Force-heat combined follow-up loading system and testing method for deformed wing rudder

Abstract

The invention provides a force-heat combined follow-up loading system and a testing method for a deformed wing rudder, and belongs to the technical field of aerospace. The deformed wing rudder is fixed on a force-heat combined follow-up loading testing platform through a mechanical interface, and a strain gauge, a thermocouple and a target are pasted according to measurement requirements; a driving force acquisition device is installed in front of a driver of the deformed wing rudder, the position and the number of follow-up loading modules are adjusted, a force loading unit is made to be in a to-be-loaded state, and the position of a laser displacement device is adjusted so that laser can be accurately irradiated to the target position; initializing the system, adjusting parameter configuration and eliminating abnormity, transmitting a control instruction to the test control module through the upper computer, and controlling the force and heat loading unit to load; the acquisition and measurement module begins to measure, transmits acquired data to the man-machine interaction module, processes the data and then transmits the processed data to the visualization module and the data storage module, so as to realize display and storage of the data; the device can be used for a deformation function test in a deformation wing ground simulation loading process.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace technology, and specifically, relates to a force-thermal combined servo loading system and a testing method for a variable wing rudder. Background Art

[0002] As a key component of an aircraft, the variable wing rudder structure can solve the problem of strong constraints on the size of the launch platform by missiles, improve the lift-drag ratio of the missile and the maneuverability at the end of the ballistic trajectory, achieve the optimal aerodynamic shape throughout the flight, and meet the requirements of multi-mission combat. However, the variable wing rudder has to bear various severe external loads during its entire service life. In order to ensure that the aircraft still has excellent flight performance under severe external loads, it is necessary to conduct ground simulation tests of aerodynamic and thermal loads on the variable wing rudder, set specific test indicators and test environments according to a certain flight condition of the aircraft, carry out structural mechanism test measurements, verify that the designed variable wing rudder meets the requirements of various functional indicators, and further improve and optimize the variable wing rudder based on the differences between experimental data and theoretical data, so as to improve the reliability of the variable wing rudder under load conditions. Summary of the Invention

[0003] Based on the above purposes, the present invention takes the variable wing rudder as the test object, and proposes a force-thermal combined servo loading system and a testing method for a variable wing rudder. By means of ground simulation tests, data information such as the wing surface load state, motion state, and structural stiffness under a certain working condition can be obtained, which is convenient for evaluating the deformation function and load-bearing performance of the variable wing under this load environment.

[0004] The present invention is realized through the following technical solutions:

[0005] A force-thermal combined servo loading system for a variable wing rudder:

[0006] It includes a loading module, a test control module, a data acquisition and measurement module, a human-machine interaction module, and a variable wing rudder;

[0007] The servo loading module is installed on a force-thermal combined servo loading test platform. The servo loading module is composed of a force loading unit and a thermal loading unit, and is connected to the test control module;

[0008] The test control module is composed of two lower computers and a multi-channel measuring instrument;

[0009] The data acquisition and measurement module is electrically connected to the test control module. The data acquisition and measurement module includes a driving force acquisition device, a motion quantity acquisition device, and a state quantity acquisition device;

[0010] The human-machine interaction module is composed of an upper computer and a display.

[0011] Furthermore, the force loading unit is composed of a driving component, a feedback component, a load component, and a mounting component. The mounting component can be installed at multiple positions within the loading area of the force-thermal combined servo loading test platform.

[0012] The thermal loading unit consists of a quartz lamp, a thermocouple, a heat insulation plate, and a mounting frame. The quartz lamp is installed on the universal mounting frame of the force-thermal combined servo loading test platform. The mounting frame is arranged on both sides of the deformable fin rudder and is used to adjust the height of the quartz lamp. The heat insulation plate is installed around the quartz lamp, and the thermocouple is pasted on the deformable fin rudder to control the temperature of the quartz lamp.

[0013] Furthermore, the two lower-level machines are a real-time controller and a programmable controller respectively, which are installed in the measurement and control cabinet of the force-thermal combined servo loading test platform. The real-time controller, the programmable controller, the multi-channel measuring instrument, and the upper-level machine are connected through a network switch and communicate via Ethernet.

[0014] The real-time controller is electrically connected to the driving component and the feedback component of the force loading unit through a motion quantity acquisition card and an analog quantity acquisition card respectively.

[0015] The programmable controller is electrically connected to the quartz lamp and the thermocouple of the thermal loading unit through a digital quantity acquisition module and a thermocouple acquisition module respectively.

[0016] Furthermore, the driving force acquisition device is composed of a torque sensor, a mounting seat, and a coupling, and is mechanically connected to the driving motor of the deformable fin rudder and is electrically connected to the real-time controller through an analog quantity acquisition card.

