Performance test tool and method for gas vane aerodynamic force test system

Abstract

The invention provides a performance test tool of a gas vane aerodynamic force test system, the gas vane aerodynamic force test system comprises a plurality of test structures, each test structure comprises a strain balance, a support rotating shaft and a servo mechanism which are connected in sequence, and the performance test tool comprises a plurality of loading devices used for being connected with the strain balance, the loading devices are connected with the strain balances through loading switching devices, the loading switching devices are connected with the ends, away from the support rotating shaft, of the strain balances, the loading devices and the strain balances are arranged in a one-to-one correspondence mode, the loading devices apply acting force to the strain balances through the loading switching devices, and the loading devices are connected with the loading switching devices through the loading switching devices. Therefore, the performance of the gas vane aerodynamic force test system is tested. The gas vane aerodynamic force testing device is applied to the gas vane aerodynamic force testing system through the loading switching device so as to simulate the scene of the gas vane aerodynamic force testing system in testing the gas vane aerodynamic force, and performance testing of the gas vane aerodynamic force testing system is achieved.

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 testing system. Background Art

[0002] The gas rudder is an important way to adjust the flight attitude of the aircraft. The relevant aerodynamic parameters of the gas rudder are generally obtained through the gas rudder aerodynamic test system. The gas rudder aerodynamic test system mainly includes the mounting bracket and the gas rudder force measuring device. As the performance of the aircraft improves, the aerodynamic force on the gas rudder gradually increases. The gas rudder aerodynamic test system has two prominent problems due to the large aerodynamic force of the gas rudder. First, the strength or stiffness failure of the mounting bracket may occur. Second, the servo mechanism in the gas rudder force measuring device cannot be correctly deflected to the specified angle according to the control command under the action of the large aerodynamic load.

[0003] Therefore, after the gas rudder aerodynamic test system is designed, 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 carrying out aerodynamic testing of the gas rudder with a rocket engine, which would affect the research and development progress. Summary of the invention

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

[0005] Based on the above 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, wherein the test structures include a strain balance, a support shaft and a servo mechanism connected in sequence, and the performance testing tool includes multiple loading devices for connecting to the strain balance, wherein the loading devices are connected to the strain balance via a loading adapter, wherein the loading adapter is connected to an end of the strain balance away from the support shaft, wherein the loading devices and the strain balance are arranged in a one-to-one correspondence, and wherein 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.

[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, a rolling bearing is sleeved on the loading rod, and the rolling bearing is connected to the loading device.

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

[0008] Furthermore, the loading assembly includes a loading ear and a hydraulic actuator connected to each other, the loading ear 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 one end of the hydraulic actuator away from the loading adapter is connected to the inner wall of the installation space.

[0010] Furthermore, the test tool also includes a plurality of simulated strain balances, and the simulated strain balances 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 when the gas rudder is at 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 performance testing tool as described above, the performance testing method comprising:

[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 the test data of the strain balance, the support shaft and the servo mechanism;

[0015] The test data of the strain 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 the loading device is controlled to load according to a preset loading load and the servo mechanism moves according to a preset motion instruction, the method further includes:

[0017] Replacing the strain balance in the gas rudder aerodynamic test system with a simulated strain 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 rudder 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 the 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] Further, the loads applied by the loading device are sequentially set according to the load loading levels to test the load-bearing capacity of the gas rudder aerodynamic test system, including:

[0024] The applied load of the loading device is sequentially set according to the load loading levels, and the values ​​of the displacement meter are sequentially recorded;

[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 scenario of testing the gas rudder aerodynamics. 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. The angular deflection of the servo mechanism and the support shaft is tested to test the following performance of the servo mechanism, thereby realizing the performance test of the gas rudder aerodynamic test system, thereby avoiding failure of the gas rudder aerodynamic test system 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 the present application or related technologies, the drawings required for use in the embodiments or related technical descriptions are briefly introduced below. Obviously, the drawings described below are only embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0029] Figure 1 It 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 the embodiment of the present application;

[0030] Figure 2 It 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 the embodiment of the present application;

[0031] Figure 3 A test structure schematic diagram of the gas rudder aerodynamic test system in the embodiment of the present application, in which a performance test tool is connected to the gas rudder aerodynamic test system;

[0032] Figure 4 It is a schematic diagram of a top view of the structure of the gas rudder aerodynamic test system connected with 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 a gas rudder aerodynamic test system equipped with a rocket engine in the prior art;

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

[0035] Figure 7 A schematic diagram of the side cross-section structure of a loading adapter connected to a simulated strain 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 a gas rudder aerodynamic test system according to an embodiment of the present application;

