Performance testing tool and method for gas rudder aerodynamic force testing system

Abstract

The application provides a performance test tool of a gas rudder aerodynamic force test system, the gas rudder aerodynamic force test system comprises a plurality of test structures, the test structure comprises a strain balance, a support rotating shaft and a servo mechanism connected in sequence, the performance test tool comprises a plurality of loading devices used for being connected with the strain balance, the loading device is connected with the strain balance through a loading adapter, the loading adapter is connected with one end of the strain balance away from the support rotating shaft, the loading device and the strain balance are arranged in one-to-one correspondence, the loading device applies a force to the strain balance through the loading adapter, so as to test the performance of the gas rudder aerodynamic force test system. The loading adapter is applied to the gas rudder aerodynamic force test system to simulate the scene that the gas rudder aerodynamic force test system tests the gas rudder aerodynamic force, and the performance test of the gas rudder aerodynamic force test system is realized.

Description

Technical Field

[0001] The present application relates to the field of mechanical testing technology, and in particular to a performance testing tool and method for a gas rudder aerodynamic test system. Background Art

[0002] The gas rudder is an important means of adjusting the flight attitude of an aircraft. The relevant aerodynamic parameters of the gas rudder are generally obtained through a gas rudder aerodynamic test system. The gas rudder aerodynamic test system mainly includes a mounting bracket and a gas rudder force measuring device. As aircraft performance improves, the aerodynamic forces acting on the gas rudder gradually increase. Due to the large aerodynamic forces of the gas rudder, the gas rudder aerodynamic test system has two prominent problems: first, the mounting bracket may fail in strength or stiffness; second, under the action of large aerodynamic loads, the servo mechanism in the gas rudder force measuring device cannot correctly deflect to the specified angle according to control instructions.

[0003] Therefore, after the design of the gas rudder aerodynamic test system is completed, a suitable method is needed to evaluate its strength and stiffness as well as the servo mechanism following characteristics and other performance, so as to avoid failure when the gas rudder is equipped with a rocket engine to carry out aerodynamic testing, thereby affecting the research and development progress. Summary of the Invention

[0004] In view of this, the purpose of this application is to propose a performance testing tool and method for a gas rudder aerodynamic test system.

[0005] Based on the above-mentioned purpose, the present application provides a performance testing tool for a gas rudder aerodynamic test system, wherein the gas rudder aerodynamic test system includes multiple test structures, each of which includes a strain balance, a support shaft and a servo mechanism connected in sequence. The performance testing tool includes multiple loading devices for connecting to the strain balance, the loading devices are connected to the strain balance through a loading adapter, the loading adapter is connected to one end of the strain balance away from the support shaft, the loading devices and the strain balance are arranged in a one-to-one correspondence, and the loading devices apply a force to the strain balance through the loading adapter to test the performance of the gas rudder aerodynamic test system.

[0006] Furthermore, the loading adapter device includes an adapter and a loading rod connected to each other, the adapter is connected to the strain balance, the loading rod is sleeved with a rolling bearing, and the rolling bearing is connected to the loading device.

[0007] Furthermore, the loading device includes two vertically arranged loading components, and the loading rod of the loading adapter device is provided with two rolling bearings, and the rolling bearings are connected to the loading components in a one-to-one correspondence.

[0008] Furthermore, the loading assembly includes a connected loading lug and a hydraulic actuator, the loading lug is connected to the rolling bearing, and the hydraulic actuator is used to output the loading effect.

[0009] Furthermore, the test fixture also includes a bearing structure, which has an installation space for accommodating the gas rudder aerodynamic test system and the loading device, and the end of the hydraulic actuator away from the loading adapter is connected to the inner wall of the installation space.

[0010] Furthermore, the test fixture also includes a plurality of simulated strain balances, which are used to replace the strain balances of the gas rudder aerodynamic test system to perform performance testing of the gas rudder aerodynamic test system.

[0011] Furthermore, the loading direction of one of the plurality of loading devices is the same as the direction of the force acting on the gas vane when it is at its maximum deflection.

[0012] Based on the same inventive concept, the present application also provides a performance testing method for a gas rudder aerodynamic test system, using the above-mentioned performance testing tooling, the performance testing method includes:

[0013] Controlling the loading device to load according to a preset loading load, and the servo mechanism to move according to a preset motion instruction, wherein the preset motion instruction includes a motion duration;

[0014] In response to determining that the servo mechanism stops moving, controlling the loading device to unload the load, and recording test data of the strain balance, the support shaft, and the servo mechanism;

[0015] The test data of the strain gauge balance, the support shaft and the servo mechanism are analyzed to obtain the performance test results of the gas rudder aerodynamic test system.

[0016] Furthermore, before controlling the loading device to load according to a preset load and the servo mechanism to move according to a preset movement instruction, the method further includes:

[0017] Replacing the strain gauge balance in the gas rudder aerodynamic test system with a simulated strain gauge balance;

[0018] The load condition of the gas rudder aerodynamic test system is analyzed to obtain the load loading level in the gas rudder aerodynamic test system coordinate system;

[0019] sequentially setting the applied load of the loading device according to the load loading levels to test the load-bearing capacity of the gas rudder aerodynamic test system;

[0020] In response to determining that the load-bearing capacity of the gas fin aerodynamic test system passes the test, setting the loading device to load according to a preset loading load, and the servo mechanism to move according to the simulated motion instruction, so as to obtain test data of the support shaft and the servo mechanism;

[0021] Analyzing test data of the support shaft and the servo mechanism to test the following characteristics of the servo mechanism;

[0022] In response to determining that the following characteristic of the servo mechanism passes the test, the analog strain balance is removed and replaced with the strain balance to test the performance of the gas rudder aerodynamic test system.

