Device and method for testing thrust of ducted thruster

Abstract

The invention provides a ducted thruster thrust testing device and testing method. The thrust testing device comprises an air duct type mounting base, an axial linear moving platform, a ducted fan, an air inlet pipe, an air outlet pipe, an auxiliary fan and a pull pressure sensor assembly. The ducted fan comprises a ducted shell and a core assembly, the core assembly comprises a supporting guide vane, an impeller and a motor assembly, a linear cylindrical guide rail assembly is arranged between the supporting guide vane and the ducted shell, and the thrust value of the core assembly can be independently measured through the arrangement of the linear cylindrical guide rail assembly. The thrust value of the core assembly is compared with the overall thrust value of the ducted fan, and the influence of the ducted shell on the thrust is evaluated; if the overall thrust value is larger than the thrust value of the core assembly, it is indicated that the thrust of the ducted shell is increased; if the overall thrust value is smaller than the thrust value of the core assembly, it shows that the duct shell causes energy loss.

Description

Technical Field

[0001] This application relates to the field of thrust testing technology for ducted fans on low-altitude aircraft, specifically to a ducted thrust testing device and method. Background Technology

[0002] As the core power component of low-altitude aircraft, the thrust performance of ducted thrusters directly determines the flight stability, payload capacity, and endurance efficiency of the aircraft. Therefore, thrust testing is a key step in the research and development and optimization of ducted thrusters.

[0003] Existing ducted thrust testing devices primarily focus on measuring the overall thrust of the ducted fan. They typically employ a fixed installation method, rigidly connecting the ducted fan to the test bench and using sensors to collect the overall axial thrust during operation. However, these devices have significant technical limitations: the thrust of a ducted fan is contributed by both the aerodynamic work of its core components (impeller, guide vanes, and motor assembly) and the airflow rectification of the duct casing. Since the core components and the duct casing remain fixedly connected, it is impossible to separate and measure the thrust contributions of these two components.

[0004] Specifically, existing testing methods lack the ability to measure the thrust of core components independently of the duct housing. This results in only obtaining the overall thrust value of the ducted fan, failing to effectively obtain thrust data of the core components. Consequently, it is impossible to quantitatively assess the actual impact of the duct housing on thrust performance. This leads to a lack of accurate data support for the aerodynamic optimization design of the ducted fan, forcing it to rely on experience for blind adjustments, which seriously affects R&D efficiency and product performance improvement.

[0005] Meanwhile, existing testing equipment also suffers from insufficient versatility. Its fixed installation structure cannot be adapted to ducted fans of different diameters and models, leading to increased testing costs. Some thrust tests simulating flight conditions rely on large wind tunnel equipment, which not only occupies a lot of space and has high testing costs, but also has drawbacks such as complex testing procedures and long cycles, making it difficult to meet the needs of enterprises for routine R&D testing.

[0006] Therefore, developing a ducted thrust test device and method that can separate the measurement of core components from the overall thrust, quantify the influence of the duct shell, and is highly versatile and low in testing cost has become an urgent technical problem to be solved in this field. Summary of the Invention

[0007] In view of this, in order to solve the above-mentioned technical problems, the present invention provides a ducted thrust test device and test method that can separate the measurement of core components from the overall thrust, quantify the influence of the duct shell, and has strong versatility and low test cost.

[0008] To achieve the above objectives, one embodiment of this application provides a ducted thrust testing device, which includes: a duct-type mounting base, an axial linear moving platform, a ducted fan, an inlet pipe, an outlet pipe, an auxiliary fan, and a tension / compression sensor assembly; the tension / compression sensor assembly includes a tension / compression sensor and a first sensor mounting plate and a second sensor mounting plate for mounting the tension / compression sensor; The axial linear moving platform is mounted on the duct-type mounting base, and the ducted fan is fixed above the axial linear moving platform; the air inlet pipe and the air outlet pipe are respectively installed on both sides of the duct-type mounting base in the axial direction, and the tail end of the air outlet pipe is connected to the auxiliary fan. The ducted fan includes a duct housing and a core component. The core component includes a support guide vane, an impeller, and a motor assembly. A linear cylindrical guide rail assembly is provided between the support guide vane and the duct housing. When the linear cylindrical guide rail assembly is in a sliding state, the tension and compression sensors are mounted on the second mounting plate to independently measure the thrust of the core component and obtain the thrust value of the core component.

[0009] According to some embodiments of the ducted propeller thrust testing device of this application, when the linear cylindrical guide rail assembly is in a locked state, a tension and compression sensor is installed on the first sensor mounting plate to measure the overall thrust of the ducted fan and obtain the overall thrust value. The overall thrust value is then compared with the thrust value of the core component to obtain the result of the influence of the duct shell on the thrust.

