A large-size flight unit performance testing system and method

Abstract

This invention belongs to the field of flight vehicle design technology, specifically relating to a performance testing system and method for large-size flight units. The system includes a test bench, a drive motor, a sensor module, a rotor module, a data acquisition card, a motor controller, a cooling system, a power distribution device, and a host computer. The positions of the rotor module and drive motor are adjusted via an adjustable platform. The cooling system and power distribution device achieve heat dissipation and power supply for the drive motor. The host computer performs linearity tests, square wave step tests, frequency sweep tests, and thermal balance tests, thereby obtaining the performance parameters and safe operating boundaries of the large-size flight unit under different positions, voltages, and heat dissipation conditions. This invention considers the high voltage and high heat dissipation requirements of large-size flight units, and designs auxiliary systems such as a cooling system and a bidirectional power distribution device, making it more suitable for actual application scenarios of large-size flight units, with smaller testing errors and strong applicability.

Description

Technical Field

[0001] This invention belongs to the field of flight vehicle design technology, specifically relating to a large-size flight unit performance testing system and method. Background Technology

[0002] The flight unit is the core of a flying car, determining its performance and safety. Vertical takeoff and landing (VTOL) capabilities allow flying cars to take off and land flexibly in urban areas without a runway; an efficient flight unit ensures a smooth transition between VTOL and horizontal cruise, balancing hovering stability and high-speed flight efficiency. Redundant designs (such as distributed flight units) and intelligent control technologies (such as autonomous obstacle avoidance) enhance safety and reliability. Extensive performance bench testing is required to verify the flight unit's performance level, ensuring the flying car's safe operation. Currently, with the continuous evolution of technology and usage requirements, large-size electric flight units have gradually become one of the key technologies in the design of heavy-duty flying cars. Large-size electric flight units generally consist of two main parts: a drive motor and a rotor or ducted fan. Due to their large size, high power requirements, significant aerodynamic interference, and numerous auxiliary system components, the performance testing requirements for large-size electric flight units are high, difficult, and complex. Conventional small flight unit testing platforms have poor safety, large testing errors, and difficulty in meeting the testing requirements of auxiliary systems, failing to meet the rapid development needs of future heavy-duty flying cars.

[0003] Therefore, there is an urgent need for a large-size flight unit performance testing system and method. Summary of the Invention

[0004] (a) Technical problems to be solved The technical problem to be solved by this invention is: in view of the needs of the prior art, how to provide a large-size flight unit performance testing system and method to solve the problems of poor safety, large testing error and difficulty in meeting the testing requirements of auxiliary systems in the existing flight unit testing, improve the efficiency of large-size flight unit performance testing, and this method also has a very wide range of application prospects in the design and development of large-tonnage flying cars.

[0005] (II) Technical Solution To solve the above-mentioned technical problems, the present invention provides a large-size flight unit performance testing system, the system comprising: a test bench, a drive motor, a sensor module, a rotor module, a data acquisition card, a motor controller, a heat dissipation system, a power distribution device, and a host computer; The test bench is fixedly connected to the drive motor via bolts. The drive motor is connected to the sensor module via a flange. The sensor module is connected to the rotor module via a flange. The drive motor is connected to the motor controller via communication cables and power cables. The drive motor is connected to the cooling system via water pipes. The sensor module is connected to the data acquisition card via communication cables. The motor controller, data acquisition card, and cooling system are all connected to the host computer via communication cables. The power distribution device is connected to the cooling system and motor controller via power cables.

[0006] The host computer includes: a drive motor control module, a heat dissipation system control module, a data recording and display module, and a safety protection module; The safety protection module is used to preset protection values ​​for parameters such as tension, voltage, current, infrared temperature, commutation speed, photoelectric speed, total power, and amplitude displacement. When a certain type of real-time test value reaches the preset protection value, the safety protection module will activate the alarm function and lock the throttle.

[0007] The sensor module includes: a tension sensor, a speed sensor, a vibration sensor, and a noise sensor.

