Testing system and method for simultaneously testing gas vane and air vane

Abstract

The invention provides a test system for simultaneously testing a gas vane and an air vane, which comprises an independent mounting bracket, a gas vane force measuring device, an engine and a cabin structure, and is characterized in that the gas vane force measuring device is used for being connected with a to-be-tested gas vane, and the outer side wall of the cabin structure is provided with an air vane mounting groove for mounting the to-be-tested air vane; an air rudder mounting groove is formed in the cabin structure, the air rudder mounting groove is formed close to the free end of the cabin structure, a gas rudder mounting seat for mounting a synchronous gas rudder is arranged on the end face of the free end of the cabin structure, and the gas rudder mounting seat and the air rudder mounting groove are correspondingly arranged; and the gas vane force measuring device is located on the periphery of the second test through hole, and a to-be-tested gas vane of the gas vane mounting seat and a to-be-tested gas vane connected with the gas vane force measuring device are uniformly arranged at the port of the free end of the cabin body structure. According to the invention, the to-be-tested air rudder and the to-be-tested gas rudder are measured at the same time, the test efficiency is improved, and the test cost is reduced.

Description

Technical Field

[0001] The present application relates to the field of aerospace testing technology, and in particular to a testing system and method for simultaneously testing a gas rudder and an air rudder. Background Art

[0002] In the aerospace field, the testing of gas rudders and air rudders is an important part of aircraft design. For a long time, these two tests have been carried out separately, which consumes a lot of time and cost. With the continuous improvement of aircraft performance requirements, higher requirements are placed on the testing of gas rudders and air rudders. How to efficiently complete the testing of gas rudders and air rudders within limited time and cost has become an urgent problem to be solved. Summary of the invention

[0003] In view of this, the purpose of the present application is to propose a testing system and method for simultaneously testing a gas rudder and an air rudder, so as to solve the problem that the gas rudder and the air rudder cannot be tested simultaneously.

[0004] Based on the above purpose, the present application provides a test system for simultaneously testing a gas rudder and an air rudder, comprising an independent mounting bracket, a gas rudder force measuring device, an engine and a cabin structure, wherein the gas rudder force measuring device is used to connect with the gas rudder to be tested and is located on one side of the independent mounting bracket, and the engine and the cabin structure connected in sequence are located on the other side of the independent mounting bracket;

[0005] An air rudder mounting groove for mounting the air rudder to be tested is provided on the outer side wall of the cabin structure, the air rudder mounting groove is arranged close to the free end of the cabin structure, a gas rudder mounting seat for mounting a synchronous gas rudder that runs synchronously with the air rudder to be tested is provided on the end surface of the free end of the cabin structure, the gas rudder mounting seat is arranged corresponding to the air rudder mounting groove, a steering gear is provided in the cabin structure, an output end of the steering gear is used to connect with the synchronous gas rudder and the air rudder to be tested, and a displacement sensor is provided on the output end;

[0006] The independent mounting bracket is provided with a first test through hole and a second test through hole which are connected to each other, wherein the first test through hole is used to provide a deflection space for the air rudder to be tested installed in the air rudder mounting groove, and the second test through hole is adapted to the periphery of the free end of the cabin structure so as to allow the free end of the cabin structure to pass through;

[0007] The gas rudder force measuring device is provided in plurality and is located at the periphery of the second test through hole, and the synchronous gas rudder and the gas rudder to be tested are evenly arranged at the ports at the free end of the cabin structure.

[0008] Furthermore, the gas rudder force measuring device includes a servo mechanism, a mounting support, a strain balance and a water-cooled adapter rod, the mounting support is connected to the independent mounting bracket, the mounting support is provided with a support shaft, one end of the support shaft away from the mounting through hole is connected to the servo mechanism, one end of the support shaft close to the mounting through hole is connected to the strain balance, the other end of the strain balance is connected to the water-cooled adapter rod, and the water-cooled adapter rod is used to connect to the gas rudder to be tested.

[0009] Furthermore, a heat protection shell is provided on one side of the mounting support close to the mounting through hole, and the heat protection shell covers the periphery of the strain balance and the water-cooled adapter rod, and a through hole adapted to the connecting end of the gas rudder to be tested is provided at one end thereof away from the mounting support, for the connecting end of the gas rudder to be tested to pass through.

[0010] Furthermore, the projections of the gas rudder mounting seat on the end surface of the free end of the cabin structure are all located within the end surface.

[0011] Further, the independent mounting bracket includes a connected mounting vertical plate, a mounting support plate and a lifting structure, the mounting support plate includes a bottom plate and a vertical plate, the mounting vertical plate is provided with the first test through hole and the second test through hole, the vertical plate is provided with a mounting through hole, the mounting vertical plate is connected to the vertical plate in a lifting manner, and the first test through hole and the second test through hole are both provided corresponding to the vertical plate;

[0012] The lifting structure comprises a mounting seat and a lifting member connected to each other, the mounting seat is located on the bottom plate, and the lifting end of the lifting member is connected to the mounting vertical plate.

[0013] Furthermore, the independent mounting bracket also includes a mounting base, and the mounting base is located at the bottom of the base plate and connected to the base plate.

[0014] Furthermore, the test system also includes a test bench, a top surface of which is evenly provided with a plurality of T-slots, and the test bench is connected to the mounting base via the T-slots to support the independent mounting bracket, the engine and the cabin structure.

[0015] Furthermore, the independent mounting bracket also includes a tensioning mechanism, and a connecting ear is provided on the top of one side of the mounting support plate close to the engine. One end of the tensioning mechanism is connected to the connecting ear, and the other end is connected to the test bench and is arranged close to the engine.

[0016] Furthermore, the tensioning mechanism includes a connecting seat and a connecting rod, the connecting seat is located on the test bench, one end of the connecting rod is rotatably connected to the connecting ear, and the other end is rotatably connected to the connecting seat.

[0017] Based on the same inventive concept, the present application also provides a method for using the above-mentioned test system for simultaneously testing the gas rudder and the air rudder, comprising the following steps:

[0018] In response to determining that the ignition request is received, an ignition signal is sent to the engine, and an operation instruction is sent to the servo mechanism of the steering engine and the gas rudder force measuring device, so that the gas rudder to be tested, the synchronous gas rudder and the air rudder to be tested are operated simultaneously;

[0019] Acquire the test deflection data collected by the displacement sensor of the steering gear, the test force data collected by the strain balance of the gas rudder force measuring device, and the test deflection data collected by the angle sensor connected to the support shaft;

[0020] Comparing and analyzing the test deflection data collected by the displacement sensor of the steering gear with the command deflection data in the operation command received by the steering gear, to obtain the following characteristic test result of the air rudder to be tested;

[0021] Comparing and analyzing the test deflection data collected by the angle sensor and the command deflection data in the operation command received by the servo mechanism of the gas rudder force measuring device, to obtain the following characteristic test result of the gas rudder to be tested;

[0022] The test force data collected by the strain balance of the gas rudder force measuring device and the test deflection data collected by the angle sensor located on the support shaft are analyzed to obtain the aerodynamic force test result of the gas rudder to be tested.

