CN118124818A - Propeller experimental testing device with shaftless drive rotary drum - Google Patents
Propeller experimental testing device with shaftless drive rotary drum Download PDFInfo
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- CN118124818A CN118124818A CN202410551618.0A CN202410551618A CN118124818A CN 118124818 A CN118124818 A CN 118124818A CN 202410551618 A CN202410551618 A CN 202410551618A CN 118124818 A CN118124818 A CN 118124818A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- General Physics & Mathematics (AREA)
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Abstract
The invention provides a propeller experiment testing device with a shaftless driving cylinder, which comprises a testing platform, a rotating part, a shaftless driving mechanism, a propeller driving mechanism and an intelligent rotating speed control system, wherein the testing platform is horizontally arranged, and the surface of the testing platform is covered with a film pressure sensor; the film pressure sensor is electrically connected with the intelligent rotating speed control system; the rotating part is arranged at the upper part of the test platform and is internally provided with an accommodating space; the shaftless driving mechanism is arranged at the upper part of the test platform and positioned at the outer side of the rotating part, and can electromagnetically drive the rotating part; the propeller is hinged on the rotating part, and one end of the propeller is connected with the power output end of the propeller driving mechanism; the propeller driving mechanism is positioned at the lower side of the test platform and is electrically connected with the intelligent rotating speed control system. The invention has convenient operation and use, can accurately measure the aerodynamic performance of the propeller with the shaftless driving rotary drum, and can effectively solve the problem that the traditional propeller can only generate axial force but can not directly generate lateral force.
Description
Technical Field
The invention relates to the technical field of aviation equipment manufacturing, in particular to a propeller experimental testing device with a shaftless driving rotary drum.
Background
In the field of aviation, propellers are a common device for generating thrust. The conventional propeller design relies primarily on its rotation to push air backward, thereby generating thrust in the opposite direction, i.e., axial force, in accordance with newton's third law. This design is very efficient in many applications, but for certain flight conditions and aircraft designs, such as helicopters or unmanned aerial vehicles, it is often desirable for the propeller to provide lateral forces in addition to axial thrust to achieve better handling and maneuverability. However, it is difficult to directly generate significant lateral force due to the limitations of the conventional propeller in terms of its structure and operation principle. To overcome this limitation, researchers in the relevant field have tried several methods to create the goal of lateral force, one of which is to use the magnus effect in fluid mechanics. The magnus effect refers to the fact that when a rotating object is subjected to fluid flow, it will experience a lateral force perpendicular to the direction of flow and the axis of rotation of the object. Although this effect is common in nature, such as banana balls for football and top spin balls for tennis, it is relatively rare to use in propeller designs, mainly due to the lack of a suitable mechanical design to achieve this effect and efficient integration into experimental testing apparatus. Therefore, there is a need for improvements in the prior art, particularly in developing propellers capable of generating lateral forces, which not only can enhance the performance of aircraft such as helicopters and unmanned aerial vehicles, but also can open up new approaches for aviation research and technical development.
In the experimental test process of the propeller, the real-time monitoring of mechanical parameters is of great importance. These parameters include, but are not limited to, thrust, lateral force, torque and pressure profiles, which are of great importance for assessing performance and efficiency of the propeller. The traditional testing device generally relies on an external sensor and a manual adjustment mode to collect data and adjust the working state of the propeller, which not only increases the complexity of experiments, but also is difficult to realize quick and accurate control and adjustment, and especially is insufficient when the dynamic flight condition needs to be simulated.
In view of the foregoing, there is a need for further innovations in the art.
Disclosure of Invention
Aiming at the technical problems in the background art, the invention provides a propeller experiment testing device with a shaftless driving rotary drum, which has reasonable structural design, is easy to produce and manufacture, is convenient to operate and use, can accurately measure the aerodynamic performance of the propeller with the shaftless driving rotary drum, and can effectively solve the problem that the traditional propeller can only generate axial force but not directly generate lateral force.
