A wing strength detection device for a target drone

Abstract

This invention relates to a wing strength testing device for a target drone, comprising a main body, an airflow generating mechanism, an exhaust mechanism, and a testing assembly. The main body includes a working cylinder, a sealing cover, and an airflow collecting mechanism. A testing chamber is located inside the working cylinder, and a sealing cover is installed at one end of the working cylinder, sealing one end of the testing chamber. The airflow generating mechanism further includes a vortex fan, an axial fan, a solenoid valve, a connecting cylinder, a regulating fan, and a diffuser. This device achieves full coverage of three testing methods, encompassing high-altitude, low-temperature, low-pressure, low-altitude, high-speed, and low-temperature, low-pressure, high-speed flight environments, meeting diverse testing needs and providing comprehensive data for wing strength assessment.

Description

Technical Field

[0001] This invention belongs to the field of wing strength testing, specifically a wing strength testing device for a target drone. Background Technology

[0002] In the field of target drone wing strength testing, existing testing methods have certain basic functions, capable of simulating high-altitude, low-temperature, and low-pressure environments as well as low-altitude, high-speed flight environments, providing preliminary environmental simulation support for wing strength testing. However, with the continuous expansion of target drone application scenarios, the functional requirements for testing devices are becoming increasingly comprehensive, and existing technologies are gradually showing obvious functional limitations—they cannot simulate and test the complex and critical scenario of high-speed flight under low-temperature and low-pressure environments. This limitation makes it difficult for the test results to fully reflect the wing strength performance of the target drone in actual complex flight environments, and cannot provide complete data support for the design optimization and safety performance assessment of target drone wings. Therefore, a target drone wing strength testing device is proposed. Summary of the Invention

[0003] The purpose of this section is to outline some aspects of embodiments of the present invention and to briefly describe some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of this application, to avoid obscuring the purpose of these documents; however, such simplifications or omissions should not be construed as limiting the scope of the invention.

[0004] In view of the following technical problems existing in the prior art, in order to solve the above technical problems, the present invention provides the following technical solution: a target drone wing strength testing device. The existing testing device has a single function and cannot simultaneously simulate high-speed flight state under low temperature and low pressure environment, making it difficult to cover complex testing scenarios; during the testing process, the manifold and the inner wall of the sealed cover are prone to generating turbulent airflow and shock waves, which interfere with the airflow near the test components and affect the testing accuracy; the response to switching between different testing methods is slow, which is not conducive to saving energy and quickly testing different test pieces, and it is also difficult to simulate the rapid switching of flight state of the target drone.

[0005] To solve the above-mentioned technical problems, the present invention provides the following technical solution: a wing strength testing device for a target drone, comprising a main body, an airflow generating mechanism, an exhaust mechanism, and a testing assembly. The main body includes a working cylinder, a sealing cover, and a flow-collecting mechanism. A testing chamber is provided inside the working cylinder, and a sealing cover is installed at one end of the working cylinder, sealing one end of the testing chamber. The airflow generating mechanism further includes a vortex fan, an axial fan, a solenoid valve, a connecting cylinder, a regulating fan, and a diffuser. An axial fan is provided on one side of the working cylinder, and the outlet of the vortex fan is connected to the solenoid valve via a pipe. A connecting cylinder is provided at the other end of the working cylinder, and the portion of the connecting cylinder extending out of the working cylinder is fixedly connected to the solenoid valve. A regulating fan, which is horn-shaped, is provided at the end of the connecting cylinder furthest from the solenoid valve. The outer ring of the diffuser is connected to the inner wall of the testing chamber. The sealing cover is connected to the exhaust mechanism via the flow-collecting mechanism. Through the collaboration of multiple mechanisms and the design of a sealed testing chamber, a stable airflow simulation environment can be established. The horn-shaped regulating fan and the diffuser work together to ensure that the airflow evenly covers the testing area, providing a basic structural support for wing strength testing.