[0008] The heat dissipation system includes a water tank, an oil tank, a cooling fan, and a temperature sensor, which are used to meet the temperature control requirements of the cooling water for the drive motor.

[0009] The power distribution device includes a current control module, a voltage control module, and a bidirectional transmission module, used to meet the power requirements of the motor controller; the voltage control module has an adjustment range of 10V-1100V.

[0010] The test bench includes: a main frame, diagonal supports, side supports, an adjustable platform, a flight unit mounting platform, a flight unit mounting flange, a counterweight, and fixing bolts. An adjustable platform is provided on the upper part of the main frame of the test stand by means of a fixing bolt. A flight unit fixing platform is provided on the upper part of the adjustable platform. A flight unit fixing flange is provided on the upper part of the flight unit fixing platform by means of a bolt. The diagonal supports and side supports of the platform are used together to provide lateral support to the main frame of the platform on both the front and rear sides. Counterweights are fixedly installed on the left and right sides of the main frame of the test bench and at the bottom of the side supports of the test bench.

[0011] The main frame of the platform includes a base frame and a longitudinal frame; The base frame includes a base frame crossbeam, a base frame longitudinal beam, a base frame diagonal beam, and fixed feet; Three base frame crossbeams and five base frame longitudinal beams are perpendicularly intersected and fixedly connected to form a square frame in the form of a slatted skeleton. The two sides of the base frame crossbeams are fixedly connected to two base frame diagonal beams respectively. Fixed feet are installed at the bottom of the base frame, and counterweights are installed above the fixed feet; The longitudinal frame includes: longitudinal frame crossbeams, longitudinal frame longitudinal beams, longitudinal frame support beams, longitudinal frame diagonal beams, and longitudinal frame middle connecting beams; Two longitudinal frame beams are fixedly connected to two longitudinal frame longitudinal beams to form a rectangular frame. Each of the two diagonals of the rectangular frame is provided with a longitudinal frame support beam, and longitudinal frame diagonal beams are provided on both sides of the longitudinal frame where the longitudinal frame longitudinal beams are located. The connecting beam in the middle of the longitudinal frame is horizontally set at the connection point of the two longitudinal frame support beams, and its two ends are respectively connected to the longitudinal frame inclined beams on both sides. The longitudinal beam of the longitudinal frame is provided with a through hole for connection to the adjustable platform. The platform's diagonal supports are arranged in pairs, with the number of pairs matching the longitudinal beams of the base frame, and there are five pairs. On the square frame body formed by three base frame crossbeams and five base frame longitudinal beams, for each base frame longitudinal beam, among the three connection points formed by its connection with the three base frame crossbeams, the two connection points on both sides are each connected to the lower end of a platform diagonal support, and the upper ends of the two platform diagonal supports converge and connect to the connecting beam in the middle of the longitudinal frame. Since a pair of platform diagonal supports and a corresponding base frame longitudinal beam form the three sides of an equilateral triangle support structure, the vertex of the equilateral triangle support structure is located on the connecting beam in the middle of the longitudinal frame, and the two base points are located on the cross beam of the base frame. Similarly, the five pairs of platform diagonal supports and the five base frame longitudinal beams form five sets of equilateral triangular support structures, which are distributed at equal intervals on the connecting beams in the middle of the longitudinal frame and the crossbeams of the base frame.

[0012] The platform has two side supports, with the upper end connected to the middle part of the connecting beam in the middle of the longitudinal frame, and the lower end extending obliquely to the horizontal ground and fixed by bolts.

