An aerodynamic wind tunnel testing apparatus and method for aircraft cable cover components

Abstract

This invention provides an aerodynamic wind tunnel testing apparatus and method for an aircraft cable cover component, comprising an aircraft test model, a cable cover component, a six-component balance, a pressure measuring tube, and a wind tunnel support rod. The aircraft test model simulates the aircraft body, and the cable cover component is mounted on the aircraft test model. The six-component balance is connected to the cable cover component to measure the dimensionless six-component aerodynamic coefficients borne by the cable cover component. The detection end of the pressure measuring tube is located inside the cavity of the aircraft test model, and the acquisition end of the pressure measuring tube is connected to a wind tunnel data acquisition system to collect pressure data on the inner surface of the cable cover component. The wind tunnel support rod is connected to the aircraft test model to fix the aircraft test model to a wind tunnel variable angle of attack support. This invention enables accurate measurement of six-component loads and real-time correction of internal pressure interference to improve measurement accuracy and ensure the design reliability and flight safety of the aircraft.

Description

Technical Field

[0001] This invention relates to the field of aerodynamic measurement technology in wind tunnel testing, and in particular to an aerodynamic wind tunnel testing apparatus and method for a cable cover component of a rocket-shaped aircraft. Background Technology

[0002] In the development of aircraft, wind tunnel testing is a core method for obtaining their aerodynamic characteristics. For aircraft with rocket-like shapes, the cable cover component, as a prominent external part, affects the overall aerodynamic characteristics of the aircraft. Accurate measurement of the aerodynamic loads (forces and moments) on the cable cover component is directly related to the structural strength design and flight stability control of the aircraft, and therefore has significant engineering value.

[0003] Specifically, the cable cover component disrupts the aircraft's original axisymmetric layout, generating asymmetric aerodynamic forces, particularly roll moment, in high-speed airflow. This effect is significantly amplified during flight at high angles of attack and roll angles, potentially inducing roll oscillations and directly threatening flight stability. Simultaneously, the localized pressure field on the surface of the cable cover component generates pulsating loads, a significant contributing factor to structural fatigue failure. Accurate measurement of these aerodynamic loads is fundamental for fatigue life analysis. Furthermore, the lateral forces and yaw moments generated by the cable cover component interfere with the aircraft's attitude control, especially in the transonic phase, where aerodynamic disturbances can lead to flight trajectory deviations. Therefore, accurate aerodynamic data is crucial for guidance system compensation.

[0004] However, existing aerodynamic measurement technologies have significant limitations when applied to cable cover components. Traditional aerodynamic measurement methods typically use single-component roll moment balances, which can only measure torque in a single direction and cannot comprehensively capture the complete aerodynamic load on the cable cover component, making it difficult to assess its overall impact on the aircraft. The current method of directly measuring the forces on the cable cover component using a six-component balance ignores a critical source of interference: when airflow passes through the cable cover component, its internal pressure interferes with the balance's measurement results, leading to deviations between the measured values ​​and the actual aerodynamic loads. More importantly, existing measurement devices lack the ability to correct for internal pressure interference in real time, resulting in significant measurement errors that fail to meet the requirements of high-precision wind tunnel testing.

[0005] Measurement errors can lead to a series of serious consequences: underestimation of roll torque may result in insufficient design margins in the control system, making it impossible to suppress roll oscillations induced by cable housing components. Misjudgment of aerodynamic loads will directly affect structural design; underestimation may lead to insufficient material strength and structural failure, while overestimation will cause unnecessary weight increases and reduce aircraft performance. Inaccurate aerodynamic data can also affect key performance indicators such as the aircraft's lift-to-drag ratio, potentially leading to problems such as reduced range and decreased maneuverability.

[0006] Therefore, for the aerodynamic measurement of aircraft cable cover components, there is an urgent need for a technical solution that can accurately measure six-component loads and correct for internal pressure interference in real time, so as to improve measurement accuracy and ensure the design reliability and flight safety of the aircraft. Summary of the Invention

[0007] The primary objective of this invention is to provide an aerodynamic wind tunnel testing apparatus for aircraft cable cover components, which addresses the problem of insufficient accuracy caused by internal pressure interference in existing wind tunnel measurements of aircraft cable cover components.

