High-speed airflow acting under metal skin dynamic load identification simulation device

Abstract

This invention belongs to the field of dynamic load identification experiments and relates to a simulation device for dynamic load identification of metal skin under high-speed airflow. It includes: an air duct, a support, a dynamic load identification component, and a two-dimensional scanning laser Doppler vibration meter. An opening is provided in the middle of the lower side plate of the air duct. The support is fixed to the lower side plate of the air duct around the opening, and the upper surface of the support is horizontal. The dynamic load identification component includes a truss member and an aerospace metal skin riveted to the upper surface of the truss member. The dynamic load identification component is fixed to the upper surface of the support. The two-dimensional scanning laser Doppler vibration meter is fixed directly below the opening and focused on the center of the aerospace metal skin. This invention can more closely approximate the actual stress state of aerospace metal skin, providing experimental data support for subsequent design and material selection.

Description

Technical Field

[0001] This utility model belongs to the field of dynamic load identification experiments, specifically relating to a simulation device for dynamic load identification of metal skin under high-speed airflow. Background Technology

[0002] Currently, for dynamic load identification tests of aerospace metal skin under high-speed airflow, the method is mostly to fix the square metal skin in the wind tunnel test section in a simply supported manner on four sides, and use a two-dimensional scanning laser Doppler vibration meter, resistance strain gauge or triaxial strain rose to collect the vibration data of the aerospace metal skin.

[0003] The above method can identify and analyze the dynamic load on aerospace metal skin under high-speed airflow, providing data for subsequent analysis of the fatigue resistance and strength of aerospace metal skin.

[0004] However, the experimental method described above differs from the actual way aircraft metal skin is fixed on aircraft. In reality, aircraft metal skin only withstands high-speed airflow disturbances on one side. Therefore, the current experimental design differs significantly from the actual situation, resulting in a difference between the dynamic load identification of aircraft metal skin and the dynamic load under actual conditions. This leads to significant errors in subsequent structural design and life estimation. Utility Model Content

[0005] To overcome the shortcomings of the aforementioned related technologies, this utility model proposes a dynamic load identification simulation device for metal skin under high-speed airflow, which can more closely approximate the actual stress state of aerospace metal skin and provide experimental data support for subsequent design and material selection.

[0006] To achieve the above technical objectives, this utility model provides a simulation device for identifying dynamic loads on metal skin under high-speed airflow. The simulation device includes: an air duct, a support frame, a dynamic load identification component, and a two-dimensional scanning laser Doppler vibration meter.

[0007] The air duct is a rectangular pipe structure, with a fan connected to one end of the air duct and an opening in the middle of the lower side plate of the air duct.

[0008] The bracket is connected to the lower side plate of the air duct, and the bracket is located around the opening, with the upper end face of the bracket being horizontal.

[0009] The dynamic load identification component includes a truss component and an aerospace metal skin riveted to the upper end face of the truss component. The dynamic load identification component is connected to the upper end face of the bracket.

[0010] The two-dimensional scanning laser Doppler vibration meter is installed directly below the opening, and the two-dimensional scanning laser Doppler vibration meter is focused on the center of the aerospace metal skin.

[0011] Preferably, the bracket includes: a front frame, a fixed frame, and a rear frame;

[0012] The fixing frame is a square frame, which is set around the perimeter of the opening and connected to the lower side plate of the air duct. The upper surface of the fixing frame is provided with multiple connection holes.

[0013] The front and rear frames are symmetrically arranged on both sides of the fixed frame. Both the front and rear frames are triangular structures. Two sets of adjacent sides of the front and rear frames are set as arc-shaped sidewalls, and the arc-shaped sidewalls are recessed into the front or rear frame. The arc-shaped sidewall of the front frame faces the side where the air duct is connected to the fan.

[0014] Preferably, the truss member includes: two crossbars and multiple trusses;

[0015] The two crossbars are arranged in parallel, and each crossbar has a fixing hole on one side that matches the connecting hole;

[0016] Multiple trusses are arranged in parallel between two crossbars, and each truss is provided with multiple rivet holes for connection with aerospace metal skin.

[0017] Preferably, the lower part of the air duct is provided with a box, and the opening of the air duct is located inside the box, and the two-dimensional scanning laser Doppler vibration meter is installed inside the box.

[0018] Preferably, the width of the air duct is greater than or equal to 2200mm; the distance between the arc-shaped sidewalls of the front and rear frames and their corresponding air duct side plates is 120mm to 200mm.

[0019] Preferably, three dynamic load identification elements are arranged sequentially on the fixing frame.

[0020] Preferably, rivets are arranged in an array on the aerospace metal skin, and the aerospace metal skin is fixedly connected to the truss by the rivets, and the distance between two adjacent rivets is 10mm~20mm.