[0010] According to some embodiments of the ducted thruster thrust testing device of this application, the effect of the duct housing on thrust includes: if the overall thrust value is greater than the thrust value of the core component, it indicates that the duct housing has increased the thrust; if the overall thrust value is less than the thrust value of the core component, it indicates that the duct housing has caused energy loss, thereby achieving a quantitative assessment of the impact of the duct housing structure on thrust performance.

[0011] According to some embodiments of the ducted propeller thrust testing device of this application, the linear cylindrical guide rail assembly includes a linear cylindrical guide rail and a slider adapted to the linear cylindrical guide rail, the slider is disposed at the top of the supporting guide vane, and the linear cylindrical guide rail is fixedly disposed on the duct housing.

[0012] According to some embodiments of the present application, the ducted thrust test device includes an outer wall surface and an inner wall surface. The inner wall surface is provided with a movable hole adapted to the slider, and the linear cylindrical guide rail is fixedly disposed in the outer wall surface.

[0013] According to some embodiments of the ducted thrust test device of this application, the gap between the movable hole and the slider in the length direction is 4-5mm, and the gap between the movable hole and the slider in the width direction is 2-3mm.

[0014] According to some embodiments of the ducted propeller thrust testing device of this application, the duct-type mounting base includes a duct, a mounting plate, a support plate, and a base; the diameter of the duct is 5-8 times the diameter of the ducted fan; the base is located at the bottom of the duct, the mounting plate is welded inside the duct and parallel to the plane of the base, and the support plate is welded to the lower part of the mounting plate; the first sensor mounting plate is located at both axial ends of the mounting plate, and the second sensor mounting plate is fixedly connected to the duct and correspondingly located at one end of the motor assembly; both the first sensor mounting plate and the second sensor mounting plate have oblong holes.

[0015] According to some embodiments of the ducted propeller thrust testing device of this application, the axial linear moving platform includes a guide rail mounting plate, a guide rail, and a ducted fan mounting plate; the guide rail mounting plate has U-shaped notches at both ends; the ducted fan mounting plate adopts a cross-shaped structure, with both ends folded downward at 90° to form a thrust collection surface, the folded edges of the thrust collection surface extending towards the U-shaped notches; the guide rail mounting plate is connected and fixed to the mounting plate of the duct-type mounting base by mounting screws, the mounting screws are equipped with mounting nuts, and the height of the axial linear moving platform can be changed by adjusting the mounting nuts.

[0016] Another embodiment of this application provides a thrust testing method based on the ducted thrust testing device described in any of the above embodiments. When testing the overall thrust of the ducted fan in forward and reverse rotation under simulated flight conditions, the testing method includes the following steps: S1: Lock the linear cylindrical guide rail assembly, assemble the duct-type mounting base, axial linear moving platform, and ducted fan, connect the inlet pipe, outlet pipe, and auxiliary fan, and install the tension and compression sensors on the first sensor mounting plate after calibration and connect them to the external display panel; calculate the operating point of the auxiliary fan according to the preset flight speed of the ducted fan, adjust the auxiliary fan to the operating point, and wait for the airflow to stabilize. S2: Turn on the ducted fan, adjust its forward rotation speed to the target value, and read the overall thrust value of the ducted fan at the corresponding speed through the external display panel of the tension and compression sensor; S3: Adjust the ducted fan to reverse direction and read the overall thrust value of each target speed in reverse direction through the external display panel of the tension and compression sensor.

[0017] According to the test method of some embodiments of this application, when testing the overall thrust of the ducted fan in forward and reverse rotation in a stationary state, the inlet pipe, outlet pipe and auxiliary fan are not assembled and connected in step S1, and the other steps remain unchanged.

[0018] According to the test method of some embodiments of this application, when testing the effect of the duct housing on the thrust, step S1 is replaced by S11: the linear cylindrical guide rail assembly is in a sliding state and the duct fan mounting plate is fixed; the tension and compression sensor is mounted on the second sensor mounting plate and connected to the rear tail cone of the core component through the force measuring screw; the length of the force measuring screw is adjusted so that the slider is at the center position of the moving hole on the inner wall of the duct. S21: Turn on the ducted fan, adjust its forward rotation speed to the target value, and read the thrust value of the core component of the ducted fan at the corresponding speed through the external display panel of the tension and compression sensor; S31: Adjust the ducted fan to reverse rotation, and read the thrust value of the core components at each target speed in reverse rotation through the external display panel of the tension / compression sensor; S41: Compare the thrust values ​​of the core components read in steps S21 and S31 with the overall thrust value of the ducted fan under the same conditions to obtain the result of the influence of the duct casing on the thrust.