[0006] As a preferred technical solution for a target drone wing strength testing device, the exhaust mechanism includes a vacuum pump and a second air pipe, and the flow collection mechanism includes a connecting groove and a manifold seat. A connecting groove is provided on one side of the inner side of the sealed cover, and a manifold seat is provided on the outer side of the sealed cover. The manifold seat is connected to the connecting groove and has several connectors. These connectors are connected to the second air pipe. A vacuum pump is located on the outer side of the working cylinder and is connected to one end of the second air pipe. The connection structure between the connecting groove and the manifold seat enables directional airflow transmission. The multiple connectors are designed to adapt to different air pipe connection requirements. The vacuum pump, in conjunction with the second air pipe, can precisely control the air pressure inside the testing chamber, meeting the requirements for low-pressure environment simulation.

[0007] As a preferred technical solution for a target drone wing strength testing device, the main component also includes a support frame, with the support frame fixedly installed on the lower side of the working cylinder. The support frame provides stable lower support for the working cylinder, preventing it from tilting due to its own weight or forces during the testing process, ensuring the stability of the internal structure of the testing chamber, and improving the safety and accuracy of the testing process.

[0008] As a preferred technical solution for a target drone wing strength testing device, an annular groove is formed on the inner side of the testing cavity, and a testing component is rotatably connected to the annular groove. The rotatable connection structure between the annular groove and the testing component allows the position of the testing component to be adjusted around the circumference of the annular groove, facilitating the adjustment of the relative angle between the test piece and the airflow, and adapting to different testing posture requirements.

[0009] As a preferred technical solution for a target drone wing strength testing device, the testing assembly includes an adjusting ring, a connecting arm, a rotary reducer, an adjusting bracket, a vertical bracket, and a locking sleeve. The adjusting ring is rotatably connected to an annular groove, and several locking bolts are threaded onto the annular groove. The locking bolts are connected to a working cylinder. A connecting arm is located on the outer side of the rotary reducer and is fixedly connected to the adjusting ring. The output flange of the rotary reducer is fixedly connected to the adjusting bracket. A vertical bracket is located on one side of the adjusting bracket, and a motor is mounted on the vertical bracket. The power output end of the motor is connected to the locking sleeve through the reducer. A test piece is inserted into the locking sleeve. The adjusting ring and the annular groove cooperate to achieve circumferential adjustment. The rotary reducer and the adjusting bracket work together to control the angular accuracy. The insertion structure of the locking sleeve can firmly fix the test piece, preventing displacement of the test piece under airflow impact and ensuring accurate deformation test data.

[0010] As a preferred technical solution for a target drone wing strength testing device, a mounting plate is provided on the top of the adjustment ring, and a laser ranging matrix is ​​provided on the lower side of the mounting plate. The laser ranging matrix is ​​composed of a dense array of several laser ranging sensors. The mounting plate provides a stable mounting carrier for the laser ranging matrix, and the densely arrayed sensor structure can cover the entire detection surface of the test piece, realizing synchronous acquisition of deformation of various parts of the test piece, and improving the comprehensiveness and accuracy of deformation detection.

[0011] As a preferred technical solution for a target drone wing strength testing device, a parallel airflow assembly is provided at each end of the testing chamber, with the two parallel airflow assemblies arranged on both sides of the testing component. The parallel airflow assemblies at both ends of the testing chamber can regulate the airflow bidirectionally from the airflow inlet and outlet, avoiding airflow turbulence inside the testing chamber, ensuring stable airflow acting on the test piece, and reducing the impact of airflow interference on the test results.