[0008] The second objective of this invention is to provide an aerodynamic wind tunnel testing method for aircraft cable cover components.

[0009] This invention provides an aerodynamic wind tunnel testing apparatus for aircraft cable cover components, comprising: Aircraft test model, used to simulate the aircraft itself; The cable cover component is mounted on the aircraft test model; A six-component balance is connected to the cable cover component to measure the dimensionless six-component aerodynamic coefficients borne by the cable cover component, namely the normal force coefficient CN, the lateral force coefficient CZ, the axial force coefficient CA, the roll moment coefficient MXG1, the yaw moment coefficient MYG1, and the pitch moment coefficient MZG1, and transmits the measurement data to the wind tunnel data acquisition system. A pressure measuring tube, the detection end of which is arranged in the inner cavity of the aircraft test model, and the acquisition end of which is connected to the wind tunnel data acquisition system to collect pressure data on the inner surface of the cable cover component; The wind tunnel support rod is connected to the aircraft test model and is used to fix the aircraft test model on the wind tunnel test variable angle of attack support.

[0010] The aerodynamic wind tunnel testing apparatus for an aircraft cable cover component provided by the present invention further includes a balance support installed inside the aircraft test model, wherein the six-component balance is fixed between the aircraft test model and the cable cover component by the balance support.

[0011] According to the aerodynamic wind tunnel testing apparatus for an aircraft cable cover component provided by the present invention, the six-component balance includes a measuring end and a supporting end that are parallel to each other, and a connecting beam connecting the measuring end and the supporting end. The measuring end is fixedly connected to the cable cover component, and the supporting end is fixedly connected to the balance support.

[0012] According to the aerodynamic wind tunnel testing apparatus for an aircraft cable cover component provided by the present invention, the balance support is provided with a mounting groove for mounting the support end, the balance support and the support end are connected and fixed by a first screw, and the cable cover component and the measuring end are connected and fixed by a second screw.

[0013] According to the aerodynamic wind tunnel test apparatus for aircraft cable cover components provided by the present invention, the aircraft test model includes a projectile body with a hollow inner cavity and a projectile head fixedly connected to one end of the projectile body. The projectile body is cylindrical and the projectile head is conical. The balance support is fixedly installed in the inner cavity of the projectile body by a pin.

[0014] According to the aerodynamic wind tunnel testing apparatus for an aircraft cable cover component provided by the present invention, the cable cover component is an elongated strip structure with a length-to-width ratio of... Greater than 6; the cable cover component is connected to the measuring end of the six-component balance by at least two second screws.

[0015] According to the aerodynamic wind tunnel testing apparatus for an aircraft cable cover component provided by the present invention, when the aspect ratio of the cable cover component is... When the number is greater than 10, the number of the second screws satisfies the formula .

[0016] According to the aerodynamic wind tunnel testing apparatus for an aircraft cable cover component provided by the present invention, the cable cover component is provided with a thickened portion, the thickened portion is embedded in the projectile body, and the portion of the cable cover component protruding from the projectile body is consistent with the shape of the projectile body.

[0017] According to the aerodynamic wind tunnel testing apparatus for an aircraft cable cover component provided by the present invention, the detection end of the pressure measuring tube is disposed in the inner cavity of the projectile body near the inner surface of the cable cover component, and the wind tunnel support rod is provided with a chamber through which the pressure measuring tube passes.

[0018] The present invention also provides an aerodynamic wind tunnel testing method for aircraft cable cover components, employing the aforementioned aerodynamic wind tunnel testing apparatus for aircraft cable cover components, comprising the following steps: S1. Fix the aircraft test model to the wind tunnel test variable angle of attack support using wind tunnel support rods to ensure that the missile body axis of the aircraft test model is consistent with the airflow direction of the wind tunnel; S2. Start the wind tunnel to a stable operating condition and simultaneously collect force data from the six-component balance and internal pressure data from the pressure measuring tube; S3. The wind tunnel data acquisition system preprocesses the acquired data, removes outliers, takes the average value, and performs dimensionless processing. S4. Calculate the dimensionless pressure data corresponding to the internal pressure based on the inner force-bearing area of ​​the cable cover component. The measured values ​​of the six-component balance were then corrected to obtain the final corrected dimensionless aerodynamic load coefficient. The correction formula is as follows:

[0019]

[0020] in, and These are the normal force coefficient and pitching moment coefficient of the cable cover component after internal pressure correction; and These are the normal force coefficient and pitching moment coefficient of the cable cover component directly measured by the six-component balance, respectively; D is the distance between the center of the six-component balance and the center of mass G1 of the cable cover component in the X-axis direction; Lr is the dimensionless reference length.