[0023] From the above, it can be seen that the present application provides a test system for simultaneously testing a gas rudder and an air rudder, wherein the gas rudder force measuring device is used to test the aerodynamic force and deflection following characteristics of the gas rudder to be tested connected thereto under the action of the engine, the servo controls the deflection of the air rudder to be tested connected thereto under the action of the engine, and the following characteristics of the air rudder to be tested are obtained by comparing the deflection angle command sent by the servo to the air rudder to be tested and the actual deflection angle of the air rudder to be tested measured by the displacement sensor on the servo under the action of the engine. The gas rudder force measuring device is used to test the gas rudder to be tested connected thereto, thereby realizing the test of the gas rudder to be tested, and further realizing the simultaneous measurement of the air rudder to be tested and the gas rudder to be tested, that is, the test of the air rudder to be tested and the gas rudder to be tested can be completed by starting the engine once, which is beneficial to improving the test efficiency and reducing the test cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] 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.

[0025] Figure 1 A schematic diagram of the three-dimensional structure of a test system for testing a gas rudder and an air rudder to be tested installed in an embodiment of the present application;

[0026] Figure 2 This is a schematic structural diagram of a gas rudder force measuring device (excluding a servo mechanism and a mounting support) according to an embodiment of the present application;

[0027] Figure 3 This is a schematic cross-sectional structure diagram of a water-cooled transfer rod according to an embodiment of the present application;

[0028] Figure 4 This is a schematic diagram of the three-dimensional structure of the independent mounting bracket according to an embodiment of the present application;

[0029] Figure 5 A schematic diagram of a three-dimensional structure for installing a vertical plate in an embodiment of the present application;

[0030] Figure 6 Schematic diagram of the three-dimensional structure of the support plate installed in the embodiment of the present application Figure 1 ;

[0031] Figure 7 Schematic diagram of the three-dimensional structure of the support plate installed in the embodiment of the present application Figure 2 ;

[0032] Figure 8 It is a side structural schematic diagram of the tensioning mechanism of an embodiment of the present application;

[0033] Fig. 9 A flowchart of a method for using a test system for simultaneously testing a gas rudder and an air rudder according to an embodiment of the present application;

[0034] Fig.10 This is a schematic diagram of the electrical connection structure of a test system for simultaneously testing a gas rudder and an air rudder according to an embodiment of the present application.

[0035] In the figure: 10, independent mounting bracket; 11, first test through hole; 12, second test through hole; 13, mounting vertical plate; 14, mounting support plate; 141, bottom plate; 142, vertical plate; 143, mounting through hole; 144, connecting ear piece; 145, reinforcing rib; 146, cross beam; 147, well beam; 148, well core column; 149, lateral reinforcing rib; 150, trapezoidal plate; 15, lifting structure; 16, mounting base; 17, tensioning mechanism; 17 1. Connecting seat; 172. Connecting rod; 20. Gas rudder force measuring device; 21. Servo mechanism; 22. Mounting support; 221. Support shaft; 23. Strain balance; 24. Water-cooled adapter rod; 241. Water filling tank; 25. Thermal protection shell; 30. Engine; 31. Engine bracket; 40. Cabin structure; 50. Test bench; 51. T-slot; 52. Limit wall; 60. Air rudder to be tested; 70. Gas rudder to be tested; 80. Synchronous gas rudder. DETAILED DESCRIPTION

[0036] 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.

[0037] 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.

[0038] As described in the background technology, currently, the aerodynamic test of the gas rudder is mainly completed by carrying out an engine hot test using a separately designed aerodynamic test system. Generally, four sets of gas rudders on the aircraft are tested simultaneously. However, this test method has the following shortcomings: (1) The test equipment is complex and the cost is high; (2) The test cycle is long and cannot quickly respond to aircraft design requirements.

[0039] Existing air rudder control strategy tests are also conducted using a separate test bench, which has a long test cycle, is unable to quickly optimize the control strategy, and is unable to achieve coordinated control of the gas rudder and the air rudder, making it difficult to fully test the performance of the aircraft.

[0040] Based on this, the present application proposes a test system and method for simultaneously testing the gas rudder and the air rudder, which can simultaneously test the gas rudder and the air rudder, and then realize the coordinated control test of the gas rudder and the air rudder, which is beneficial to improving the performance of the aircraft.

[0041] Testing the gas rudder and air rudder at the same time has the following characteristics and advantages: 1) Saving test equipment: Using one engine to test the gas rudder and air rudder at the same time avoids repeated investment and reduces test costs. 2) Shortening the test cycle: One engine can carry out two tests at the same time, which improves test efficiency, shortens the test cycle, and helps to quickly respond to aircraft design requirements. 3) Simulating the real flight environment: Using the engine to conduct the test, the actual flight environment of the aircraft is truly simulated, which improves the accuracy of the test results. 4) Cooperative control: By conducting gas rudder and air rudder tests at the same time, the coordinated control of the gas rudder and air rudder can be achieved to give full play to the performance of the aircraft.

[0042] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0043] A test system for testing both gas rudder and air rudder, such as Figure 1 As shown, it comprises an independent mounting bracket 10, a gas rudder force measuring device 20, an engine 30 and a cabin structure 40. The gas rudder force measuring device 20 is used to connect with the gas rudder 70 to be tested and is located on one side of the independent mounting bracket 10. The engine 30 and the cabin structure 40 connected in sequence are located on the other side of the independent mounting bracket 10.

[0044] An air rudder mounting groove for mounting the air rudder 60 to be tested is provided on the outer side wall of the cabin structure 40, and the air rudder mounting groove is arranged close to the free end of the cabin structure 40. A gas rudder mounting seat for mounting a synchronous gas rudder 80 that runs synchronously with the air rudder 60 to be tested is provided on the end surface of the free end of the cabin structure 40, and the gas rudder mounting seat is arranged corresponding to the air rudder mounting groove. A steering gear is provided in the cabin structure 40, and an output end of the steering gear is used to connect with the synchronous gas rudder 80 and the air rudder 60 to be tested, and a displacement sensor is provided on the output end.

[0045] The independent mounting bracket 10 is provided with a first test through hole 11 and a second test through hole 12 which are connected to each other. The first test through hole 11 is used to provide a deflection space for the air rudder 60 to be tested which is installed in the air rudder mounting groove. The second test through hole 12 is adapted to the periphery of the free end of the cabin structure 40 so as to allow the free end of the cabin structure 40 to pass through.