[0017] The motion quantity acquisition device is composed of a horizontal laser displacement sensor and a vertical laser displacement sensor orthogonal in the horizontal and vertical directions, and a first guide rail seat and a second guide rail seat. The horizontal laser displacement sensor and the vertical laser displacement sensor are installed on the force-thermal combined servo loading platform through the first guide rail seat and the second guide rail seat and can adjust their positions in three degrees of freedom. The horizontal laser displacement sensor and the vertical laser displacement sensor are connected to the real-time controller through an analog quantity acquisition card via signal filtering and amplification inside and a cable.

[0018] The state quantity acquisition device is composed of a thermocouple and a strain gauge. The thermocouple and the strain gauge are pasted on the surface of the deformable fin rudder. The thermocouple is connected to the thermocouple acquisition module through a terminal block and then connected to the programmable controller through a wire. The strain gauge is connected to the multi-channel measuring instrument.

[0019] Further, a post-processing program is written in the host computer to display the data collected by the host computer after post-processing; the human-computer interaction module is provided with a system initialization module, a parameter configuration module, a collection and testing module, a data processing module, a visualization module, a data storage module, and an abnormal alarm module.

[0020] Further, the system initialization module: is used for initializing the parameters of each sensor and the data of each module of the thermal-mechanical combined servo loading test platform;

[0021] The parameter configuration module: is used for zeroing the control parameters of the closed-loop control and the open-closed-loop parameters;

[0022] The collection and testing module: The user inputs control instructions to the host computer according to the test needs, and the thermal-mechanical combined servo loading test platform tests the deformable wing rudder and collects and transmits the data to the host computer;

[0023] The data processing module: inputs the collected data into the data processing module for post-processing;

[0024] The visualization module: displays the post-processed data on the user interface;

[0025] The data storage module: inputs the data of the lower computer into the host computer and saves it locally, and the test data can be queried or exported by the user for use;

[0026] The abnormal alarm module: is used to send an alarm prompt to the user interface terminal when an abnormal situation occurs in the servo loading module.

[0027] A testing method for a thermal-mechanical combined servo loading system of a deformable wing rudder:

[0028] The method includes the following steps:

[0029] S1. Fix the deformable wing rudder to be measured on the thermal-mechanical combined servo loading test platform through a mechanical interface;

[0030] S2. Paste strain gauges, thermocouples and targets on the deformable wing rudder according to the measurement requirements, and install a driving force acquisition device in front of the driver of the deformable wing rudder;

[0031] S3. Adjust the position and quantity of the servo loading module according to the loaded area and loaded area of the deformable wing rudder, and then control the force loading unit to be in a waiting-to-load state through the test control module;

[0032] S4. Adjust the positions of the horizontal laser displacement sensor and the vertical laser displacement sensor so that the laser accurately hits the target position;

[0033] S5. Initialize the system for the test control module, acquisition and measurement module, and system initialization module, adjust the parameter values in the parameter configuration module, and start the test after eliminating anomalies based on the information provided by the anomaly alarm module;

[0034] S6. Input the control instructions into the host computer through the human-machine interaction module, and send the instructions to the test control module through the host computer program. The test control module controls the force loading unit and the thermal loading unit to perform loading;

[0035] S7. Control the acquisition and measurement module to start measurement, send the acquired data into the human-machine interaction module, and then transmit the required data to the visualization module and the data storage module through the data processing module to achieve data display and storage.

[0036] Furthermore, in the above S6, the measured true values obtained by the host computer all come from sensors, and the specific steps are as follows:

[0037] Input the loading instructions into the test control module through the human-machine interaction module. The initial state of the variable wing rudder is retracted and in a horizontal attitude. Under the control of the test control module, the thermal loading unit is activated to simulate the thermal environment. The data collected by the thermocouple is sent to the programmable logic controller through the thermocouple acquisition module. The start and stop of the thermal loading unit are controlled through the preset temperature threshold to control the temperature. The force loading unit under the fixed section of the variable wing rudder starts to act, applying a force load, and the precise loading of the force value is achieved through the feedback component;

[0038] The variable wing rudder starts to deform. The telescopic amount x of the variable wing rudder is measured by a horizontal laser displacement sensor. After reaching the limit position, it folds. The vertical change amount y of the folding is measured by a vertical laser displacement sensor. Then, according to the length d from the folding root to the top, the folding angle is calculated as θ = arctan(y / d), and the other motion data is calculated by the data processing module; the deformation time t is the start and stop time of the actuator, and the deformation accuracy is obtained by comparing the measurement data with the deformation instruction; at the same time, the test control module controls the torque sensor of the driving force acquisition device to collect and measure the driving force value;