[0019] According to the test method of some embodiments of this application, the effect of the duct housing on thrust includes: if the overall thrust value is greater than the thrust value of the core component, it indicates that the duct housing increases the thrust; if the overall thrust value is less than the thrust value of the core component, it indicates that the duct housing causes energy loss.

[0020] The beneficial effects of this invention are: This application provides a ducted thrust testing device and method. The thrust testing device includes a duct-type mounting base, an axial linear moving platform, a ducted fan, an inlet pipe, an outlet pipe, an auxiliary fan, and a tension / compression sensor assembly. The ducted fan includes a duct housing and a core component. The core component includes a support guide vane, an impeller, and a motor assembly. A linear cylindrical guide rail assembly is provided between the support guide vane and the duct housing. When the linear cylindrical guide rail assembly is in a sliding state, the tension / compression sensor is mounted on a second mounting plate to independently measure the thrust of the core component and obtain the thrust value of the core component. Furthermore, when the linear cylindrical guide rail assembly is in a locked state, a tension / compression sensor is installed on the first sensor mounting plate to measure the overall thrust of the ducted fan and obtain the overall thrust value. The thrust value of the core component is then compared with the overall thrust value to obtain the result of the duct housing's influence on the thrust: if the overall thrust value is greater than the thrust value of the core component, it indicates that the duct housing has increased the thrust; if the overall thrust value is less than the thrust value of the core component, it indicates that the duct housing has caused energy loss, thus achieving a quantitative assessment of the impact of the duct housing structure on thrust performance.

[0021] Furthermore, the axial linear moving platform and the duct-type mounting base are connected by mounting screws, allowing for height adjustment to accommodate ducted fans of different diameters and models, offering strong versatility. With the help of inlet / outlet ducts and a variable frequency auxiliary fan, it can accurately simulate airflow environments under different flight conditions without relying on a wind tunnel, significantly reducing testing costs and site requirements. Moreover, the testing process is simple, operation is convenient, and data reading is intuitive, shortening the product design and development cycle. Attached Figure Description

[0022] The following figures are provided to further illustrate this application and form part of this application. They are intended to be illustrative and explanatory only, and are not intended to limit the scope of the invention. In the figures: Figure 1 This is a schematic diagram of the ducted thrust test device under simulated flight conditions, as described in an embodiment of this application. Figure 2 This is a schematic diagram of a ducted propeller thrust testing device in a static state, according to another embodiment of this application. Figure 3 This is a schematic diagram of the structure of a linear cylindrical guide rail assembly provided at the top of the support guide vanes of a ducted fan in some embodiments of this application. Figure 4 This is a cross-sectional structural schematic diagram of a ducted fan used in some embodiments of this application; Figure 5 This is a schematic diagram of the structure of an axial linear moving platform according to some embodiments of this application; Figure 6 This is a schematic diagram of the installation structure of some embodiments of this application when testing the effect of the duct shell on thrust; Figure 7 for Figure 6 A magnified view of a section at point A in the middle; Figure 8 This is a flowchart of a test method for testing the overall thrust of a ducted fan in forward and reverse rotation during simulated flight, according to some embodiments of this application. Figure 9 This is a flowchart illustrating a test method for testing the overall thrust of a ducted fan in both forward and reverse rotation when the fan is stationary, according to some embodiments of this application. Figure 10 This is a flowchart of a test method for testing the effect of the duct shell on thrust in some embodiments of this application.

[0023] Figure label: 1. Air duct type mounting base; 11. Air duct; 12. Mounting plate; 13. Support plate; 14. Base foot; 120. Oblong hole; 2. Axial linear moving platform; 21. Guide rail mounting plate; 22. Ducted fan mounting plate; 23. Guide rail; 210. U-shaped notch; 221. Thrust collection surface; 24. Mounting screw; 25. Mounting nut; 3. Ducted fan; 30. Duct housing; 300. Moving hole; 301. Outer wall surface; 302. Inner wall surface; 31. Core component; 311. Impeller; 312. Support guide vane; 313. Motor assembly; 32. Linear cylindrical guide rail assembly; 321. Linear cylindrical guide rail; 322. Slider; 33. Rear tail cone; 4. Air inlet duct; 5. Air outlet duct; 6. Auxiliary fan; 7. Tension / compression sensor assembly; 71. Tension / compression sensor; 72. Sensor mounting plate; 721. First sensor mounting plate; 722. Second sensor mounting plate; 73. Force measuring screw; 74. Fixing screw. Detailed Implementation

[0024] The following illustrations will disclose several embodiments of this application, providing a clear and complete description of the technical solution of the present invention. The accompanying drawings, which constitute a part of this application, are used to provide a further understanding of the present invention. The illustrative embodiments and descriptions of the present invention are used to explain the present invention and do not constitute an improper limitation of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0025] In this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, without necessarily requiring or implying any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0026] The technical solutions of the various embodiments of this application can be combined with each other, but only if they are based on the ability of a person skilled in the art to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0027] The following are examples of specific implementation processes provided to illustrate the technical solutions to be protected in this application. However, this application may also be implemented in other ways different from those described herein. Those skilled in the art can implement this application by different technical means under the guidance of the concept of this application. Therefore, this application is not limited to the specific embodiments below.