[0012] As a preferred technical solution for a target drone wing strength testing device, the parallel airflow assembly includes a blade-shaped bracket, airflow adjustment cylinders, and a mounting arc plate. The blade-shaped bracket is vertically arranged, and multiple airflow adjustment cylinders are fixedly mounted on it. The diameter of the airflow adjustment cylinders increases sequentially from the inside to the outside. The mounting arc plate is mounted on the blade-shaped bracket and fits against the outer side of the testing chamber. Fixing bolts connect the mounting arc plate to the working cylinder. A blade-shaped bracket is located at the top and bottom of the parallel airflow assembly, and one edge of the airflow adjustment cylinder is streamlined. The gradually changing diameter of the airflow adjustment cylinder and the streamlined edge design reduce airflow resistance. The vertical arrangement of the blade-shaped bracket and the upper and lower double-bracket structure enhance the stability of the assembly. The close and fixed fit between the mounting arc plate and the working cylinder ensures that the assembly position does not shift, further improving the airflow regularization effect.

[0013] As a preferred technical solution for a target drone wing strength testing device, the exhaust mechanism also includes an air pipe 1 and a solenoid valve 3. The exhaust port of the vacuum pump is connected to the solenoid valve 3 through the air pipe 1. The solenoid valve 3 is also connected to another air pipe 1, which extends into the gas storage chamber. The combination structure of the two air pipes 1 and the solenoid valve 3 can realize the switching and control of the airflow path, which is convenient for adjusting the gas extraction path according to the testing requirements. At the same time, the air pipe 1 extending into the gas storage chamber can directly act on the gas in the gas storage chamber, improving the response speed of air pressure regulation.

[0014] As a preferred technical solution for a target drone wing strength testing device, the exhaust mechanism also includes a refrigerator, an evaporator, and a gas storage chamber. The gas storage chamber is located on one side of the diffusion stage, and a sealed box is installed at the top of the testing chamber. The sealed box and the inner wall of the working cylinder form the gas storage chamber. The refrigerator is located at the top of the working cylinder, and an evaporator is installed inside the refrigerator, extending into the gas storage chamber. The top of a second solenoid valve extends into the gas storage chamber, and the bottom of the second solenoid valve is connected to a connecting cylinder. The gas storage chamber formed by the sealed box and the working cylinder can store low-temperature gas. The evaporator extending into the gas storage chamber can directly cool the gas inside the chamber. The second solenoid valve, connecting the gas storage chamber and the connecting cylinder, can control the flow of low-temperature gas, providing structural protection for low-temperature environment simulation and simultaneously enabling the directional delivery of low-temperature gas.

[0015] The beneficial effects of the target drone wing strength testing device of the present invention are as follows: it achieves full coverage of three testing modes, encompassing high-altitude, low-temperature, low-pressure, low-altitude, high-speed, and low-temperature, low-pressure, high-speed flight environments, meeting diverse testing needs and providing comprehensive data for wing strength assessment; the parallel airflow component can make the airflow tend to be straight, avoiding turbulent airflow and shock wave interference in the testing area, and greatly restoring the interaction between the wing and the air during flight; by closing relevant solenoid valves to retain low-temperature gas, it can achieve rapid switching of testing modes, saving energy, improving testing efficiency, and accurately simulating the rapid switching of flight states of the target drone; the laser ranging matrix collects the deformation data of the test piece in real time, ensuring that the wing strength testing results are accurate and reliable, providing strong support for the design and safety performance assurance of the target drone wing. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Wherein:

[0017] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0018] Figure 2 This is a schematic cross-sectional view of the front of the present invention;

[0019] Figure 3 This is a schematic diagram of the cross-sectional structure of the side of the present invention. Figure 1 ;

[0020] Figure 4 This is a schematic diagram of the cross-sectional structure of the side of the present invention. Figure 2 ;

[0021] Figure 5 This is a schematic diagram of the parallel airflow assembly of the present invention;

[0022] Figure 6 This is a schematic diagram of the internal components of the refrigeration unit of the present invention.

