of the blade aircraft during flight is realized by changing the attack angle of the blades at different angles in a periodic pitch changing mode. The power system of the traditional aircraft mainly comprises a servo motor, a paddle main shaft rod, an inclined disc, a connecting rod, a torque arm and a gearbox, wherein the lower end of the paddle main shaft rod is inserted into the gearbox and is connected with a gear set in the gearbox, and the inclined disc is positioned between the paddle and the gearbox; the tilting disk is driven to move by at least three servo motors, and a connecting rod on the tilting disk is connected with a torsion arm arranged on each blade to realize torque transmission. The power system has a complex structure and high manufacturing and maintenance costs, and the paddle and the tilting disk are in a contact transmission mode, so that the mechanical abrasion of the mechanism is serious after long-term use, and the flight life of the aircraft is shortened.
SUMMERY OF THE UTILITY MODEL
The technical problem that this application mainly solved provides a driving system and aircraft, can cancel the moment transmission mode of contact, simplifies the driving system structure, reduces the maintenance cost, increases the reliability that the aircraft used, prolongs the life of aircraft.
In order to solve the technical problem, the application adopts a technical scheme that: a power system is provided for an aircraft, comprising: a propeller assembly; the power assembly comprises a magnetic piece and a hollow magnetic generation device; the magnetic piece is fixedly connected with the propeller assembly, at least part of the magnetic piece is positioned in the magnetic generation device, and a gap is formed between the magnetic piece and the inner wall of the magnetic generation device; the magnetic part moves along the vertical direction under the action of the magnetic generation device so as to drive the propeller assembly to move.
The magnetism generating device comprises a hollow iron core and a coil wound on the periphery of the iron core, and at least part of the magnetic part is positioned in the iron core.
Wherein the propeller assembly comprises: one end of the main connecting rod is fixedly connected with the magnetic part; the other end of the master connecting rod is hinged with one end of the slave connecting rod; the other end of the slave connecting rod is fixedly connected with the paddle clamp; when the magnetic part moves along the vertical direction, the included angle between the hinge positions of the main connecting rod and the auxiliary connecting rod is changed, and then the included angle between the paddle and the plane perpendicular to the vertical direction is changed.
The middle part of the paddle clamp is provided with a through groove along the axial direction of the magnetism generating device; the main connecting rod comprises a first rod body and a second rod body which are fixedly connected and form an included angle with each other; the first rod body is fixedly connected with the magnetic part, extends along the axis direction and penetrates through the through groove; the orthographic projection of one end, far away from the first rod body, of the second rod body on the paddle clamp is positioned outside the paddle clamp; the slave connecting rod comprises a third rod body and a fourth rod body which are hinged with each other, the fourth rod body is fixedly arranged on the outer side surface of the paddle clamp, and two ends of the third rod body are hinged with the second rod body and the fourth rod body respectively.
Wherein, the power component still includes: the rotation control device is fixedly connected with the paddle clamp and used for driving the paddle clamp to rotate in a plane perpendicular to the vertical direction; the rotation control device includes: a power source including a rotary output; the hollow driven shaft is fixedly connected with the rotary output end, at least part of the driven shaft is positioned in the through groove, and the main connecting rod penetrates through the driven shaft; the fixing piece is used for fixedly connecting the driven shaft positioned in the through groove with the paddle clamp at the position of the through groove; the rotation control device further includes: and the angle sensor is used for measuring the rotating angle of the rotating output end.
The paddle clamp comprises a length extending direction perpendicular to the axis direction, grooves are formed in two opposite ends of the paddle clamp in the length extending direction, and one blade is fixedly arranged at each groove; the oar press from both sides still to be provided with the intercommunication the recess with the via hole that leads to the groove, the mounting is worn to establish the via hole, just the both ends of mounting respectively with correspond position department the oar press from both sides with driven shaft fixed connection.
In the axial direction, two inner walls of the grooves, which are oppositely arranged, are respectively provided with a recess, so that the paddle has multiple fixing forms at the positions of the grooves.
In order to solve the above technical problem, another technical solution adopted by the present application is: there is provided an aircraft comprising a power system as described in any of the embodiments above.
