Jet flow interference force measurement test method and device of wind tunnel and storage medium

Abstract

The embodiment of the invention provides a wind tunnel jet flow interference force measurement test method and device and a storage medium, and the method comprises the steps: presetting an attack angle or a sideslip angle of a wind tunnel test model, starting an ejector and a main gas source, and carrying out a jet-free test, and obtaining jet-free dynamic data; jet flow is further started, a jet test is carried out, and jet pneumatic data are obtained; closing a main gas source, returning the attack angle or the sideslip angle to zero, carrying out a nozzle thrust calibration test, setting the working time of the ejector not to exceed a preset value, and obtaining nozzle thrust calibration data; and according to the non-jet pneumatic data, the jet pneumatic data and the jet pipe thrust calibration data, a jet flow pneumatic interference factor is obtained. Therefore, three types of tests of spraying, non-spraying and spraying pipe thrust calibration in the same wind tunnel operation train number can be carried out, the jet flow pneumatic interference factor is finally obtained, the test efficiency is improved, and the test is faster and simpler.

Description

Technical Field

[0001] This document relates to the field of wind tunnel test methods, and in particular to a wind tunnel jet interference force measurement test method, device and storage medium. Background Art

[0002] The jet aerodynamic interference factor is used to quantify the influence of the jet on the dynamic characteristics of the aircraft. By calculating and analyzing the jet aerodynamic interference factor, the impact of the jet on the aircraft performance can be more accurately predicted and evaluated.

[0003] When determining the jet aerodynamic factor, the prior art needs to conduct tests in two wind tunnel environments using direct force measurement and indirect force measurement to obtain jet data and thrust data.

[0004] However, the existing technology needs to be tested in two wind tunnel environments, which makes the test work more cumbersome; and the existing thrust data is measured in a wind tunnel using a vacuum pump. Since the ambient back pressure fluctuates greatly after the jet is turned on, the ambient back pressure rises rapidly after a large number of jets are turned on, and the required back pressure environment cannot be stabilized, resulting in large fluctuations in the nozzle thrust calibration data, thereby affecting the accuracy of the jet interference factor. Summary of the invention

[0005] In view of the above scheme, the present application aims to propose a wind tunnel jet interference force measurement test method, device and storage medium to solve at least one of the above technical problems.

[0006] In a first aspect, one or more embodiments of this specification provide a method for testing jet interference force in a wind tunnel, comprising:

[0007] Pre-set the angle of attack or sideslip angle of the wind tunnel test model, turn on the ejector and main air source, conduct a no-jet test, and obtain no-jet dynamic data;

[0008] The jet is further opened to conduct a jet test to obtain jet dynamic data;

[0009] Turn off the main air source, return the angle of attack or sideslip angle to zero, perform a nozzle thrust calibration test, set the ejector working time not to exceed a preset value, and obtain nozzle thrust calibration data; and

[0010] A jet aerodynamic interference factor is obtained according to the jet-free aerodynamic data, the jet-with aerodynamic data and the nozzle thrust calibration data.

[0011] Furthermore, the wind tunnel test was completed through an ejection-type temporary impulse wind tunnel.

[0012] Furthermore, the nozzle in the wind tunnel test model is connected to the wind tunnel test model in a fixed integrated manner.

[0013] Further, in the non-injection test and the injection test, the sequence of preset attack angles or preset sideslip angles is the same.

[0014] Furthermore, the calculation formula of the jet aerodynamic interference factor is as follows:

[0015] K i =(C i有喷 -C i无喷 ) / C i喷流

[0016] Among them, K i represents the jet aerodynamic disturbance factor;

[0017] C i有喷 Indicates that there is jet data;

[0018] C i无喷 Indicates no jet data; and

[0019] C i喷流 Indicates nozzle thrust calibration data.

[0020] In a second aspect, an embodiment of the present application provides a wind tunnel jet interference force measurement test device, comprising:

[0021] The non-jet test module is used to pre-set the angle of attack or sideslip angle of the wind tunnel test model, turn on the ejector and main air source, conduct a non-jet test, and obtain non-jet dynamic data;

[0022] The spray test module is used to further open the spray flow, conduct the spray test, and obtain the spray dynamic data;

[0023] A nozzle thrust calibration test module is used to shut down the main air source, return the angle of attack or sideslip angle to zero, perform a nozzle thrust calibration test, and obtain nozzle thrust calibration data; and

[0024] The calculation module is used to obtain the jet aerodynamic interference factor according to the non-jet aerodynamic data, the jet aerodynamic data and the nozzle thrust calibration data.

[0025] Furthermore, the wind tunnel test was completed through an ejection-type temporary impulse wind tunnel.