[0021] The beneficial effects of this utility model are as follows:

[0022] This invention places a two-dimensional scanning laser Doppler vibration meter on the outside of the air duct and collects vibration data of the aerospace metal skin through an opening on the lower side plate of the air duct. This avoids the vibration of the two-dimensional scanning laser Doppler vibration meter caused by the high-speed airflow in the air duct, thus preventing data distortion.

[0023] Meanwhile, this utility model uses a dynamic load identification component to fix the aerospace metal skin to the truss component by simulating the riveting method in reality, and connect it to the fixed frame of the bracket. In this state, a dynamic load identification experiment under high-speed airflow can be carried out to obtain data that is closer to reality, providing more reliable data support for subsequent design. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a structural diagram of the present invention;

[0026] Figure 2 This is a structural diagram of the bracket of this utility model inside the air duct;

[0027] Figure 3 This is a schematic diagram of the support structure in this utility model;

[0028] Figure 4 This is a structural diagram of the dynamic load identification component of this utility model mounted on a bracket;

[0029] Figure 5 This is a structural diagram of the truss components of this utility model;

[0030] Figure 6 This is a structural diagram of the dynamic load identification component of this utility model. Detailed Implementation

[0031] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0032] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model 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, and therefore should not be construed as a limitation of this utility model; the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In addition, unless otherwise explicitly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood according to the specific circumstances.

[0033] like Figures 1 to 6 As shown, this utility model provides a simulation device for identifying dynamic loads on metal skin under high-speed airflow. The simulation device for identifying dynamic loads on metal skin under high-speed airflow includes: an air duct 1, a support 2, a dynamic load identification component 3, and a two-dimensional scanning laser Doppler vibration meter 4.

[0034] The air duct 1 is a rectangular pipe structure, with a fan connected to one end. An opening 11 is provided in the middle of the lower side plate of the air duct 1. The support 2 is connected to the lower side plate of the air duct 1 and is located around the opening 11. The upper surface of the support 2 is horizontal. The dynamic load identification component 3 includes a truss component 31 and an aviation metal skin 32 riveted to the upper surface of the truss component 31. The dynamic load identification component 3 is connected to the upper surface of the support 2. The two-dimensional scanning laser Doppler vibration meter 4 is installed directly below the opening 11 and is focused on the center of the aviation metal skin 32.

[0035] Specifically, in this embodiment, a fan provides airflow into the interior of the air duct 1, creating a high-speed airflow of 20~25m / s within the air duct 1. An airflow boundary layer is generated at the lower side plate of the air duct 1. To avoid the airflow boundary layer affecting the detection of the aerospace metal skin 32, this embodiment uses a bracket 2 to raise the aerospace metal skin 32. The aerospace metal skin 32 can be made of 0.8~1.5mm aluminum alloy square plate with a size of 600mm*600mm.

[0036] In this embodiment, the support 2 includes: a front frame 21, a fixed frame 22, and a rear frame 23; the fixed frame 22 is a square frame, the fixed frame 22 is disposed around the opening 11, and the fixed frame 22 is connected to the lower side plate of the air duct 1, and the upper surface of the fixed frame 22 is provided with multiple connection holes; the front frame 21 and the rear frame 23 are symmetrically disposed on both sides of the fixed frame 22, and both the front frame 21 and the rear frame 23 are triangular structures, and two sets of adjacent sides of the front frame 21 and the rear frame 23 are set as arc-shaped sidewalls, and the arc-shaped sidewalls are recessed into the interior of the front frame 21 or the rear frame 23; the arc-shaped sidewall of the front frame 21 faces the side of the air duct 1 connected to the fan, that is, during the inspection of the aviation metal skin 32, the arc-shaped sidewall of the front frame 21 faces the windward side, and the arc-shaped sidewall of the rear frame 23 faces the leeward side.

[0037] The width of the air duct 1 is greater than or equal to 2200mm; the distance between the arc-shaped sidewalls of the front frame 21 and the rear frame 23 and the side plate of the corresponding air duct 1 is 120mm~200mm.

[0038] Based on the above embodiments, the airflow of the air boundary layer is diverted by the front frame 21 to avoid causing large turbulence. At the same time, there is a gap of 120mm to 200mm between the two arc-shaped sidewalls of the front frame 21 and the side plate of the corresponding air duct 1, so that the diverted airflow of the air boundary layer can pass through, preventing the air boundary layer from flowing back or around and intruding into the middle of the fixed frame. Specifically, in this embodiment, the distance between the two sidewalls of the air duct 1 is 2200mm, and the distance between the arc-shaped sidewalls of the front frame 21 and the rear frame 23 and the side plate of the corresponding air duct 1 is 200mm. In addition, the height of the bracket 2 is not less than 100mm. In this embodiment, it can be 120mm, that is, the height of the front frame 21, the fixed frame 22 and the rear frame 23 are all 120mm.