[0013] Furthermore, the present invention also provides a method for testing the performance of a large-size flight unit, which is implemented based on the aforementioned system, and the method includes the following steps: Step 1: Secure the adjustable platform to the test bench using the fixing bolts according to the test requirements; for flight unit tests that do not consider ground effect, the vertical distance between the adjustable platform and the base frame should be greater than 1 times the diameter of the rotor module. Step 2: Connect the test bench, drive motor, sensor module, rotor module, data acquisition card, motor controller, heat dissipation system, power distribution device, and host computer to the power supply cable, communication cable, and water pipe. Step 3: Design the output steady-state voltage U through the power distribution device, start the power distribution device, and supply power to the heat dissipation system and motor controller; Step 4: Design the coolant outlet temperature T of the heat dissipation system through the host computer to ensure the heat dissipation requirements of the drive motor; Step 5: Design the motor controller parameters through the host computer. First, start the linear test. The speed of the drive motor increases linearly from 0% to 100% at a certain fixed slope α. The torque-speed curve, thrust-speed curve, power-speed curve and data are obtained through the host computer. Step 6: Perform a square wave step test using the drive motor control module of the host computer; the drive motor speed input increases in steps from 0% to 100%, with a step gradient of... After reaching 100%, the thrust decreases stepwise. The dynamic characteristics of acceleration and deceleration at different speed positions are tested to obtain the corresponding output thrust curves and data. After data analysis, the parameters of afterburner time, initial settling time, and super-stable time are obtained. Step 7: Perform a frequency sweep test using the drive motor control module on the host computer; the drive motor speed input is varied from 50% to 75% according to the frequency. f Sine wave transformation was performed to obtain the speed-torque curve and speed-force curve; after data analysis, the system response time, power overshoot value and safety control frequency parameters were obtained. Step 8: Perform a thermal balance test using the drive motor control module of the host computer; the drive motor speed input increases linearly from 10% to 100%, pausing at 5% speed intervals. t For minutes, observe whether the motor temperature rises at this speed; record the speed, over-temperature running time, and inlet and outlet coolant temperatures at the final thermal equilibrium. Step 9: Change the output steady-state voltage U or the coolant outlet temperature T, and repeat the test content of steps 5-8 to obtain the flight unit performance parameters and safe operating boundaries under different voltage and heat dissipation conditions.

[0014] (III) Beneficial Effects Compared with the prior art, the present invention has the following beneficial effects: (1) The present invention provides a test bench with an adjustable platform, which can install flight units of different sizes. In particular, for large-sized flight units, the altitude can be adjusted according to requirements to carry out performance tests considering and not considering the influence of ground effect. The device is flexible and highly applicable.

[0015] (2) The present invention adopts a frame-type test bench and installs and fixes safety supports and counterweights in multiple directions to ensure the safety of large-size flight unit testing; at the same time, it adopts a vertical test bench, which has smaller testing errors and a testing environment that is more in line with actual application scenarios compared with conventional horizontal small test benches.

[0016] (3) The test system of the present invention takes into account the high voltage and high heat dissipation requirements of large-size flight units, and designs auxiliary systems such as heat dissipation system and bidirectional power distribution device, fully taking into account the actual application conditions of large-size flight units on flying cars; at the same time, by setting different auxiliary system boundaries, more comprehensive flight unit performance data and safe use boundaries are obtained, providing important data support for the flight test of flying cars.

[0017] (4) The test method proposed in this invention includes linear test, square wave step test and frequency sweep test, which can obtain the static characteristics and dynamic response characteristics of the flight unit, providing important data for the design of the flight controller control strategy of the flying car, thereby ensuring the flight stability and safety of the flying car.

[0018] (5) The above-mentioned system and speed measurement methods can be used in the research and development of flying cars, vertical take-off and landing vehicles, and unmanned aerial vehicles. The device is reliable and flexible, and the testing methods are comprehensive and reliable, which can effectively improve research and development efficiency. In addition, the obtained flight unit information can also provide strong support for applications such as health monitoring and structural fault diagnosis of flying cars, and has broad application prospects and benefits. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of a large-size flight unit performance testing system according to the present invention; Figure 2 This is an axial view of the test bench in this invention; Figure 3 This is a side view of the test bench in this invention; Figure 4 This is a top view of the test bench in this invention; Figure 5 This is a front view of the test bench in this invention; Figure 6 This is an axial view of the main frame of the test bench in this invention; Figure 7 This is an axial view of the base frame of the main frame of the test bench in this invention; Figure 8 This is a longitudinal frame axis view of the main frame of the test bench in this invention; Figure 9 This is a schematic diagram of the rotor module in an example of the present invention.