In order to solve the technical problems, the invention provides a propeller experiment testing device with a shaftless driving cylinder, which comprises a testing platform, a rotating part, a shaftless driving mechanism, a propeller driving mechanism and an intelligent rotating speed control system; the test platform is horizontally arranged, and the surface of the test platform is covered with a film pressure sensor; the film pressure sensor is electrically connected with the intelligent rotating speed control system; the rotating component is arranged at the upper part of the test platform in a matching way, and an accommodating space is formed in the rotating component; the shaftless driving mechanism is arranged at the upper part of the test platform and is matched with the outer side of the rotating component, and can electromagnetically drive the rotating component; the screw propeller is hinged on the rotating component in a matching way, and one end of the screw propeller is connected with the power output end of the screw propeller driving mechanism in a matching way; the propeller driving mechanism is located at the lower side of the testing platform and is electrically connected with the intelligent rotating speed control system.
The propeller experimental testing device with the shaftless driving cylinder comprises a shaftless driving motor rotor and a shaftless driving motor stator; the shaftless driving motor rotor is matched and sleeved outside the lower end of the rotating part, and an annular permanent magnet is arranged inside the shaftless driving motor rotor; the shaftless drive motor stator is electrically connected with the intelligent rotating speed control system, is matched and sleeved on the radial outer part of the shaftless drive motor rotor and is matched and hinged with the shaftless drive motor rotor; the axial lower end part of the shaftless driving motor stator is fixedly connected with the test platform, and a winding group is arranged in an inner cavity; the rotating component is electromagnetically driven by the shaftless drive motor stator and the shaftless drive motor rotor, and the propeller drive mechanism comprises a servo motor and a planetary reducer; the servo motor is positioned at the bottom side of the test platform, and the power output end of the servo motor is matched with the planetary reducer; and the power output end of the planetary reducer is connected with the propeller in a matching way.
The propeller experimental testing device with the shaftless driving cylinder comprises a radial outer wall of a shaftless driving motor rotor and a radial inner cavity wall of a shaftless driving motor stator, wherein a lubricating bearing is arranged between the radial outer wall of the shaftless driving motor rotor and the radial inner cavity wall of the shaftless driving motor stator in a matching mode, so that the shaftless driving motor rotor can rotate relative to the shaftless driving motor stator.
The intelligent rotating speed control system comprises an operation terminal, a data acquisition device, a development board, a driving module and a transformer; the operation terminal is used as an interface for interaction between a user and the system; the signal output end of the data acquisition device is electrically connected with the operation terminal, and the signal input end of the data acquisition device is electrically connected with the film pressure sensor; the signal input end of the development board is electrically connected with the operation terminal, and the signal output end of the development board is electrically connected with the signal input end of the driving module; the signal output end of the driving module is respectively and electrically connected with the shaftless driving motor stator and the servo motor; the transformer is respectively and electrically connected with the film pressure sensor, the shaftless driving motor stator, the servo motor, the operation terminal, the data acquisition device, the development board and the driving module.
The propeller experimental testing device with the shaftless driving cylinder comprises a propeller shaft and a blade; the upper end of the paddle shaft is matched and hinged with the inner cavity wall at the upper end of the rotating part through a first bearing, and the lower end of the paddle shaft is matched and hinged with the inner cavity wall at the lower end of the rotating part through a second bearing; the lower end of the paddle shaft is hinged with the test platform in a matching way through a third bearing; the paddle is fixedly arranged at one end of the paddle extending out of the outer side of the upper end of the rotating part in a matching way.
The propeller experimental testing device with shaftless driving cylinder, wherein: the axial lower end part of the second bearing is in contact connection with the test platform, and a lubricating body is smeared on the contact surface.
The propeller experimental testing device with shaftless driving cylinder, wherein: the third bearing is matched and fixed at the bottom of the test platform and used for limiting the paddle shaft.
The propeller experiment testing device with the shaftless driving cylinder is characterized in that the testing platform is of a plate-shaped structure, and a through hole through which the propeller shaft can pass through in a movable mode is formed in the center of the testing platform in a matched and penetrating mode along the vertical direction.