[0039] In this embodiment, the truss component 31 includes: two crossbars 311 and a plurality of truss members 312; the two crossbars 311 are arranged in parallel, and each crossbar 311 has a fixing hole on one side that matches the connecting hole; the plurality of truss members 312 are arranged in parallel between the two crossbars 311, and each truss member 312 has a plurality of riveting holes for connecting with the aerospace metal skin 32; rivets are arranged in an array on the aerospace metal skin 32, and the aerospace metal skin 32 is fixedly connected to the truss members 312 by the rivets, and the distance between two adjacent rivets is 10mm~20mm.

[0040] In specific implementation, three dynamic load identification elements 3 are arranged sequentially on the fixed frame 22; the three dynamic load identification elements 3 are connected to the fixed frame 22 by bolts, and the opening 11 of the air duct 1 is covered by the bracket 2 and the dynamic load identification elements 3 to prevent the airflow in the air duct 1 from overflowing; at the same time, arranging the three dynamic load identification elements 3 side by side can minimize the impact of the dynamic load identification element 3 located in the middle on the return flow and flow around the airflow boundary layer.

[0041] In addition, a box is provided at the lower part of the air duct 1, and the opening 11 of the air duct 1 is located inside the box. The two-dimensional scanning laser Doppler vibration meter 4 is installed inside the box. In this embodiment, the box is not shown in the figure.

[0042] Adjust the two-dimensional scanning laser Doppler vibration meter 4 to focus on the center point of the aerospace metal skin 32; introduce high-speed airflow into the air duct 1 through a fan, and the aerospace metal skin 32 vibrates under the action of the high-speed airflow. Collect the vibration mode, vibration velocity and displacement distribution data of the aerospace metal skin 32 through the two-dimensional scanning laser Doppler vibration meter 4 to complete the experiment.

[0043] Finally, it should be noted that the above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A device for simulating dynamic load identification of metal skin under high-speed airflow, characterized in that, include: Air ducts, supports, dynamic load identification components, and two-dimensional scanning laser Doppler vibration meters; The air duct is a rectangular pipe structure, with a fan connected to one end of the air duct and an opening in the middle of the lower side plate of the air duct. The bracket is connected to the lower side plate of the air duct, and the bracket is located around the opening, with the upper end face of the bracket being horizontal. The dynamic load identification component includes a truss component and an aerospace metal skin riveted to the upper end face of the truss component. The dynamic load identification component is connected to the upper end face of the bracket. The two-dimensional scanning laser Doppler vibration meter is installed directly below the opening, and the two-dimensional scanning laser Doppler vibration meter is focused on the center of the aerospace metal skin.

2. The simulation device for identifying dynamic loads on metal skin under high-speed airflow as described in claim 1, characterized in that, The bracket includes: a front frame, a fixed frame, and a rear frame; The fixing frame is a square frame, which is set around the perimeter of the opening and connected to the lower side plate of the air duct. The upper surface of the fixing frame is provided with multiple connection holes. The front and rear frames are symmetrically arranged on both sides of the fixed frame. Both the front and rear frames are triangular structures. Two sets of adjacent sides of the front and rear frames are set as arc-shaped sidewalls, and the arc-shaped sidewalls are recessed into the front or rear frame. The arc-shaped sidewall of the front frame faces the side where the air duct is connected to the fan.

3. The simulation device for identifying dynamic loads on metal skin under high-speed airflow as described in claim 2, characterized in that, The truss components include: two crossbars and multiple trusses; The two crossbars are arranged in parallel, and each crossbar has a fixing hole on one side that matches the connecting hole; Multiple trusses are arranged in parallel between two crossbars, and each truss is provided with multiple rivet holes for connection with aerospace metal skin.

4. The dynamic load identification simulation device for metal skin under high-speed airflow according to claim 3, characterized in that, The lower part of the air duct is provided with a box, and the opening of the air duct is located inside the box. The two-dimensional scanning laser Doppler vibration meter is installed inside the box.

5. The simulation device for identifying dynamic loads on metal skin under high-speed airflow according to claim 4, characterized in that, The width of the air duct is greater than or equal to 2200mm; The distance between the arc-shaped sidewalls of the front and rear frames and their corresponding air duct side plates is 120mm to 200mm.

6. The simulation device for identifying dynamic loads on metal skin under high-speed airflow as described in claim 5, characterized in that, Three dynamic load identification components are arranged sequentially on the fixed frame.

7. The simulation device for identifying dynamic loads on metal skin under high-speed airflow as described in claim 6, characterized in that, The aerospace metal skin is arranged in an array of rivets, which are fixedly connected to the truss by the rivets, and the distance between two adjacent rivets is 10mm to 20mm.

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