[0020] Figure 10 This is a schematic diagram of the linear test of the host computer flight unit in an example of the present invention.

[0021] Figure 11 This is a schematic diagram of the square wave step test of the host computer flight unit in an example of the present invention.

[0022] Figure 12 This is a schematic diagram of the frequency sweep test of the host computer flight unit in an example of the present invention.

[0023] Among them, 1-test bench, 2-drive motor, 3-sensor module, 4-rotor module, 5-data acquisition card, 6-motor controller, 7-heat dissipation system, 8-power distribution device, 9-host computer; 1-1-Main frame of the test bench, 1-2-Diagonal support of the test bench, 1-3-Side support of the test bench, 1-4-Adjustable platform, 1-5-Flight unit mounting platform, 1-6-Flight unit mounting flange, 1-7-Counterweight block, 1-8-Fixing and locking bolts; 1-1-1-Base frame, 1-1-2-Longitudinal frame; 1-1-1-1-Base frame crossbeam, 1-1-1-2-Base frame longitudinal beam, 1-1-1-3-Base frame diagonal beam, 1-1-1-4-Fixed feet; 1-1-2-1-Longitudinal frame crossbeam, 1-1-2-2-Longitudinal frame longitudinal beam, 1-1-2-3-Longitudinal frame support beam, 1-1-2-4-Longitudinal frame diagonal beam. Detailed Implementation

[0024] To make the objectives, contents, and advantages of the present invention clearer, the specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples.

[0025] To address the aforementioned technical problems, this invention provides a large-size flight unit performance testing system, such as... Figures 1-8 As shown, the system includes: a test bench, a drive motor, a sensor module, a rotor module, a data acquisition card, a motor controller, a heat dissipation system, a power distribution device, and a host computer; The test bench is fixedly connected to the drive motor via bolts. The drive motor is connected to the sensor module via a flange. The sensor module is connected to the rotor module via a flange. The drive motor is connected to the motor controller via communication cables and power cables. The drive motor is connected to the cooling system via water pipes. The sensor module is connected to the data acquisition card via communication cables. The motor controller, data acquisition card, and cooling system are all connected to the host computer via communication cables. The power distribution device is connected to the cooling system and motor controller via power cables.

[0026] The host computer includes: a drive motor control module, a heat dissipation system control module, a data recording and display module, and a safety protection module; The safety protection module is used to preset protection values ​​for parameters such as tension, voltage, current, infrared temperature, commutation speed, photoelectric speed, total power, and amplitude displacement. When a certain real-time test value reaches the preset protection value, the safety protection module executes the alarm function (the real-time data display position flashes "red" and the device emits an alarm sound) and performs a throttle lock operation.

[0027] The sensor module includes: a tension sensor, a speed sensor, a vibration sensor, and a noise sensor.

[0028] The heat dissipation system includes a water tank, an oil tank, a cooling fan, and a temperature sensor, which are used to meet the temperature control requirements of the cooling water for the drive motor.

[0029] The power distribution device includes a current control module, a voltage control module, and a bidirectional transmission module, used to meet the power requirements of the motor controller; the voltage control module has an adjustment range of 10V-1100V.

[0030] The test bench includes: a main frame, diagonal supports, side supports, an adjustable platform, a flight unit mounting platform, a flight unit mounting flange, a counterweight, and fixing bolts. An adjustable platform is provided on the upper part of the main frame of the test stand by means of a fixing bolt. A flight unit fixing platform is provided on the upper part of the adjustable platform. A flight unit fixing flange is provided on the upper part of the flight unit fixing platform by means of a bolt. The diagonal supports and side supports of the platform are used together to provide lateral support to the main frame of the platform on both the front and rear sides. Counterweights are fixedly installed on the left and right sides of the main frame of the test bench and at the bottom of the side supports of the test bench.