[0021] This invention provides an aerodynamic wind tunnel testing apparatus for aircraft cable cover components. It is used for high-precision aerodynamic wind tunnel testing and measurement of cable cover components of rocket-shaped aircraft. By setting up a six-component balance, the dimensionless six-component aerodynamic coefficients of the cable cover component can be directly measured. By setting up a pressure measuring tube, the internal pressure data of the cable cover component's inner surface can be measured in real time by the pressure inside the aircraft test model. The wind tunnel data acquisition system processes the acquired dimensionless six-component aerodynamic coefficients and internal pressure data, thereby correcting for internal pressure interference in real time and eliminating the interference of internal pressure on the force measurement of the cable cover component, resulting in more accurate aerodynamic forces on the surface of the cable cover component. Therefore, this invention integrates six-component force measurement and internal pressure correction, enabling accurate measurement of six-component loads and real-time correction of internal pressure interference to improve measurement accuracy, ensure the design reliability and flight safety of the aircraft, and effectively solve the problem of high-precision measurement of small-load aerodynamic forces in cable cover components of rocket-shaped aircraft. Attached Figure Description

[0022] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the aerodynamic wind tunnel testing device for the cable cover component of an aircraft according to the present invention; Figure 2 for Figure 1 Sectional view along axis AA; Figure 3 for Figure 1 BB-direction sectional view; Figure 4 This is a schematic diagram showing the positional relationship between the coordinate axes of the six-component balance and the cable cover component.

[0024] Explanation of reference numerals in the attached figures: 1. Cable cover assembly; 2. Six-component balance; 201. Measuring end; 202. Support end; 203. Connecting beam; 3. Pressure measuring tube; 4. Wind tunnel support rod; 5. Wind tunnel data acquisition system; 6. Balance support; 7. First screw; 8. Second screw; 9. Projectile body; 10. Projectile head; 11. First pin; 12. Third screw; 13. Second pin. Detailed Implementation

[0025] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0026] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0027] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly; for example, they may refer to a fixed connection, a detachable connection, or an integral connection; they may refer to a mechanical connection or an electrical connection; they may refer to a direct connection or an indirect connection through an intermediate medium; and they may refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0028] like Figures 1 to 4As shown, the aerodynamic wind tunnel test apparatus for an aircraft cable cover component according to an embodiment of the present invention includes an aircraft test model, a cable cover component 1, a six-component balance 2, a pressure measuring tube 3, and a wind tunnel support rod 4.

[0029] The aircraft test model is used to simulate the aircraft body and provide an installation reference. The cable cover component 1 is installed on the aircraft test model and serves as the component under test for force measurement. The six-component balance 2 is connected to the cable cover component 1 and is used to measure the dimensionless six-component aerodynamic coefficients borne by the cable cover component 1, namely the normal force coefficient CN, the lateral force coefficient CZ, the axial force coefficient CA, the roll moment coefficient MXG1, the yaw moment coefficient MYG1, and the pitch moment coefficient MZG1, and transmits the measurement data to the wind tunnel data acquisition system 5.

[0030] The pressure measuring tube 3 has its detection end located inside the cavity of the aircraft test model, and its acquisition end is connected to the wind tunnel data acquisition system 5. This system is used to collect pressure data on the inner surface of the cable cover component 1 in real time, and the collected pressure data is used to correct the balance measurement value. The wind tunnel support rod 4 is connected to the aircraft test model and is used to fix the aircraft test model onto the wind tunnel test variable angle of attack support (not shown in the figure).