[0023] Furthermore, the step of sequentially setting the applied load of the loading device according to the load loading levels to test the load-bearing capacity of the gas rudder aerodynamic test system includes:

[0024] sequentially setting the applied load of the loading device according to the load loading levels, and sequentially recording the values ​​of the displacement meter;

[0025] Checking the value measured by the displacement meter and the appearance of the gas rudder aerodynamic test system to determine whether the load-bearing capacity of the gas rudder aerodynamic test system has passed the test;

[0026] In response to determining that the values ​​of the displacement meter are all within a preset range and that the bearing structure has no cracks, it is determined that the bearing capacity of the gas rudder aerodynamic test system has passed the test.

[0027] From the above, it can be seen that the performance test tooling of the gas rudder aerodynamic test system provided in the present application can simulate the force applied by the gas rudder to the aerodynamic test system when the gas rudder aerodynamic test system is in use by setting a loading adapter and a loading device connected to the test structure of the gas rudder aerodynamic test system, and apply the force to the test structure of the gas rudder aerodynamic test system through the loading adapter to simulate the gas rudder aerodynamic test system in the test of the gas rudder aerodynamic scene. In the process, the bearing capacity of the gas rudder aerodynamic test system is tested to determine whether the strength of the gas rudder aerodynamic test system can meet the forces in the test process. By testing the angular deflection of the servo mechanism and the support shaft, the following performance of the servo mechanism is tested, thereby realizing the performance test of the gas rudder aerodynamic test system, avoiding the gas rudder aerodynamic test system from malfunctioning when carrying out aerodynamic testing of the gas rudder with a rocket engine, thereby affecting the research and development progress. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in this application or related technologies, the following briefly introduces the drawings required for use in the embodiments or related technical descriptions. Obviously, the drawings described below are merely embodiments of this application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0029] Figure 1 This is a schematic diagram of the three-dimensional structure of the connection between the performance test tooling of the gas rudder aerodynamic test system and the gas rudder aerodynamic test system according to an embodiment of the present application;

[0030] Figure 2 This is a schematic diagram of the main structure of the connection between the performance test tool of the gas rudder aerodynamic test system and the gas rudder aerodynamic test system according to an embodiment of the present application;

[0031] Figure 3 This is a test structure diagram of the connection between the performance test tooling of the gas rudder aerodynamic test system and the gas rudder aerodynamic test system according to an embodiment of the present application;

[0032] Figure 4 This is a schematic top view of the structure of the gas rudder aerodynamic test system connected to the performance test tool of the gas rudder aerodynamic test system according to an embodiment of the present application;

[0033] Figure 5 It is a schematic diagram of the three-dimensional structure of the aerodynamic test system of the gas rudder equipped with a rocket engine in the prior art;

[0034] Figure 6 This is a schematic diagram of the three-dimensional structure of the loading adapter device connected to the simulated strain balance according to an embodiment of the present application;

[0035] Figure 7 This is a schematic side cross-sectional view of the loading adapter connected to the simulated strain gauge balance according to an embodiment of the present application;

[0036] Figure 8 This is a schematic diagram of the connection structure between two loading devices and the gas rudder aerodynamic test system according to an embodiment of the present application;

[0037] Figure 9 This is a flow chart of a performance testing method for a gas rudder aerodynamic testing system according to an embodiment of the present application;

[0038] Figure 10 A schematic diagram of preset motion instructions for the servo mechanism according to an embodiment of the present application;

[0039] Figure 11 A schematic diagram of simulated motion instructions for the servo mechanism according to an embodiment of the present application;

[0040] Figure 12This is a data transmission diagram of the loading device in the gas rudder aerodynamic test system and performance test tooling in an embodiment of the present application.

[0041] In the figure: 8, independent mounting bracket; 9, base; 10, test structure; 11, strain balance; 12, support shaft; 13, servo mechanism; 14, mounting support; 20, loading device; 21, loading assembly; 211, loading ear; 212, hydraulic actuator; 30, loading adapter; 31, adapter; 32, loading rod; 33, rolling bearing; 34, bolt; 40, load-bearing structure; 50, simulated strain balance. DETAILED DESCRIPTION

[0042] In order to make the objectives, technical solutions and advantages of this application more clear, this application is further described in detail below in combination with specific embodiments and with reference to the accompanying drawings.

[0043] It should be noted that, unless otherwise defined, the technical terms or scientific terms used in the embodiments of the present application should have the usual meanings understood by people with ordinary skills in the field to which this application belongs. The "first", "second" and similar words used in the embodiments of the present application do not indicate any order, quantity or importance, but are only used to distinguish different components. "Include" or "comprise" and similar words mean that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0044] As described in the background technology, the existing gas rudder aerodynamic test system is prone to various problems during use due to the large aerodynamic force of the gas rudder: first, the mounting bracket may fail in strength or rigidity, affecting the test of the gas rudder aerodynamic force; second, the servo mechanism cannot correctly deflect to the corresponding angle according to the control instructions, affecting the normal use of the gas rudder aerodynamic test system.

[0045] Therefore, before the gas rudder aerodynamic test system is put into production and application, a method is needed to assess its strength, stiffness and servo mechanism following characteristics to avoid failure of the gas rudder aerodynamic test system when testing the gas rudder aerodynamics with a rocket engine, thereby affecting the research and development progress.