[0039] During the extension process of the variable wing rudder, the force loading unit below it moves upward. According to the given loading formula F 0 = ΔS(t) × p for loading, where F is the output load of the force loading unit, p is the uniform pressure borne by the variable wing rudder, and ΔS(t) is the area change amount, to achieve the effect of force follow-up;

[0040] During the folding process of the variable wing rudder, the output force F of the force loading unit below it has an angular relationship with the loading direction, and the loading formula is F 1= p·S / cosθ°, where S is the area of the folded part, θ is the folding angle, and p is the uniform pressure borne by the deformable wing rudder;

[0041] During the combined force and heat loading process, the thermocouple and strain gauge collect the temperature and strain on the surface of the deformable wing rudder. All the above data are saved in the background through the data storage module and displayed by the visualization module. The retraction process is the same.

[0042] An electronic device includes a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, the steps of the above method are implemented.

[0043] A computer-readable storage medium is used to store computer instructions. When the computer instructions are executed by the processor, the steps of the above method are implemented.

[0044] Advantages of the present invention

[0045] The present invention provides a combined force and heat servo loading system for a deformable wing rudder. Through the servo loading module, the aerodynamic heat environment of the deformable wing rudder under a certain flight condition is simulated on the ground, and the load simulation is more comprehensive. The modular design improves the versatility of the combined force and heat servo loading test platform. Through the test control module, the servo loading module is controlled in real time, and the characteristic of sectional loading is realized. Due to different acquisition frequency requirements, two lower-level computers are respectively set up. The lower-level computers are connected to the actuators and sensors, which minimizes electromagnetic interference to the greatest extent and increases the loading accuracy. In addition, the acquisition and measurement module can be controlled to perform real-time measurement of multiple parameters by multiple integrated sensors, which increases the multi-parameter test function of the combined force and heat servo loading test platform and improves the integration degree of the combined force and heat servo loading test platform. Through the construction of the human-computer interaction module, the background storage and foreground display of the acquired information are realized. The user can perform the combined force and heat servo loading test through the human-computer interaction interface, which simplifies the operation steps and improves the operability.

[0046] The present invention provides a combined force and heat servo loading test method for a deformable wing rudder. For the above control system, a general test process is provided, and a numerical test method for the deformation function of the deformable wing rudder is proposed. Through different layout forms of the movement amount acquisition device, the measurement under various deformation states of the deformable wing rudder is realized, which improves the versatility of the test function. The ground test data of the deformable wing rudder obtained by the measurement of multiple sensors is beneficial to exposing the existing problems of the existing deformable wing rudder, guiding the subsequent improvement and upgrade of the deformable wing rudder, and at the same time, the theoretical data can also be applied to subsequent research. Description of the drawings

[0047] Figure 1 It is a perspective view of the assembly structure of a combined force and heat servo loading system for a deformable wing rudder provided by the present invention;

[0048] Figure 2 It is the rear view of the assembly structure of a variable-wing rudder force and heat combined servo loading system provided by the present invention;

[0049] Figure 3 It is the schematic diagram of the principle of a variable-wing rudder force and heat combined servo loading system provided by the present invention;

[0050] Figure 4 It is the schematic diagram of the structures of the servo loading module and the acquisition and measurement module;

[0051] Figure 5 It is the schematic diagram of the structural relationship between the test control module and the servo loading module;

[0052] Figure 6 It is the schematic diagram of the structural relationship between the test control module and the acquisition and measurement module;

[0053] Figure 7 It is the schematic diagram of the principle of the human-computer interaction module;

[0054] Figure 8 It is the flow chart of the test method of the variable-wing rudder force and heat combined servo loading test platform provided by the present invention.

[0055] It includes a servo loading module (1), a force loading unit (11), a driving component (111), a feedback component (112), a load component (113), a mounting component (114), a heat loading unit (12), a quartz lamp (121), a heat insulation plate (122), and a mounting frame (123);

[0056] A test control module (2), a real-time controller (21), a programmable logic controller (22), a multi-channel measuring instrument (23), a measurement and control cabinet (24), a motion amount acquisition card (211), an analog quantity acquisition card (212), a digital quantity acquisition module (221), and a thermocouple acquisition module (222);

[0057] An acquisition and measurement module (3), a driving force acquisition device (31), a torque sensor (311), a mounting seat (312), a coupling structure (313), a driving motor (314), a motion amount acquisition device (32), a horizontal laser displacement sensor (321), a vertical laser displacement sensor (322), a horizontal guide rail seat (323), a second guide rail seat (324), a status quantity acquisition device (33), a thermocouple (331), and a strain gauge (332);