Different from the prior art, the beneficial effects of the application are that: the power system in the application comprises a propeller assembly and a power assembly; the power assembly comprises a magnetic part and a hollow magnetic generating device, wherein the magnetic part is fixedly connected with the propeller assembly, and at least part of the magnetic part is positioned in the magnetic generating device and has a certain gap with the inner wall of the magnetic generating device; the magnetic part moves along the vertical direction under the action of the magnetic generating device so as to drive the propeller component to move. In above-mentioned driving system, have the clearance between the inner wall of magnetic part and magnetic force generating device, cancelled traditional contact moment transmission mode, reduced mechanism mechanical wear, utilize the interact of magnetic force to make the magnetic part along vertical direction motion to drive the motion of screw subassembly, can simplify system architecture, reduce the maintenance cost, the reliability of reinforcing aircraft use, the life of extension aircraft.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts. Wherein:
FIG. 1 is a schematic block diagram illustrating an embodiment of a powertrain of the present application;
FIG. 2 is a schematic structural view of one embodiment of the propeller assembly of FIG. 1;
FIG. 3 is a schematic diagram of the structure of one embodiment of the paddle clamp of FIG. 1;
FIG. 4 is a schematic diagram of the structure of one embodiment of the rotation control apparatus of FIG. 1;
FIG. 5 is a schematic structural diagram of another embodiment of the power system of the present application;
fig. 6 is an exploded view of another embodiment of the power system of fig. 5.
Detailed Description
The technical solutions in the embodiments of the present application will be described clearly and completely with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
Referring to FIG. 1, FIG. 1 is a schematic block diagram of an embodiment of the present invention. The power system 100 provided herein includes a propeller assembly 10 and a power assembly 20. The propeller assembly 10 comprises a main connecting rod 101, a slave connecting rod 102, a propeller clamp 103 and a blade 104; the power assembly 20 includes a magnetic member 201, a hollow magnetism generating means 202, and a rotation control means 203. The magnetism generating device 202 includes a hollow core 2021 and a coil 2022 wound around the core.
In the present application, the magnetic member 201 is fixedly connected to the propeller assembly 10, at least a portion of the magnetic member 201 is located inside the magnetic generating device 202, and a gap 30 is provided between the magnetic member and an inner wall of the magnetic generating device 202, and the size of the gap 30 is not limited herein. The magnetic member 201 moves in the vertical direction under the action of the magnetism generating device 202, and the magnetic member 201 is fixedly connected with the propeller assembly 10, so that the propeller assembly 10 is driven to move. In the present embodiment, the vertical direction refers to the axial direction of the magnetic member 201. In the power system 100, the magnetic part 201 and the magnetic generating device 202 are not in contact with each other, so that a contact torque transmission mode is cancelled, the structure of the power system is simplified, the maintenance cost is reduced, the use reliability of the aircraft is enhanced, and the service life of the aircraft is prolonged.
In this embodiment, the magnetic member 201 may be a cylindrical magnet, a square magnet, or any other magnet as long as it has magnetism and can be rigidly and fixedly connected to the propeller assembly 10; the magnetism generating device 202 includes a hollow core 2021 and a coil 2022 wound around the core 2021, and at least a portion of the magnetic member 201 is located inside the core 2021. The coil 2022 generates repulsive magnetic force between the core 2021 and the magnetic member 201 through a circuit, thereby driving the magnetic member 201 to move up and down in the vertical direction. The design mode cancels a contact torque transmission mode, reduces mechanical abrasion of the mechanism and prolongs the flight life of the aircraft.
In this embodiment, the magnetism generating device 202 may be a voice coil motor, may be an electromagnetic relay, and may be any device capable of generating an electromagnetic operating force, and the specific embodiment is not limited herein.