[0028] The following is in conjunction with the appendix Figures 1-10 This application provides a detailed description of the specific implementation methods of the ducted thrust testing device and testing method, so that those skilled in the art can accurately understand and implement this technical solution.

[0029] Example 1 Combination Figures 1-7 As shown, the ducted thrust test device of this embodiment includes a duct-type mounting base 1, an axial linear moving platform 2, a ducted fan 3, an air inlet pipe 4, an air outlet pipe 5, an auxiliary fan 6, and a tension / compression sensor assembly 7. These components work together to achieve the core objectives of simulating real working conditions, accurate force measurement, and multi-functional testing. Specifically: the duct-type mounting base 1 serves as the overall support foundation, with its base 14 firmly attached to the ground for stable fixation. The internally welded mounting plate 12 is parallel to the plane of the base 14, providing a horizontal mounting reference for the axial linear moving platform 2. The lower support plate 13 further enhances the load-bearing strength of the mounting plate 12, preventing vibration from affecting data accuracy during testing. The axial linear moving platform 2 is fixed to the mounting plate 12 by mounting screws 24. Adjusting the mounting nut 25 allows for flexible changes in platform height, adapting to ducted fans 3 of different diameters and models, solving the problem of poor versatility in traditional devices. The ducted fan 3 is fixed to the ducted fan mounting plate 22 of the axial linear moving platform 2, ensuring the stability of the ducted fan 3's installation posture during testing. The air inlet duct 4 and the air outlet duct 5 are respectively installed on both sides of the axial direction of the duct-type mounting base 1. The tail of the air outlet duct 5 is sealed to the auxiliary fan 6 to form a controllable airflow channel, which can accurately simulate the airflow environment at different flight speeds without relying on expensive wind tunnel equipment. The first sensor mounting plate 721 of the tension and compression sensor assembly 7 is set at both ends of the mounting plate 12 axially, and the second sensor mounting plate 722 is fixed on the duct 11 and corresponds to one end of the motor assembly 313. Both mounting plates have waist-shaped holes 120 to facilitate fine adjustment of the position of the tension and compression sensor 71, ensuring that the force measurement direction is consistent with the thrust direction of the ducted fan 3, thereby improving the accuracy of force measurement.

[0030] Combination Figure 3 , Figure 4 As shown, the ducted fan 3 in this embodiment is the test object, which consists of a duct housing 30 and a core component 31 disposed inside the duct housing. The linear cylindrical guide rail assembly 32 is the key structure for realizing the thrust test of the separated core component, as detailed below: The core component 31 includes a support guide vane 312, an impeller 311, and a motor assembly 313. One end of the support guide vane 312 is fixedly connected to the motor assembly, and the other end (i.e., the end near the duct housing) is locked / slidably connected to the duct housing 30 through a linear cylindrical guide rail assembly 32. The linear cylindrical guide rail assembly 32 consists of a linear cylindrical guide rail 321 and a matching slider 322. The slider 322 is located at the top of the support guide vane 312. The linear cylindrical guide rail 321 is fixed inside the outer wall surface 301 of the duct housing 30, and stops are provided at both ends of the linear cylindrical guide rail to limit the displacement trajectory of the slider and prevent the slider from derailing.

[0031] The inner wall surface 302 of the duct housing 30 is provided with a movable hole 300 adapted to the slider 322. The movable hole 300 has a gap of 4-5mm in the length direction and a gap of 2-3mm in the width direction with the slider 322. This gap allows the core component 31 to make a small displacement relative to the duct housing 30.

[0032] This application does not limit the specific implementation structure for switching between the locked / sliding state between the linear cylindrical guide rail 321 and the slider 322 in the linear cylindrical guide rail assembly 32. In the prior art, as long as the locked / sliding state of the slider can be achieved, it is acceptable. For example, corresponding pin holes can be opened on the linear cylindrical guide rail 321 and the slider 322. The relative movement of the two can be locked by inserting the pin, and the sliding state can be switched by pulling out the pin.