[0058] A human-computer interaction module (4), a host computer (41), a system initialization module (411), a parameter configuration module (412), an acquisition and test module (413), a data processing module (414), a visualization module (415), a data storage module (416), an abnormal alarm module (417), a display (42); a variable-wing rudder (5) Detailed implementation mode

[0059] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0060] The experimental methods used in the following embodiments are all conventional methods unless otherwise specified. The materials, reagents, methods and instruments used are all conventional materials, reagents, methods and instruments in the art unless otherwise specified, and those skilled in the art can obtain them through commercial channels.

[0061] Embodiment 1: In combination with Figures 1 to 3 To illustrate this embodiment, this embodiment proposes a variable wing rudder force-thermal combined servo loading system:

[0062] It includes a loading module 1, a test control module 2, a collection and measurement module 3, a human-computer interaction module 4, and a variable wing rudder 5;

[0063] The servo loading module 1 is installed on the force-thermal combined servo loading test platform. The servo loading module 1 is composed of a force loading unit 11 and a thermal loading unit 12, and is connected to the test control module 2;

[0064] The test control module 2 is composed of two lower computers and a multi-channel measuring instrument 23;

[0065] The collection and measurement module 3 is electrically connected to the test control module 2. The collection and measurement module 3 includes a driving force collection device 31, a motion amount collection device 32, and a state amount collection device 33;

[0066] The human-computer interaction module 4 is composed of an upper computer 41 and a display 42.

[0067] In combination with Figures 1-4 To illustrate this embodiment, the force loading unit 11 is composed of a driving component 111, a feedback component 112, a load component 113, and a mounting component 114. The mounting component 114 can be installed at multiple positions within the loading area of the force-thermal combined servo loading test platform;

[0068] The thermal loading unit 12 is composed of a quartz lamp 121, a thermocouple 331, a heat insulation plate 122 and a mounting bracket 123. The quartz lamp 121 is mounted on the universal mounting bracket 123 of the force-thermal combined servo loading test platform. The mounting bracket 123 is arranged on both sides of the deformable fin rudder 5 and is used to adjust the height of the quartz lamp 121. The heat insulation plate 122 is mounted around the quartz lamp 121. The thermocouple 331 is pasted on the deformable fin rudder 5 and is used to control the temperature of the quartz lamp 121. Other compositions and connection relationships are the same as those in the above embodiments.

[0069] Combined Figures 1-3 with 5, this embodiment is described. The two slave computers are respectively a real-time controller 21 and a programmable logic controller 22, which are installed in the measurement and control cabinet 24 of the force-thermal combined servo loading test platform. The real-time controller 21, the programmable logic controller 22, the multi-channel measuring instrument 23 and the host computer 41 are connected through a network switch and communicate via Ethernet.

[0070] The real-time controller 21 is electrically connected to the drive assembly 111 and the feedback assembly 112 of the force loading unit through a motion amount acquisition card 211 and an analog quantity acquisition card 212 respectively.

[0071] The programmable logic controller 22 is electrically connected to the quartz lamp 121 and the thermocouple 331 of the thermal loading unit 12 through a digital quantity acquisition module 221 and a thermocouple acquisition module 222 respectively.

[0072] Combined Figures 1-4 with 6, this embodiment is described. The driving force acquisition device 31 is composed of a torque sensor 311, a mounting seat 312 and a coupling 313, and is mechanically connected to the driving motor 314 of the deformable fin rudder, and is electrically connected to the real-time controller 21 through an analog quantity acquisition card 212.

[0073] The motion amount acquisition device 32 is composed of a horizontal laser displacement sensor 321 and a vertical laser displacement sensor 322 that are orthogonal in the horizontal and vertical directions, and a first guide rail seat 323 and a second guide rail seat 324. The horizontal laser displacement sensor 321 and the vertical laser displacement sensor 322 are mounted on the force-thermal combined servo loading platform through the first guide rail seat 323 and the second guide rail seat 324 and can adjust their positions in three degrees of freedom directions. The horizontal laser displacement sensor 321 and the vertical laser displacement sensor 322 are connected to the real-time controller 21 through a cable via an internal signal filtering and amplification through an analog quantity acquisition card 212.

[0074] The state quantity acquisition device 33 is composed of a thermocouple 331 and a strain gauge 332. The thermocouple 331 and the strain gauge 332 are pasted on the surface of the deformable fin rudder 5. The thermocouple 331 is connected to the thermocouple acquisition module 222 through a wiring terminal and then connected to the programmable controller 22 through a wire. The strain gauge 332 is connected to the multi-channel measuring instrument 23.