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

[0038] Fig.10 A schematic diagram of a preset motion instruction of a servo mechanism according to an embodiment of the present application;

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

[0040] Fig.12This is a data transmission schematic diagram of a loading device in a gas rudder aerodynamic test system and a 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 the present application more clearly understood, the present 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 be the usual meanings understood by people with ordinary skills in the field to which the present application belongs. The "first", "second" and similar words used in the embodiments of the present application do not represent any order, quantity or importance, but are only used to distinguish different components. "Including" or "comprising" and similar words mean that the elements or objects appearing in front of 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 can 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 stiffness, affecting the gas rudder aerodynamic test; second, the servo mechanism cannot correctly deflect to the corresponding angle according to the control instruction, 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, so as 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, so as to simulate the aerodynamic force of the gas rudder 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 Figure 1 to Figure 4 As shown, the present application provides a performance test tool for a gas rudder aerodynamic test system, the gas rudder aerodynamic test system comprising a plurality of test structures 10, the test structure 10 comprising a strain balance 11, a support shaft 12 and a servo mechanism 13 connected in sequence, the performance test tool comprising a plurality of loading devices 20 for connecting to the strain balance 11, the loading device 20 being connected to the strain balance 11 via a loading adapter 30, the loading adapter 30 being connected to an end of the strain balance 11 away from the support shaft 12, the loading device 20 and the strain balance 11 being arranged in a one-to-one correspondence, the loading device 20 applying a force to the strain balance 11 via the loading adapter 30, so as to test the performance of the gas rudder aerodynamic test system.

[0049] Specifically, Figure 5 As shown, the gas rudder aerodynamic test system includes an independent mounting bracket 8 and a plurality of test structures 10 located on the independent mounting bracket 8, wherein the test structure 10 is connected to the independent mounting bracket 8 via a mounting bracket 14, a support shaft 12 in the test structure 10 passes through the mounting bracket 14 and is connected to the mounting bracket 14, and an angle deflector is connected to the support shaft 12 to determine the deflection angle of the support shaft 12. The independent mounting bracket 8 is located on a base 9, so that when testing a gas rudder equipped with a rocket engine, it is convenient to install the gas rudder equipped with a rocket engine on the independent mounting bracket 8.

[0050] In addition, the strain balance in the test structure 10 is arranged close to the mounting hole on the independent mounting bracket 8, that is, the aerodynamic force of the gas rudder acts on the strain balance 11, and 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 a test result. Therefore, connecting the performance test tooling with the strain balance in the test structure 10 can completely simulate the stress conditions of the gas rudder aerodynamic test system during actual use, thereby improving the test accuracy of the performance test tooling.

[0051] The performance testing tooling includes a plurality of the loading devices 20 and the 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. Correspondingly, 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 transfer 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 testing of the performance of the gas rudder aerodynamic test system.

[0052] It should be noted that when testing the strength and rigidity 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 and the top 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 result.

[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 tooling 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 implement 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, it is possible to simulate the force applied by the gas rudder to the aerodynamic test system when the gas rudder aerodynamic test system is in use, and apply the force 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 of the gas rudder aerodynamic test scenario, in the process by testing the bearing capacity of the gas rudder aerodynamic test system, determine whether the strength of the gas rudder aerodynamic test system can meet the force in the test process, by testing the angular deflection of the servo mechanism 13 and the support shaft 12, test the following performance of the servo mechanism 13, and then achieve the performance test of the gas rudder aerodynamic test system, to avoid the gas rudder aerodynamic test system when carrying a rocket engine to carry out aerodynamic testing of the gas rudder Failure, affecting the research and development progress.

[0055] In some embodiments, 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 , and 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 the side wall. The bolt 34 passes through the through hole and is threadedly connected to the threaded groove, so that the adapter 31 and the loading rod 32 are fixedly connected, and 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 with the loading device 20 through a rolling bearing 33, which can realize the adapter function. During the test of the gas rudder aerodynamic test system, when the loading adapter 30 is damaged, the adapter 31 and the loading rod 32 are connected to each other, which can also avoid the adapter 31 and the loading rod 32 from being completely damaged, thereby reducing the test cost and facilitating the practicality of the performance test tooling.

