CN-121994494-A - Ducted propeller thrust testing device and testing method

CN121994494ACN 121994494 ACN121994494 ACN 121994494ACN-121994494-A

Abstract

The application provides a duct propeller thrust testing device and a testing method, wherein the thrust testing device comprises a wind barrel type mounting base, an axial linear moving platform, a duct fan, an air inlet pipe, an air outlet pipe, an auxiliary fan and a pulling pressure sensor component, the duct fan comprises a duct shell and a core component, the core component comprises a supporting guide vane, an impeller and a motor component, a linear cylindrical guide rail component is arranged between the supporting guide vane and the duct shell, the thrust testing device can independently measure the thrust value of the core component through the arrangement of the linear cylindrical guide rail component, the thrust value of the core component is compared with the integral thrust value of the duct fan, the influence of the duct shell on thrust is evaluated, if the integral thrust value is larger than the thrust value of the core component, the duct shell is indicated to promote thrust, and if the integral thrust value is smaller than the thrust value of the core component, the duct shell is indicated to cause energy loss.

Inventors

DAI MEIJUN
ZHENG MENGLIN
WU SHAOWEN
ZHANG YU
HANG FEI

Assignees

浙江金盾风机股份有限公司
浙江涵翼智能推进科技有限公司

Dates

Publication Date: 20260508
Application Date: 20260203

Claims (10)

1. The ducted propeller thrust testing device is characterized by comprising 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 pulling pressure sensor assembly, wherein the pulling pressure sensor assembly comprises a pulling pressure sensor, a first sensor mounting plate and a second sensor mounting plate; The air inlet pipe and the air outlet pipe are respectively arranged in the axial directions of two sides of the air duct type mounting base, and the tail part of the air outlet pipe is connected with the auxiliary fan; The ducted fan comprises a ducted shell and a core component, wherein the core component comprises a supporting guide vane, an impeller and a motor component, a linear cylindrical guide rail component is arranged between the supporting guide vane and the ducted shell, when the linear cylindrical guide rail component is in a sliding state, the tension and pressure sensor is arranged on the second mounting plate, and the thrust of the core component is independently measured to obtain a thrust value of the core component.
2. The ducted propeller thrust testing device of claim 1, wherein when the linear cylindrical guide rail assembly is in a locked state, the pull pressure sensor is mounted on the first sensor mounting plate, the overall thrust of the ducted fan is measured to obtain an overall thrust value, and the overall thrust value and the core assembly thrust value are compared to obtain an impact result of the ducted housing on thrust.
3. The ducted propeller thrust testing device of claim 2, wherein the result of the impact of the ducted casing on the thrust includes an indication that the ducted casing has lifted the thrust if the overall thrust value is greater than the thrust value of the core assembly, and an indication that the ducted casing has resulted in energy loss if the overall thrust value is less than the thrust value of the core assembly.
4. The ducted propeller thrust testing device of claim 1, wherein the linear cylindrical guide rail assembly comprises a linear cylindrical guide rail and a slider adapted to the linear cylindrical guide rail, the slider is disposed at a top end of the support vane, and the linear cylindrical guide rail is fixedly disposed on the ducted housing.
5. The ducted propeller thrust testing device of claim 2, wherein the ducted casing comprises an outer wall surface and an inner wall surface, a moving hole site matched with the sliding block is formed in the inner wall surface, the linear cylindrical guide rail is fixedly arranged in the outer wall surface, a gap between the moving hole site and the sliding block in the length direction is 4-5mm, and a gap between the moving hole site and the sliding block in the width direction is 2-3mm.
6. The ducted propeller thrust testing device of claim 1, wherein the duct mounting base comprises a duct, a mounting plate, a supporting plate and a foot, the diameter of the duct is 5-8 times of that of a duct fan, the foot is arranged at the bottom of the duct, the mounting plate is welded inside the duct and is parallel to the plane of the foot, the supporting plate is welded at the lower part of the mounting plate, the first sensor mounting plate is arranged at two axial ends of the mounting plate, the second sensor mounting plate is fixedly connected to the duct and is correspondingly arranged at one end of the motor assembly, and waist-shaped holes are formed in the first sensor mounting plate and the second sensor mounting plate.
7. The ducted propeller thrust testing device of claim 6, wherein the axial linear moving platform comprises a guide rail mounting plate, a guide rail and a ducted fan mounting plate, wherein U-shaped notches are formed at two ends of the guide rail mounting plate, the ducted fan mounting plate is of a cross-shaped structure, two downward 90-degree folded edges form a thrust collecting surface, the folded edges of the thrust collecting surface extend to the U-shaped notches, the guide rail mounting plate and the mounting plate of the duct type mounting base are fixedly connected through a mounting screw, the mounting screw is provided with a mounting nut, and the height of the axial linear moving platform can be changed by adjusting the mounting nut.
8. A thrust testing method based on the ducted propeller thrust testing device of any one of claims 1 to 7, characterized by comprising the steps of, when testing the ducted fan to simulate the overall thrust of forward and reverse rotation in flight: S1, setting a linear cylindrical guide rail assembly in a locking state, assembling a wind barrel type mounting base, an axial linear moving platform and a ducted fan, connecting an air inlet pipe, an air outlet pipe and an auxiliary fan, and installing a pull pressure sensor on a first sensor mounting plate after calibration and connecting an external display panel; S2, starting the ducted fan, regulating the forward rotation speed of the ducted fan to a target value, and reading the integral thrust value of the ducted fan at the corresponding rotation speed through an external display panel of the pull pressure sensor; and S3, adjusting the ducted fan to a reverse rotation state, and reading the whole thrust value of each target rotating speed in the reverse rotation state through an external display panel of the pull pressure sensor.
9. The testing method of claim 8, wherein when testing the forward and reverse rotation integral thrust of the ducted fan in the static state, the air inlet pipe, the air outlet pipe and the auxiliary fan are not assembled and connected in step S1, and the rest steps are unchanged.
10. The test method of claim 8, wherein when the influence of the duct housing on the thrust is tested, step S1 is replaced by S11, wherein the linear cylindrical guide rail assembly is in a sliding state, and the duct fan mounting plate is fixed; s21, starting the ducted fan, regulating the forward rotation speed of the ducted fan to a target value, and reading the thrust value of a core component of the ducted fan at the corresponding rotation speed through an external display panel of the pull pressure sensor; S31, adjusting the ducted fan to a reverse rotation state, and reading thrust values of the core components of each target rotating speed in the reverse rotation state through an external display panel of the pull pressure sensor; s41, comparing the thrust value of the core component read in the steps S21 and S31 with the integral thrust value of the ducted fan in the same state to obtain the thrust influence result of the ducted shell, wherein the thrust influence result of the ducted shell comprises that if the integral thrust value is larger than the thrust value of the core component, the ducted shell promotes the thrust, and if the integral thrust value is smaller than the thrust value of the core component, the ducted shell causes energy loss.