[0075] Combined with Figure 1 、 Figure 3 and Figure 7 This embodiment is described. A post-processing program is written in the host computer 41, and the data collected by the host computer 41 is displayed after post-processing; the human-computer interaction module 4 is provided with a system initialization module 411, a parameter configuration module 412, a collection and test module 413, a data processing module 414, a visualization module 415, a data storage module 416, and an abnormal alarm module 417.

[0076] The system initialization module 411: is used for initializing the parameters of each sensor and the data of each module of the force-thermal combined servo loading test platform;

[0077] The parameter configuration module 412: is used for zeroing the control parameters of the closed-loop control and the open / closed-loop parameters;

[0078] The collection and test module 413: The user inputs a control instruction to the host computer 41 according to the test needs, and the force-thermal combined servo loading test platform tests the deformable fin rudder 5 and collects and transmits the data to the host computer 41;

[0079] The data processing module 414: inputs the collected data into the data processing module for post-processing;

[0080] The visualization module 415: The post-processed data is displayed on the user interface;

[0081] The data storage module 416: inputs the data of the lower computer into the host computer 41 and saves it locally, and the test data can be queried or exported by the user for use;

[0082] The abnormal alarm module 417: is used for sending an alarm prompt to the user interface terminal when an abnormal situation occurs in the servo loading module 1.

[0083] Embodiment 2: The embodiment of the present invention also provides a test method for a force-thermal combined servo loading of a deformable fin rudder, which can be used for the above-mentioned force-thermal combined servo loading system of a deformable fin rudder. Combined with Figure 8 This embodiment is described as follows:

[0084] A test method for a force-thermal combined servo loading system of a deformable fin rudder: The method includes the following steps:

[0085] S1. Fix the deformable wing rudder 5 of the object to be measured on the force-thermal combined servo loading test platform through a mechanical interface;

[0086] S2. Paste strain gauges 332, thermocouples 331 and targets on the deformable wing rudder 5 according to measurement requirements, and install a driving force acquisition device 31 in front of the driver of the deformable wing rudder 5;

[0087] S3. Adjust the position and quantity of the servo loading module 1 according to the loaded area and loaded area of the deformable wing rudder 5, and then control the force loading unit 11 to be in a waiting loading state through the test control module 2;

[0088] S4. Adjust the positions of the horizontal laser displacement sensor 321 and the vertical laser displacement sensor 322 so that the laser hits the target position precisely;

[0089] S5. Turn on the test control module 2, the acquisition and measurement module 3, and the system initialization module 411 for system initialization, adjust the parameter values in the parameter configuration module 412, and start the test after eliminating the abnormalities according to the information provided by the abnormal alarm module 417;

[0090] S6. Input control instructions into the host computer 41 through the human-computer interaction module 4, and send the instructions to the test control module 2 through the host computer 41 program. The test control module 2 controls the force loading unit 11 and the thermal loading unit 12 to load.

[0091] In step S6, the measured true values obtained by the host computer 41 all come from sensors, and the specific steps are as follows:

[0092] Input the loading instructions into the test control module 2 through the human-computer interaction module 4. The initial state of the deformable wing rudder 5 is retracted and in a horizontal attitude. Under the control of the test control module 2, turn on the thermal loading unit 12 to simulate the thermal environment. The data collected by the thermocouple 331 is sent to the programmable controller 22 through the thermocouple acquisition module 222. Control the start and stop of the thermal loading unit 12 through a preset temperature threshold to control the temperature. The force loading unit 11 under the fixed section of the deformable wing rudder 5 starts to act, applies a force load, and realizes precise force loading through the feedback component 112;

[0093] The deformable wing rudder 5 starts to deform. The telescopic amount x of the deformable wing rudder 5 is measured by the horizontal laser displacement sensor 321. After reaching the limit position, it folds. The folding is measured by the vertical laser displacement sensor 322 for its change amount y in the vertical direction. Then, according to the length d from the folding root to the top, the folding angle is calculated as θ = arctan(y / d). The remaining motion data is calculated by the data processing module 414. The deformation time t is the start-stop time of the driver, and the deformation accuracy is obtained by comparing the measurement data with the deformation instruction. At the same time, the test control module 2 controls the torque sensor 311 of the driving force acquisition device 31 to collect and measure the driving force value.