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

[0060] Specifically, since the function of the loading device 20 is to simulate the aerodynamic force of the gas rudder on the strain balance 11, the force of the gas rudder received by the strain balance 11 during the test is analyzed. The forces received by the strain balance 11 include two types, one is an axial force perpendicular to the axial direction of the gas rudder (i.e., the axial direction of the strain balance 11), and the other is a normal force perpendicular to the rudder surface of the gas rudder. Therefore, the loading device 20 needs to simulate two forces, i.e., axial force and normal force. The axial force and normal force are two forces acting vertically, so the loading device 20 includes two vertically arranged loading components 21, one loading component 21 simulates the axial force, which is perpendicular to the axial direction of the strain balance 11, and the other loading component 21 simulates the normal force, which is perpendicular to the mounting surface of the independent mounting bracket 8. The loading components 21 in each loading device 20 simulate the force when the gas rudder aerodynamic test system is running.

[0061] In addition, since one loading adapter 30 connects two loading assemblies 21, two rolling bearings 33 are arranged on the loading adapter 30, so that the two rolling bearings 33 are respectively connected to the two loading assemblies 21, which 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 helps to improve 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, Figure 8 As shown, the loading assembly 21 includes a loading ear 211 and a hydraulic cylinder 212 connected to each other. The loading ear 211 is connected to the rolling bearing 33, and the hydraulic cylinder 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 with 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 popularization and application of the performance testing tooling.

[0065] In some embodiments, Figure 1 to Figure 4 As shown, the test fixture also includes a bearing structure 40, and the bearing structure 40 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 bear 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, Figure 6 As shown, the test fixture further includes a plurality of simulated strain balances 50, and the simulated strain balances 50 are used to replace the strain balances 11 of the gas rudder aerodynamic test system to perform a performance test 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 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 the strain balance 11 from being damaged during the test of the gas rudder aerodynamic test system, thereby ensuring the test progress of the gas rudder aerodynamic test system.

[0071] In some embodiments, 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 maximum deflection.

[0072] Specifically, the loading device 20 is used to simulate the force of the gas rudder when the gas rudder aerodynamic test system is tested. 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 applied force is the axial force and the normal force deflected according to the deflection angle. Therefore, setting one of the multiple loading devices 20 so that the loading direction of the loading device 20 is the same as the direction of the force at the maximum deflection angle of the gas rudder can avoid interference with the loading device 20 and at the same time improve the simulation reality 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 performance test tooling as described above, such as Fig. 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 movement instruction, wherein the preset movement instruction includes a movement 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 in a powered-on state, and the strain balance 11 can output the induced stress in the form of an electrical signal.

[0076] The tester controls the loading device 20 in the performance test tooling to load and maintain the preset loading load, and the preset loading load is to simulate the stress condition of each servo mechanism 13 when the gas rudder is at the maximum deflection angle. The servo mechanism 13 moves according to the preset motion instruction while the loading device 20 is loading, so as to test the following characteristics of the servo mechanism 13, the stiffness and strength of the strain balance of the aerodynamic test system when the gas rudder is at the maximum deflection angle. Testing the parameters of the aerodynamic test system at the maximum deflection angle of the gas rudder is equivalent to testing the limit value of the aerodynamic test system. If the performance of the aerodynamic test system is good when the gas rudder is at the maximum deflection angle, it can still maintain good performance during the test process under other conditions, which not only simplifies the test, but also improves the accuracy of the test.

[0077] Exemplarily, 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 gas rudder installed on the mounting surface of 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 the same as the load direction when the gas vane is not deflected (that is, perpendicular and parallel to the mounting surface of the gas vane mounted on the independent mounting bracket 8, such as Figure 8 F x and F y ) and is arranged around the installation surface of the gas vane. 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 gas rudder surface is at the maximum deflection angle δ max =30°, 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, and the loading directions of 3 of the loading devices 20 are the same, so the preset loading load is the same, which is F x =8892.3N, F y =8598.1N, the loading direction of another 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 according to their corresponding preset loading loads respectively, and maintains the loading effect. During this period, the servo mechanism 13 is controlled to move according to the preset motion instructions, that is, the servo mechanism 13 is controlled to actively rotate a specific angle within a specific time. During the process, the deflection angle of the support shaft 12 connecting the servo mechanism 13 and the strain balance 11 is observed, and the difference between the two angles is compared to test the following characteristics of the servo mechanism 13 when the gas rudder is at the maximum deflection angle.

[0081] The preset motion instruction may be, for example, Fig.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 the test data of the strain 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 balance 11 , the support shaft 12 and the servo mechanism 13 to obtain the performance test results of the gas rudder aerodynamic test system.