[0023] Reference numerals: 100, Main body component; 101, Working cylinder; 102, Sealing cover; 103, Support frame; 104, Sealing box; 105, Annular groove; 106, Connecting groove; 107, Manifold; 200, Airflow generating mechanism; 201, Vortex fan; 202, Axial flow fan; 203, Solenoid valve one; 204, Connecting cylinder; 205, Regulating fan; 206, Diffuser platform; 300, Exhaust mechanism; 301, Vacuum pump; 302, Air pipe one; 303, Solenoid valve three; 304, Refrigeration unit; 305, Air pipe two 306. Pressure gauge; 307. Evaporator; 308. Gas storage chamber; 309. Solenoid valve II; 310. Condenser; 311. Compressor; 312. Expansion valve; 400. Testing and inspection components; 401. Adjusting ring; 402. Connecting arm; 403. Rotary reducer; 404. Adjusting bracket; 405. Vertical bracket; 406. Locking sleeve; 407. Laser ranging matrix; 500. Parallel airflow assembly; 501. Blade-shaped bracket; 502. Airflow adjusting cylinder; 503. Mounting arc plate; 600. Test piece. Detailed Implementation

[0024] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0025] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0026] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that is mutually exclusive with other embodiments.

[0027] Secondly, the present invention is described in detail with reference to the schematic diagrams. When detailing the embodiments of the present invention, for ease of explanation, the cross-sectional views illustrating the device structure may be partially enlarged, not according to the usual scale. Furthermore, the schematic diagrams are merely examples and should not limit the scope of protection of the present invention. In addition, actual fabrication should include three-dimensional spatial dimensions of length, width, and depth.

[0028] like Figures 1-6 As shown, this invention proposes a wing strength testing device for a target drone, comprising a main body 100, an airflow generating mechanism 200, an exhaust mechanism 300, and a testing assembly 400. The main body 100 includes a working cylinder 101, a sealing cover 102, and an airflow collecting mechanism. A testing chamber is provided inside the working cylinder 101, and the sealing cover 102 is installed at one end of the working cylinder 101, sealing one end of the testing chamber. The airflow generating mechanism 200 further includes a vortex fan 201, an axial flow fan 202, and a solenoid valve 203. The system includes a connecting cylinder 204, a regulating fan 205, and a diffuser 206. An axial flow fan 202 is provided on one side of the working cylinder 101. The outlet of the vortex fan 201 is connected to a solenoid valve 203 via a pipe. A connecting cylinder 204 is provided at the other end of the working cylinder 101. The part of the connecting cylinder 204 extending out of the working cylinder 101 is fixedly connected to the solenoid valve 203. A regulating fan 205 is provided at the end of the connecting cylinder 204 away from the solenoid valve 203. The regulating fan 205 is horn-shaped. The outer ring of the diffuser 206 is connected to the inner wall of the detection chamber.

[0029] The sealing cover 102 is connected to the exhaust mechanism 300 via a collection mechanism. The collection mechanism includes a connecting groove 106 and a manifold seat 107.

[0030] The exhaust mechanism 300 includes a vacuum pump 301 and a second air pipe 305. The flow collection mechanism includes a connecting groove 106 and a manifold seat 107. The connecting groove 106 is provided on one side of the inner side of the sealing cover 102, and the manifold seat 107 is provided on the outer side of the sealing cover 102. The manifold seat 107 is connected to the connecting groove 106. Several connectors are provided on the manifold seat 107, and the connectors of the manifold seat 107 are connected to the second air pipe 305. The vacuum pump 301 is provided on the outer side of the working cylinder 101, and the vacuum pump 301 is connected to one end of the second air pipe 305. The connection structure between the connecting groove and the manifold seat can realize the directional transmission of airflow. The multiple connectors are designed to adapt to different air pipe connection requirements. The vacuum pump and the second air pipe work together to accurately control the air pressure in the detection chamber and meet the requirements of low-pressure environment simulation.