[0031] The aerodynamic wind tunnel testing device of this invention is used for high-precision aerodynamic wind tunnel testing and measurement of cable cover components of aircraft with rocket-like shapes. By setting a six-component balance 2, the six-component aerodynamic forces of the cable cover component 1 can be directly measured. By setting a pressure measuring tube 3, the internal pressure data of the inner surface of the cable cover component 1 can be measured in real time by the pressure inside the aircraft test model. The wind tunnel data acquisition system 5 can process the acquired six-component aerodynamic force data and internal pressure data, thereby correcting the internal pressure interference in real time, eliminating the interference of internal pressure on the force measurement of the cable cover component 1, and obtaining more accurate aerodynamic forces on the surface of the cable cover component 1.

[0032] Therefore, the aerodynamic wind tunnel test device of this invention can integrate six-component force measurement and internal pressure correction into one unit, enabling accurate measurement of six-component loads and real-time correction of internal pressure interference to improve measurement accuracy, ensure the design reliability and flight safety of the aircraft, and effectively solve the problem of high-precision measurement of small-load aerodynamic forces of cable cover components of rocket-shaped aircraft.

[0033] Furthermore, the aerodynamic wind tunnel testing apparatus for the aircraft cable cover component also includes a balance support 6 installed inside the aircraft test model. The six-component balance 2 is fixed between the aircraft test model and the cable cover component 1 via the balance support 6. The balance support 6 enables the stable and reliable installation and fixation of the six-component balance 2 inside the aircraft test model.

[0034] Specifically, the six-component balance 2 includes a measuring end 201 and a supporting end 202. The measuring end 201 and the supporting end 202 are arranged parallel to each other vertically, and are connected and fixedly connected by a connecting beam 203. The measuring end 201 is connected and fixedly connected to the cable cover component 1, and the supporting end 202 is connected and fixedly connected to the balance support 6.

[0035] Specifically, the balance support 6 is provided with a mounting groove for mounting the support end 202. The balance support 6 and the support end 202 are connected and fixed by the first screw 7, and the cable cover component 1 is connected and fixed to the measuring end 201 by the second screw 8.

[0036] Traditional balances use a cantilever support method to measure the force on the components, resulting in a small force-bearing surface between the components and the balance. In this embodiment, the support end 202 of the six-component balance 2 is installed in the groove of the balance support 6, and the measuring end 201 of the six-component balance 2 is directly connected to the cable cover component 1. While ensuring structural strength, the surface support method ensures the stability and accuracy of the balance measurement.

[0037] Specifically, the aircraft test model includes a missile body 9 with a hollow inner cavity and a warhead 10 fixedly connected to one end of the missile body 9. The missile body 9 is cylindrical and the warhead 10 is conical. The balance support 6 is installed and fixed to the inner cavity of the missile body 9 by a first pin 11 and a third screw 12.

[0038] Furthermore, the first end of the balance support 6 is located at the left end of the inner cavity of the projectile body 9, and the second end of the balance support 6 extends outside the inner cavity of the projectile body 9. A mounting cavity for installing the wind tunnel support rod 4 is provided at the second end of the balance support 6. The left end of the wind tunnel support rod 4 is fitted into this mounting cavity, and the wind tunnel support rod 4 is connected and fixed to the balance support 6 by a second pin 13. Because the balance support 6 is quickly fixed to each component using screws and pins, it facilitates experimental assembly and disassembly.

[0039] Specifically, the cable cover component 1 has a long strip structure, and the length-to-width ratio of the cable cover component 1 is... Greater than 6. The cable cover component 1 is connected and fixed to the measuring end 201 of the six-component balance 2 by at least two second screws 8.

[0040] When the length-to-width ratio of cable cover component 1 When the number is greater than 10, the number of second screws 8 satisfies the formula. This ensures a stable and reliable connection between the cable cover component 1 and the six-component balance 2.

[0041] Specifically, the cable cover component 1 has a thickened portion, which is embedded within the projectile body 9. The portion of the cable cover component 1 that protrudes from the projectile body 9 maintains the same shape as the actual projectile body. By using an embedded installation method, the cable cover component 1 can effectively prevent incoming gas from entering the inner cavity of the projectile body 9 and affecting the internal pressure measurement of the cable cover component 1.