Referring to fig. 1 and 2 together, fig. 2 is a schematic structural diagram of an embodiment of the propeller assembly of fig. 1. One end of the main link 101 in the propeller assembly 10 is fixedly connected to the magnetic member 201, for example, the magnetic member 201 may be fixed to the main link 101 by a screw, a snap, or the like. The other end of the master link 101 is hinged to one end of the slave link 102, and for example, in the extending direction of the slave link 102, the other end of the master link 101 is provided with a through groove (not shown), a pivot shaft (not shown) is provided in the groove, a through hole is provided at a position of the slave link 102 corresponding to the pivot shaft, and the slave link 102 is rotatable about the pivot shaft. And a plurality of paddles 104 are fixedly arranged on the paddle clamp 103 and fixedly connected with the paddle clamp 103 from the other end of the connecting rod 102. When the magnetic member 201 moves in the vertical direction, the angle between the hinge positions of the master link 101 and the slave link 102 changes, so that the angle between the paddle 104 and the plane perpendicular to the vertical direction changes. The propeller assembly 10 is simple in structure, the up-and-down movement of the magnetic part 201 can be converted into the rotation of the propeller clamp 103, the transmission of torque is realized, the structure of a system is simplified, and the manufacturing and maintenance cost is reduced.
Further, the main link 101 includes a first rod 1011 and a second rod 1012 fixedly connected and forming an angle therebetween, preferably, the angle between the first rod 1011 and the second rod 1012 is 90 °, and one end of the first rod 1011 is fixedly connected to one end of the second rod 1012. The slave link 102 includes a third rod body 1021 and a fourth rod body 1022 which are hinged to each other. The first rod body 1011 is fixedly connected with the magnetic piece 201, the orthographic projection of one end, far away from the first rod body 1011, of the second rod body 1012 on the paddle clamp 103 is located on the outer side of the paddle clamp 103, the fourth rod body 1022 is fixedly arranged on the outer side face of the paddle clamp 103, and two ends of the third rod body 1021 are hinged to the second rod body 1012 and the fourth rod body 1022 respectively. When the magnetic member 201 moves in the vertical direction, the included angle between the hinged positions of the second rod 1012 and the third rod 1021 changes, so that the included angle between the third rod 1021 and the fourth rod 1022 changes, and the fourth rod 1022 is fixedly connected to the paddle clamp 103, thereby driving the paddle clamp 103 to move. A complete four-bar mechanism is formed by the four bar bodies, the motion transmission and conversion can be realized by the design mode, only one bar mechanism is arranged in the power system in the application, the structure of the power system is simplified on the one hand by reducing the number of the bar mechanisms, and meanwhile, the maintenance cost in the later period of the mechanism is also reduced.
In this embodiment, please refer to fig. 2 and fig. 3, and fig. 3 is a schematic structural diagram of an embodiment of the paddle clip of fig. 1. A through groove 1031 is arranged in the middle of the paddle clamp 103 along the axial direction X of the magnetism generating device 202; the paddle holder 103 includes a length extending direction Y perpendicular to the axial direction of the magnetism generating device 202. In the length extending direction Y, two opposite ends of the paddle clip 103 are respectively provided with a groove 1032, and the paddle clip 103 is further provided with a via hole 1033 communicating the groove 1032 with the through groove 1031. The first rod 1011 extends along the axial direction of the magnetism generating device 202 and penetrates through the through slot 1031 of the paddle clip, one blade 104 is fixedly arranged at the position of each groove 1032 through a bolt, and recesses 1034 are respectively arranged on two inner walls of the grooves 1032 which are oppositely arranged in the axial direction of the through hole 1033, so that the blades 104 can have various fixing forms at the positions of the grooves 1032. For example, the surface 1041 of the blade 104 in fig. 1 may be fixedly mounted on the blade clamp 103 in a manner approximately parallel to the longitudinal extension direction of the blade clamp 103; for another example, the surface 1041 of the blade 104 may be mounted and fixed to the blade clamp in a manner approximately perpendicular to the extension direction of the length of the blade clamp, and the blade 104 may be snapped into the recess 1034. The fixing modes of the paddles on the same paddle clamp can be the same or different, and can be specifically set according to requirements.