[0046] Based on this, the present application proposes a performance testing tool and method for a gas rudder aerodynamic test system. By setting a loading device to simulate the aerodynamic force of the gas rudder, and setting a loading adapter device to connect the loading device to the test structure of the gas rudder aerodynamic test system, the aerodynamic force of the gas rudder is simulated to act on the test structure, thereby realizing the test of the gas rudder aerodynamic test system.

[0047] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0048] like Figures 1 to 4 As shown, the present application provides a performance testing tool for a gas rudder aerodynamic test system, wherein the gas rudder aerodynamic test system includes multiple test structures 10, each of which includes a strain balance 11, a support shaft 12, and a servo mechanism 13 connected in sequence. The performance testing tool includes multiple loading devices 20 for connecting to the strain balance 11, wherein the loading devices 20 are connected to the strain balance 11 via a loading adapter 30, and the loading adapter 30 is connected to an end of the strain balance 11 away from the support shaft 12. The loading devices 20 and the strain balance 11 are arranged in a one-to-one correspondence, and the loading devices 20 apply a force to the strain balance 11 via the loading adapter 30 to test the performance of the gas rudder aerodynamic test system.

[0049] Specifically, such as Figure 5 As shown, the gas rudder aerodynamic test system includes a stand-alone mounting bracket 8 and multiple test structures 10 located on the stand-alone mounting bracket 8. The test structures 10 are connected to the stand-alone mounting bracket 8 via mounting brackets 14. A support shaft 12 in the test structures 10 passes through the mounting bracket 14 and is connected to the mounting bracket 14. The support shaft 12 is connected to an angle deflector to determine the deflection angle of the support shaft 12. The stand-alone mounting bracket 8 is located on a base 9 to facilitate mounting a gas rudder equipped with a rocket engine on the stand-alone mounting bracket 8 when testing the gas rudder equipped with a rocket engine.

[0050] In addition, the strain balance in the test structure 10 is arranged near the mounting hole on the independent mounting bracket 8, that is, the aerodynamic force of the gas rudder acts on the strain balance 11. When the gas rudder aerodynamic test system tests the aerodynamic force of the gas rudder, the strain balance 11 can output a corresponding voltage signal to obtain the test result. Therefore, connecting the performance test tool to the strain balance in the test structure 10 can fully simulate the stress conditions of the gas rudder aerodynamic test system during actual use, thereby improving the test accuracy of the performance test tool.

[0051] The performance testing tooling includes a plurality of loading devices 20 and loading adapter devices 30. Each of the test structures 10 on the gas rudder aerodynamic test system is connected to a loading adapter device 30. Accordingly, each of the loading adapter devices 30 is connected to a loading device 20. The loading device 20 is a power device for outputting a force simulating the aerodynamic force of the gas rudder. The loading adapter device 30 is used to transmit the force of the loading device 20 to the test structure 10 to simulate the gas rudder applying a force to the test structure 10, thereby facilitating the performance testing of the gas rudder aerodynamic test system.

[0052] It should be noted that when testing the strength and stiffness of the gas rudder aerodynamic test system, it is necessary to determine the structural stability of the performance test tooling during and after the performance test tooling simulates the aerodynamic force output by the gas rudder to achieve the test. The independent mounting bracket 8 is the "bracket" of the aerodynamic test system, so it is necessary to test the structural stability of the independent mounting bracket 8. Since the bottom of the independent mounting bracket 8 is connected to the base 9, the top of the independent mounting bracket 8 is a free end provided with the displacement meter to monitor the deformation of the independent mounting bracket 8 during the test of the gas rudder aerodynamic test system and whether there is any breakage or cracking, so as to obtain the test results.

[0053] When testing the following characteristics of the servo mechanism 13 of the gas rudder aerodynamic test system, it is necessary to control the servo mechanism 13 to deflect at a fixed angle while the performance test tool simulates the gas rudder output aerodynamic force, obtain the deflection angle of the support shaft 12 during the process through the angle deflector, and compare the deflection angle with the deflection angle of the servo mechanism 13 to determine the following characteristics of the servo mechanism 13 and realize the following characteristics test of the servo mechanism 13.

[0054] In this embodiment, by providing a loading adapter 30 and a loading device 20 connected to the test structure 10 of the gas rudder aerodynamic test system, the force applied by the gas rudder to the aerodynamic test system when the gas rudder aerodynamic test system is in use can be simulated, and the force is applied to the test structure 10 of the gas rudder aerodynamic test system through the loading adapter 30 to simulate the gas rudder aerodynamic test system in the gas rudder aerodynamic test scenario. During the process, the bearing capacity of the gas rudder aerodynamic test system is tested to determine whether the strength of the gas rudder aerodynamic test system can meet the forces in the test process. By testing the angular deflection of the servo mechanism 13 and the support shaft 12, the following performance of the servo mechanism 13 is tested, thereby realizing the performance test of the gas rudder aerodynamic test system, thereby avoiding the gas rudder aerodynamic test system from malfunctioning when carrying out aerodynamic testing of the gas rudder on a rocket engine, thereby affecting the research and development progress.

[0055] In some embodiments, as Figure 6 and Figure 7 As shown, the loading adapter 30 includes an adapter 31 and a loading rod 32 connected to each other. The adapter 31 is connected to the strain balance 11 . A rolling bearing 33 is sleeved on the loading rod 32 . The rolling bearing 33 is connected to the loading device 20 .