[0042] Specifically, the detection end of the pressure measuring tube 3 is located inside the cavity of the projectile body 9, near the inner surface of the cable cover component 1. The wind tunnel support rod 4 has a chamber through which the pressure measuring tube 3 passes, allowing it to connect to the external wind tunnel data acquisition system 5 after passing through the wind tunnel support rod 4. By collecting the internal pressure data at the bottom of the cable cover component 1 through the pressure measuring tube 3, the measurement results of the six-component balance 2 can be corrected, eliminating the interference of internal pressure on the force measurement of the cable cover component 1, and obtaining a more accurate aerodynamic force on the surface of the cable cover component 1.

[0043] The specific assembly process of the aerodynamic wind tunnel testing device for aircraft cable cover components according to an embodiment of the present invention is as follows: The non-tested component is fixedly connected to the missile body 9 to ensure that the aerodynamic shape of the test model of the aircraft is consistent with the actual shape.

[0044] Install and fix the balance support 6 onto the projectile body 9, and then install and fix the six-component balance 2 between the balance support 6 and the cable cover component 1 with screws to ensure the connection strength between the components.

[0045] Arrange the pressure measuring tube 3 along the inner side of the cable cover component 1, so that the acquisition end of the pressure measuring tube 3 is close to the geometric center of the cable cover component 1, and connect the output end of the pressure measuring tube 3 to the wind tunnel data acquisition system 5.

[0046] This invention also provides an aerodynamic wind tunnel testing method for aircraft cable cover components, using the aerodynamic wind tunnel testing apparatus for aircraft cable cover components described in the above embodiments. The method specifically includes the following steps: The assembled aircraft test model is fixed to the wind tunnel test variable angle of attack bracket by wind tunnel support rod 4, and the aircraft test model is leveled by wind tunnel angle of attack mechanism to ensure that the missile axis of the aircraft test model is consistent with the airflow direction of the wind tunnel.

[0047] The wind tunnel is started up to a stable operating condition, allowing airflow to pass through the aerodynamic wind tunnel test device. A six-component balance 2 collects the force and torque data in real time, and through coordinate axis transformation and dimensionless processing, obtains the dimensionless force coefficients (CN, CZ, CA) and torque coefficients (MXG1, MYG1, MZG1) at the centroid G1 of the cable cover component in real time. Simultaneously, pressure measuring tube 3 collects the internal pressure on the inner surface of the cable cover component 1, obtaining dimensionless pressure data. ; The data is processed using the wind tunnel data acquisition system 5, utilizing dimensionless pressure data. The measured values ​​of the six-component balance are corrected to obtain the dimensionless aerodynamic load coefficient of the cable cover component.

[0048] The specific correction principle is as follows: According to the appendix Figure 4 The given coordinate system position diagram is corrected using the following formula:

[0049]

[0050] in, and These are the normal force coefficient and pitching moment coefficient of the cable cover component after internal pressure correction; and These are the normal force coefficient and pitching moment coefficient of the cable cover component directly measured by the six-component balance, respectively; D is the distance between the center of the six-component balance and the center of mass G1 of the cable cover component in the X-axis direction; Lr is the dimensionless reference length.

[0051] Assuming D = 0.15m and Lr = 1.2m, without using dimensionless pressure data... The test data at the centroid G1 of the modified cable cover component are shown in Table 1 below:

[0052] Table 1 shows the uncorrected test results for CN and MZG1. Dimensionless pressure data The test data at the centroid G1 of the modified cable cover component are shown in Table 2 below:

[0053] Table 2 shows the corrected test results for CN and MZG1. Therefore, it can be seen that the method of the present invention uses the pressure measuring tube 3 to measure the pressure on the inner surface of the cable cover component 1 and corrects the normal force CN and longitudinal moment MZG1 of the cable cover component 1, so as to obtain accurate force measurement test results on the surface of the cable cover component.

