Temperature-controlled electric propeller test system and test method

Abstract

The present application relates to the propeller test field, specifically discloses a temperature control type electric propeller test system and test method, the test system includes test module, support component and motion device;The test module includes test platform and test assembly arranged on the test platform;The test assembly includes motor mounting seat, propeller, rotating speed sensor, torque sensor, motor and temperature control box;The support component includes rack, and the central axis of the rack is provided with a rotating shaft;The test platform is hinged on the rack as a whole through the rotating shaft, and the test platform can swing up and down around the rotating shaft under the driving of the motion device.The present application can accurately measure the push-pull force and torque generated by the motor-driven propeller in different poses at different temperatures through the combination of the rotating speed sensor, S-type tension sensor and torque sensor and the motion device, improve the authenticity and accuracy of measurement, and has simple structure, high efficiency and accuracy.

Description

Technical Field

[0001] This invention relates to the field of propeller testing technology, specifically to a temperature-controlled electric propeller testing system and method. Background Technology

[0002] An electric propeller propulsion system refers to a system where an electric motor drives a propeller to rotate, generating thrust and lift to propel the aircraft. Propeller performance is a crucial part of aircraft design and manufacturing. Before an aircraft enters service, the propeller and drive motor must undergo performance testing. The test data is vital for the design of electric aircraft. However, due to the complex flight environment and operating conditions during flight, it is difficult to directly measure these parameters.

[0003] Currently, propeller performance testing both domestically and internationally primarily utilizes bench testing systems. However, these systems neglect temperature variations during flight, failing to account for changes in propeller thrust and rotational speed under different temperatures. Furthermore, aircraft exhibit diverse flight attitude variations during flight. Existing test benches can only measure the aircraft's dynamic parameters in the vertical direction, resulting in incomplete data that fails to fully reflect the aircraft's performance parameters during flight. To accurately measure these performance indicators, a test bench with controllable motor temperature and adjustable propeller attitude is designed. This bench accurately reflects the propeller's true motion parameters and boasts a simple, efficient, and accurate structure. Summary of the Invention

[0004] To address the problems existing in the prior art, this invention provides a temperature-controlled electric propeller testing system and method. By placing the motor inside a temperature-controlled chamber, the system can simulate the changes in the motor's operating temperature at different flight altitudes. Through the combination of a speed sensor, a tension sensor, and a torque sensor with a motion device, the system addresses the changes in tension and torque generated by the motor driving the propeller at different temperatures and under different flight attitudes, thus solving the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a temperature-controlled electric propeller testing system, the testing system comprising a testing module, a support assembly, and a motion device; the testing module comprising a testing platform and testing components mounted on the testing platform; the testing components comprising a motor mounting base, a propeller, a speed sensor, a torque sensor, a motor, and a temperature control chamber; the support assembly comprising a frame, wherein a rotating shaft is disposed on the central axis of the frame; the testing platform is integrally hinged to the frame via the rotating shaft, and the testing platform can swing up and down around the rotating shaft under the drive of the motion device.

[0006] Preferably, a guide rail is fixedly installed on the test platform, and the motor mounting base is slidably mounted on the guide rail by a slider, and can reciprocate along the guide rail.

[0007] Preferably, a temperature control box is fixedly installed on the motor mounting base, and the motor is installed inside the temperature control box; the temperature of the temperature control box is controllable and can simulate the temperature environment in which the motor operates at different flight altitudes of the aircraft.

[0008] The motor mounting base has two bearing seats fixedly installed on it, and the motor drive shaft of the motor extends under the support of the bearing seats; the propeller is fixedly installed at the end of the motor drive shaft, and the torque sensor is fixedly installed between the two bearing seats to detect the torque generated by the propeller in flight attitude.

[0009] Preferably, a propeller protective cover is fixedly installed at the front end of the test platform to prevent the propeller from colliding with the frame during rotation and causing a safety accident; a speed sensor is provided at the end of the motor drive shaft near the propeller protective cover to detect the speed of the propeller in flight attitude.

[0010] Preferably, the test platform is provided with a tension bracket at the rear end, the middle part of the push-pull force converter is hinged to the tension bracket, and the S-shaped tension sensor is fixedly installed at the rear of the test platform; the upper end of the push-pull force converter is connected to the motor mounting base through a tension rod, and the lower end of the push-pull force converter is connected to the S-shaped tension sensor.

[0011] Preferably, the motion device includes a pull rod, an eccentric wheel, and an electric motor; the electric motor is fixedly mounted on the frame, and the eccentric wheel is mounted on the electric motor; one end of the pull rod is hinged to the eccentric wheel, and the other end is hinged to a boss set on the test platform. Driven by the eccentric wheel, the test platform swings up and down around the frame with the rotation axis.