[0033] Because the core components of ducted fans used in low-altitude aircraft are fixedly connected to the duct shell and cannot be displaced, otherwise structural failure would occur. However, this application's thrust testing device, in order to test the thrust data of the core component, breaks through conventional thinking and innovatively invents a displaceable structure between the core component and the duct shell. Specifically, a linear cylindrical guide rail assembly is set between the support guide vanes of the core component and the duct shell, achieving a lockable / sliding connection between the core component and the duct shell. When the linear cylindrical guide rail assembly is in a sliding state, the tension and compression sensors are mounted on the second mounting plate to independently measure the thrust of the core component. Furthermore, the thrust value of the core component is compared with the overall thrust value to obtain the influence of the duct shell on the thrust: if the overall thrust value is greater than the thrust value of the core component, it indicates that the duct shell increases the thrust; if the overall thrust value is less than the thrust value of the core component, it indicates that the duct shell causes energy loss. This achieves a quantitative assessment of the impact of the duct shell structure on thrust performance, providing data support for optimizing the design of ducted fans.

[0034] Specifically, the linear cylindrical guide rail assembly 32 described in this application embodiment is specifically configured in the thrust testing device and testing method of this application, and its specific functions are listed below: ① Thrust contribution of separating the duct shell and core components When the slider is in the sliding state, the duct housing is fixed, and the impeller, guide vanes, and motor assembly can move axially along the linear cylindrical guide rail. At this time, the thrust measured by the tension and compression sensors only reflects the aerodynamic performance of the core components (impeller, guide vanes, etc.), eliminating the interference from the duct housing structure (such as lip radius and curvature).

[0035] ② Quantitatively assess the impact of the duct shell on thrust. By comparing the overall thrust value and the core component thrust value under two identical conditions, the thrust gain or loss of the duct shell can be directly calculated, providing a basis for optimizing the aerodynamic shape of the ducted fan (such as lip radius and wall curvature).

[0036] ③Simplify the multivariate testing process The overall thrust and core component thrust can be compared by switching the slider's locked / sliding state, allowing for the measurement of core component thrust without disassembly. The thrust values ​​at different directions and speeds can be directly read using tension and compression sensor components at both ends of the wind tunnel mounting base, significantly improving testing efficiency, shortening the testing cycle, and reducing operational complexity. This solves the problem of separating the duct shell from the core component thrust in traditional wind tunnel testing, providing key technical support for low-cost, high-precision thrust performance analysis.

[0037] ④ By separating and testing the thrust data of the core components and combining it with the overall thrust value of the ducted fan, the specific impact of the duct shell structure on thrust performance can be quantitatively evaluated. If the overall thrust value is significantly greater than the core component thrust value, it indicates that the duct shell improves thrust through airflow rectification, such as by reducing airflow separation through the inner wall curvature design. If the overall thrust is less than the core component thrust, energy loss may be due to duct shell lip vortices or wall curvature design. By comparing the overall thrust value and the core component thrust value data, specific problems can be identified, and key structural parameters of the duct shell can be optimized, for example: Curvature of the inner and outer walls of the duct shell: By adjusting the curvature, the thrust changes under different conditions are tested to find the surface shape that makes the airflow velocity uniform and the pressure loss minimal, such as using NACA airfoil curves.

[0038] Lip radius: By comparing thrust data under different lip radii, the optimal radius value that can reduce inlet airflow distortion and improve intake efficiency is determined.

[0039] Guide vane quantity and angle: Optimize the installation angle and quantity of guide vanes by combining the thrust data of the core components.

[0040] Verifying the effectiveness of design improvements: During iterative optimization, the performance improvement of the ducted fan after the duct shell improvement can be directly verified by repeatedly testing the thrust of the core components and the overall thrust. This data-driven quantitative analysis avoids the blind spots of traditional experience-based design and makes the optimization of the ducted fan's aerodynamic shape more targeted.

[0041] Example 2 Based on Embodiment 1, as a preferred implementation method, such as Figure 2 As shown, the duct-type mounting base 1 includes a duct 11, a mounting plate 12, a support plate 13, and feet 14. The diameter of the duct 11 is set to 5-8 times the diameter of the ducted fan 3. This size design ensures that the airflow forms a stable flow field within the duct 11, avoiding airflow distortion due to excessively narrow flow channels, and ensuring that the airflow environment during simulated flight is consistent with that during actual flight. The mounting plate 12 and the support plate 13 are welded together to form a rigid support structure, which can withstand the vibration and thrust generated by the ducted fan 3 during operation, preventing base deformation that could lead to test reference deviation and ensuring the stability of long-term testing. The feet 14 are made of non-slip and wear-resistant material to increase friction with the ground, preventing overall displacement of the device during testing and further improving the reliability of test data.