[0094] During the extension process of the deformable wing rudder 5, the force loading unit 11 below it moves upward. According to the given loading formula F 0 = ΔS(t) × p for loading, where F is the output load of the force loading unit 11, p is the uniform pressure borne by the deformable wing rudder 5, and ΔS(t) is the area change amount, achieving the effect of force follow-up. The loading curve is a broken line graph of the relationship between the deformation area ΔS(t) and the loading force F.

[0095] During the folding process of the deformable wing rudder 5, the output force F of the force loading unit 11 below it has an angular relationship with the loading direction. The loading formula is F 1 = p·S / cosθ°, where S is the area of the folded part, θ is the folding angle, and p is the uniform pressure borne by the deformable wing rudder 5.

[0096] During the combined force and heat loading process, the thermocouple 331 and the strain gauge 332 collect the temperature and strain on the surface of the deformable wing rudder 5. All the above data is saved in the background by the data storage module 416 and displayed by the visualization module 415. The retraction process is the same.

[0097] S7. The control acquisition and measurement module 3 starts to measure, sends the collected data into the human-computer interaction module 4, and then transmits the required data to the visualization module 415 and the data storage module 416 through the data processing module 414 to realize the display and storage of the data.

[0098] An electronic device includes a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, the steps of the above method are implemented.

[0099] A computer-readable storage medium is used to store computer instructions. When the computer instructions are executed by a processor, the steps of the above method are implemented.

[0100] The memory in the embodiments of the present application can be a volatile memory or a non-volatile memory, or can include both volatile and non-volatile memories. Among them, the non-volatile memory can be a read only memory (ROM), a programmable ROM (PROM), an erasable PROM (EPROM), an electrically erasable PROM (EEPROM), or a flash memory. The volatile memory can be a random access memory (RAM), which is used as an external cache. By way of example but not limitation, many forms of RAM are available, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDR SDRAM), enhanced SDRAM (ESDRAM), synchlink DRAM (SLDRAM), and direct rambus RAM (DR RAM). It should be noted that the memory of the method described in the present invention is intended to include but not limited to these and any other suitable types of memories.

[0101] In the above embodiments, it can be implemented in whole or in part by software, hardware, firmware, or any combination thereof. When implemented using software, it can be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer instructions. When the computer instructions are loaded and executed on a computer, the processes or functions described in the embodiments of the present application are generated in whole or in part. The computer can be a general-purpose computer, a special-purpose computer, a computer network, or other programmable devices. The computer instructions can be stored in a computer-readable storage medium or transmitted from one computer-readable storage medium to another. For example, the computer instructions can be transmitted from one website, computer, server, or data center to another website, computer, server, or data center via wired means such as coaxial cable, optical fiber, digital subscriber line (DSL), or wireless means such as infrared, wireless, microwave, etc. The computer-readable storage medium can be any available medium that can be accessed by a computer or a data storage device such as a server or a data center that includes one or more integrated available media. The available medium can be a magnetic medium such as a floppy disk, a hard disk, a magnetic tape, an optical medium such as a high-density digital video disc (DVD), or a semiconductor medium such as a solid-state disc (SSD), etc.

[0102] In the implementation process, the steps of the above method can be completed by the integrated logic circuit of the hardware in the processor or the instructions in the form of software. The steps of the method disclosed in combination with the embodiments of the present application can be directly embodied as being executed by the hardware processor or executed by the combination of the hardware and software modules in the processor. The software module can be located in a mature storage medium in the art such as random access memory, flash memory, read-only memory, programmable read-only memory, or electrically erasable programmable memory, registers, etc. This storage medium is located in the memory, and the processor reads the information in the memory and combines its hardware to complete the steps of the above method. To avoid repetition, it will not be described in detail here.

[0103] It should be noted that the processor in the embodiments of the present application may be an integrated circuit chip with signal processing capabilities. In the implementation process, each step of the above method embodiments can be completed by the integrated logic circuit in the hardware of the processor or instructions in the form of software. The above-mentioned processor may be a general-purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components. It can implement or execute the various methods, steps, and logic block diagrams disclosed in the embodiments of the present application. The general-purpose processor may be a microprocessor, or the processor may also be any conventional processor, etc. The steps of the method disclosed in combination with the embodiments of the present application can be directly embodied as being executed and completed by the hardware decoding processor, or executed and completed by a combination of the hardware and software modules in the decoding processor. The software module may be located in a mature storage medium in the art such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory, or an electrically erasable programmable memory, a register, etc. This storage medium is located in the memory, and the processor reads the information in the memory and combines its hardware to complete the steps of the above method.