[0054] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention 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 or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aerodynamic wind tunnel test device for an aircraft cable shroud component, characterized by, include: Aircraft test model, used to simulate the aircraft itself; The cable cover component is mounted on the aircraft test model; A six-component balance is connected to the cable cover component to measure the dimensionless six-component aerodynamic coefficients borne by the cable cover component, namely the normal force coefficient CN, the lateral force coefficient CZ, the axial force coefficient CA, the roll moment coefficient MXG1, the yaw moment coefficient MYG1, and the pitch moment coefficient MZG1, and transmits the measurement data to the wind tunnel data acquisition system. A pressure measuring tube, the detection end of which is arranged in the inner cavity of the aircraft test model, and the acquisition end of which is connected to the wind tunnel data acquisition system, for collecting pressure data on the inner surface of the cable cover component; The wind tunnel support rod is connected to the aircraft test model and is used to fix the aircraft test model on the wind tunnel test variable angle of attack support.

2. The aerodynamic wind tunnel test apparatus for an aircraft cable shroud component of Claim 1, wherein, It also includes a balance support installed inside the aircraft test model, and the six-component balance is fixed between the aircraft test model and the cable cover component through the balance support.

3. The aerodynamic wind tunnel test apparatus for an aircraft cable shroud component of Claim 2, wherein, The six-component balance includes a measuring end, a supporting end, and a connecting beam connecting the measuring end and the supporting end. The measuring end is fixedly connected to the cable cover component, and the supporting end is fixedly connected to the balance support.

4. The aerodynamic wind tunnel test apparatus for an aircraft cable shroud component of Claim 3, wherein, The balance support is provided with a mounting groove for mounting the support end. The balance support and the support end are connected and fixed by a first screw. The cable cover component is connected and fixed to the measuring end by a second screw.

5. The apparatus according to claim 2, wherein, The aircraft test model includes a projectile body with a hollow inner cavity and a projectile head fixedly connected to one end of the projectile body. The projectile body is cylindrical and the projectile head is conical. The balance support is fixed to the inner cavity of the projectile body by means of pins.

6. The aerodynamic wind tunnel testing apparatus for aircraft cable cover components according to claim 4, characterized in that, The cable cover component has a long strip-shaped structure, and the aspect ratio of the cable cover component is... Greater than 6; the cable cover component is connected to the measuring end of the six-component balance by at least two second screws.

7. The aerodynamic wind tunnel testing apparatus for aircraft cable cover components according to claim 6, characterized in that, When the aspect ratio of the cable cover component When the number is greater than 10, the number of the second screws satisfies the formula .

8. The apparatus according to claim 5, wherein, The cable cover component has a thickened portion, in which the bullet body is embedded, and the portion of the cable cover component that protrudes from the bullet body maintains the same shape as the bullet body.

9. The apparatus of claim 5, wherein, The detection end of the pressure measuring tube is located in the inner cavity of the projectile body near the inner surface of the cable cover component, and the wind tunnel support rod is provided with a chamber through which the pressure measuring tube passes.

10. A method for aerodynamic wind tunnel testing of an aircraft cable shroud component using the aerodynamic wind tunnel testing device for an aircraft cable shroud component according to any one of claims 1 to 9, characterized in that Includes the following steps: S1. Fix the aircraft test model to the wind tunnel test variable angle of attack support using wind tunnel support rods to ensure that the missile body axis of the aircraft test model is consistent with the airflow direction of the wind tunnel; S2. Start the wind tunnel to a stable operating condition and simultaneously collect force data from the six-component balance and internal pressure data from the pressure measuring tube; S3. The wind tunnel data acquisition system preprocesses the acquired data, removes outliers, takes the average value, and performs dimensionless processing. S4. Calculate the dimensionless pressure data corresponding to the internal pressure based on the inner force-bearing area of ​​the cable cover component. The measured values ​​of the six-component balance were then corrected to obtain the final corrected dimensionless aerodynamic load coefficient. The correction formula is as follows: wherein, and are the corrected normal force coefficient and the corrected pitching moment coefficient of the cable cover component, respectively; and are the normal force coefficient and the pitching moment coefficient of the cable cover component measured directly by the six-component balance, respectively; D is the distance between the center of the six-component balance and the center of mass G1 of the cable cover component in the X-axis direction; and Lr is a non-dimensional coefficient reference length.

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