[0042] Combination Figure 2 , Figure 5 As shown, the axial linear moving platform 2 includes a guide rail mounting plate 21, a guide rail 23, and a ducted fan mounting plate 22. The guide rail mounting plate 21 has U-shaped notches 210 at both ends. The ducted fan mounting plate 22 adopts a cross-shaped structure, with both ends bent downwards at 90° to form a thrust collection surface 221, extending towards the U-shaped notches 210. This thrust collection surface 221 can accurately receive the overall axial thrust generated by the ducted fan 3, while avoiding interference with the guide rail mounting plate 21. The guide rail mounting plate 21 and the mounting plate 12 are connected by mounting screws 24 and mounting nuts 25. The overall height of the axial linear moving platform 2 can be adjusted by rotating the mounting nuts 25, adapting to the testing of different models of ducted fans and significantly improving the versatility of the device.

[0043] Combination Figure 6 , Figure 7As shown, the tension / compression sensor assembly 7 includes a tension / compression sensor 71, a first sensor mounting plate 721, a second sensor mounting plate 722, a force-measuring screw 73, and a fixing screw 74. The fixing screw 74 is used to tighten and fix the duct fan mounting plate 22, ensuring the stability of the duct housing 30 position during the thrust influence test. The first sensor mounting plate 721 is used to mount the tension / compression sensor 71 to test the overall thrust and is fixedly connected to the mounting plate 12 to ensure the stability of the force measurement reference. The second sensor mounting plate 722 is used to mount the tension / compression sensor 71 and is connected to the rear tail cone 33 of the core component 31 through the force-measuring screw 73 to realize independent thrust testing of the core component 31. After calibration, the tension / compression sensor 71 is connected to an external display panel, which can read thrust data in real time, meeting the high-precision evaluation requirements of thrust performance during the R&D stage. The length of the force-measuring screw 73 is adjustable to ensure that the slider 322 is in the center position of the moving hole 300, avoiding interference of initial offset on the force measurement results.

[0044] Example 3 Based on the thrust testing devices in Embodiments 1 and 2 above, this application provides three core testing scenarios, and the implementation process of each scenario is as follows: (a) Overall thrust test of ducted fan in forward and reverse rotation under simulated flight conditions This test scenario uses auxiliary fan 6 to simulate flight airflow, enabling precise measurement of the thrust of ducted fan 3 in actual flight conditions. Figure 8 As shown, the steps are as follows: S1: Lock the linear cylindrical guide rail of the linear cylindrical guide rail assembly 32 to the slider to ensure that the duct housing 30 and the core component 31 are subjected to force synchronously, simulating the overall working state; assemble the air duct type mounting base 1, the axial linear moving platform 2 and the duct fan 3, and seal the connection between the air inlet pipe 4, the air outlet pipe 5 and the auxiliary fan 6; calibrate the tension and compression sensor 71 and install it on the first sensor mounting plate 721, and connect it to the external display panel; according to the preset flight speed of the duct fan 3 (e.g., 20m / s), obtain the operating condition point (e.g., air volume) of the auxiliary fan 6 through fluid dynamics calculation, adjust the auxiliary fan 6 to the operating condition point, such as by adjusting the speed through frequency conversion to achieve the required air volume operating condition, and wait for the airflow to stabilize; S2: After the airflow stabilizes, turn on the ducted fan 3 and adjust its forward rotation speed to the target value (e.g., 1000-5000rpm, set in 500rpm increments) through the motor controller. The tension and compression sensor 71 collects thrust data in real time and transmits it to the external display panel. Read the overall thrust value at each speed and record the data.

[0045] S3: Keep the auxiliary fan 6 operating condition unchanged, adjust the ducted fan 3 to reverse, adjust the speed according to the same speed gradient, and read the overall thrust value at each target speed through the external display panel to complete the overall thrust test in forward and reverse rotation during flight.

[0046] In this test scenario, the auxiliary fan 6, in conjunction with the inlet and outlet pipes, replaced the traditional wind tunnel, significantly reducing test costs; the locking design of the linear cylindrical guide rail assembly 32 ensures the testing of the overall thrust.

[0047] (ii) Overall thrust test of ducted fan in forward and reverse rotation under static state This test scenario is suitable for basic thrust testing that does not require simulated airflow, combined with Figure 9 As shown, the steps are as follows: S10: Lock the linear cylindrical guide rail assembly 32, assemble the duct-type mounting base 1, the axial linear moving platform 2 and the ducted fan 3, without connecting the air inlet pipe 4, the air outlet pipe 5 and the auxiliary fan 6, to ensure that the test environment is still air; install the calibrated tension and compression sensor 71 on the first sensor mounting plate 721 and connect it to the external display panel.

[0048] S20: Turn on the ducted fan 3, adjust the forward rotation speed to the target value, and read and record the overall thrust value at the corresponding speed through the external display panel.