[0056] Specifically, the rolling bearing 33 is sleeved on the loading rod 32 and fixedly connected to the loading rod 32. The loading device 20 applies a force to the loading rod 32 through the rolling bearing 33. Correspondingly, the loading rod 32 applies a force to the strain balance 11 through the adapter 31.

[0057] In addition, one end of the adapter 31 is adapted to the size of the end of the strain balance 11, and is provided with a hole adapted to the through hole on the strain balance 11, and is fixedly connected by a bolt 34. The other end is provided with a groove adapted to one end of the loading rod 32, and a through hole is provided on the side wall of the groove. The loading rod 32 is located in the groove, and a threaded groove adapted to the through hole is provided on its side wall. The bolt 34 passes through the through hole and is threadedly connected to the threaded groove to fix the adapter 31 and the loading rod 32. The free end of the loading rod 32 is sleeved with the rolling bearing 33.

[0058] In this embodiment, the adapter 31 is used to connect with the strain balance 11, and the loading rod 32 is connected to the loading device 20 through a rolling bearing 33, which can realize the adapter function. When the loading adapter 30 is damaged during the test of the gas rudder aerodynamic test system, the connected adapter 31 and the loading rod 32 can also avoid the complete damage of the adapter 31 and the loading rod 32, thereby reducing the testing cost and facilitating the practicality of the performance testing tooling.

[0059] In some embodiments, the loading device 20 includes two vertically arranged loading assemblies 21 , and the loading rod 32 of the loading adapter 30 is provided with two rolling bearings 33 , and the rolling bearings 33 are connected to the loading assemblies 21 in a one-to-one correspondence.

[0060] Specifically, the loading device 20 simulates the aerodynamic force of the gas rudder on the strain gauge 11 and analyzes the gas rudder force applied to the strain gauge 11 during testing. The strain gauge 11 experiences two types of forces: an axial force perpendicular to the axial direction of the gas rudder (i.e., the axial direction of the strain gauge 11), and a normal force perpendicular to the rudder surface. Therefore, the loading device 20 needs to simulate two forces: an axial force and a normal force. These two forces act perpendicularly to each other, so the loading device 20 includes two vertically arranged loading assemblies 21: one loading assembly 21 simulates the axial force, perpendicular to the axial direction of the strain gauge 11, and the other loading assembly 21 simulates the normal force, perpendicular to the mounting surface of the independent mounting bracket 8. Each loading assembly 21 in the loading device 20 simulates the forces applied during operation of the gas rudder aerodynamic test system.

[0061] In addition, since one loading adapter 30 is connected to two loading assemblies 21, two rolling bearings 33 are provided on the loading adapter 30, so that the two rolling bearings 33 are respectively connected to the two loading assemblies 21. This can not only realize independent operation between the two loading assemblies 21, but also enable the two loading assemblies 21 to apply force to one strain balance 11 at the same time, which is beneficial to improving the realism of the loading device 20 simulating the aerodynamic force applied by the gas rudder, and further beneficial to improving the test accuracy of the performance test tooling.

[0062] It should be noted that a boss is provided at the free end of the loading rod 32, one of the rolling bearings 33 is located on the boss, and the other rolling bearing 33 is located on the loading rod 32, which can not only ensure the independence of the action of the rolling bearings 33, but also ensure that the force of the two rolling bearings 33 acting on the loading rod 32 is located on the axis of the loading rod 32, thereby ensuring the rationality of the load applied by the loading device 20, and thus helping to improve the test accuracy, practicality and promotion and applicability of the performance testing tooling.

[0063] In some embodiments, as Figure 8 As shown, the loading assembly 21 includes a loading lug 211 and a hydraulic actuator 212 connected to each other. The loading lug 211 is connected to the rolling bearing 33, and the hydraulic actuator 212 is used to output the loading effect.

[0064] Specifically, the hydraulic actuator 212 is a power output structure, and the loading ear 211 is connected in parallel to the hydraulic actuator 212 to transmit the force of the hydraulic actuator 212 to the rolling bearing 33 in the loading adapter 30. The setting of the loading ear 211 facilitates the connection between the hydraulic actuator 212 and the loading adapter 30, which is beneficial to the practicality and promotion and application of the performance testing tooling.

[0065] In some embodiments, as Figures 1 to 4 As shown, the test fixture also includes a bearing structure 40, which has an installation space for accommodating the gas rudder aerodynamic test system and the loading device 20, and the end of the hydraulic actuator 212 away from the loading adapter 30 is connected to the inner wall of the installation space.

[0066] Specifically, the bearing structure 40 is located on the base 9 of the gas rudder aerodynamic test system. The bearing structure 40 is used to support the hydraulic actuator 212. It can not only fix the hydraulic actuator 212, but also bear the reaction force exerted on the hydraulic actuator 212 when the hydraulic actuator 212 is loaded.

[0067] It should be noted that the bearing structure 40 includes a frame-type bearing structure 40 arranged around the independent mounting bracket 8, and also includes a vertical bearing structure 40 located on the front side of the independent mounting bracket 8, providing an installation space for the loading adapter device 30 and the loading device 20, and also providing support for the hydraulic actuator 212 in the loading device 20.

[0068] In some embodiments, as Figure 6 As shown, the test fixture further includes a plurality of simulated strain balances 50 , which are used to replace the strain balances 11 of the gas rudder aerodynamic test system to perform performance testing of the gas rudder aerodynamic test system.