[0031] The main frame of the platform includes a base frame and a longitudinal frame; The base frame includes a base frame crossbeam, a base frame longitudinal beam, a base frame diagonal beam, and fixed feet; Three base frame crossbeams and five base frame longitudinal beams are perpendicularly intersected and fixedly connected to form a square frame in the form of a slatted skeleton. The two sides of the base frame crossbeams are fixedly connected to two base frame diagonal beams respectively. Fixed feet are installed at the bottom of the base frame, and counterweights are installed above the fixed feet; The longitudinal frame includes: longitudinal frame crossbeams, longitudinal frame longitudinal beams, longitudinal frame support beams, longitudinal frame diagonal beams, and longitudinal frame middle connecting beams; Two longitudinal frame beams are fixedly connected to two longitudinal frame longitudinal beams to form a rectangular frame. Each of the two diagonals of the rectangular frame is provided with a longitudinal frame support beam, and longitudinal frame diagonal beams are provided on both sides of the longitudinal frame where the longitudinal frame longitudinal beams are located. The connecting beam in the middle of the longitudinal frame is horizontally set at the connection point of the two longitudinal frame support beams, and its two ends are respectively connected to the longitudinal frame inclined beams on both sides. The longitudinal beam of the longitudinal frame is provided with a through hole for connection to the adjustable platform. The platform's diagonal supports are arranged in pairs, with the number of pairs matching the longitudinal beams of the base frame, and there are five pairs. On the square frame body formed by three base frame crossbeams and five base frame longitudinal beams, for each base frame longitudinal beam, among the three connection points formed by its connection with the three base frame crossbeams, the two connection points on both sides are each connected to the lower end of a platform diagonal support, and the upper ends of the two platform diagonal supports converge and connect to the connecting beam in the middle of the longitudinal frame. Since a pair of platform diagonal supports and a corresponding base frame longitudinal beam form the three sides of an equilateral triangle support structure, the vertex of the equilateral triangle support structure is located on the connecting beam in the middle of the longitudinal frame, and the two base points are located on the cross beam of the base frame. Similarly, the five pairs of platform diagonal supports and the five base frame longitudinal beams form five sets of equilateral triangular support structures, which are distributed at equal intervals on the connecting beams in the middle of the longitudinal frame and the crossbeams of the base frame.

[0032] The number of inclined supports for the test bench can also be adjusted according to the test site.

[0033] The platform has two side supports, with the upper end connected to the middle part of the connecting beam in the middle of the longitudinal frame, and the lower end extending obliquely to the horizontal ground and fixed by bolts.

[0034] Furthermore, the present invention also provides a method for testing the performance of a large-size flight unit, which is implemented based on the aforementioned system, and the method includes the following steps: Step 1: Secure the adjustable platform to the test bench using the fixing bolts according to the test requirements; for flight unit tests that do not consider ground effect, the vertical distance between the adjustable platform and the base frame should be greater than 1 times the diameter of the rotor module. Step 2: Connect the test bench, drive motor, sensor module, rotor module, data acquisition card, motor controller, heat dissipation system, power distribution device, and host computer to the power supply cable, communication cable, and water pipe. Step 3: Design the output steady-state voltage U through the power distribution device, start the power distribution device, and supply power to the heat dissipation system and motor controller; Step 4: Design the coolant outlet temperature T of the heat dissipation system through the host computer to ensure the heat dissipation requirements of the drive motor; Step 5: Design the motor controller parameters through the host computer. First, start the linear test. The speed of the drive motor increases linearly from 0% to 100% at a certain fixed slope α. The torque-speed curve, thrust-speed curve, power-speed curve and data are obtained through the host computer. Step 6: Perform a square wave step test using the drive motor control module of the host computer; the drive motor speed input increases in steps from 0% to 100%, with a step gradient of... After reaching 100%, the thrust decreases stepwise. The dynamic characteristics of acceleration and deceleration at different speed positions are tested to obtain the corresponding output thrust curves and data. After data analysis, the parameters of afterburner time, initial settling time, and super-stable time are obtained. Step 7: Perform a frequency sweep test using the drive motor control module on the host computer; the drive motor speed input is varied from 50% to 75% according to the frequency. f Sine wave transformation was performed to obtain the speed-torque curve and speed-force curve; after data analysis, the system response time, power overshoot value and safety control frequency parameters were obtained. Step 8: Perform a thermal balance test using the drive motor control module of the host computer; the drive motor speed input increases linearly from 10% to 100%, pausing at 5% speed intervals. t For minutes, observe whether the motor temperature rises at this speed; record the speed, over-temperature running time, and inlet and outlet coolant temperatures at the final thermal equilibrium. Step 9: Change the output steady-state voltage U or the coolant outlet temperature T, and repeat the test content of steps 5-8 to obtain the flight unit performance parameters and safe operating boundaries under different voltage and heat dissipation conditions. Example