[0049] S30: Adjust the ducted fan 3 to reverse, test at the same speed gradient, read and record the overall thrust value at each speed, and complete the static state test.

[0050] This test scenario omits the airflow simulation component. The height adjustment function of the axial linear moving platform 2 can be adapted to different product models, improving the versatility of the test.

[0051] (III) Quantitative testing of the influence of the duct shell on thrust This test scenario accurately assesses the structural contribution of the duct shell 30 by separating the thrust data from the core components and the duct shell, combined with... Figure 10 As shown, the steps are as follows: S11: Position the slider of the linear cylindrical guide rail assembly 32 in a sliding state; tighten the fixed duct fan mounting plate 22 by fixing screws 74 at both ends to ensure that the duct housing 30 remains stationary; install the tension / compression sensor 71 on the second sensor mounting plate 722, connect the tension / compression sensor 71 to the rear tail cone 33 of the core assembly 31 by force measuring screw 73, adjust the length of force measuring screw 73 to position the slider 322 at the center of the moving hole 300, and eliminate the initial force deviation.

[0052] S21: Turn on the ducted fan 3, adjust the forward rotation speed to the target value, and read and record the independent thrust value of the core component 31 at each speed through the external display panel.

[0053] S31: Adjust the ducted fan 3 to reverse, test at the same speed gradient, and read and record the independent thrust value of the core component 31 at each speed.

[0054] S41: Compare the thrust value of the core component recorded in steps S21 and S31 with the overall thrust value under the same conditions (flight / stationary, same rotation speed, same direction): If the overall thrust value is greater than the thrust value of the core component, it means that the duct shell 30 has increased the thrust through the airflow rectification effect; if the overall thrust value is less than the thrust value of the core component, it means that there is energy loss in the lip design, curvature design, etc. of the duct shell 30, and the structural parameters of the duct shell 30 can be optimized accordingly.

[0055] In this test scenario, the sliding state of the linear cylindrical guide rail assembly 32 enables the separation of the thrust contribution of the core component. The cooperation of the second sensor mounting plate 722, the tension and compression sensor 71, and the force measuring screw 73 ensures the accurate acquisition of the thrust of the core component. The comparative analysis results provide direct data support for the optimized design of the duct housing 30.

[0056] In summary, this application provides a ducted thrust testing device and method, which solves the problems of existing technologies such as reliance on wind tunnels for flight condition testing, limited functionality, and poor adaptability. Its advantages are as follows: ① It can simulate flight airflow without a wind tunnel. By using auxiliary fans and wind tunnels, the testing cost is reduced and the space occupied is small, meeting the routine testing needs of enterprises.

[0057] ② The switching between locked and sliding states of the linear cylindrical guide rail assembly enables multi-dimensional testing of overall thrust and core component thrust, improving testing efficiency and providing key technical support for low-cost, high-precision thrust performance analysis.

[0058] ③ The height adjustment function of the axial linear moving platform is compatible with different models of ducted fans, which is highly versatile and reduces equipment investment costs.

[0059] ④ Quantitatively assess the impact of the duct shell on thrust, providing accurate data for optimizing the duct shell's lip radius, curvature parameters, etc., avoiding the blindness of traditional experience-based design.

[0060] It should be noted that the descriptions of each embodiment in the above embodiments have different focuses. For parts that are not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0061] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.

[0062] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

[0063] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A ducted thrust test device, characterized in that, include: The system includes a duct-type mounting base, an axial linear moving platform, a ducted fan, an air inlet pipe, an air outlet pipe, an auxiliary fan, and a tension / compression sensor assembly; the tension / compression sensor assembly includes a tension / compression sensor and a first sensor mounting plate and a second sensor mounting plate for mounting the tension / compression sensor. The axial linear moving platform is mounted on the duct-type mounting base, and the ducted fan is fixed above the axial linear moving platform; the air inlet pipe and the air outlet pipe are respectively installed on both sides of the duct-type mounting base in the axial direction, and the tail end of the air outlet pipe is connected to the auxiliary fan. The ducted fan includes a duct housing and a core component. The core component includes a support guide vane, an impeller, and a motor assembly. A linear cylindrical guide rail assembly is provided between the support guide vane and the duct housing. When the linear cylindrical guide rail assembly is in a sliding state, the tension and compression sensors are mounted on the second mounting plate to independently measure the thrust of the core component and obtain the thrust value of the core component.

2. The ducted thrust test device as described in claim 1, characterized in that... When the linear cylindrical guide rail assembly is in a locked state, the tension and compression sensors are installed on the first sensor mounting plate to measure the overall thrust of the ducted fan and obtain the overall thrust value. The overall thrust value is then compared with the thrust value of the core component to obtain the result of the influence of the duct shell on the thrust.