[0031] The main component 100 also includes a support frame 103, which is fixedly installed on the lower side of the working cylinder 101. The support frame provides stable lower support for the working cylinder, preventing the working cylinder from tilting due to its own weight or the force exerted during the testing process, ensuring the stability of the internal structure of the testing chamber, and improving the safety and accuracy of the testing process.

[0032] An annular groove 105 is formed on the inner side of the detection chamber, and a detection test component 400 is rotatably connected to the annular groove 105. The rotatable connection structure between the annular groove and the detection test component allows the position of the detection test component to be adjusted around the circumference of the annular groove, which facilitates the adjustment of the relative angle between the test piece and the airflow and adapts to different detection posture requirements.

[0033] The testing assembly 400 includes an adjusting ring 401, a connecting arm 402, a rotary reducer 403, an adjusting bracket 404, a vertical bracket 405, and a locking sleeve 406. The adjusting ring 401 is rotatably connected to an annular groove 105. Several locking bolts are threaded onto the annular groove 105 and connected to the working cylinder 101. The connecting arm 402 is provided on the outer side of the rotary reducer 403 and is fixedly connected to the adjusting ring 401. The output flange of the rotary reducer 403 is fixedly connected to the adjusting bracket 404. A vertical bracket 405 is provided on one side of the adjusting bracket 404. A motor is provided on the vertical bracket 405, and the power output end of the motor is connected to the locking sleeve 406 through the reducer. A test piece 600 is inserted into the locking sleeve 406. The adjusting ring and the annular groove work together to achieve circumferential adjustment. The rotary reducer and the adjusting bracket work together to control the angle accuracy. The locking sleeve's plug-in structure can firmly fix the test piece, preventing the test piece from shifting under the impact of airflow and ensuring the accuracy of deformation test data.

[0034] A mounting plate is provided on the top of the adjusting ring 401, and a laser ranging matrix 407 is provided on the lower side of the mounting plate. The laser ranging matrix 407 is composed of a dense array of several laser ranging sensors. The mounting plate provides a stable mounting carrier for the laser ranging matrix, and the dense array of sensor structures can cover the entire detection surface of the test piece, realizing synchronous acquisition of deformation of various parts of the test piece, and improving the comprehensiveness and accuracy of deformation detection.

[0035] A parallel airflow assembly 500 is installed at each end of the detection chamber, with the two parallel airflow assemblies 500 positioned on either side of the detection test assembly 400. The parallel airflow assemblies at both ends of the detection chamber can regulate the airflow bidirectionally from the airflow inlet and outlet, preventing airflow turbulence inside the detection chamber, ensuring stable airflow acting on the test piece, and reducing the impact of airflow interference on the test results.

[0036] The parallel airflow assembly 500 includes a blade-shaped bracket 501, an airflow adjusting cylinder 502, and a mounting arc plate 503. The blade-shaped bracket 501 is vertically arranged, and multiple airflow adjusting cylinders 502 are fixedly mounted on it. The diameter of the airflow adjusting cylinders 502 increases from the inside to the outside. The mounting arc plate 503 is mounted on the blade-shaped bracket 501 and fits against the outer side of the detection chamber. The mounting arc plate 503 is connected to the working cylinder 101 by fixing bolts. A blade-shaped bracket 501 is set at the top and bottom of the parallel airflow assembly 500, and one edge of the airflow adjusting cylinder 502 is streamlined. The gradually changing diameter of the airflow adjusting cylinder and the streamlined edge design can reduce airflow resistance. The vertical arrangement of the blade-shaped bracket and the upper and lower double bracket structure enhance the stability of the assembly. The fit and fixation of the mounting arc plate with the working cylinder ensures that the position of the assembly does not shift, further improving the airflow regularization effect. The side of the blade-shaped bracket 501 facing the axial flow fan 202 is a blade.