[0085] Specifically, the test personnel conduct a specific analysis on the test data of the strain balance 11 , the support shaft 12 , and the servo mechanism 13 to obtain the performance test results of the gas rudder 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 can be determined whether the strain balance 11 operates normally during the test (that is, 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] Exemplarily, 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 has not been 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, by analyzing the test process of the aerodynamic test system and analyzing the limit effects it is subjected to during the test of the gas rudder, the preset loading load is obtained, 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 one 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, in step S100: before the loading device 20 is controlled to load according to a preset loading load and the servo mechanism 13 moves according to a preset movement instruction, the method further includes:

[0091] Step S400, replacing the strain balance in the gas rudder aerodynamic test system with a simulated strain balance 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, 3 of which 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 rudder on the independent mounting bracket 8 is the maximum deflection angle δ of the gas rudder 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 them for a fixed time. After each load loading level, the tester observes whether the independent mounting bracket 8 and the simulated strain balance 50 have any cracks or fissures, 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 fissures 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 rudder aerodynamic test system passes the test, setting the loading device 20 to load according to a preset loading load, and the servo mechanism 13 to move according to the simulated motion instruction, so as 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 test personnel set 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] Exemplarily, the simulated motion instruction is as follows: Fig.11 As shown, the deflection angle of the servo mechanism 13 gradually increases to 30°, is maintained 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] Step S900 , in response to determining that the following characteristic of the servo mechanism 13 passes the test, the analog strain balance 50 is removed and replaced with the strain 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 tests 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 simulated strain balance 50 replaces the strain balance 11, thereby achieving a preliminary test of the aerodynamic test system. It is possible to 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 the test cost and improving the practicability 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, the displacement meter is provided in plurality and is 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, fissures, 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 such cracks occur 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 observing the appearance alone.

[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 rudder 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 bearing capacity of the independent mounting bracket 8 has passed the test, and if the mounting support 14 and the simulated strain balance 50 have no cracks or cracks, it can be determined that the bearing capacity of the gas rudder aerodynamic test system has passed the test.

[0115] Exemplarily, the preset range is (0-5 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 by 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, Fig.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 describes some embodiments of the present application. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recorded in the claims can be performed in an order different from that in the above embodiments and still achieve the desired results. In addition, the processes depicted in the accompanying drawings do not necessarily require the specific order or continuous order shown to achieve the desired results. In some 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. In line with the concept 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 is apparent to those skilled in the art that the present application embodiments can be implemented without these specific details or when these specific details are varied. Therefore, these descriptions should be considered illustrative rather than restrictive.

[0121] Although 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 the present 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, the test structures comprising a strain 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, wherein the loading devices are connected to the strain balance via a loading adapter, wherein the loading adapter is connected to one end of the strain balance away from the support rotating shaft, wherein the loading devices and the strain balance are arranged in a one-to-one correspondence, and wherein 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.

2. The performance test tool of the gas rudder aerodynamic test system according to claim 1, characterized in that: The loading adapter device comprises an adapter and a loading rod connected to each other. The adapter is connected to the strain balance. A rolling bearing is sleeved on the loading rod. The rolling bearing is connected to the loading device.

3. The performance test tooling of the gas rudder aerodynamic test system according to claim 2 is characterized in that: The loading device comprises two vertically arranged loading assemblies, and the loading rod of the loading adapter device is provided with two rolling bearings, and the rolling bearings are connected to the loading assemblies in a one-to-one correspondence.

4. The performance test tooling of the gas rudder aerodynamic test system according to claim 3 is characterized in that: The loading assembly comprises a loading ear and a hydraulic actuator connected to each other, the loading ear is connected to the rolling bearing, and the hydraulic actuator is used to output the loading effect.

5. The performance test tooling of the gas rudder aerodynamic test system according to claim 4 is 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 one end of the hydraulic actuator away from the loading adapter is connected to the inner wall of the installation space.

6. 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 balance of the gas rudder aerodynamic test system to perform performance testing of the gas rudder aerodynamic test system.

7. 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 when the gas vane is at maximum deflection.

8. A performance test method for a gas rudder aerodynamic test system, characterized in that: Using the performance testing tool as described in any one of claims 1 to 7, the performance testing method comprises: 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 the test data of the strain balance, the support shaft and the servo mechanism; The test data of the strain balance, the support shaft and the servo mechanism are analyzed to obtain the performance test results of the gas rudder aerodynamic test system.

9. The performance test method of the gas rudder aerodynamic test system according to claim 8, characterized in that: Before controlling the loading device to load according to the preset loading load and the servo mechanism to move according to the preset movement instruction, the method further includes: Replacing the strain balance in the gas rudder aerodynamic test system with a simulated strain 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 rudder 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 the 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.

10. The performance test method of the gas rudder aerodynamic test system according to claim 9, 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: The applied load of the loading device is sequentially set according to the load loading levels, and the values ​​of the displacement meter are sequentially recorded; 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.

Images