3. The ducted thrust test device as described in claim 2, characterized in that, The impact of the duct shell on thrust includes the following: if the overall thrust value is greater than the thrust value of the core component, it indicates that the duct shell increases the thrust; if the overall thrust value is less than the thrust value of the core component, it indicates that the duct shell causes energy loss.

4. The ducted thrust test device as described in claim 1, characterized in that, The linear cylindrical guide rail assembly includes a linear cylindrical guide rail and a slider adapted to the linear cylindrical guide rail. The slider is disposed at the top of the supporting guide vane, and the linear cylindrical guide rail is fixedly disposed on the duct housing.

5. The ducted thrust test device as described in claim 2, characterized in that, The duct housing includes an outer wall and an inner wall. The inner wall has a movable hole adapted to the slider. The linear cylindrical guide rail is fixedly installed in the outer wall. The movable hole has a gap of 4-5mm in the length direction and a gap of 2-3mm in the width direction with the slider.

6. The ducted thrust test device as described in claim 1, characterized in that, The duct-type mounting base includes a duct, a mounting plate, a support plate, and a base; the diameter of the duct is 5-8 times the diameter of the ducted fan; the base is located at the bottom of the duct, the mounting plate is welded inside the duct and parallel to the plane of the base, and the support plate is welded to the lower part of the mounting plate; the first sensor mounting plate is located at both ends of the axial direction of the mounting plate, and the second sensor mounting plate is fixedly connected to the duct and correspondingly located at one end of the motor assembly; both the first sensor mounting plate and the second sensor mounting plate have oblong holes.

7. The ducted thrust test device as described in claim 6, characterized in that, The axial linear moving platform includes a guide rail mounting plate, a guide rail, and a ducted fan mounting plate. The guide rail mounting plate has U-shaped notches at both ends. The ducted fan mounting plate has a cross-shaped structure with both ends bent downwards at 90° to form a thrust collection surface, the bent edges of which extend towards the U-shaped notches. The guide rail mounting plate is connected and fixed to the mounting plate of the duct-type mounting base via mounting screws. The mounting screws are equipped with mounting nuts, and the height of the axial linear moving platform can be changed by adjusting the mounting nuts.

8. A thrust testing method based on the ducted thrust testing device according to any one of claims 1-7, characterized in that, When testing the overall thrust of a ducted fan in simulated flight conditions with forward and reverse rotation, the following steps are included: S1: Lock the linear cylindrical guide rail assembly, assemble the duct-type mounting base, axial linear moving platform, and ducted fan, connect the inlet pipe, outlet pipe, and auxiliary fan, and install the tension and compression sensors on the first sensor mounting plate after calibration and connect them to the external display panel; calculate the operating point of the auxiliary fan according to the preset flight speed of the ducted fan, adjust the auxiliary fan to the operating point, and wait for the airflow to stabilize. S2: Turn on the ducted fan, adjust its forward rotation speed to the target value, and read the overall thrust value of the ducted fan at the corresponding speed through the external display panel of the tension and compression sensor; S3: Adjust the ducted fan to reverse direction and read the overall thrust value of each target speed in reverse direction through the external display panel of the tension and compression sensor.

9. The test method as described in claim 8, characterized in that, When testing the overall thrust of the ducted fan in forward and reverse rotation while it is stationary, the inlet pipe, outlet pipe and auxiliary fan are not assembled and connected in step S1, and the other steps remain unchanged.

10. The test method as described in claim 8, characterized in that, When testing the effect of the duct housing on thrust, step S1 is replaced with S11: the linear cylindrical guide rail assembly is in a sliding state and the duct fan mounting plate is fixed; the tension and compression sensors are installed on the second sensor mounting plate and connected to the rear tail cone of the core component through the force measuring screw; the length of the force measuring screw is adjusted so that the slider is at the center of the moving hole on the inner wall of the duct. S21: Turn on the ducted fan, adjust its forward rotation speed to the target value, and read the thrust value of the core component of the ducted fan at the corresponding speed through the external display panel of the tension and compression sensor; S31: Adjust the ducted fan to reverse rotation, and read the thrust value of the core components at each target speed in reverse rotation through the external display panel of the tension / compression sensor; S41: The thrust value of the core component read in steps S21 and S31 is compared with the overall thrust value of the ducted fan under the same conditions to obtain the result of the influence of the duct casing on the thrust; the result of the influence of the duct casing on the thrust includes: if the overall thrust value is greater than the thrust value of the core component, it means that the duct casing has increased the thrust; if the overall thrust value is less than the thrust value of the core component, it means that the duct casing has caused energy loss.

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