[0069] Specifically, the simulated strain balance 50 is used to replace the strain balance in the test structure 10 when the performance test tool tests the gas rudder aerodynamic test system, so as to avoid damage to the strain balance 11 during the test process, increase the test cost, and help improve the practicality of the performance test tool.

[0070] In addition, when using the simulated strain balance 50 for testing, after the gas rudder aerodynamic test system passes the test, the simulated strain balance 50 is removed and replaced with the strain balance 11, and then the gas rudder aerodynamic test system is tested to further test the strain balance 11, thereby avoiding damage to the strain balance 11 during the test of the gas rudder aerodynamic test system and ensuring the test progress of the gas rudder aerodynamic test system.

[0071] In some embodiments, as Figure 8 As shown, the loading direction of one of the plurality of loading devices 20 is the same as the direction of the force when the gas vane is at its maximum deflection.

[0072] Specifically, the loading device 20 is used to simulate the force of the gas rudder during the test of the gas rudder aerodynamic test system. According to the working principle of the gas rudder, when it is not deflected (that is, when it is installed on the independent mounting bracket 8), the force applied includes axial force and normal force. When it is deflected (that is, when there is a deflection angle between the gas rudder and the independent mounting bracket 8), the force applied is the axial force and the normal force deflected according to the deflection angle. Therefore, the loading direction of one of the multiple loading devices 20 is the same as the direction of the force at the maximum deflection angle of the gas rudder, which can avoid interference with the loading device 20 and improve the simulation realism of the performance test tooling, thereby helping to improve the test accuracy.

[0073] Based on the same inventive concept, the present application also provides a performance test method for a gas rudder aerodynamic test system, using the above-mentioned performance test tooling, such as Figure 9 As shown, the performance testing method includes:

[0074] Step S100, controlling the loading device 20 to load according to a preset loading load, and the servo mechanism 13 to move according to a preset motion instruction, wherein the preset motion instruction includes a motion duration;

[0075] Specifically, the performance test fixture is connected to the aerodynamic test system. The servo mechanism 13 and the strain balance in the aerodynamic test system are both powered on. The strain balance 11 can output the stress it senses in the form of an electrical signal.

[0076] The tester controls the loading device 20 in the performance test fixture to load and maintain a preset load. The preset load simulates the force applied to each servo mechanism 13 when the gas rudder is at its maximum deflection angle. While the loading device 20 maintains the load, the servo mechanism 13 moves according to the preset motion instructions to test the tracking characteristics of the servo mechanism 13, as well as the stiffness and strength of the strain gauge, of the aerodynamic test system when the gas rudder is at its maximum deflection angle. Testing the parameters of the aerodynamic test system at the gas rudder's maximum deflection angle is equivalent to testing the aerodynamic test system's limit values. If the aerodynamic test system performs well at the gas rudder's maximum deflection angle, it will maintain this performance during testing under other conditions, simplifying testing and improving test accuracy.

[0077] For example, the aerodynamic test system includes four test structures 10, and correspondingly, the performance test fixture includes four loading devices 20 and four loading adapters 30, wherein the load direction applied by one of the loading devices 20 is consistent with the load direction when the gas vane is at the maximum deflection angle (i.e., Figure 8 As shown, the maximum deflection angle δ of the mounting surface of the gas rudder mounted on the independent mounting bracket 8 is max Load direction F n and F a ), the load directions applied by the other three loading devices 20 are all in the same direction as the load direction when the gas vane is not deflected (i.e., perpendicular and parallel to the mounting surface of the gas vane mounted on the independent mounting bracket 8, such as Figure 8 F in x and F y ) and is arranged around the installation surface of the gas fin. x Indicates the force parallel to the mounting surface, F y Indicates the force normal to the mounting surface.

[0078] It is known that when the rudder surface of the gas rudder is at the maximum deflection angle δ max =30°, the normal force F n =12000N, axial force F a =3000N, then the independent mounting bracket 8 is subjected to forces F in two directions. x =8892.3N, F y =8598.1N.

[0079] The preset loading load is F n =12000N, F a =3000N, F x =8892.3N, F y=8598.1N, the loading devices 20 include 4, of which 3 loading devices 20 have the same loading direction, and the preset loading load is the same, which is F x =8892.3N, F y =8598.1N, the loading direction of the other loading device 20 is different from the loading directions of the other three loading devices 20, corresponding to the maximum deflection angle of the gas rudder, and the preset loading load F n =12000N, F a =3000N.

[0080] The tester controls the four loading devices 20 to load the gas rudder according to their corresponding preset loads and maintains the loading action. During this period, the tester controls the servo mechanism 13 to move according to the preset motion instructions, that is, controls the servo mechanism 13 to actively rotate at a specific angle within a specific time period. During this process, the deflection angle of the support shaft 12 connecting the servo mechanism 13 and the strain gauge balance 11 is observed. By comparing the difference between the two angles, the following characteristics of the servo mechanism 13 when the gas rudder is at the maximum deflection angle are tested.

[0081] The preset motion instruction may be, for example, Figure 10 As shown, the servo mechanism 13 outputs a deflection of 5° which is maintained for 0.5 seconds.

[0082] Step S200 , in response to determining that the servo mechanism 13 stops moving, controlling the loading device 20 to unload the load, and recording test data of the strain gauge balance 11 , the support shaft 12 , and the servo mechanism 13 ;

[0083] Specifically, the servo mechanism 13 moves according to the preset motion instruction and stops moving after completing the preset motion instruction. After the tester observes that the servo mechanism 13 stops moving, the loading device 20 is unloaded, that is, the force of the performance test tool on the aerodynamic test system is released, and the test data of the strain balance 11, the support shaft 12 and the servo mechanism 13 during the joint action of the servo mechanism 13 and the loading device 20 are recorded to obtain the performance test results of the aerodynamic test system.