[0012] Preferably, the bottom of the frame is provided with a fixing plate, and a plurality of ground nail holes are symmetrically distributed on the fixing plate to fix the frame to the ground.

[0013] In addition, to achieve the above objectives, the present invention also provides the following technical solution: a testing method for a temperature-controlled electric propeller testing system, the testing method comprising the following steps:

[0014] S1. The temperature is adjusted by the temperature control box to simulate the working temperature environment of the motor when the aircraft is at different flight altitudes;

[0015] S2. Start the motor. The motor drive shaft drives the propeller to start rotating. The speed of the propeller is measured by a speed sensor installed on the motor drive shaft. The torque generated by the propeller in flight attitude is measured by a torque sensor fixed between the bearing seats.

[0016] S3. The thrust generated by the propeller rotation drives the motor mounting base to move along the guide rail via the slider. The motor mounting base drives the upper part of the push-pull force converter to move via the tension rod, thereby driving the push-pull force converter to rotate around the hinge point. The lower end of the push-pull force converter is connected to the S-type tension sensor, which converts the thrust generated by the propeller rotation into thrust and measures it through the S-type tension sensor.

[0017] S4. Start the electric motor in the motion device. The electric motor drives the eccentric wheel to start working. Driven by the eccentric wheel, the test platform swings up and down around the frame with the rotating axis, simulating the pitching and diving of the aircraft in actual flight.

[0018] S5, through coupling with speed sensor, torque sensor and S-type tension sensor, comprehensively and accurately measures the motion parameters of motor and propeller under different temperatures and tilt angles.

[0019] Preferably, during the testing process, the frame is fixed to the ground through the ground nail holes on the fixing plate to avoid the friction and displacement generated during the movement of the frame affecting the measurement parameter data.

[0020] The beneficial effects of this invention are as follows: By setting up a temperature control chamber, this invention can simulate the temperature changes caused by flight altitude during actual flight. The electrical components are installed inside the temperature control chamber, providing different temperature environments. The test platform is driven to swing via a motion device, simulating different aircraft postures during flight. Through coupling with a speed sensor, torque sensor, and S-shaped tension sensor, the relevant motion parameters of the motor and propeller (changes in tension and torque generated under different flight postures) can be comprehensively and accurately measured at different temperatures and tilt angles. The invention is simple in structure, highly efficient, and accurate. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the overall structure of the temperature-controlled electric propeller testing system of the present invention;

[0022] Figure 2 This is a schematic diagram of the test platform structure of the present invention;

[0023] Figure 3 This is a schematic diagram of the frame motion device mechanism of the present invention;

[0024] Figure 4 This is a magnified schematic diagram of the test platform of the present invention;

[0025] In the diagram, 1-fixed plate, 2-frame, 3-propeller protective cover, 4-test platform, 41-guide rail, 42-slider, 43-motor mounting base, 44-motor drive shaft, 45-propeller, 46-speed sensor, 47-torque sensor, 48-bearing housing, 49-motor, 410-temperature control box, 411-tension rod, 412-push-pull force converter, 413-tension bracket, 414-S-type tension sensor, 415-rotating shaft, 416-bore, 5-motion device, 51-pull rod, 52-eccentric wheel, 53-electric motor, 6-ground spike hole. Detailed Implementation

[0026] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] Example 1

[0028] Please see Figures 1-4 This invention provides a technical solution: a temperature-controlled electric propeller testing system, such as... Figure 1 As shown, the testing system includes a testing module, a support assembly, and a motion device 5. The testing module includes a testing platform 4 and testing components mounted on the testing platform. The testing components include a motor mounting base 43, a propeller 45, a speed sensor 46, a torque sensor 47, a motor 49, and a temperature control chamber 410. The support assembly includes a frame 2, with a rotating shaft 415 mounted on the central axis of the frame 2. The testing platform 4 is hinged to the frame via the rotating shaft, and can swing up and down around the rotating shaft 415 under the drive of the motion device 5. The testing platform is coupled with a torque transmission unit and a push-pull force transmission unit, enabling the testing of torque and pull forces generated under different temperatures and flight attitudes.

[0029] Furthermore, such as Figure 4 As shown, a temperature control box 410 is fixedly installed on the motor mounting base 43, and the motor 49 is installed inside the temperature control box; the temperature of the temperature control box is controllable and can simulate the temperature environment of the motor when the aircraft is flying at different altitudes.

[0030] Furthermore, such as Figure 4 As shown, two bearing seats 48 are fixed on the motor mounting seat 43. The motor drive shaft 44 of the motor extends outward under the support of the bearing seats 48. The propeller 45 is installed at the end of the motor drive shaft. The propeller 45 is driven to rotate through the motor drive shaft 44. The torque sensor 47 is fixedly installed between the two bearing seats to detect the torque generated by the propeller in the flight attitude.