[0104] The above has introduced in detail a deformable wing rudder force and heat combined servo loading system and a test method proposed by the present invention, and has elaborated on the principle and implementation manner of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manner and application scope. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. A deformable wing-rudder combined with thermal follow-up loading system, characterized in that: The system comprises a loading module (1), a test control module (2), a collection and measurement module (3), a human-computer interaction module (4) and a deformable wing rudder (5); The servo loading module (1) is installed on a force-heat combined servo loading test platform, and the servo loading module (1) is composed of a force loading unit (11) and a heat loading unit (12), and is connected to the test control module (2); The test control module (2) is composed of two slave computers and a multi-channel measuring instrument (23); The acquisition and measurement module (3) is electrically connected to the test control module (2), and the acquisition and measurement module (3) comprises a driving force acquisition device (31), a motion quantity acquisition device (32) and a state quantity acquisition device (33); The human-computer interaction module (4) is composed of a host computer (41) and a display (42).

2. The follow-up loading system according to claim 1, characterized in that: The force loading unit (11) is composed of a driving component (111), a feedback component (112), a load component (113) and a mounting component (114); the mounting component (114) can be installed at multiple positions in a loading area of ​​a combined force and heat follow-up loading test platform; The thermal loading unit (12) is composed of a quartz lamp (121), a thermocouple (331), a heat shield (122) and a mounting frame (123); the quartz lamp (121) is mounted on a universal mounting frame (123) of a combined force-heat follow-up loading test platform; the mounting frame (123) is arranged on both sides of the deformable wing rudder (5) and is used to adjust the height of the quartz lamp (121); the heat shield (122) is installed around the quartz lamp (121); the thermocouple (331) is attached to the deformable wing rudder (5) and is used to control the temperature of the quartz lamp (121).

3. The follow-up loading system according to claim 2, characterized in that: The two lower computers are respectively a real-time controller (21) and a programmable controller (22), which are installed in a measurement and control cabinet (24) of a combined force and heat follow-up loading test platform. The real-time controller (21), the programmable controller (22), the multi-channel measuring instrument (23) and the upper computer (41) are connected via a network switch and communicate via Ethernet; The real-time controller (21) is electrically connected to the driving component (111) and the feedback component (112) of the force loading unit through a motion quantity acquisition card (211) and an analog quantity acquisition card (212), respectively. The programmable controller (22) is electrically connected to the quartz lamp (121) and the thermocouple (331) of the heat loading unit (12) via a digital quantity acquisition module (221) and a thermocouple acquisition module (222), respectively.

4. The follow-up loading system according to claim 3, characterized in that: The driving force acquisition device (31) is composed of a torque sensor (311), a mounting seat (312) and a coupling (313), is mechanically connected to the driving motor (314) of the deformable wing rudder, and is electrically connected to the real-time controller (21) through an analog quantity acquisition card (212); The motion quantity acquisition device (32) is composed of a horizontal laser displacement sensor (321) and a vertical laser displacement sensor (322) in a horizontal direction and a vertical direction orthogonal to each other, and a first guide rail seat (323) and a second guide rail seat (324). The horizontal laser displacement sensor (321) and the vertical laser displacement sensor (322) are installed on a force-heat combined follow-up loading platform through the first guide rail seat (323) and the second guide rail seat (324), and their positions can be adjusted in three degrees of freedom directions. The horizontal laser displacement sensor (321) and the vertical laser displacement sensor (322) are connected to the real-time controller (21) through a cable through an analog quantity acquisition card (212) after internal signal filtering and amplification. The state quantity acquisition device (33) is composed of a thermocouple (331) and a strain gauge (332). The thermocouple (331) and the strain gauge (332) are attached to the surface of the deformable wing rudder (5). The thermocouple (331) is connected to the thermocouple acquisition module (222) via a wiring terminal and then connected to the programmable controller (22) via a wire. The strain gauge (332) is connected to the multi-channel measuring instrument (23).

5. The follow-up loading system according to claim 4, characterized in that: The host computer (41) is programmed with a post-processing program, and the data collected by the host computer (41) is displayed after post-processing; the human-computer interaction module (4) is provided with a system initialization module (411), a parameter configuration module (412), an acquisition test module (413), a data processing module (414), a visualization module (415), a data storage module (416) and an abnormal alarm module (417).

6. The follow-up loading system according to claim 5, characterized in that: The system initialization module (411) is used to initialize the parameters of each sensor and the data of each module of the combined mechanical and thermal follow-up loading test platform; The parameter configuration module (412) is used to adjust the control parameters of the closed-loop control and the open-loop and closed-loop parameters; The acquisition test module (413): the user inputs control instructions to the host computer (41) according to the test requirements, and the mechanical and thermal combined follow-up loading test platform tests the deformable wing rudder (5), and collects and transmits the data to the host computer (41); The data processing module (414) inputs the collected data into the data processing module for post-processing; The visualization module (415) displays the post-processed data on a user interface; The data storage module (416) inputs the lower computer data into the upper computer (41) and stores it locally. The test data can be queried or exported by the user. The abnormal alarm module (417) is used to send an alarm prompt to the user interface terminal when the follow-up loading module (1) has an abnormal use.