[0037] The exhaust mechanism 300 also includes a first air pipe 302 and a third solenoid valve 303. The outlet of the vacuum pump 301 is connected to the third solenoid valve 303 via the first air pipe 302. The third solenoid valve 303 is also connected to another first air pipe 302, which extends into the gas storage chamber 308. The combination of the two first air pipes and the third solenoid valve allows for switching and control of the airflow path, facilitating adjustment of the gas extraction path according to testing requirements. Simultaneously, the first air pipe extending into the gas storage chamber directly acts on the gas within, improving the response speed of pressure regulation. A pressure gauge 306 is installed on the second air pipe 305 for real-time monitoring of the gas pressure within it. The locking sleeve 406's insertion and engagement structure securely fixes the test piece 600. The cryogenic gas is stored in the gas storage chamber 308, maintaining the low-temperature environment for the next test, achieving a pre-cooling function, and reducing the cooling time for the next test.

[0038] The exhaust mechanism 300 also includes a refrigerator 304, an evaporator 307, and a gas storage chamber 308. The gas storage chamber 308 is located on one side of the diffusion stage 206. A sealed box 104 is located at the top of the detection chamber. The sealed box 104 and the inner wall of the working cylinder 101 form the gas storage chamber 308. The refrigerator 304 is located at the top of the working cylinder 101. The evaporator 307 is located inside the refrigerator 304 and extends into the gas storage chamber 308. The top of the solenoid valve 309 extends into the gas storage chamber 308, and the bottom of the solenoid valve 309 is connected to the connecting cylinder 204. The gas storage chamber formed by the sealed box and the working cylinder can store low-temperature gas. The evaporator extending into the gas storage chamber can directly cool the gas inside. The solenoid valve 309 connects the gas storage chamber and the connecting cylinder to control the flow of low-temperature gas, providing structural support for low-temperature environment simulation and simultaneously enabling directional delivery of low-temperature gas.

[0039] The specific implementation method is as follows: the wing of the target aircraft, which serves as the test piece, is inserted into the locking sleeve 406. The locking sleeve 406 is provided with connecting bolts. The test piece 600 is locked to the locking sleeve 406 by the connecting bolts. The pitch angle of the test piece 600 is controlled by a motor. The rotary reducer 403 adjusts the angle between the test piece 600 and the detection airflow by controlling the rotation of the locking sleeve 406. The tilt angle of the test piece 600 on the locking sleeve 406 is controlled by the adjusting ring 401. The tilt angles include 30 degrees, 60 degrees, 90 degrees and 180 degrees.

[0040] The detection airflow is generated by regulating fan 205, and three detection methods are available:

[0041] 1. Similar to existing detection methods, first connect solenoid valve 303 to the outside environment. Use vacuum pump 301 and solenoid valve 303 to reduce the air pressure in the detection chamber. Then, open solenoid valve 209 and close solenoid valve 203. Use evaporator 307 to cool the air in storage chamber 308. Solenoid valve 303 connects two air pipes 1 302. A stable low-temperature airflow is formed through vacuum pump 301, air pipe 1 302, air pipe 2 305, storage chamber 308, solenoid valve 2 309, connecting cylinder 204 and diffuser 206 to keep the test piece 600 in a low-temperature and low-pressure state to simulate the low-temperature and low-pressure environment at high altitude.

[0042] 2. Similar to existing testing methods, solenoid valve 303 controls air pipe 205 to connect to the outside, solenoid valve 209 is closed, vacuum pump 301 operates at low power, and vortex fan 201 works in conjunction with regulating fan 205 to form a stable high-intensity airflow that blows onto the test piece, simulating low-altitude high-speed flight. Vacuum pump 301 promptly removes air and directly discharges it into the external environment, ensuring that the air pressure in the testing chamber is consistent with the low-altitude air pressure. The low-altitude range is 50 to 500 meters above sea level, and the low-altitude air pressure range is 90 to 101 kPa.