The screw experimental testing device with the shaftless driving cylinder comprises a rotating component, wherein the rotating component is a thin-wall rotary cylinder, the lower end part of the rotating component is in contact connection with the top surface of the testing platform, and a lubricating body is smeared on the contact surface of the rotating component.
By adopting the technical scheme, the invention has the following beneficial effects:
The experimental testing device for the propeller with the shaftless driving cylinder has the advantages of simple and reasonable structural design, easiness in processing and installation, suitability for wind tunnels, and capability of being used for experimental testing of special propellers of helicopters or unmanned planes; in addition, the invention has wide application prospect and can provide important technical support for research and development work in the related fields.
The invention integrates advanced sensing technology and intelligent control system, thus not only greatly improving the precision and efficiency of experimental test, but also providing strong data support for the design optimization of the propeller. The high-sensitivity film pressure sensor covered on the surface of the test platform can accurately capture tiny mechanical changes and convert the tiny mechanical changes into electric signals, and key input data is provided for an intelligent control system; the intelligent control system realizes accurate adjustment of the rotating speed of the rotating component and the propeller through an intelligent control algorithm (based on an artificial intelligence neural network method, such as a depth deterministic strategy gradient algorithm DDPG), and can automatically adjust parameters according to real-time feedback of a film pressure sensor so as to ensure that the rotating component operates in an optimal state (namely, increase the thrust of the propeller and the lateral force of the rotating drum).
The main advantages of the invention are embodied in the following aspects:
1) The rotating component is combined with key components such as a shaftless drive motor stator, a shaftless drive motor rotor and the like to form a shaftless drive rotating cylinder, and a lateral force is generated by utilizing a Magnus effect in incoming flow, so that a lateral propelling function can be realized;
2) The coordinated operation of the servo motor and the planetary reducer ensures the stable operation of the propeller, and each bearing and each propeller shaft are responsible for bearing and transmission functions;
3) Aiming at the limitation of the prior art, the surface of the test platform is covered with the film pressure sensor, the innovative design enables the surface of the whole test platform to be a highly sensitive sensing surface, and the sensor can continuously monitor and capture the tiny mechanical changes generated by the operation of the propeller and transmit the data to the intelligent rotating speed control system in real time;
4) The intelligent rotating speed control system is an intelligent center, has data processing and analyzing capabilities, can intelligently adjust the rotating speed of the rotating component and the rotating speed of the propeller according to the mechanical parameters monitored in real time, thereby optimizing the performance of the propeller, ensuring high-efficiency and stable operation under different test conditions, and effectively realizing the analysis of the aerodynamic performance of the device;
5) According to the invention, rotating parts with different forms (including changing length, section shape or surface roughness and the like) and propeller shafts and propellers with corresponding sizes can be replaced according to experimental requirements, so that a series of experimental comparative researches can be carried out.
The invention not only maintains the basic function of the traditional propeller, but also effectively utilizes the magnus effect to generate necessary lateral force in the operation process of the propeller through the special design of the rotating cylinder driven by the shaftless. The method provides a brand new experimental platform for propeller design, so that researchers can evaluate and optimize the design of the special propeller in an environment which is closer to the actual operating condition.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a propeller test apparatus having a shaftless drive cylinder of the present invention;
FIG. 2 is a side view of a propeller test rig of the present invention having a shaftless drive cylinder;
FIG. 3 is a top view of a propeller test rig having a shaftless drive cylinder of the present invention;
FIG. 4 is a cross-sectional view of a propeller test apparatus having a shaftless drive cylinder of the present invention;
FIG. 5 is a detailed cross-sectional view of one side of a propeller test apparatus of the present invention having a shaftless drive cylinder;
FIG. 6 is a detailed cross-sectional view of one side of a motor of a propeller test apparatus having a shaftless drive cylinder of the present invention;
fig. 7 is a schematic diagram of the structural connection of the intelligent rotational speed control system of the experimental propeller test apparatus with shaftless drive cylinder of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention is further illustrated with reference to specific embodiments.