[0035] This embodiment provides a large-size flight unit performance testing system and method, and its specific testing process is as follows: like Figure 9As shown, the rotor module has a diameter of 2 meters. The static and dynamic response characteristics of the rotor are tested using the testing device of this invention, without considering the influence of ground effect. After mounting the rotor module, sensor module, and drive motor on the test bench, the adjustable platform is adjusted to a vertical distance of 2.5 meters from the base frame, and then fixedly connected to the test bench using locking bolts. The test bench is fixed in a preset location, and the four counterweights are set to a weight of 20 kg based on the rotor numerical simulation results. The drive motor and motor controller are then connected via communication and power cables. The drive motor and cooling system are connected via water pipes. The sensor module is connected to the data acquisition card via communication cables. The motor controller, data acquisition card, and cooling system are all connected to the host computer via communication cables. The power distribution device is connected to the cooling system and motor controller via power cables.

[0036] After verifying that the entire test system's connections and communication are normal, the power distribution device was activated to ensure a steady-state output voltage U of 900V, supplying power to the cooling system and motor controller. The coolant outlet temperature T of the cooling system was set to 65°C via the host computer. Motor controller parameters were designed via the host computer, and static linearity testing began first. The drive motor speed increased linearly from 0% to 100% with a fixed slope α of 50. The thrust-speed curve and power-speed curve were measured via the host computer, as shown below. Figure 10 As shown.

[0037] Then, a square wave step test is performed via the drive motor control module of the host computer. The speed input of the drive motor increases in steps from 0% to 100%, with a step gradient of... The initial value is 10%, and after reaching 100%, it decreases stepwise. The dynamic characteristics of acceleration and deceleration at different speed positions are tested to obtain corresponding output thrust curves and other data, such as... Figure 11 As shown. Data analysis revealed that the time from signal reception to performance stabilization was approximately 300ms. Frequency sweep testing was performed using the drive motor control module on the host computer. The drive motor speed input was varied between 50% and 75% according to the frequency. f A sinusoidal change was applied at 50Hz, incrementally, and the real-time response curves of rotational speed and tension were measured. Data analysis revealed that the system response time is approximately 500ms.

[0038] Finally, a thermal balance test was conducted using the drive motor control module on the host computer. The drive motor speed input was linearly increased from 10% to 100%, with a 20-minute pause at every 5% speed increment to observe whether the motor temperature rose at this speed. Information such as the speed at the final thermal balance, the over-temperature running time, and the inlet and outlet coolant temperatures were recorded. After completing one round of testing, the output steady-state voltage U or the coolant outlet temperature T is changed, and the static linearity test, square wave step test, frequency sweep test and thermal balance test are repeated to obtain the flight unit performance parameters and safe operating boundaries under different voltage and heat dissipation conditions.

[0039] Based on the flight unit performance information predicted by the above steps, further observation and analysis can be conducted to determine whether the flight unit meets the technical requirements, guiding the performance optimization design of flying cars. Furthermore, it can provide strong support for applications such as health monitoring and structural fault diagnosis of flying cars, demonstrating broad application prospects and benefits.