In this embodiment, please refer to fig. 4, wherein fig. 4 is a schematic structural diagram of an embodiment of the rotation control apparatus in fig. 1. The rotation control device 203 includes a power source 2031, a driven shaft 2032, a fixing member 2033, an angle sensor 2034, and a fixing base 2036. Therein, the power source 2031 comprises a rotary output 2035 for driving the paddle clamp 103 to rotate in a plane perpendicular to the vertical direction. The driven shaft 2032 is fixedly connected with the rotary output end 2035 and the power source 2031, and at least part of the driven shaft 2032 is positioned in the through groove 1031 of the paddle clamp 103; the fixed base 2036 is fixedly connected to the power source 2031, for example, the power source 2031 may be fixed to the fixed base 2036 by means of screw threads, insertion, or the like; the angle sensor 2034 is interposed between the stationary base 2036 and the power source 2031, and is configured to measure the rotation angle of the power source 2031. The fixing part 2033 is used for fixedly connecting the rotation output end 2035 in the through groove 1031 to the paddle clip 103 at the through groove 1031, so as to drive the paddle clip 103 to rotate in a plane perpendicular to the vertical direction.
Further, the angle sensor 2034 is not limited to a magnetic encoder, a grating encoder, a carbon film potentiometer, or the like.
In this embodiment, referring to fig. 1, the power source 2031 is located between the paddle clamp 103 and the magnetic generating device 202, at least a portion of the rotation output end 2035 is located in the through groove 1031 of the paddle clamp 103, and the main connecting rod 101 is fixedly connected to the magnetic member 201 after penetrating through the power source 2031 and the driven shaft 2032.
In another embodiment, referring to fig. 5 and 6, fig. 6 is an exploded schematic view of another embodiment of the power system of fig. 5. The power source 2031a is located on the side of the magnetic generating device 202a away from the paddle clamp 103a, the driven shaft 2032a and the rotating output end 2035a penetrate through the magnetic generating device 202a, the magnetic element 201a is located in the driven shaft 2032a, and the main connecting rod 101a is inserted into the driven shaft 2032a to be fixedly connected with the magnetic element 201 a.
Furthermore, the power systems mentioned in the above embodiments may be sold separately or integrated into an aircraft that may include other necessary structures, such as fuselages, landing gear, empennage, etc.
Further, the control method of the aircraft of the present application including the power system mentioned in the above embodiment includes: in response to the propeller assembly 10 rotating to a preset angle in a plane perpendicular to the vertical direction, the magnetic generation device 202 in the power assembly 20 drives the magnetic member 201 to move in the vertical direction, so that the propeller assembly 10 fixedly connected with the magnetic member 201 moves.
Specifically, after receiving an attitude control instruction, the aircraft sends a control signal to the controller through the circuit; detecting the rotation angle of the power source 2031 by the angle sensor 2034, and sending detection data to the controller; when the power source 2031 is detected to reach a preset angle, the controller controls the magnetic generation device 202 to work, and the magnetic generation device 202 drives the magnetic member 201 to move upwards; when the magnetic member 201 moves upwards, the main connecting rod 101 is driven to move upwards; the master link 101 drives the slave link 102 to move upwards, and an included angle between the third rod 1021 and the fourth link 1022 changes, so as to drive the paddle clamp 103 to rotate around the fixing part 2033; the paddle clamp 103 drives the paddle 104 to rotate so as to realize the periodic pitch change of the aircraft. In summary, different from the prior art, the present application provides a power system, wherein a gap is formed between a magnetic member and an inner wall of a magnetic force generating device, a conventional contact torque transmission mode is eliminated, mechanical wear of the mechanism is reduced, the magnetic member is moved in a vertical direction by utilizing interaction of magnetic force, so as to drive a propeller assembly to move, thereby simplifying a system structure, reducing maintenance cost, enhancing use reliability of an aircraft, and prolonging service life of the aircraft.
The above description is only for the purpose of illustrating embodiments of the present application and is not intended to limit the scope of the present application, and all modifications of equivalent structures and equivalent processes, which are made by the contents of the specification and the drawings of the present application or are directly or indirectly applied to other related technical fields, are also included in the scope of the present application.
Claims (9)
1. A power system for an aircraft, comprising:
a propeller assembly;
the power assembly comprises a magnetic piece and a hollow magnetic generation device; the magnetic piece is fixedly connected with the propeller assembly, at least part of the magnetic piece is positioned in the magnetic generation device, and a gap is formed between the magnetic piece and the inner wall of the magnetic generation device; the magnetic part moves along the vertical direction under the action of the magnetic generation device so as to drive the propeller assembly to move.