[0046] The gas rudder force measuring device 20 is provided in plurality and is located at the periphery of the second test through hole 12 . The synchronous gas rudder 80 and the gas rudder to be tested 70 are evenly arranged at the ports at the free end of the cabin structure 40 .

[0047] Specifically, the engine 30 is the power source of the test system, that is, the ignition starter, which is used to simulate the real action scene of the gas rudder 70 to be tested, the air rudder 60 to be tested, and the synchronous gas rudder 80 when they are used in aerospace. The cabin structure 40 is the action carrier of the synchronous gas rudder 80, the gas rudder 70 to be tested, and the air rudder 60 to be tested, that is, the action force of the engine 30 on the synchronous gas rudder 80, the gas rudder 70 to be tested, and the air rudder 60 to be tested is transmitted through the cabin structure 40, which also simulates the real action scene of the synchronous gas rudder 80, the gas rudder 70 to be tested, and the air rudder 60 to be tested when they are used in aerospace.

[0048] The independent mounting bracket 10 is used to install the gas rudder force measuring device 20 and to allow the free end of the cabin structure 40 to pass through, so as to simulate the operation of the synchronous gas rudder 80 and the air rudder 60 to be tested in a real scene, and at the same time, the force exerted on the gas rudder 70 to be tested can be transmitted to the independent mounting bracket 10, so as to avoid damage to the gas rudder 70 to be tested or the cabin structure 40, thereby improving the convenience of testing the air rudder 60 to be tested, the synchronous gas rudder 80 and the gas rudder 70 to be tested.

[0049] The servo is located in the cabin structure 40, near the air servo mounting slot and the gas servo mounting seat, so as to be connected with the air servo to be tested 60 and the synchronous gas servo 80. The output end of the servo drives the air servo to be tested 60 and the synchronous gas servo 80 to deflect synchronously at the same angle. Since the synchronous gas servo 80 moves in the engine jet, it will generate aerodynamic force, thereby affecting the control effect of the servo. When the air servo to be tested 60 and the synchronous gas servo 80 are connected to the output end of the servo at the same time to detect the aerodynamic force generated by the synchronous gas servo 80, the servo controls the control effect of the air servo to be tested 60, that is, the following characteristic. The synchronous gas servo 80 installed on the gas servo mounting seat plays the role of simulating the real operation scene, and does not participate in the gas servo aerodynamic test, but it is in the same group as the gas servo to be tested 70 to simulate the action of the gas servo in the real operation scene, thereby facilitating the test accuracy. Exemplarily, in actual application, four of the gas rudders 70 to be tested are set on the free end face of the cabin structure 40, and when testing them, only three of the gas rudders 70 to be tested that are connected to the gas rudder force measuring device 20 are tested, and the other gas rudder 70 to be tested (i.e., the synchronous gas rudder 80) does not participate in the test, but needs to be installed in the corresponding position to avoid affecting the authenticity of the test results of the gas rudder 70 to be tested.

[0050] The end face of the free end of the cabin structure 40 is arranged parallel to a side of the independent mounting bracket 10 on which the gas rudder force measuring device 20 is mounted. During testing, the distance between the end faces of the independent mounting bracket and the free end of the cabin structure 40 is adjusted to ensure that the rudder axes of the synchronous gas rudder 80 and the gas rudder 70 to be tested are located on the same plane, so that the gas rudder 70 to be tested connected to the gas rudder force measuring device 20 and the synchronous gas rudder 80 located on the gas rudder mounting seat are at the same distance from the end face of the free end of the cabin structure 40, thereby simulating the normal use state of the gas rudder 70 to be tested, which is beneficial to improving the accuracy of the test results of the gas rudder 70 to be tested.

[0051] Since the air rudder 60 to be tested is arranged close to the free end of the cabin structure 40, and the end face of the free end of the cabin structure 40 is arranged parallel to the end face of the independent mounting bracket 10 on which the gas rudder force measuring device 20 is installed, and there is adjustment space between them, in order to prevent the independent mounting bracket 10 from affecting the deflection operation of the air rudder 60 to be tested, the first test through hole 11 is provided to provide a deflection space for the air rudder 60 to be tested, which is beneficial to the testing of the air rudder 60 to be tested.

[0052] The gas rudder to be tested 70 and the synchronous gas rudder 80 are both located at the port of the free end of the cabin structure 40 to receive the aerodynamic force generated by the engine 30 transmitted through the port of the cabin structure 40, simulating the actual action scenario of the gas rudder to be tested 70, thereby facilitating the testing of the gas rudder to be tested 70.

[0053] In this embodiment, the gas rudder force measuring device 20 is used to test the aerodynamic force and deflection following characteristics of the gas rudder to be tested 70 connected thereto under the action of the engine 30, the servo motor controls the deflection of the air rudder 60 to be tested connected thereto under the action of the engine 30, and the following characteristics of the air rudder 60 to be tested are obtained by comparing the deflection angle command sent by the servo motor to the air rudder 60 to be tested and the actual deflection angle of the air rudder 60 to be tested measured by the displacement sensor on the servo motor under the action of the engine 30. The gas rudder force measuring device 20 is used to test the gas rudder 70 to be tested connected thereto, thereby realizing the test of the gas rudder 70 to be tested, and further realizing the simultaneous measurement of the air rudder 60 to be tested and the gas rudder 70 to be tested, that is, the test of the air rudder 60 to be tested and the gas rudder 70 to be tested can be completed by starting the engine 30 once, which is beneficial to improving the test efficiency and reducing the test cost.

[0054] In some embodiments, Figure 1 and Figure 2 As shown, the gas rudder force measuring device 20 includes a servo mechanism 21, a mounting support 22, a strain balance 23 and a water-cooled adapter rod 24. The mounting support 22 is connected to the independent mounting bracket 10. A support shaft 221 is provided on the mounting support 22. One end of the support shaft 221 away from the mounting through hole 143 is connected to the servo mechanism 21, and one end of the support shaft 221 close to the mounting through hole 143 is connected to the strain balance 23. The other end of the strain balance 23 is connected to the water-cooled adapter rod 24. The water-cooled adapter rod 24 is used to connect to the gas rudder 70 to be tested.

[0055] Specifically, the mounting support 22 is a fixing structure of the gas rudder force measuring device 20, so that the gas rudder force measuring device 20 is fixed on the independent mounting bracket 10, and the support shaft 221 is arranged through the mounting support 22 and is rotatably connected to the mounting support 22, so that the servo mechanism 21 can drive the gas rudder to deflect through the support shaft 221, the strain balance 23 and the water-cooled adapter rod 24.