[0043] 3. Existing technical solutions cannot simultaneously simulate high-speed flight testing under low temperature and low pressure environments. To address the shortcomings of existing technologies, firstly, solenoid valve 303 is connected to the outside environment. Vacuum pump 301 and solenoid valve 303 are used to reduce the air pressure in the testing chamber. Then, solenoid valve 209 is opened, solenoid valve 203 is closed, and solenoid valve 303 is used to connect two air pipes 302. Adjusting fan 205 is started, so that the low-temperature airflow impacts the test piece 600 at high speed. Evaporator 307 in gas storage chamber 308 continuously cools the gas. Air pipe 205 and vacuum pump 301 continuously pump air to remove excess gas and maintain the low temperature of the testing chamber.

[0044] In addition, by closing solenoid valve 2 309 and controlling solenoid valve 3 303 to close the air pipe 1 302 connected to the air storage chamber 308, the low temperature gas is stored in the air storage chamber 308 to maintain the next test, which is equivalent to pre-cooling. The three test modes can be switched quickly. The quick switching is not only conducive to saving energy and quickly testing different test pieces, but also can simulate the rapid switching of flight status of the target drone.

[0045] The parallel airflow assembly 500 near the diffuser 206 makes the airflow tend to be straight, so that the test piece 600 is impacted by the same airflow and simulates flight. The parallel airflow assembly 500 away from the diffuser 206 makes the airflow passing through the test piece 600 return to straight, and reduces the airflow turbulence and shock wave interference on the airflow near the test piece 600 caused by the inner wall of the confluence seat 107 and the sealing cover 102.

[0046] The laser ranging matrix 407 detects the displacement and deformation of various parts of the test piece 600 during the test, thereby achieving the purpose of testing its strength. By recording and analyzing the displacement parameters, it is determined whether its strength meets the design requirements. The vortex fan 201 is equivalent to sucking in low-altitude gas, and its air pressure and temperature are similar to low-altitude flight, which helps to enhance the airflow intensity. The refrigerator 304 has a built-in compressor 311, condenser 310, expansion valve 312 and evaporator 307. Through the cyclic process of compressor 311 compressing refrigerant, condenser 310 dissipating heat, expansion valve 312 throttling and reducing pressure, and evaporator 307 absorbing heat, the gas in the gas storage chamber 308 is cooled.

[0047] It should be understood that numerous specific implementation decisions can be made during the development of any practical implementation, such as in any engineering or design project. Such development efforts may be complex and time-consuming, but for those skilled in the art who benefit from this disclosure, the development effort will be a routine work of design, manufacturing, and production without requiring much experimentation.

[0048] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A wing strength testing device for a target drone, characterized in that: It includes a main body component (100), an airflow generating mechanism (200), an exhaust mechanism (300), and a testing assembly (400). The main body component (100) includes a working cylinder (101), a sealing cover (102), and a flow collecting mechanism. The working cylinder (101) has a testing chamber on its inner side, and a sealing cover (102) is installed at one end of the working cylinder (101) to seal one end of the testing chamber. The airflow generating mechanism (200) also includes a vortex fan (201), an axial fan (202), a solenoid valve (203), a connecting cylinder (204), a regulating fan (205), and a diffuser (206). An axial fan (202) is provided on one side of the working cylinder (101). The outlet of the vortex fan (201) is connected to the solenoid valve (203) through a pipe. A connecting cylinder (204) is provided at the other end of the working cylinder (101). The part of the connecting cylinder (204) extending out of the working cylinder (101) is fixedly connected to the solenoid valve (203). A regulating fan (205) is provided at the end of the connecting cylinder (204) away from the solenoid valve (203). The regulating fan (205) is horn-shaped. The outer ring of the diffuser (206) is connected to the inner wall of the detection chamber. The sealing cover (102) is connected to the exhaust mechanism (300) through the collection mechanism. The exhaust mechanism (300) includes a vacuum pump (301) and a second air pipe (305). The collection mechanism includes a connecting groove (106) and a manifold (107). The connecting groove (106) is provided on one side of the inner side of the sealing cover (102). The manifold (107) is provided on the outer side of the sealing cover (102). The manifold (107) is connected to the connecting groove (106). Several connectors are provided on the manifold (107). The connectors of the manifold (107) are connected to the second air pipe (305). The vacuum pump (301) is provided on the outer side of the working cylinder (101). The vacuum pump (301) is connected to one end of the second air pipe (305). The exhaust mechanism (300) also includes a first air pipe (302) and a third solenoid valve (303). The exhaust port of the vacuum pump (301) is connected to the first air pipe (302). The solenoid valve is connected to the third solenoid valve (303), and another air pipe (302) is also connected to the third solenoid valve (303). The air pipe (302) extends into the gas storage chamber (308). The exhaust mechanism (300) also includes a refrigerator (304), an evaporator (307) and a gas storage chamber (308). The detection chamber is located on one side of the diffusion stage (206) and a gas storage chamber (308) is provided. A sealed box (104) is provided on the top of the detection chamber. The sealed box (104) and the inner wall of the working cylinder (101) form a gas storage chamber (308). The refrigerator (304) is located at the top of the working cylinder (101). An evaporator (307) is provided inside the refrigerator (304). The evaporator (307) extends into the gas storage chamber (308). The top of the second solenoid valve (309) extends into the gas storage chamber (308). The bottom of the second solenoid valve (309) is connected to the connecting cylinder (204).