[0084] Step S300 , analyzing the test data of the strain gauge balance 11 , the support shaft 12 , and the servo mechanism 13 to obtain a performance test result of the gas fin aerodynamic test system.

[0085] Specifically, the test personnel conduct a detailed analysis on the test data of the strain gauge balance 11 , the support shaft 12 , and the servo mechanism 13 to obtain the performance test results of the gas fin aerodynamic test system.

[0086] The test data of the strain balance 11 is electrical signal data. By observing the changes in the data of the strain balance 11, it is possible to determine whether the strain balance 11 operates normally during the test (i.e., whether it is damaged due to the force of the loading device 20). The test data of the support shaft 12 is obtained through the angle deflector located on the support shaft 12. The test data of the servo mechanism 13 is the deflection angle in the preset motion instruction based on which the servo mechanism 13 moves. By comparing the test data of the support shaft 12 and the servo mechanism 13, the following characteristics of the servo mechanism 13 can be determined.

[0087] For example, the test data of the servo mechanism 13 is 5°, the test data of the support shaft 12 is 5.1°, and the following characteristic judgment standard of the servo mechanism 13 is: good 0~0.1; bad 0.1~0.5, then it can be determined that the following characteristic of the servo mechanism 13 is good, and the servo mechanism 13 passes the test; the test data of the strain balance 11 are all 5V and have not changed, then it can be determined that the strain balance 11 is not damaged and has passed the test.

[0088] If the test data of the strain gauge balance 11 is 0V or changes from 5V to 0V, it can be determined that the strain gauge balance 11 is damaged and fails the test.

[0089] In this embodiment, the test process of the aerodynamic test system is analyzed, and the limit effects it is subjected to during the test of the gas rudder are analyzed to obtain the preset loading load, so that the loading device 20 is loaded according to the preset loading load, and the strength and stiffness of the strain balance in the aerodynamic test system are tested. At the same time, the servo mechanism 13 is set to move according to the corresponding preset motion instructions to test the following characteristics of the servo mechanism 13 during the test of the gas rudder, thereby achieving the effect of testing two performances at a time, which not only simplifies the test process but also improves the test accuracy, which is beneficial to the practicality of the performance testing method.

[0090] In some embodiments, before step S100: controlling the loading device 20 to load according to a preset load and the servo mechanism 13 to move according to a preset movement instruction, the method further includes:

[0091] Step S400, replacing the strain gauge in the gas rudder aerodynamic test system with a simulated strain gauge 50;

[0092] Specifically, before testing the aerodynamic test system, the strain balance therein is first replaced with a simulated strain balance 50, and a pre-test is performed on this basis to avoid directly testing the aerodynamic test system, which may damage the strain balance 11 and increase the test cost.

[0093] Step S500, analyzing the load condition of the gas rudder aerodynamic test system to obtain the load loading level of the loading device 20;

[0094] Specifically, the load conditions on the aerodynamic test system when testing the gas rudder are analyzed, and it is found that the load on the aerodynamic test system is the largest when the gas rudder is at the maximum deflection angle. On this basis, a safety factor is taken to determine the maximum loading load of the loading device 20 on the aerodynamic test system, and on this basis, load loading levels are set, with the maximum level corresponding to the maximum loading load. By gradually increasing the loading load on the aerodynamic test system, the strength and rigidity of the independent mounting bracket 8 in the aerodynamic test system are tested.

[0095] For example, the safety factor f=1.5, F n =12000N, F a =3000N, F x =8892.3N, F y =8598.1N, then F x,max =f×F x =13338.5N, F y,max =f×F y =12897.1N、F n,max =f×F n =18000N, F a,max =f×F a =4500N, the loading device 20 is provided with 4, of which 3 apply a load of F x and F y , and the other applied load is F n and F a , and the angle between the mounting surface of the gas vane on the independent mounting bracket 8 is the maximum deflection angle δ of the gas vane max =30°, the load loading levels are as shown in Table 1.

[0096] Table 1 Loading levels of the loading device

[0097]

[0098] Step S600, sequentially setting the applied load of the loading device 20 according to the load loading levels to test the load-bearing capacity of the gas rudder aerodynamic test system;

[0099] Specifically, the tester sets the applied loads of multiple loading devices 20 according to the load loading levels, and maintains a fixed time, and observes whether the independent mounting bracket 8 and the simulated strain balance 50 have any cracks or cracks after each load loading level, so as to test the load-bearing capacity of the aerodynamic test system, that is, the stiffness and strength. If the independent mounting bracket 8 and the simulated strain balance 50 have no cracks or cracks that affect the structural stability, it is determined that the load-bearing capacity of the aerodynamic test system has passed the test.

[0100] Step S700: In response to determining that the load-bearing capacity of the gas fin aerodynamic test system passes the test, setting the loading device 20 to load according to a preset load, and setting the servo mechanism 13 to move according to the simulated motion instruction to obtain test data of the support shaft 12 and the servo mechanism 13;

[0101] Specifically, after determining that the load-bearing capacity of the gas rudder aerodynamic test system has passed the test, the tester sets the loading device 20 to load according to the preset loading load, and the preset loading load corresponds to the load condition of the aerodynamic test system when the gas rudder is at the maximum deflection angle, that is, the load under extreme conditions is applied to the aerodynamic test system and maintained. At the same time, the servo mechanism 13 is set to move according to the simulated motion instruction, and the simulated motion instruction corresponds to the process of gradually increasing the deflection angle of the servo mechanism 13 to the maximum deflection angle, so as to test the angular deflection following characteristics of the servo mechanism 13 under extreme conditions. The test data of the support shaft 12 is obtained by the angle deflector installed on the support shaft 12.