As shown in fig. 1, the experimental propeller testing device with the shaftless driving cylinder provided in this embodiment includes a testing platform 1, a rotating component 2, a shaftless driving mechanism 3, a propeller 4, a propeller driving mechanism 5 and an intelligent rotation speed control system.
The test platform 1 is of a plate-shaped structure, and a through hole is formed in the middle of the test platform in a matching and penetrating manner; wherein, the surface of the test platform 1 is covered with a high-sensitivity film pressure sensor 11; the film pressure sensor 11 is electrically connected with the intelligent rotating speed control system; the film pressure sensor 11 can monitor various mechanical parameter changes in the experimental process in real time and feed back the pressure condition born by the rotating component 2, and transmits a sensing signal to an intelligent rotating speed control system, so that the rotating speeds of the rotating component 3 and the propeller 4 can be intelligently regulated, and the aerodynamic performance of the device is analyzed.
The rotating part 2 is arranged at the center of the upper part of the test platform 1 in a matching way, and an accommodating space is formed in the rotating part; the rotating part 2 adopts a thin-wall rotary drum and is vertically arranged in the center of the top surface of the test platform 1 in a matching way, the lower end part of the rotating part 2 is in contact connection with the top surface of the test platform 1, and a lubricating body is smeared on the contact surface.
The shaftless driving mechanism 3 is mounted in the upper center of the test platform 1 in a matching manner, and comprises a shaftless driving motor rotor 31 and a shaftless driving motor stator 32. The shaftless driving motor rotor 31 is matched and sleeved outside the lower end of the rotating part 2, and annular permanent magnets are arranged inside the shaftless driving motor rotor; the shaftless driving motor stator 32 is matched and sleeved outside the circumference of the shaftless driving motor rotor 31 and is matched and hinged with the shaftless driving motor rotor 31, the axial lower end part of the shaftless driving motor stator 32 is fixedly connected with the test platform 1 through bolts, and a winding group is arranged in an inner cavity of the shaftless driving motor stator 32. Wherein small lubrication bearings are arranged between the radially outer wall of the shaftless drive motor rotor 31 and the radially inner cavity wall of the shaftless drive motor stator 32 in a matching manner, so that the shaftless drive motor rotor 31 can rotate relative to the shaftless drive motor stator 32. The rotating component 2 is electromagnetically driven under the cooperation of the shaftless driving motor stator 32, the shaftless driving motor rotor 31 and the intelligent rotating speed control system (the specific principle of electromagnetic driving is that after the shaftless driving motor stator 32 is electrified, the shaftless driving motor stator 32 generates a magnetic field through current, the shaftless driving motor rotor 31 has magnetic field inductivity, the magnetic field of the shaftless driving motor stator 32 interacts with the magnetic field of the shaftless driving motor rotor 31 to generate electromagnetic force to move the shaftless driving motor rotor 31, and the shaftless driving motor rotor 31 starts to rotate under the action of electromagnetic force to drive the rotating component 2 to rotate).
The propeller 4 is matingly mounted on the rotating member 2 and comprises a propeller shaft 41 and a blade 42. Wherein, the paddle shaft 41 vertically penetrates through the inner cavity of the rotating component 2 in a matching way, the upper end of the paddle shaft extends out of the upper end of the rotating component 2, and the lower end of the paddle shaft firstly penetrates through the rotating component 2 and then movably penetrates through a through hole in the center of the test platform 1 and extends out of the lower side of the test platform 1; the upper end of the paddle shaft 41 is in matched hinge connection with the inner cavity wall of the upper end of the rotating component 2 through a first bearing 411, the lower end of the paddle shaft 41 is in matched hinge connection with the inner cavity wall of the lower end of the rotating component 2 through a second bearing 412, the axial lower end of the second bearing 412 is in contact with the test platform 1, and a contact surface is coated with a lubricating body (without limiting materials and can comprise solid lubricating grease of components such as graphite, molybdenum disulfide, tungsten disulfide, silicon dioxide and the like); meanwhile, the lower end of the paddle shaft 41 is hinged to the test platform 1 in a matching manner through a third bearing 413, and the third bearing 413 is fixed in the center of the bottom of the test platform 1 in a matching manner and can be used for limiting the paddle shaft 41. The paddle 42 is fixedly mounted to an end of the paddle shaft 41 extending outward from the upper end of the rotating member 2. The inner walls and outer walls of the first bearing 411 and the second bearing 412 are tightly combined with the paddle shaft 41 and the rotating member 2, respectively, and play a role of supporting and relatively rotating.