7. A testing method for the combined mechanical and thermal follow-up loading system of a deformable wing and rudder according to any one of claims 1 to 6, characterized in that: The method comprises the following steps: S1, fixing the deformable wing rudder (5) of the test object on the combined mechanical and thermal follow-up loading test platform through a mechanical interface; S2, the strain gauge (332), the thermocouple (331) and the target are attached to the deformable wing rudder (5) according to the measurement requirements, and the driving force collection device (31) is installed in front of the driver of the deformable wing rudder (5); S3, adjusting the position and number of the follow-up loading modules (1) according to the load-bearing region and the load-bearing area of ​​the deformable wing rudder (5), and then controlling the force loading unit (11) to be in a loading state through the test control module (2); S4, adjusting the positions of the horizontal laser displacement sensor (321) and the vertical laser displacement sensor (322) so that the laser can accurately hit the target position; S5, start the test control module (2), the acquisition and measurement module (3) and the system initialization module (411) to initialize the system, adjust the values ​​of the parameters in the parameter configuration module (412), and start the test after eliminating the abnormality according to the information provided by the abnormality alarm module (417); S6, inputting the control instruction into the host computer (41) through the human-computer interaction module (4), transmitting the instruction to the test control module (2) through the program of the host computer (41), and the test control module (2) controlling the force loading unit (11) and the heat loading unit (12) to load, S7, controlling the acquisition and measurement module (3) to start measurement, sending the acquired data to the human-computer interaction module (4), and then transmitting the required data to the visualization module (415) and the data storage module (416) through the data processing module (414), so as to realize data display and storage.

8. The testing method according to claim 7, characterized in that: In said S6, the measurement true values ​​acquired by the host computer (41) all come from the sensor, which specifically includes the following steps: The loading instruction is input into the test control module (2) through the human-computer interaction module (4), the initial state of the deformable wing rudder (5) is a retracted, horizontal posture, the heat loading unit (12) is turned on under the control of the test control module (2), the thermal environment is simulated, the data collected by the thermocouple (331) is transmitted to the programmable controller (22) through the thermocouple collection module (222), the start and stop of the heat loading unit (12) is controlled by a preset temperature threshold, and the temperature is controlled, the force loading unit (11) below the fixed section of the deformable wing rudder (5) starts to work, applies a force load, and realizes accurate loading of the force value through the feedback component (112); The deformable wing rudder (5) begins to deform, and the extension and contraction amount x of the deformable wing rudder (5) is measured by a horizontal laser displacement sensor (321). After reaching the limit position, the rudder is folded. The vertical change amount y of the folding is measured by a vertical laser displacement sensor (322). Then, according to the length d from the folding root to the top, the folding angle is calculated to be θ=arctan(y / d). The remaining motion data is calculated by a data processing module (414); the deformation time t is the start and stop time of the driver, and the deformation accuracy is obtained by comparing the measured data with the deformation instruction; at the same time, the test control module (2) controls the torque sensor (311) of the driving force acquisition device (31) to collect and measure the driving force value; During the extension of the deformable wing rudder (5), the force loading unit (11) below it moves upward and is loaded according to a given loading formula F0=ΔS(t)×p, where F is the output load of the force loading unit (11), p is the uniform pressure borne by the deformable wing rudder (5), and ΔS(t) is the area change, thereby achieving a force following effect; During the folding process of the deformable wing rudder (5), the force F output by the force loading unit (11) below the deformable wing rudder (5) has an angular relationship with the loading direction, and the loading formula is F1=p·S / cosθ°, where S is the area of ​​the folded part, θ is the folding angle, and p is the uniformly distributed pressure borne by the deformable wing rudder (5); During the combined force and heat loading process, the thermocouple (331) and the strain gauge (332) collect the temperature and strain of the surface of the deformable wing rudder (5), and all the above data are stored in the background through the data storage module (416). The visualization module (415) displays the data, and the retraction process is similar.

9. An electronic device comprising a memory and a processor, wherein the memory stores a computer program, wherein: When the processor executes the computer program, the steps of the method described in claim 7 or 8 are implemented.

10. A computer-readable storage medium for storing computer instructions, characterized in that: When the computer instructions are executed by a processor, the steps of the method described in claim 7 or 8 are implemented.

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