[0056] When the gas rudder 70 to be tested is subjected to aerodynamic force, the servo mechanism 21 drives the gas rudder 70 to be tested to deflect a corresponding angle, that is, a controlled deflection angle of the gas rudder 70 to be tested. The angle sensor on the support shaft 221 measures the deflection angle of the support shaft 221, thereby measuring the deflection angle of the gas rudder 70 to be tested, that is, the actual deflection angle of the gas rudder 70 to be tested. By comparing the actual deflection angle of the gas rudder 70 to be tested under the action of aerodynamic force with the controlled deflection angle of the servo mechanism 21, the deflection following characteristic of the gas rudder 70 to be tested under the action of aerodynamic force is determined, thereby testing the deflection following characteristic of the gas rudder 70 to be tested.

[0057] The strain balance 23 is connected to the gas rudder 70 to be tested. During the test, the engine 30 is ignited and started to generate thermal gas power acting on the gas rudder 70 to be tested. The gas rudder 70 to be tested is subjected to a corresponding force. The strain balance 23 can sense the magnitude of the force applied to the gas rudder 70 to be tested, thereby realizing aerodynamic testing of the gas rudder 70 to be tested.

[0058] like Figure 3 As shown, a water injection groove 241 is provided in the water-cooling adapter rod 24, and a water inlet and a water outlet connected to the water injection groove 241 are provided on the water-cooling adapter rod 24, and water is injected into the water injection groove 241 through the water inlet. One end of the water-cooling adapter rod 24 is connected to the strain balance 23, and the other end is connected to the gas rudder 70 to be tested. The water injection groove 241 is located at the end of the water-cooling adapter rod 24 connected to the strain balance 23, and can cool the heat conducted by the gas rudder 70 to be tested, so as to prevent the heat of the gas rudder 70 to be tested from being conducted to the strain balance 23, thereby affecting the sensing sensitivity of the strain balance 23, and further affecting the force measuring accuracy of the gas rudder force measuring device 20.

[0059] In this embodiment, when the gas rudder 70 to be tested is acted upon by the aerodynamic force of the engine 30, the gas rudder force measuring device 20 can obtain the force applied to the gas rudder 70 to be tested through the strain balance 23, thereby testing the aerodynamic force of the gas rudder 70 to be tested, and testing the deflection following characteristics of the gas rudder 70 to be tested through the servo mechanism 21 and the angle sensor on the support shaft 221. The heat conducted by the gas rudder 70 to be tested is cooled through the water-cooled adapter rod 24 to avoid affecting the strain balance 23, which is beneficial to improving the measurement accuracy of the strain balance 23 and further beneficial to the test accuracy of the gas rudder force measuring device 20.

[0060] In some embodiments, Figure 1As shown, a heat protection shell 25 is provided on one side of the mounting support 22 close to the mounting through hole 143. The heat protection shell 25 is arranged to cover the periphery of the strain balance 23 and the water-cooled adapter rod 24. A through hole adapted to the connecting end of the gas fin 70 to be tested is provided at one end thereof away from the mounting support 22, so that the connecting end of the gas fin 70 to be tested can pass through.

[0061] Specifically, the gas rudder 70 to be tested is arranged corresponding to the free end port of the cabin structure 40. Accordingly, the structure connected to the gas rudder 70 to be tested and close to the port of the cabin structure 40 (that is, the strain balance 23 and the water-cooled adapter rod 24) is easily affected by the heat emitted from the port. Therefore, the heat protection shell 25 is arranged to cover the outer periphery of the strain balance 23 and the water-cooled adapter rod 24 to isolate the hot air from the port of the cabin structure 40 from affecting the normal use of the strain balance 23 and the water-cooled adapter rod 24. The setting of the heat protection shell 25 is beneficial to improving the test accuracy of the gas rudder force measuring device 20, and further beneficial to the test accuracy of the test system.

[0062] It should be noted that one end of the heat protection shell 25 connected to the mounting support 22 is an annular end portion, which is adapted to the side of the mounting support 22 so as to be tightly connected to the mounting support 22. The other end of the heat protection shell 25 is a closed structure so as to cover the strain balance 23 and the water-cooled adapter rod 24. A through hole is provided at this end so that the gas rudder 70 to be tested can pass through and be connected to the water-cooled adapter rod 24 without affecting the deflection of the gas rudder 70 to be tested and the transmission of the force it is subjected to.

[0063] In some embodiments, the projection of the gas rudder mounting seat on the end surface of the free end of the cabin structure 40 is located within the end surface.

[0064] Specifically, the gas rudder mounting seat is located on the end face of the free end of the cabin structure 40, the air rudder mounting groove is located on the side wall of the cabin structure 40 and is arranged close to the free end of the cabin structure 40, the position of the air rudder mounting groove at the free end of the cabin structure 40 coincides with the position of the gas rudder mounting seat at the free end of the cabin structure 40, the air rudder 60 to be tested is installed on the air rudder mounting groove, and needs to not be interfered with when performing deflection, therefore, the projection of the gas rudder mounting seat on the end face of the free end of the cabin structure 40 is arranged to be located within the end face, that is, the projection does not protrude from the side wall of the cabin structure 40, so as to avoid the gas rudder mounting seat interfering with the deflection of the air rudder 60 to be tested, thereby affecting the test of the air rudder 60 to be tested.

[0065] In some embodiments, Figure 4 , Figure 5 and Figure 6 As shown, the independent mounting bracket 10 includes a mounting vertical plate 13, a mounting support plate 14 and a lifting structure 15 connected to each other, the mounting support plate 14 includes a bottom plate 141 and a vertical plate 142, the mounting vertical plate 13 is provided with the first test through hole 11 and the second test through hole 12, the vertical plate 142 is provided with a mounting through hole 143, the mounting vertical plate 13 and the vertical plate 142 can be lifted and lowered, and the first test through hole 11 and the second test through hole 12 are both arranged corresponding to the vertical plate 142;

[0066] The lifting structure 15 includes a mounting seat and a lifting member connected to each other. The mounting seat is located on the bottom plate 141 , and a lifting end of the lifting member is connected to the mounting vertical plate 13 .

[0067] Specifically, the bottom plate 141 of the mounting support plate 14 is the supporting structure of the mounting support plate 14, the vertical plate 142 of the mounting support plate 14 is the connecting structure of the mounting support plate 14, the vertical plate 142 is stacked with the mounting vertical plate 13, the vertical plate 142 is provided with a vertical long hole, the mounting vertical plate 13 is provided with a circular hole corresponding to the long hole, and the bolt passes through the circular hole and the long hole at the same time to connect the mounting vertical plate 13 with the vertical plate 142.