[0102] For example, the simulated motion instruction is as follows: Figure 11 As shown, the deflection angle of the servo mechanism 13 gradually increases to 30°, remains for a period of time, then gradually decreases to -30°, and finally gradually increases to 0°. The test data of the servo mechanism 13 can be obtained from the simulated motion instruction. The result output by the angle deflector is compared with the simulated motion instruction to determine whether the test data of the support shaft 12 measured by the angle deflector at the same time is the same as the data of the servo mechanism 13, so as to test the following characteristics of the servo mechanism 13.

[0103] Step S800 , analyzing the test data of the support shaft 12 and the servo mechanism 13 to test the following characteristics of the servo mechanism 13 ;

[0104] In step S900 , in response to determining that the following characteristic of the servo mechanism 13 passes the test, the simulated strain gauge balance 50 is removed and replaced with the strain gauge balance 11 to test the performance of the gas rudder aerodynamic test system.

[0105] Specifically, the following characteristics of the servo mechanism 13 pass the test, that is, it is determined that the aerodynamic test system passes the test of strength, stiffness and following characteristics when using the simulated strain balance 50, that is, the preliminary test passes. On this basis, the simulated strain balance 50 is disassembled and replaced with the strain balance 11 actually used in the aerodynamic test system, and then the aerodynamic test system is subjected to a performance test.

[0106] In this embodiment, the aerodynamic test system is tested after the strain balance 11 is replaced by the simulated strain balance 50, thereby achieving a preliminary test of the aerodynamic test system. This can avoid directly testing the aerodynamic test system equipped with the strain balance 11, thereby avoiding damage to the strain balance 11 during the test, which is beneficial to reducing test costs and improving the practicality of the test.

[0107] In some embodiments, step S600: sequentially setting the applied load of the loading device 20 according to the load loading levels to test the load-bearing capacity of the gas rudder aerodynamic test system includes:

[0108] Step S601, setting the applied load of the loading device 20 in sequence according to the load loading levels, and recording the values ​​of the displacement meter in sequence;

[0109] Specifically, a plurality of displacement meters are provided and located on the top of the independent mounting bracket 8 of the aerodynamic test system to monitor whether the independent mounting bracket 8 has cracks, etc.

[0110] The tester sets the applied load of the loading device 20 step by step according to the load loading levels and maintains it, and records the value of the displacement meter during the process to determine whether the independent mounting bracket 8 has cracks, etc. If so, it is determined that the bearing capacity of the independent mounting bracket 8 cannot pass the test. If no cracks appear until the load is loaded to the highest level, it is determined that the bearing capacity of the independent mounting bracket 8 passes the test.

[0111] Step S602: Checking the value measured by the displacement meter and the appearance of the gas rudder aerodynamic test system to determine whether the load-bearing capacity of the gas rudder aerodynamic test system passes the test;

[0112] Specifically, the value measured by the displacement meter is used to determine the load-bearing capacity of the independent mounting bracket 8 of the aerodynamic test system, and the load-bearing capacity of other structures of the aerodynamic test system is judged by observing the appearance, such as the mounting support 14 and the simulated strain balance 50, which have a smaller structure and are fixed on the independent mounting bracket 8, and their load-bearing capacity can be determined by only observing the appearance.

[0113] Step S603 : In response to determining that the values ​​of the displacement meter are all within a preset range and there is no cracking, it is determined that the load-bearing capacity of the gas fin aerodynamic test system has passed the test.

[0114] Specifically, the preset range is the safe deformation of the independent mounting bracket, that is, if the deformation of the independent mounting bracket during the test is within the safe range, it can be determined that the load-bearing capacity of the independent mounting bracket 8 has passed the test; if the mounting support 14 and the simulated strain balance 50 have no cracks or fissures, it can be determined that the load-bearing capacity of the gas rudder aerodynamic test system has passed the test.

[0115] Exemplarily, the preset range is (0 to 5 mm), and when the values ​​of the displacement meter are 1 mm, 2 mm, and 4 mm, respectively, it is determined that the independent mounting bracket has passed the test. If the values ​​of the displacement meter are 1 mm, 2 mm, and 6 mm, respectively, and the value of one of the displacement meters is not within the preset range, it is determined that the independent mounting bracket has failed the test.

[0116] In this embodiment, the load-bearing capacity of the independent mounting bracket 8 in the aerodynamic test system is tested by a displacement meter, and the load-bearing capacity of the mounting support 14 and the simulated strain balance 50 is tested by observing the appearance, so as to achieve a preliminary test of the load-bearing capacity of the aerodynamic test system. On this basis, the simulated strain balance 50 is replaced with the strain balance 11 of the aerodynamic test system, and then the aerodynamic test system is tested, which can reduce the testing cost and improve the test pass rate.

[0117] For example, Figure 12 The electrical connection relationship between the performance test fixture and the data acquisition and input control in the gas rudder aerodynamic test system is shown to obtain various data of the performance test fixture during the test process, thereby achieving the test purpose.