The propeller driving mechanism 5 is located at the bottom side of the test platform 1 and is matched with one end of the propeller shaft 41 mounted on the propeller 4 penetrating out to the lower end of the rotating component 2, and comprises a servo motor 51 and a planetary reducer 52. The servo motor 51 is located at the bottom side of the test platform 1 and is electrically connected with the intelligent rotating speed control system, and a planetary reducer 52 is installed at the power output end of the servo motor in a matched mode; the power output end of the planetary reducer 52 is connected with one end of the propeller shaft 41 of the propeller 4 extending downwards to the test platform 1 in a matching way.
As shown in fig. 7, the intelligent rotational speed control system includes an operation terminal 61, a data collector 62, a development board 63, a driving module 64, and a transformer 65.
The operation terminal 61 is electrically connected to the data collector 62 and the development board 63, respectively, and generally employs a computer as an interface for a user to interact with the system, and the user can send control instructions and receive system status information through the operation terminal 61.
The signal output end of the data collector 62 is electrically connected with the operation terminal 61, and the signal input end of the data collector 62 is electrically connected with the film pressure sensor 11 covered on the surface of the test platform 1. The data acquisition unit 62 can acquire sensing signals output by the film pressure sensor 11 in real time, wherein the sensing signals generally relate to force changes generated by the drum and are the basis for rotating speed control.
The signal input end of the development board 63 is electrically connected with the operation terminal 61, and the signal output end of the development board 63 is electrically connected with the signal input end of the driving module 64; the development board 63 may be an embedded development board such as STM32, and is configured to receive the sensor signal data collected from the data collector 62 after being processed by the operation terminal 61, make a decision according to a preset control algorithm, and also is responsible for executing a command from the operation terminal 61.
The signal output end of the driving module 64 is electrically connected with the shaftless driving motor stator 32 for driving the shaftless driving mechanism 3 and the servo motor 51 of the propeller driving mechanism 5; the driving module 64 receives the control signal from the development board 63 and converts the control signal into a signal required for driving the shaftless driving mechanism 3 and the propeller driving mechanism 5, and the shaftless driving mechanism 3 and the propeller driving mechanism 5 adjust the motion states of the rotating member 2 and the propeller 4 according to the signal provided by the driving module 64.
The transformer 65 provides necessary power for the film pressure sensor 11, the shaftless drive motor stator 32 of the shaftless drive mechanism 3, the servo motor 51 of the propeller drive mechanism 5, the operation terminal 61, the data collector 62, the development board 63 and the drive module 64, ensuring that each electronic component is supplied with a proper voltage to work normally.
The working principle of the intelligent rotating speed control system is as follows:
1) The user sets a control parameter or issues a control command through the operation terminal 61;
2) The film pressure sensor 11 monitors the stress condition of the rotary drum in real time and transmits the sensing signal data to the data collector 62;
3) The data collector 62 transmits data to the development board 63 via the operation terminal 61 through a serial port or other communication interface;
4) The development board 63 processes information through a built-in control algorithm according to the received data and user commands, and generates corresponding control signals;
5) The driving module 64 receives the control signal of the development board 63 and converts the control signal into a signal capable of commanding the shaftless driving mechanism 3 and the propeller driving mechanism 5 to act;
6) The shaftless driving mechanism 3 and the propeller driving mechanism 5 respond to the signals of the driving module 64 to adjust the rotation speed and the direction of the rotating component 2 and the propeller 4;
7) The transformer 65 provides a stable power supply for the film pressure sensor 11, the shaftless drive motor stator 32 of the shaftless drive mechanism 3, the servo motor 51 of the propeller drive mechanism 5, the operation terminal 61, the data collector 62, the development board 63 and the drive module 64, and ensures continuous and stable operation of the experimental device.