[0068] The mounting seat of the lifting structure 15 is located on the bottom plate 141 , and the lifting end of the lifting structure 15 is fixedly connected to the mounting vertical plate 13 to drive the mounting vertical plate 13 and the bolt to move along the long hole, thereby realizing the lifting of the mounting vertical plate 13 .

[0069] The lifting structure 15 can be a worm gear mechanism, one end of the worm is a free end connected to the mounting vertical plate 13 , and the lifting of the worm can be achieved by rotating the worm gear, thereby achieving the lifting of the mounting vertical plate 13 .

[0070] During actual use, the heights of the first test through hole 11 and the second test through hole 12 on the mounting vertical plate 13 can be adjusted by the lifting structure 15, so that the second test through hole 12 has the same end face height and axial center height as the free end of the cabin structure 40, so as to simulate that the gas rudder 70 to be tested is located at the free end of the cabin structure 40, which is beneficial to the measurement accuracy of the gas rudder force measuring device 20.

[0071] The mounting vertical plate 13 is arranged away from the engine 30 relative to the vertical plate 142, and the first test through hole 11 and the second test through hole 12 on the mounting vertical plate 13 are arranged opposite to the mounting through hole 143 on the vertical plate 142, so that the free end of the cabin structure 40 passes through the mounting through hole 143 on the vertical plate 142 and abuts against the second test through hole 12, so that the second test through hole 12 supports the free end of the cabin structure 40, and the mounting through hole 143 is larger than the first test through hole 11 and the second test through hole 12, which can prevent the mounting through hole 143 from affecting the connection between the cabin structure 40 and the second test through hole 12, and prevent the mounting through hole 143 from affecting the deflection operation of the air rudder 60 to be tested.

[0072] It should be noted that the gas rudder force measuring device 20 is connected to the mounting vertical plate 13. The bottom plate 141 and the vertical plate 142 are vertically connected, and reinforcing ribs 145 are provided on both sides of the connection. Figure 7 As shown, in order to enhance the connection strength and rigidity of the bottom plate 141 and the vertical plate. The vertical plate 142 is provided with a crossbeam 146 and a well beam 147 in the horizontal direction, and a well core column 148 in the vertical direction. The well beam 147 and the well core column 148 are both arranged near the periphery of the installation through hole 143, and lateral reinforcing ribs 149 are arranged at other peripheries of the installation through hole 143 to further enhance the rigidity and strength of the vertical plate 142 and the installation through hole 143, which is beneficial to the safety of the installation support plate 14. The crossbeam 146, the well beam 147, the well core column 148 and the lateral reinforcing ribs 149 are all located on the side of the vertical plate 142 away from the installation vertical plate 13, so as to avoid affecting the connection between the vertical plate 142 and the installation vertical plate 13, and also avoid affecting the support stability after the vertical plate 142 and the installation vertical plate 13 are connected.

[0073] Trapezoidal plates 150 are provided at both ends of the vertical plate 142 , and the bottom of the trapezoidal plates 150 is connected to the bottom plate 141 , which is beneficial to the connection stability and rigidity between the vertical plate 142 and the bottom plate 141 .

[0074] In some embodiments, Figure 4 As shown, the independent mounting bracket 10 further includes a mounting base 16 , and the mounting base 16 is located at the bottom of the base plate 141 and connected to the base plate 141 .

[0075] Specifically, the mounting base 16 is connected to the bottom plate 141 to provide support for the bottom plate 141, enhance the strength of the bottom plate 141, and avoid damage to the bottom plate 141. The mounting vertical plate 13 may also be raised so that the second test through hole 12 on the mounting vertical plate 13 is flush with the free end height of the cabin structure 40, which is beneficial to the test accuracy of the test system.

[0076] It should be noted that a plurality of evenly arranged U-shaped grooves are provided on the bottom plate 141 , and the mounting base 16 and the bottom plate 141 are fixedly connected via the U-shaped grooves and bolts.

[0077] In some embodiments, Figure 1 As shown, the test system also includes a test bench 50, a top surface of which is evenly provided with a plurality of T-slots 51, and the test bench 50 is connected to the mounting base 16 via the T-slots 51 to support the independent mounting bracket 10, the engine 30 and the cabin structure 40.

[0078] Specifically, the test bench 50 is located below the engine 30, the cabin structure 40 and the independent mounting bracket 10 to support the engine 30, the cabin structure 40 and the independent mounting bracket 10, and is a supporting structure of the test system. The engine 30 and the cabin structure 40 are connected and are both connected to the test bench 50 through the engine bracket 31. The test bench 50 supports the engine 30 and the cabin structure 40 through the engine bracket 31.

[0079] The multiple T-slots 51 provided on the test bench 50 can facilitate the connection between the engine 30, the cabin structure 40 and the independent mounting bracket 10 and the test bench 50, and also enable the engine 30 to slide along the T-slots 51 under the action of the T-slots 51 to approach or move away from the independent mounting bracket 10 to complete the installation of the test system. After the position is determined, the engine 30 can be fixed on the test bench 50.

[0080] It should be noted that the engine 30 , the cabin structure 40 and the independent mounting bracket 10 are arranged in sequence along the length direction of the T-shaped slot 51 so that the engine 30 can move along the T-shaped slot 51 .

[0081] In addition, a limiting wall 52 is provided on the top of the test bench 50. The limiting wall 52 is located at the end of the engine 30 to limit the engine 30, which is beneficial to improving the test safety of the test system.

[0082] In some embodiments, Figure 4 and Figure 8 As shown, the independent mounting bracket 10 also includes a tensioning mechanism 17, and a connecting ear 144 is provided on the top of the side of the mounting support plate 14 close to the engine 30. One end of the tensioning mechanism 17 is connected to the connecting ear 144, and the other end is connected to the test bench 50 and is arranged close to the engine 30.

[0083] Specifically, the tensioning mechanism 17 is located on a side of the mounting support plate 14 away from the mounting vertical plate 13, and the tensioning mechanism 17 is connected to the top of the mounting support plate 14 to tighten the mounting support plate 14, and then tighten the mounting vertical plate 13, which can enhance the rigidity and strength of the independent mounting bracket 10 and prevent it from being broken or otherwise damaged due to the power of the engine 30 during the test.

[0084] The connection ear piece 144 provided on the mounting support plate 14 can facilitate the connection between the mounting support plate 14 and the tensioning mechanism 17 .

[0085] It should be noted that the tensioning structure is provided with two, which are respectively arranged near the two ends of the mounting support plate 14 and symmetrically arranged relative to the center line of the mounting support plate 14, so that the force exerted by the tensioning mechanism 17 on the mounting support plate 14 is uniform, which can prevent the mounting support plate 14 from being deformed under the action of the tensioning mechanism 17 and affecting the normal operation of the test system, thereby facilitating the test accuracy of the test system.