[0118] It should be noted that the above description is limited to some embodiments of the present application. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recited in the claims may be performed in an order different from that described in the above embodiments and still achieve the desired results. Furthermore, the processes depicted in the accompanying drawings do not necessarily require the specific order or sequential order shown to achieve the desired results. In certain embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0119] Those skilled in the art should understand that the discussion of any of the above embodiments is merely illustrative and is not intended to imply that the scope of the present application (including the claims) is limited to these examples. Within the scope of the present application, the technical features in the above embodiments or different embodiments may be combined, the steps may be implemented in any order, and there are many other variations of the different aspects of the embodiments of the present application as described above, which are not provided in detail for the sake of simplicity.

[0120] In addition, when specific details are set forth to describe exemplary embodiments of the present application, it will be apparent to those skilled in the art that the present application embodiments can be implemented without these specific details or with variations in these specific details. Therefore, these descriptions should be considered illustrative rather than restrictive.

[0121] While the present application has been described in conjunction with specific embodiments thereof, many alternatives, modifications and variations of these embodiments will be apparent to those skilled in the art in light of the foregoing description.

[0122] The embodiments of the present application are intended to cover all such substitutions, modifications, and variations that fall within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the embodiments of the present application should be included in the scope of protection of this application.

Claims

1. A performance test fixture for a gas rudder aerodynamic test system, the gas rudder aerodynamic test system comprising a plurality of test structures, each of which comprises a strain gauge balance, a support shaft, and a servo mechanism connected in sequence, characterized in that: The performance testing tooling includes a plurality of loading devices for connecting to the strain balance. The loading devices are connected to the strain balance via a loading adapter. The loading adapter is connected to an end of the strain balance away from the support shaft. The loading devices and the strain balance are arranged in a one-to-one correspondence. The loading devices apply a force to the strain balance via the loading adapter to test the performance of the gas rudder aerodynamic test system. In which, the loading adapter device includes a connected adapter and a loading rod, the adapter is connected to the strain balance, the loading rod is provided with a rolling bearing, and the rolling bearing is connected to the loading device; the loading device includes two vertically arranged loading components, the loading rod of the loading adapter device is provided with two rolling bearings, and the rolling bearings are connected to the loading components one by one.

2. The performance test tool for the gas rudder aerodynamic test system according to claim 1, characterized in that: The loading assembly includes a loading lug and a hydraulic actuator connected to each other. The loading lug is connected to the rolling bearing, and the hydraulic actuator is used to output the loading effect.

3. The performance test tool for the gas rudder aerodynamic test system according to claim 2, characterized in that: It also includes a bearing structure having an installation space for accommodating the gas rudder aerodynamic test system and the loading device, and the end of the hydraulic actuator away from the loading adapter is connected to the inner wall of the installation space.

4. The performance test tool for the gas rudder aerodynamic test system according to claim 1, characterized in that: It also includes a plurality of simulated strain balances, which are used to replace the strain balances of the gas rudder aerodynamic test system to perform performance tests on the gas rudder aerodynamic test system.

5. The performance test tool for the gas rudder aerodynamic test system according to claim 1, characterized in that: The loading action direction of one of the plurality of loading devices is the same as the direction of the force acting when the gas vane is at its maximum deflection.

6. A performance test method for a gas rudder aerodynamic test system, characterized in that: Using the performance testing tool according to any one of claims 1 to 5, the performance testing method includes: Controlling the loading device to load according to a preset loading load, and the servo mechanism to move according to a preset motion instruction, wherein the preset motion instruction includes a motion duration; In response to determining that the servo mechanism stops moving, controlling the loading device to unload the load, and recording test data of the strain balance, the support shaft, and the servo mechanism; The test data of the strain gauge balance, the support shaft and the servo mechanism are analyzed to obtain the performance test results of the gas rudder aerodynamic test system.

7. The performance testing method of the gas rudder aerodynamic testing system according to claim 6, characterized in that: Before controlling the loading device to load according to a preset loading load and the servo mechanism to move according to a preset motion instruction, the method further includes: Replacing the strain gauge balance in the gas rudder aerodynamic test system with a simulated strain gauge balance; The load condition of the gas rudder aerodynamic test system is analyzed to obtain the load loading level in the gas rudder aerodynamic test system coordinate system; sequentially setting the applied load of the loading device according to the load loading levels to test the load-bearing capacity of the gas rudder aerodynamic test system; In response to determining that the load-bearing capacity of the gas fin aerodynamic test system passes the test, setting the loading device to load according to a preset loading load, and the servo mechanism to move according to the simulated motion instruction, so as to obtain test data of the support shaft and the servo mechanism; Analyzing test data of the support shaft and the servo mechanism to test the following characteristics of the servo mechanism; In response to determining that the following characteristic of the servo mechanism passes the test, the analog strain balance is removed and replaced with the strain balance to test the performance of the gas rudder aerodynamic test system.

8. The performance testing method of the gas rudder aerodynamic testing system according to claim 7, characterized in that: The step of sequentially setting the applied load of the loading device according to the load loading levels to test the load-bearing capacity of the gas rudder aerodynamic test system includes: sequentially setting the applied load of the loading device according to the load loading levels, and sequentially recording the values ​​of the displacement meter; Checking the value measured by the displacement meter and the appearance of the gas rudder aerodynamic test system to determine whether the load-bearing capacity of the gas rudder aerodynamic test system has passed the test; In response to determining that the values ​​of the displacement meter are all within a preset range and that the bearing structure has no cracks, it is determined that the bearing capacity of the gas rudder aerodynamic test system has passed the test.

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