[0031] like Figure 2 and Figure 4 As shown, a guide rail 41 is fixedly installed on the test platform 4. The motor mounting base 43 is slidably mounted on the guide rail 41 via a slider 42. The temperature control box 410, the motor 49 and the motor mounting base 43 are fixed together as one unit and can reciprocate along the guide rail.

[0032] Furthermore, a propeller protective cover 3 is fixedly installed at the front end of the test platform 4 to prevent the propeller from colliding with the frame during rotation and causing a safety accident. During the test, it rotates together with the test platform 4 to protect the propeller 45 during safe operation. A speed sensor 46 is installed at the end of the motor drive shaft near the propeller protective cover 3 to detect the speed of the propeller in flight attitude.

[0033] Furthermore, such as Figure 2 As shown, a tension bracket 413 is provided at the rear end of the test platform 4, the middle part of the push-pull force converter 412 is hinged to the tension bracket, and the S-shaped tension sensor 414 is fixedly installed at the tail of the test platform 4; the upper end of the push-pull force converter 412 is connected to the motor mounting base 43 through the tension rod 411, and the lower end of the push-pull force converter is connected to the S-shaped tension sensor 414.

[0034] The pulling force generated by the rotation of propeller 45 drives motor mounting base 43 to move along guide rail 41 via slider 42. Motor mounting base 43 drives the upper part of push-pull force converter 412 to move via tension rod 411, thereby driving push-pull force converter to rotate around hinge point. The lower end contacts S-shaped tension sensor, converting the pulling force generated by the rotation of propeller 45 into thrust for measurement. During the measurement process, the tension and thrust can be balanced to keep the test platform in a stationary state, avoiding the influence of friction and displacement generated during frame movement on the measurement data.

[0035] Furthermore, such as Figure 3 As shown, the motion device 5 includes a pull rod 51, an eccentric wheel 52, and an electric motor 53. The electric motor is fixedly mounted on the frame, and the eccentric wheel is mounted on the electric motor. One end of the pull rod 51 is hinged to the eccentric wheel, and the other end is hinged to a boss 416 set on the test platform. Driven by the eccentric wheel, the test platform swings up and down around the frame along the rotation axis. This simulates the pitching and diving of an aircraft during actual flight, and allows for the measurement of the thrust and torque of the aircraft at different angles of attack.

[0036] Furthermore, such as Figure 1 As shown, a fixing plate 1 is provided at the bottom of the frame 2. Several ground nail holes 6 are symmetrically distributed on the fixing plate 1, and the frame is fixed to the ground through the ground nail holes.

[0037] The temperature-controlled electric propeller testing platform of this invention houses the motor inside a temperature-controlled chamber, which can simulate the changes in the motor's operating temperature at different flight altitudes. By combining a speed sensor, a pull sensor, and a torque sensor with a motion device, the push-pull force and torque generated by the motor driving the propeller in different positions at different temperatures can be accurately measured, thereby improving the realism and accuracy of the measurement.

[0038] Example 2

[0039] A test method for a temperature-controlled electric propeller testing system includes the following steps:

[0040] S1. The temperature is adjusted by the temperature control box 410 to simulate the working temperature environment of the motor when the aircraft is at different flight altitudes.

[0041] S2. Start the motor 49. The motor drive shaft 44 drives the propeller 45 to start rotating. The speed of the propeller is measured by the speed sensor 46 installed on the motor drive shaft. The torque generated by the propeller in flight attitude is measured by the torque sensor 47 fixedly installed between the bearing seats.

[0042] S3. The pulling force generated when the propeller 45 rotates drives the motor mounting base 43 to move along the guide rail through the slider. The motor mounting base drives the upper part of the push-pull force converter 412 to move through the tension rod 411, thereby driving the push-pull force converter to rotate around the hinge point. The lower end of the push-pull force converter is connected to the S-type tension sensor 414 to convert the pulling force generated when the propeller rotates into thrust, and the S-type tension sensor measures it.

[0043] S4. Start the electric motor 53 in the motion device 5. The electric motor drives the eccentric wheel to start working. Driven by the eccentric wheel, the test platform swings up and down around the frame with the rotating axis to simulate the pitching and diving of the aircraft in actual flight.

[0044] S5. Through coupling with the speed sensor 46, torque sensor 47, and S-type tension sensor 414, the motion parameters of the motor and propeller under different temperatures and tilt angles can be measured comprehensively and accurately.

[0045] Furthermore, during the testing process, the frame is fixed to the ground through the ground nail holes 6 on the fixing plate 1 to avoid the friction and displacement generated during the movement of the frame 2 affecting the measurement parameter data.