[0086] In some embodiments, Figure 8 As shown, the tensioning mechanism 17 includes a connecting seat 171 and a connecting rod 172 . The connecting seat 171 is located on the test bench 50 . One end of the connecting rod 172 is rotatably connected to the connecting ear piece 144 , and the other end is rotatably connected to the connecting seat 171 .

[0087] Specifically, the connecting seat 171 is used to connect with the test bench 50, and the connecting rod 172 is used to connect the connecting seat 171 and the connecting ear 144 to tighten the mounting support plate 14. The connecting rod 172 is rotatably connected with the connecting seat 171 and the connecting ear 144 so that the connecting rod 172 can connect the connecting seat 171 and the connecting ear 144 in a straight line, thereby avoiding the influence of the tightening effect of the connecting rod 172 on the mounting support plate 14 due to the direction fixation during the fixed connection, thereby affecting the effect of the tightening mechanism 17 on the mounting support plate 14, which is beneficial to improving the practicality of the test system.

[0088] In addition, the connecting rod 172 includes a ball joint 1, a connecting rod 1, a forward and reverse threaded screw, a connecting rod 2 and a ball joint 2 connected in sequence. The ball joints at both ends of the connecting rod 172 can facilitate the connection of the connecting rod. The forward and reverse threaded screws can adjust the length of the connecting rod 172 to achieve the tightening of the connecting rod 172.

[0089] The connecting seat 171 is provided with an ear adapter, one end of which is rotatably connected to the connecting rod 172, and the other end is detachably connected to the connecting seat 171, so as to adjust the front, back, left, and right positions of the connection between the connecting rod 172 and the connecting seat 171, which is beneficial to the tightening effect of the tightening mechanism 17.

[0090] Based on the same inventive concept, the present application also provides a method for using the above-mentioned test system for simultaneously testing the gas rudder and the air rudder, such as Fig. 9 As shown, the following steps are included:

[0091] Step S100, in response to determining that an ignition request is received, an ignition signal is sent to the engine 30, and an operation instruction is sent to the servo mechanism 21 of the steering engine and the gas rudder force measuring device 20, so that the gas rudder 70 to be tested, the air rudder 60 to be tested and the synchronous gas rudder 80 are operated simultaneously;

[0092] Specifically, before using the test system to test the gas rudder 70 to be tested and the air rudder 60 to be tested, the air rudder 60 to be tested is installed on the air rudder installation slot of the cabin structure 40 and connected to the output end of the steering gear, so that the steering gear can drive the air rudder 60 to be tested and the synchronous gas rudder 80 to be deflected accordingly. The gas rudder 70 to be tested is installed on a plurality of gas rudder force measuring devices 20 respectively, and the synchronous gas rudder 80 which is a set with the gas rudder 70 to be tested is installed on the gas rudder mounting seat, which is connected to the output end of the steering gear, so that the steering gear can drive the synchronous gas rudder 80 to be deflected accordingly. After completing the installation of the air rudder 60 to be tested, the synchronous gas rudder 80 and the gas rudder 70 to be tested, the test process of the test system is entered. Two pre-tests are required before entering the formal test to determine that the connection and operation of the test system and the gas rudder 70 to be tested, the air rudder 60 to be tested and the synchronous gas rudder 80 are normal. This step is a formal test process for the gas rudder 70 to be tested and the air rudder 60 to be tested.

[0093] In this step, the ignition request is equivalent to a timing signal, that is, the ignition of the engine 30, the start-up of the steering gear and the gas rudder force measuring device 20 are carried out simultaneously to realize the operation of the engine 30, that is, to carry out the test of the air rudder 60 to be tested and the gas rudder 70 to be tested, which is beneficial to the simultaneous testing of the gas rudder 70 to be tested and the air rudder 60 to be tested, and can also unify the data collection time, so as to subsequently compare and analyze the collected test data to obtain the test results.

[0094] It should be noted that if Fig.10As shown, the test system also includes a controller, which is remotely connected to the steering gear and the gas rudder force measuring device 20. An ignition request button is provided on the controller. When the ignition request button is pressed, it is determined that the ignition request is received, and the controller sends an ignition signal to the engine 30, and controls the operation of the steering gear and the gas rudder force measuring device 20. In the controller, what is connected to the servo is a servo controller and a servo test system; what is connected to the gas rudder force measuring device 20 is a motor driver and a motor control program; what is connected to the engine 30 is an ignition control system; the servo test system sends an operation instruction to the servo controller so that the servo controller drives the air rudder 60 to be tested and the synchronous gas rudder 80 to deflect simultaneously; the motor control program sends an operation instruction to the motor driver so that the motor driver drives the servo mechanism 21 connected thereto to deflect according to the operation instruction, thereby driving the support shaft 221, the strain balance 23 and the gas rudder 70 to be tested to deflect; and the ignition control system controls the ignition operation of the engine 30 based on the received ignition signal to provide a test scenario for the test system.

[0095] Step S200, acquiring the test deflection data collected by the displacement sensor of the steering gear, the test force data collected by the strain balance 23 of the gas rudder force measuring device 20, and the test deflection data collected by the angle sensor connected to the support shaft 221;

[0096] Specifically, the engine 30, the steering gear and the gas rudder force measuring device 20 are all running, so that the test data of the air rudder 60 to be tested and the gas rudder 70 to be tested can be obtained. The test data of the air rudder 60 to be tested is the test deflection data, that is, the actual deflection data of the air rudder 60 to be tested measured by the displacement sensor. The test data of the gas rudder 70 to be tested connected to the gas rudder force measuring device 20 includes test force data and test deflection data. The test deflection data is measured by the angle sensor connected to the support shaft 221 in the gas rudder force measuring device 20. The test force data is measured by the strain balance 23 in the gas rudder force measuring device 20. The strain balance 23 can output the sensed force in the form of strain or electrical signal. The test force data can be obtained by analyzing the strain or electrical signal measured by the strain balance 23.

[0097] It should be noted that the displacement sensor is connected to the steering gear test system, and the steering gear test system collects the test deflection data of the air rudder 60 to be tested measured by the displacement sensor. The controller also includes a data collector, and the data collector runs simultaneously with the motor control program, the steering gear test system and the ignition control system, that is, the collection start time of the data collection device is the same as the operation of the servo mechanism 21 and the ignition start time of the engine 30, and the data collector is connected to the angle sensor and the strain balance 23 to collect data from the angle sensor and the strain balance 23 according to a preset collection frequency.