2. The target drone wing strength testing device according to claim 1, characterized in that: The main component (100) also includes a support frame (103), and the support frame (103) is fixedly installed on the lower side of the working cylinder (101).

3. The target drone wing strength testing device according to claim 1, characterized in that: An annular groove (105) is provided on the inner side of the detection chamber, and a detection test assembly (400) is rotatably connected to the annular groove (105).

4. The target drone wing strength testing device according to claim 3, characterized in that: The test assembly (400) includes an adjusting ring (401), a connecting arm (402), a rotary reducer (403), an adjusting bracket (404), a vertical bracket (405), and a locking sleeve (406). The adjusting ring (401) is rotatably connected to the annular groove (105). Several locking bolts are threaded onto the annular groove (105). The locking bolts are connected to the working cylinder (101). The connecting arm (402) is provided on the outside of the rotary reducer (403). The connecting arm (402) is fixedly connected to the adjusting ring (401). The output flange of the rotary reducer (403) is fixedly connected to the adjusting bracket (404). A vertical bracket (405) is provided on one side of the adjusting bracket (404). A motor is provided on the vertical bracket (405). The power output end of the motor is connected to the locking sleeve (406) through the reducer. A test piece (600) is inserted into the locking sleeve (406).

5. The target drone wing strength testing device according to claim 4, characterized in that: The top of the adjustment ring (401) is provided with a mounting plate, and the lower side of the mounting plate is provided with a laser ranging matrix (407), which is composed of a dense array of several laser ranging sensors.

6. The target drone wing strength testing device according to claim 1, characterized in that: A parallel airflow assembly (500) is provided at each end of the detection chamber, and the two parallel airflow assemblies (500) are arranged on both sides of the detection test assembly (400).

7. The target drone wing strength testing device according to claim 6, characterized in that: The parallel airflow assembly (500) includes a blade-shaped bracket (501), an airflow adjustment cylinder (502), and a mounting arc plate (503). The blade-shaped bracket (501) is arranged vertically, and multiple airflow adjustment cylinders (502) are fixedly installed on the blade-shaped bracket (501). The diameter of the airflow adjustment cylinders (502) increases from the inside to the outside. The mounting arc plate (503) is installed on the blade-shaped bracket (501). The mounting arc plate (503) fits against the outside of the detection chamber. The mounting arc plate (503) is connected to the working cylinder (101) by fixing bolts. A blade-shaped bracket (501) is installed at the top and bottom of the parallel airflow assembly (500). One side edge of the airflow adjustment cylinder (502) is streamlined.

Images