The intelligent rotating speed control system can be arranged in the wind tunnel for experimental test, when the wind tunnel is started and the flow speed is stable, the intelligent rotating speed control system is started, the rotating speeds of the propeller 4 and the rotating component 2 are respectively and intelligently controlled according to the feedback of the film pressure sensor 11, the purpose of increasing the wall pressure is achieved, the surface and wake flow characteristics of the propeller 4 and the rotating component 2 can be observed through a tracing method, and experimental data are collected.
The invention has reasonable structural design, is easy to produce and manufacture, is convenient to operate and use, can accurately measure the aerodynamic performance of the propeller with the shaftless driving rotary drum, and can effectively solve the problem that the traditional propeller can only generate axial force but can not directly generate lateral force.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention 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 scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (9)
1. The propeller experiment testing device with the shaftless driving cylinder is characterized by comprising a testing platform (1), a rotating part (2), a shaftless driving mechanism (3), a propeller (4), a propeller driving mechanism (5) and an intelligent rotating speed control system;
The test platform (1) is horizontally arranged, and the surface of the test platform is covered with a film pressure sensor (11); the film pressure sensor (11) is electrically connected with the intelligent rotating speed control system;
the rotating component (2) is arranged at the upper part of the test platform (1) in a matching way, and an accommodating space is formed in the rotating component;
The shaftless driving mechanism (3) is arranged at the upper part of the test platform (1) and is matched with the outer side of the rotating component (2), so that the rotating component (2) can be electromagnetically driven;
The screw propeller (4) is hinged on the rotating component (2) in a matching way, and one end of the screw propeller is connected with the power output end of the screw propeller driving mechanism (5) in a matching way; the propeller driving mechanism (5) is located at the lower side of the test platform (1) and is electrically connected with the intelligent rotating speed control system.
2. The propeller experimental testing apparatus with shaftless drive cylinder as set forth in claim 1, characterized in that the shaftless drive mechanism (3) comprises a shaftless drive motor rotor (31) and a shaftless drive motor stator (32); the shaftless driving motor rotor (31) is matched and sleeved outside the lower end of the rotating part (2), and annular permanent magnets are arranged inside the shaftless driving motor rotor; the shaftless drive motor stator (32) is electrically connected with the intelligent rotating speed control system, is matched and sleeved on the radial outer part of the shaftless drive motor rotor (31) and is matched and hinged with the shaftless drive motor rotor (31); the axial lower end part of the shaftless driving motor stator (32) is fixedly connected with the test platform (1), and a winding group is arranged in an inner cavity; the rotating part (2) is electromagnetically driven by the shaftless drive motor stator (32) and the shaftless drive motor rotor (31);
The propeller driving mechanism (5) comprises a servo motor (51) and a planetary reducer (52); the servo motor (51) is positioned at the bottom side of the test platform (1), and the power output end of the servo motor is matched with the planetary reducer (52); the power output end of the planetary reducer (52) is connected with the propeller (4) in a matching way.
3. A propeller experimental testing arrangement having a shaftless drive cylinder as set forth in claim 2, wherein a lubricated bearing is matingly disposed between the radially outer wall of the shaftless drive motor rotor (31) and the radially inner cavity wall of the shaftless drive motor stator (32) to enable rotational movement of the shaftless drive motor rotor (31) relative to the shaftless drive motor stator (32).