[0098] Step S300, comparing and analyzing the test deflection data collected by the displacement sensor of the steering gear with the command deflection data in the operation command received by the steering gear, to obtain a test result of the following characteristic of the air rudder 60 to be tested;

[0099] Specifically, the test result of the following characteristic of the air rudder 60 to be tested is obtained by comparing the command deflection data and the test deflection data of the air rudder 60 to be tested. When the difference between the command deflection data and the test deflection data is within a normal range, a test result indicating that the following characteristic of the air rudder 60 to be tested is good is obtained. When the difference between the command deflection data and the test deflection data is not within the normal range, a test result indicating that the following characteristic of the air rudder 60 to be tested is poor is obtained. The normal range is a set range, which is determined through a comprehensive analysis based on the test system, the actual operating scenario of the air rudder 60 to be tested, and other conditions.

[0100] Step S400, comparing and analyzing the test deflection data collected by the angle sensor and the command deflection data in the operation command received by the servo mechanism 21 of the gas rudder force measuring device 20, to obtain a follow-up characteristic test result of the gas rudder 70 to be tested;

[0101] Specifically, the test result of the following characteristic of the gas rudder 70 to be tested connected to the gas rudder force measuring device 20 is obtained by comparing the command deflection data and the test deflection data of the gas rudder 70 to be tested. When the difference between the command deflection data and the test deflection data is within the normal range, the test result of a good following characteristic of the gas rudder 70 to be tested is obtained. When the difference between the command deflection data and the test deflection data is not within the normal range, the test result of a poor following characteristic of the gas rudder 70 to be tested is obtained. The normal range is a set range, which is determined by comprehensive analysis based on the test system, the actual operating scenario of the gas rudder 70 to be tested, and other conditions.

[0102] Step S500 , analyzing the test force data collected by the strain balance 23 of the gas rudder force measuring device 20 and the test deflection data collected by the angle sensor on the support shaft 221 , to obtain the aerodynamic force test result of the gas rudder 70 to be tested.

[0103] Specifically, the aerodynamic force test result of the gas rudder 70 to be tested connected to the gas rudder force measuring device 20 is obtained by testing the strain balance 23. By analyzing the strain or electrical signal measured by the strain balance 23, the magnitude of the force applied to the strain balance 23 in the axial direction and the normal direction of the gas rudder 70 to be tested is obtained, and then the aerodynamic force test result of the gas rudder 70 to be tested is obtained.

[0104] It should be noted that the direction of the force obtained by analyzing the strain balance 23 is related to the deflection angle of the gas rudder 70 to be tested. The deflection angle of the gas rudder 70 to be tested is obtained by the test deflection data collected by the angle sensor located on the support shaft 221. When the gas rudder 70 to be tested is not deflected, that is, the rudder surface of the gas rudder 70 to be tested is opposite to the free end of the cabin structure 40, the direction of the force applied to the strain balance 23 includes the normal force perpendicular to the rudder surface of the gas rudder 70 to be tested and the axial force perpendicular to the axis of the gas rudder 70 to be tested. When the strain balance 23 is connected to the gas rudder 70 to be tested, the direction of the force relative to the strain balance 23 can be determined. After the direction of the force of the strain balance 23 is determined, the magnitude of the force of different gas rudders 70 to be tested at different deflection angles can be analyzed and obtained.

[0105] In this embodiment, the testing process, test data acquisition process and test result determination process of the testing system are explained, so as to achieve the technical effect that the testing system simultaneously tests the air rudder 60 to be tested and the gas rudder 70 to be tested. The testing of the air rudder 60 to be tested and the gas rudder 70 to be tested can be completed by starting the engine 30 once, which is beneficial to improving the testing efficiency and reducing the testing cost.

[0106] The following describes the installation process and pre-test process of the test system:

[0107] 1. Installation process

[0108] (1) Install the gas rudder force measuring device 20

[0109] Install three sets of gas rudder force measuring devices 20 onto the mounting vertical plate 13 .

[0110] (2) Installation of engine 30, cabin structure 40, etc.

[0111] According to the assembly relationship, the cabin structure 40 , the air rudder 60 to be tested, the gas rudder 70 to be tested and other components are assembled; after the engine 30 is installed on the test bench 50 , the cabin structure 40 is docked with the engine 30 .

[0112] (3) Install the independent mounting bracket 10

[0113] The mounting support plate 14 is mounted on the mounting base 16 by means of bolts, and is hoisted to the test bench 50. After hoisting the mounting vertical plate 13 through the hoisting holes on the mounting vertical plate 13, the mounting vertical plate 13 is moved to ensure that its back is in contact with the frame. The approximate vertical position of the mounting vertical plate 13 can be determined by hoisting. After the lifting structure 15 is installed, the vertical position of the mounting vertical plate 13 can be precisely adjusted by means of the lifting structure 15, and the installation accuracy can be controlled within ±0.1mm, ensuring that the coaxiality of the center hole of the mounting vertical plate 13 with the engine 30 and the cabin structure 40 meets the requirements. After the installation position of the mounting vertical plate 13 is determined, the mounting vertical plate 13 is locked to the frame by means of hexagon socket bolts.

[0114] (4) Adjust the distance between the independent mounting bracket 10 and the cabin structure 40

[0115] The axial distance between the independent mounting bracket 10 and the cabin structure 40 is adjusted to meet the requirements, and the mounting base 16 is mounted on the test bench 50 by bolts. The tensioning mechanism 17 is further installed to lock the independent mounting bracket 10.

[0116] 2. Pre-testing process

[0117] (1) Carry out joint debugging without the engine 30: Test the ignition control system, the steering gear test system, the motor control program and the data collector to see if they are operating normally. After confirming that all structures are operating normally, conduct subsequent simulation tests with the engine 30.

[0118] (2) Simulation test with engine 30: The ignition control system is disconnected from the engine 30, and all commands and test actions that are the same as those in the formal test are executed according to normal test steps, except for the ignition of the engine 30, to confirm that the equipment is in normal condition, the test system works in a coordinated manner, and the power supply at the test site meets the requirements.

[0119] After the ignition request is issued, the simulated engine 30 is ignited, and the steering gear test system and the servo control system simultaneously output steering commands to respectively control the gas steering 70 to be tested and the air steering 60 to be tested to deflect according to the specified requirements. For example, among the three sets of gas steering force measuring devices 20, two sets move according to the trapezoidal control law, and the other set moves according to the actual steering deflection law.

[0120] The data collected by the data collector are analyzed to determine that the starting time of the angle sensor, the strain balance 23, the steering gear test system, and the motor control program are unified.

[0121] 3. Formal Testing Process

[0122] The above embodiment is the formal test process of the test system. It should be noted that before sending the ignition request, it is necessary to test whether the ignition control system, the servo test system, the motor control program and the data acquisition device are operating normally. After confirming that each structure is operating normally, the step of sending the ignition request is entered.