2. The power system of claim 1,
the magnetism generating device comprises a hollow iron core and a coil wound on the periphery of the iron core, and at least part of the magnetic part is positioned in the iron core.
3. The power system of claim 1, wherein the propeller assembly comprises:
one end of the main connecting rod is fixedly connected with the magnetic part;
the other end of the master connecting rod is hinged with one end of the slave connecting rod;
the other end of the slave connecting rod is fixedly connected with the paddle clamp;
when the magnetic part moves along the vertical direction, the included angle between the hinge positions of the main connecting rod and the auxiliary connecting rod is changed, and then the included angle between the paddle and the plane perpendicular to the vertical direction is changed.
4. The power system of claim 3,
a through groove is formed in the middle of the paddle clamp along the axial direction of the magnetism generating device;
the main connecting rod comprises a first rod body and a second rod body which are fixedly connected and form an included angle with each other; the first rod body is fixedly connected with the magnetic part, extends along the axis direction and penetrates through the through groove; the orthographic projection of one end, far away from the first rod body, of the second rod body on the paddle clamp is positioned outside the paddle clamp;
the slave connecting rod comprises a third rod body and a fourth rod body which are hinged with each other, the fourth rod body is fixedly arranged on the outer side surface of the paddle clamp, and two ends of the third rod body are hinged with the second rod body and the fourth rod body respectively.
5. The power system of claim 4, wherein the power assembly further comprises: the rotation control device is fixedly connected with the paddle clamp and used for driving the paddle clamp to rotate in a plane perpendicular to the vertical direction; the rotation control device includes:
a power source including a rotary output;
the hollow driven shaft is fixedly connected with the rotary output end, at least part of the driven shaft is positioned in the through groove, and the main connecting rod penetrates through the driven shaft;
and the fixing piece is used for fixedly connecting the driven shaft positioned in the through groove with the paddle clamp at the position of the through groove.
6. The power system of claim 5,
the power source is positioned between the paddle clamp and the magnetism generating device, and the main connecting rod penetrates through the power source and the driven shaft and then is fixedly connected with the magnetic part; or the power source is positioned on one side of the magnetic generating device, which is far away from the paddle clamp, the driven shaft penetrates through the magnetic generating device, the magnetic part is positioned in the driven shaft, and the main connecting rod is inserted in the driven shaft so as to be fixedly connected with the magnetic part;
the rotation control device further includes: and the angle sensor is used for measuring the rotating angle of the rotating output end.
7. The power system of claim 5,
the paddle clamp comprises a length extending direction perpendicular to the axis direction, grooves are respectively formed in two opposite ends of the paddle clamp in the length extending direction, and one blade is fixedly arranged at each groove;
the oar press from both sides still to be provided with the intercommunication the recess with the via hole that leads to the groove, the mounting is worn to establish the via hole, just the both ends of mounting respectively with correspond position department the oar press from both sides with driven shaft fixed connection.
8. The power system of claim 7,
in the axial direction, two inner walls of the groove, which are oppositely arranged, are respectively provided with a recess, so that the blade has multiple fixing forms at the position of the groove.
9. An aircraft comprising the power system of any one of claims 1-8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022620974.3U CN214649017U (en) | 2020-11-12 | 2020-11-12 | Power system and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022620974.3U CN214649017U (en) | 2020-11-12 | 2020-11-12 | Power system and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214649017U true CN214649017U (en) | 2021-11-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022620974.3U Active CN214649017U (en) | 2020-11-12 | 2020-11-12 | Power system and aircraft |
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| Country | Link |
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| CN (1) | CN214649017U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220194557A1 (en) * | 2020-12-17 | 2022-06-23 | Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company | Aircraft rotor assembly with plural rotors |
-
2020
- 2020-11-12 CN CN202022620974.3U patent/CN214649017U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220194557A1 (en) * | 2020-12-17 | 2022-06-23 | Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company | Aircraft rotor assembly with plural rotors |
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