[0040] In summary, this invention belongs to the field of flying vehicle design technology, specifically relating to a performance testing system and method for large-size flying units. The system includes a test bench, a drive motor, a sensor module, a rotor module, a data acquisition card, a motor controller, a cooling system, a power distribution device, and a host computer. The positions of the rotor module and drive motor are adjusted via an adjustable platform. The cooling system and power distribution device achieve heat dissipation and power supply for the drive motor. The host computer performs linearity tests, square wave step tests, frequency sweep tests, and thermal balance tests, thereby obtaining performance parameters and safe operating boundaries of the large-size flying unit under different positions, voltages, and heat dissipation conditions. This invention considers the high voltage and high heat dissipation requirements of large-size flying units, and designs auxiliary systems such as a cooling system and a bidirectional power distribution device, making it more suitable for actual application scenarios of large-size flying units. It has smaller testing errors, strong applicability, and can provide important data support for the research, design, and testing of flying cars.

[0041] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for testing the performance of a large-size flight unit, characterized in that, The testing method is implemented based on a testing system, which includes: a test bench, a drive motor, a sensor module, a rotor module, a data acquisition card, a motor controller, a heat dissipation system, a power distribution device, and a host computer. The test bench is bolted to the drive motor, which is connected to the sensor module via a flange. The sensor module is connected to the rotor module via a flange. The drive motor is connected to the motor controller via communication and power cables. The drive motor is connected to the cooling system via water pipes. The sensor module is connected to the data acquisition card via communication cables. The motor controller, data acquisition card, and cooling system are all connected to the host computer via communication cables. The power distribution device is connected to the cooling system and motor controller via power cables. The test bench includes: main frame, diagonal support, side support, adjustable platform, flight unit mounting platform, flight unit mounting flange, counterweight, and fixing bolts. An adjustable platform is provided on the upper part of the main frame of the test stand by means of a fixing bolt. A flight unit fixing platform is provided on the upper part of the adjustable platform. A flight unit fixing flange is provided on the upper part of the flight unit fixing platform by means of a bolt. The diagonal supports and side supports of the platform are used together to provide lateral support to the main frame of the platform on both the front and rear sides. Counterweights are fixedly installed on the left and right sides of the main frame of the test bench and at the bottom of the side supports of the test bench. The main frame of the platform includes a base frame and a longitudinal frame; The base frame includes a base frame crossbeam, a base frame longitudinal beam, a base frame diagonal beam, and fixed feet; Three base frame crossbeams and five base frame longitudinal beams are perpendicularly intersected and fixedly connected to form a square frame in the form of a slatted skeleton. The two sides of the base frame crossbeams are fixedly connected to two base frame diagonal beams respectively. Fixed feet are installed at the bottom of the base frame, and counterweights are installed above the fixed feet; The longitudinal frame includes: longitudinal frame crossbeams, longitudinal frame longitudinal beams, longitudinal frame support beams, longitudinal frame diagonal beams, and longitudinal frame middle connecting beams; Two longitudinal frame beams are fixedly connected to two longitudinal frame longitudinal beams to form a rectangular frame. Each of the two diagonals of the rectangular frame is provided with a longitudinal frame support beam, and longitudinal frame diagonal beams are provided on both sides of the longitudinal frame where the longitudinal frame longitudinal beams are located. The connecting beam in the middle of the longitudinal frame is horizontally set at the connection point of the two longitudinal frame support beams, and its two ends are respectively connected to the longitudinal frame inclined beams on both sides. The longitudinal beams of the longitudinal frame are provided with through holes for connection to the adjustable platform; The method includes the following steps: Step 1: Secure the adjustable platform to the test bench using the fixing bolts according to the test requirements; for flight unit tests that do not consider ground effect, the vertical distance between the adjustable platform and the base frame should be greater than 1 times the diameter of the rotor module. Step 2: Connect the test bench, drive motor, sensor module, rotor module, data acquisition card, motor controller, heat dissipation system, power distribution device, and host computer to the power supply cable, communication cable, and water pipe. Step 3: Design the output steady-state voltage U through the power distribution device, start the power distribution device, and supply power to the heat dissipation system and motor controller; Step 4: Design the coolant outlet temperature T of the heat dissipation system through the host computer to ensure the heat dissipation requirements of the drive motor; Step 5: Design the motor controller parameters through the host computer. First, start the linear test. The speed of the drive motor increases linearly from 0% to 100% at a certain fixed slope α. The torque-speed curve, thrust-speed curve, power-speed curve and data are obtained through the host computer. Step 6: Perform a square wave step test using the drive motor control module of the host computer; the speed input of the drive motor increases stepwise from 0% to 100%, with a step gradient of φ, and decreases stepwise after reaching 100%. Test the dynamic characteristics of acceleration and deceleration at different speed positions to obtain the corresponding output thrust curve and data; after data analysis, obtain the parameters of acceleration time, initial stabilization time, and super stabilization time. Step 7: Perform a frequency sweep test using the drive motor control module on the host computer; the drive motor speed input is varied from 50% to 75% according to the frequency. f Sinusoidal changes were performed to obtain the speed-torque curve and the speed-force curve; after data analysis, the response time, power overshoot value, and safety control frequency parameters of the test system were obtained. Step 8: Perform a thermal balance test using the drive motor control module of the host computer; the drive motor speed input increases linearly from 10% to 100%, pausing at 5% speed intervals. t For minutes, observe whether the motor temperature rises at this speed; record the speed, over-temperature running time, and inlet and outlet coolant temperatures at the final thermal equilibrium. Step 9: Change the output steady-state voltage U or the coolant outlet temperature T, and repeat the test content of steps 5-8 to obtain the flight unit performance parameters and safe operating boundaries under different voltage and heat dissipation conditions.