[0123] A person 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 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.

[0125] In addition, to simplify the description and discussion, and in order not to make the embodiments of the present application difficult to understand, the known power supply / ground connection with the integrated circuit (IC) chip and other components may or may not be shown in the provided drawings. In addition, the device can be shown in the form of a block diagram to avoid making the embodiments of the present application difficult to understand, and this also takes into account the fact that the details of the implementation of these block diagram devices are highly dependent on the platform to be implemented in the embodiments of the present application (that is, these details should be fully within the scope of understanding of those skilled in the art). In the case of elaborating specific details (e.g., circuits) to describe exemplary embodiments of the present application, it is obvious to those skilled in the art that the embodiments of the present application can be implemented without these specific details or when these specific details are changed. Therefore, these descriptions should be considered to be illustrative rather than restrictive.

[0126] 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.

[0127] The embodiments of the present application are intended to cover all such substitutions, modifications and variations that fall within the broad scope of the present application. 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 protection scope of the present application.

Claims

1. A test system for testing gas rudders and air rudders simultaneously, characterized in that: It comprises an independent mounting bracket, a gas rudder force measuring device, an engine and a cabin structure, wherein the gas rudder force measuring device is used to connect with the gas rudder to be tested and is located on one side of the independent mounting bracket, and the engine and the cabin structure connected in sequence are located on the other side of the independent mounting bracket; An air rudder mounting groove for mounting the air rudder to be tested is provided on the outer side wall of the cabin structure, the air rudder mounting groove is arranged close to the free end of the cabin structure, a gas rudder mounting seat for mounting a synchronous gas rudder that runs synchronously with the air rudder to be tested is provided on the end surface of the free end of the cabin structure, the gas rudder mounting seat is arranged corresponding to the air rudder mounting groove, a steering gear is provided in the cabin structure, an output end of the steering gear is used to connect with the synchronous gas rudder and the air rudder to be tested, and a displacement sensor is provided on the output end; The independent mounting bracket is provided with a first test through hole and a second test through hole which are connected to each other, wherein the first test through hole is used to provide a deflection space for the air rudder to be tested installed in the air rudder mounting groove, and the second test through hole is adapted to the periphery of the free end of the cabin structure so as to allow the free end of the cabin structure to pass through; The gas rudder force measuring device is provided in plurality and is located at the periphery of the second test through hole, and the synchronous gas rudder and the gas rudder to be tested are evenly arranged at the ports at the free end of the cabin structure.

2. The test system for simultaneously testing a gas rudder and an air rudder according to claim 1, characterized in that: The gas rudder force measuring device includes a servo mechanism, a mounting support, a strain balance and a water-cooled adapter rod. The mounting support is connected to the independent mounting bracket. The mounting support is provided with a support shaft. One end of the support shaft away from the mounting through hole is connected to the servo mechanism, and one end of the support shaft close to the mounting through hole is connected to the strain balance. The other end of the strain balance is connected to the water-cooled adapter rod. The water-cooled adapter rod is used to connect to the gas rudder to be tested.

3. The test system for simultaneously testing a gas rudder and an air rudder according to claim 2, characterized in that: A heat protection shell is provided on one side of the mounting support close to the mounting through hole, and the heat protection shell covers the periphery of the strain balance and the water-cooled adapter rod. A through hole adapted to the connecting end of the gas rudder to be tested is provided at one end thereof away from the mounting support, for the connecting end of the gas rudder to be tested to pass through.

4. The test system for simultaneously testing a gas rudder and an air rudder according to claim 1, characterized in that: The projections of the gas rudder mounting seat on the end surface of the free end of the cabin structure are all located within the end surface.

5. The test system for simultaneously testing a gas rudder and an air rudder according to claim 1, characterized in that: The independent mounting bracket comprises a connected mounting vertical plate, a mounting support plate and a lifting structure, the mounting support plate comprises a bottom plate and a vertical plate, the mounting vertical plate is provided with the first test through hole and the second test through hole, the vertical plate is provided with a mounting through hole, the mounting vertical plate is connected to the vertical plate in a lifting manner, and the first test through hole and the second test through hole are both provided corresponding to the vertical plate; The lifting structure comprises a mounting seat and a lifting member connected to each other, the mounting seat is located on the bottom plate, and the lifting end of the lifting member is connected to the mounting vertical plate.

6. The test system for simultaneously testing a gas rudder and an air rudder according to claim 5, characterized in that: The independent mounting bracket also includes a mounting base, and the mounting base is located at the bottom of the base plate and connected to the base plate.

7. The test system for simultaneously testing a gas rudder and an air rudder according to claim 6, characterized in that: The test system also includes a test bench, a top surface of which is evenly provided with a plurality of T-shaped slots, and the test bench is connected to the mounting base via the T-shaped slots to support the independent mounting bracket, the engine and the cabin structure.

8. The test system for simultaneously testing a gas rudder and an air rudder according to claim 7, characterized in that: The independent mounting bracket also includes a tensioning mechanism. A connecting ear is provided on the top of one side of the mounting support plate close to the engine. One end of the tensioning mechanism is connected to the connecting ear, and the other end is connected to the test bench and is arranged close to the engine.

9. The test system for simultaneously testing a gas rudder and an air rudder according to claim 8, characterized in that: The tensioning mechanism comprises a connecting seat and a connecting rod, wherein the connecting seat is located on the test bench, one end of the connecting rod is rotatably connected to the connecting ear piece, and the other end of the connecting rod is rotatably connected to the connecting seat.

10. A method for using the test system for simultaneously testing a gas rudder and an air rudder according to any one of claims 1 to 9, comprising the following steps: In response to determining that the ignition request is received, an ignition signal is sent to the engine, and an operation instruction is sent to the servo mechanism of the steering engine and the gas rudder force measuring device, so that the gas rudder to be tested, the synchronous gas rudder and the air rudder to be tested are operated simultaneously; Acquire the test deflection data collected by the displacement sensor of the steering gear, the test force data collected by the strain balance of the gas rudder force measuring device, and the test deflection data collected by the angle sensor connected to the support shaft; Comparing and analyzing the test deflection data collected by the displacement sensor of the steering gear with the command deflection data in the operation command received by the steering gear, to obtain the following characteristic test result of the air rudder to be tested; Comparing and analyzing the test deflection data collected by the angle sensor and the command deflection data in the operation command received by the servo mechanism of the gas rudder force measuring device, to obtain the following characteristic test result of the gas rudder to be tested; The test force data collected by the strain balance of the gas rudder force measuring device and the test deflection data collected by the angle sensor located on the support shaft are analyzed to obtain the aerodynamic force test result of the gas rudder to be tested.

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