Description

Ducted propeller thrust testing device and testing method Technical Field The application relates to the technical field of thrust testing of ducted fans on low-altitude aircrafts, in particular to a ducted propeller thrust testing device and a ducted propeller thrust testing method. Background The ducted propeller is used as a core power component of the low-altitude aircraft, and the thrust performance of the ducted propeller directly determines the flight stability, the loading capacity and the cruising efficiency of the aircraft, so that the thrust test is a key link in the research and development and optimization processes of the ducted propeller. The existing ducted propeller thrust testing device mainly focuses on measurement of the integral thrust of the ducted fan, the ducted fan is rigidly connected with a test bench in a fixed installation mode, and the integral axial thrust of the ducted fan during operation is collected through a sensor. However, the device has the obvious technical defects that the thrust of the ducted fan is jointly contributed by the pneumatic acting of the core component (impeller, supporting guide vane and motor component) and the airflow rectification of the ducted shell, but the core component of the ducted fan and the ducted shell are always in a fixed connection state, and the separation measurement of the thrust contribution of the core component and the ducted shell cannot be realized. Specifically, the existing test scheme lacks to enable the core assembly to independently perform thrust measurement relative to the duct shell, so that the whole thrust value of the duct fan can be obtained, the thrust data of the core assembly cannot be obtained effectively, the actual influence of the duct shell on the thrust performance cannot be evaluated quantitatively, the pneumatic appearance optimization design of the duct fan lacks accurate data support, blind adjustment can be performed only depending on experience, and research and development efficiency and product performance improvement are seriously affected. Meanwhile, the existing testing device has the problem of insufficient universality, the installation structure is fixed, ducted fans with different diameters and different models cannot be adapted, the testing cost is increased, the thrust testing of the partially simulated flight state depends on large wind tunnel equipment, the occupied space is large, the testing cost is high, the defects of complex testing flow, long period and the like are overcome, and the requirements of enterprise normalized research and development testing are difficult to meet. Therefore, developing a device and a method for testing the thrust of a ducted propeller, which can separate and measure the core component from the overall thrust and quantify the influence of the ducted shell, and has strong universality and low testing cost, becomes a technical problem to be solved in the current field. Disclosure of Invention In view of the above, in order to solve the above technical problems, the embodiment of the invention provides a ducted propeller thrust testing device and a testing method which can separate and measure a core component from an overall thrust and quantify the influence of a ducted casing, and have strong universality and low testing cost. In order to achieve the aim, the embodiment of the application provides a thrust testing device of a ducted propeller, which comprises a wind barrel 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, wherein the pull pressure sensor assembly comprises a pull pressure sensor, a first sensor mounting plate and a second sensor mounting plate; The air inlet pipe and the air outlet pipe are respectively arranged in the axial directions of two sides of the air duct type mounting base, and the tail part of the air outlet pipe is connected with the auxiliary fan; The ducted fan comprises a ducted shell and a core component, wherein the core component comprises a supporting guide vane, an impeller and a motor component, a linear cylindrical guide rail component is arranged between the supporting guide vane and the ducted shell, when the linear cylindrical guide rail component is in a sliding state, the tension and pressure sensor is arranged on the second mounting plate, and the thrust of the core component is independently measured to obtain a thrust value of the core component. According to the ducted propeller thrust testing device provided by some embodiments of the application, when the linear cylindrical guide rail assembly is in a locked state, the pull pressure sensor is arranged on the first sensor mounting plate, the integral thrust of the ducted fan is measured to obtain an integral thrust value, and the integral thrust value and the core assembly thrust value are compared to obtain an influence result of the ducted shell on t