2. The performance testing method for large-size flight units as described in claim 1, characterized in that, The host computer includes: a drive motor control module, a heat dissipation system control module, a data recording and display module, and a safety protection module; The safety protection module is used to preset protection values ​​for parameters such as tension, voltage, current, infrared temperature, commutation speed, photoelectric speed, total power, and amplitude displacement. When the real-time test value reaches the preset protection value, the safety protection module will activate the alarm function and lock the throttle.

3. The performance testing method for large-size flight units as described in claim 1, characterized in that, The sensor module includes: a tension sensor, a speed sensor, a vibration sensor, and a noise sensor.

4. The performance testing method for large-size flight units as described in claim 1, characterized in that, The heat dissipation system includes a water tank, an oil tank, a cooling fan, and a temperature sensor, which are used to meet the temperature control requirements of the cooling water for the drive motor.

5. The performance testing method for large-size flight units as described in claim 1, characterized in that, The power distribution device includes a current control module, a voltage control module, and a bidirectional transmission module, used to meet the power requirements of the motor controller; the voltage control module has an adjustment range of 10V-1100V.

6. The performance testing method for large-size flight units as described in claim 1, characterized in that, The platform diagonal supports are arranged in pairs, and the number of pairs matches the longitudinal beams of the base frame, with five pairs provided. On the square frame body formed by three base frame crossbeams and five base frame longitudinal beams, for each base frame longitudinal beam, among the three connection points formed by its connection with the three base frame crossbeams, the two connection points on both sides are each connected to the lower end of a platform diagonal support, and the upper ends of the two platform diagonal supports converge and connect to the connecting beam in the middle of the longitudinal frame. Since a pair of platform diagonal supports and a corresponding base frame longitudinal beam form the three sides of an equilateral triangle support structure, the vertex of the equilateral triangle support structure is located on the connecting beam in the middle of the longitudinal frame, and the two base points are located on the cross beam of the base frame. Similarly, the five pairs of platform diagonal supports and the five base frame longitudinal beams form five sets of equilateral triangular support structures, which are distributed at equal intervals on the connecting beams in the middle of the longitudinal frame and the crossbeams of the base frame.

7. The performance testing method for large-size flight units as described in claim 6, characterized in that, The platform has two side supports, the upper end of which is connected to the middle part of the connecting beam in the middle of the longitudinal frame, and the lower end extends obliquely to the horizontal ground and is fixed by bolts.

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