4. The propeller experimental testing apparatus with shaftless drive cylinder of claim 2, wherein the intelligent rotational speed control system comprises an operation terminal (61), a data collector (62), a development board (63), a drive module (64) and a transformer (65);
The operation terminal (61) is used as an interface for the interaction of a user and a system;
the signal output end of the data collector (62) is electrically connected with the operation terminal (61), and the signal input end of the data collector (62) is electrically connected with the film pressure sensor (11);
the signal input end of the development board (63) is electrically connected with the operation terminal (61), and the signal output end of the development board (63) is electrically connected with the signal input end of the driving module (64);
The signal output end of the driving module (64) is respectively and electrically connected with the shaftless driving motor stator (32) and the servo motor (51);
The transformer (65) is electrically connected with the film pressure sensor (11), the shaftless driving motor stator (32), the servo motor (51), the operation terminal (61), the data collector (62), the development board (63) and the driving module (64) respectively.
5. The propeller experimental testing apparatus with shaftless drive cylinder as set forth in claim 2, characterized in that the propeller (4) comprises a propeller shaft (41) and a paddle (42);
The upper end of the paddle shaft (41) is matched and hinged with the upper end inner cavity wall of the rotating part (2) through a first bearing (411), and the lower end of the paddle shaft (41) is matched and hinged with the lower end inner cavity wall of the rotating part (2) through a second bearing (412); the lower end of the paddle shaft (41) is hinged with the test platform (1) in a matching way through a third bearing (413);
The paddle (42) is fixedly arranged at one end of the paddle shaft (41) extending outwards from the upper end of the rotating part (2) in a matching way.
6. A propeller experimental testing apparatus having a shaftless drive cylinder as set forth in claim 5, wherein: the axial lower end part of the second bearing (412) is in contact connection with the test platform (1), and a lubricating body is smeared on the contact surface.
7. A propeller experimental testing apparatus having a shaftless drive cylinder as set forth in claim 5, wherein: the third bearing (413) is fixed at the bottom of the test platform (1) in a matching way and used for limiting the paddle shaft (41).
8. The propeller experimental testing apparatus with a shaftless driving cylinder as set forth in claim 5, wherein the testing platform (1) is a plate-like structure, and a through hole through which the propeller shaft (41) can pass through is formed at the center thereof in a vertically matched manner.
9. The propeller experimental testing device with a shaftless driving cylinder according to claim 1, wherein the rotating component (2) adopts a thin-wall rotary drum, the lower end part of the rotating component is in contact connection with the top surface of the testing platform (1), and a lubricating body is smeared on the contact surface.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20090039563A (en) * | 2007-10-18 | 2009-04-22 | 한국항공우주연구원 | Helicopter tail rotor test rig |
| CN111707442A (en) * | 2020-06-30 | 2020-09-25 | 中国科学院工程热物理研究所 | Supersonic wind tunnel propeller numerical model measurement verification system and control method thereof |
| CN115560946A (en) * | 2022-09-26 | 2023-01-03 | 中国船舶科学研究中心 | Tail pulsating pressure testing device and method for underwater navigation model with propeller in wind tunnel |
| CN116714775A (en) * | 2023-07-31 | 2023-09-08 | 中国民用航空飞行学院 | Multi-environment simulation variable-pitch propeller power system testing device and testing method |
| CN117429618A (en) * | 2023-09-25 | 2024-01-23 | 仁合智航科技(武汉)有限责任公司 | Aeroengine propeller side wind test device and test method |
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- 2024-05-07 CN CN202410551618.0A patent/CN118124818B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20090039563A (en) * | 2007-10-18 | 2009-04-22 | 한국항공우주연구원 | Helicopter tail rotor test rig |
| CN111707442A (en) * | 2020-06-30 | 2020-09-25 | 中国科学院工程热物理研究所 | Supersonic wind tunnel propeller numerical model measurement verification system and control method thereof |
| CN115560946A (en) * | 2022-09-26 | 2023-01-03 | 中国船舶科学研究中心 | Tail pulsating pressure testing device and method for underwater navigation model with propeller in wind tunnel |
| CN116714775A (en) * | 2023-07-31 | 2023-09-08 | 中国民用航空飞行学院 | Multi-environment simulation variable-pitch propeller power system testing device and testing method |
| CN117429618A (en) * | 2023-09-25 | 2024-01-23 | 仁合智航科技(武汉)有限责任公司 | Aeroengine propeller side wind test device and test method |
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