[0046] The above testing method overcomes the limitations of existing test benches, which can only test the power parameters of an aircraft in vertical flight. The test data is incomplete and cannot fully reflect the various performance parameters of the aircraft during flight. It also overcomes the lack of data on the changes in thrust and rotational speed of the propeller under different temperatures during flight. This invention can accurately test the torque and thrust generated under different temperatures and flight attitudes, accurately reflect the true motion parameters of the propeller, and has a simple, efficient and accurate structure.

[0047] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A test method for a temperature-controlled electric propeller testing system, characterized in that, The temperature-controlled electric propeller testing system includes a testing module, a support assembly, and a motion device (5); the testing module includes a testing platform (4) and a testing assembly set on the testing platform; the testing assembly includes a motor mounting base (43), a propeller (45), a speed sensor (46), a torque sensor (47), a motor (49), and a temperature control box (410); the support assembly includes a frame (2), and a rotating shaft (415) is set on the central axis of the frame (2); the testing platform (4) is hinged to the frame as a whole through the rotating shaft, and the testing platform can swing up and down around the rotating shaft (415) under the drive of the motion device (5); a guide rail (41) is fixedly installed on the testing platform (4), and the motor mounting base (43) is slidably set on the guide rail (41) through a slider (42), and can reciprocate along the guide rail; The test platform (4) is provided with a tension bracket (413) at the rear end. The middle part of the push-pull force converter (412) is hinged to the tension bracket. The S-type tension sensor (414) is fixedly installed at the tail of the test platform (4). The upper end of the push-pull force converter (412) is connected to the motor mounting base (43) through the tension rod (411), and the lower end of the push-pull force converter is connected to the S-type tension sensor (414). A temperature control box (410) is fixedly installed on the motor mounting base (43), and the motor (49) is installed inside the temperature control box; the temperature of the temperature control box is controllable and can simulate the temperature environment of the motor when the aircraft is flying at different altitudes; Two bearing seats (48) are fixedly provided on the motor mounting base (43), and the motor drive shaft (44) of the motor (49) extends under the support of the bearing seats (48); the propeller (45) is fixedly installed at the end of the motor drive shaft, and the torque sensor (47) is fixedly installed between the two bearing seats to detect the torque generated by the propeller in flight attitude. The motion device (5) includes a pull rod (51), an eccentric wheel (52), and an electric motor (53); the electric motor is fixedly mounted on the frame, and the eccentric wheel is mounted on the electric motor; one end of the pull rod (51) is hinged to the eccentric wheel, and the other end is hinged to the boss (416) set on the test platform. Driven by the eccentric wheel, the test platform swings up and down around the frame with the rotation axis. The testing method includes the following steps: S1. The temperature is adjusted by the temperature control box (410) to simulate the working temperature environment of the motor when the aircraft is at different flight altitudes; S2. Start the motor (49), the motor drive shaft (44) drives the propeller (45) to start rotating, the speed of the propeller is measured by the speed sensor (46) installed on the motor drive shaft, and the torque generated by the propeller in flight attitude is measured by the torque sensor (47) fixedly installed between the bearing seats. S3. The pulling force generated when the propeller (45) rotates drives the motor mounting base (43) to move along the guide rail through the slider. The motor mounting base drives the upper part of the push-pull force converter (412) to move through the tension rod (411), thereby driving the push-pull force converter to rotate around the hinge point. The lower end of the push-pull force converter is connected to the S-type tension sensor (414) to convert the pulling force generated when the propeller rotates into thrust, and measure it through the S-type tension sensor. S4. Start the electric motor (53) in the motion device (5). The electric motor drives the eccentric wheel to start working. Driven by the eccentric wheel, the test platform swings up and down around the frame with the rotating shaft to simulate the pitching and diving of the aircraft in actual flight. S5. By coupling with the speed sensor (46), torque sensor (47), and S-type tension sensor (414), the motion parameters of the motor and propeller under different temperatures and tilt angles can be measured comprehensively and accurately.

2. The test method for the temperature-controlled electric propeller test system according to claim 1, characterized in that: The test platform (4) is fixedly equipped with a propeller protective cover (3) at the front end to prevent the propeller from colliding with the frame during rotation and causing a safety accident; a speed sensor (46) is provided at the end of the motor drive shaft near the propeller protective cover (3) to detect the speed of the propeller in flight attitude.

3. The test method for the temperature-controlled electric propeller test system according to claim 1, characterized in that: The bottom of the frame (2) is provided with a fixing plate (1), and a number of ground nail holes (6) are symmetrically distributed on the fixing plate (1) to fix the frame to the ground.

4. The test method for the temperature-controlled electric propeller test system according to claim 1, characterized in that: During the test, the frame is fixed to the ground through the ground nail holes (6) on the fixed plate (1) to avoid the friction and displacement generated during the movement of the frame (2) affecting the measurement parameter data.

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