[0026] Furthermore, the nozzle in the wind tunnel test model is connected to the wind tunnel test model in a fixed integrated manner.

[0027] Further, in the non-injection test and the injection test, the sequence of preset attack angles or preset sideslip angles is the same.

[0028] In a third aspect, an embodiment of the present application provides a storage medium for storing computer-executable instructions, characterized in that when the computer-executable instructions are executed, the steps of the wind tunnel jet interference force measurement test method described in any one of the first aspects are implemented.

[0029] Compared with the prior art, this application can at least achieve the following technical effects:

[0030] The present application can complete the non-jet, jet and nozzle thrust calibration tests in the same wind tunnel test, and obtain the nozzle thrust data, non-jet aerodynamic data and jet aerodynamic data required for calculating the aerodynamic interference factor at one time, thereby simplifying the test process; the nozzle thrust calibration data is obtained under the condition of the ejector being turned on, and the ejector is used to extract the wind tunnel to a relatively low pressure, so that the ambient back pressure is stable, thereby obtaining a more reliable nozzle thrust and improving the accuracy of the jet aerodynamic interference factor. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate one or more embodiments of this specification or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this specification. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0032] Figure 1 A flow chart of a wind tunnel jet interference force measurement test method provided for one or more embodiments of this specification;

[0033] Figure 2 A schematic structural diagram of a wind tunnel jet interference force measurement test device provided in one or more embodiments of the present specification. DETAILED DESCRIPTION

[0034] In order to enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the following will be combined with the drawings in one or more embodiments of this specification to clearly and completely describe the technical solutions in one or more embodiments of this specification. Obviously, the described embodiments are only part of the embodiments of this specification, not all of the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of this document.

[0035] When an aircraft is conducting a wind tunnel test, it is necessary to complete the nozzle thrust calibration test, the non-jet test and the jet test in two environments. The test workload is cumbersome, and the ambient back pressure fluctuates greatly after the jet is turned on under the condition of vacuum pump extraction. After the large-flow jet is turned on, the ambient back pressure rises rapidly and cannot be stabilized at the required ambient back pressure conditions, causing certain fluctuations in the jet of the nozzle thrust calibration result, which is not conducive to the subsequent processing and analysis of aerodynamic interference data.

[0036] Embodiment 1

[0037] In view of the above technical problems, the present application proposes a wind tunnel jet interference force measurement test method, such as Figure 1 As shown, the specific steps are as follows:

[0038] Step S1, pre-setting the angle of attack or sideslip angle of the wind tunnel test model, turning on the ejector and the main air source, performing a non-jet test, and obtaining non-jet pneumatic data.

[0039] In an embodiment of the present application, before the wind tunnel test, the angle of attack, sideslip angle, total pressure of the incoming flow, total temperature and other conditions of the wind tunnel test model are accurately set according to the test purpose and test requirements. For example: the angle of attack is adjusted from 0 degrees to 20 degrees, with an increment of 2 degrees. The wind tunnel test model is fixed in the test section, and the angle of attack mechanism is used to accurately adjust the model posture to ensure that it can change according to the preset angle. Make sure that all measuring equipment (such as force measuring balances, pressure sensors, etc.) have been calibrated and connected to the data acquisition system. Then check the status of the ejector to confirm whether the ejector is in good working condition and that the nozzle and other key parts are not damaged or blocked. When the wind tunnel test model and measuring equipment have been debugged, enter the wind tunnel test process and run the wind tunnel according to the specified test state.

[0040] First, the pressure in the test chamber is gradually reduced to a predetermined value (for example, to simulate the low pressure environment required for high-altitude conditions) by turning on the ejector. The ejector generates a strong driving force by creating a high-speed airflow after the high-pressure fluid flows through the nozzle, thereby driving the airflow in the wind tunnel; and the ejector can continue to work in the wind tunnel or test chamber to maintain the required low pressure environment. This helps simulate the real environment of the aircraft when flying at high altitudes, thereby conducting more accurate testing and evaluation.

[0041] Secondly, when the pressure in the test chamber reaches the preset value, the main air source is started, the incoming flow field is established, and the preset pressure, temperature and other operating parameters are set for the main air source to simulate the atmospheric conditions at different altitudes and environments during the flight, ensuring that the gas provided by the main air source can stably enter the wind tunnel test section and form a uniform and consistent incoming flow field to meet the speed and density conditions required by the test. Among them, the main air source is the core component in the wind tunnel test, responsible for providing stable and continuous airflow, and can also adjust the parameters of the airflow according to the test requirements, such as airflow speed, pressure and temperature, etc. It plays an important role in providing stable airflow, adjusting airflow parameters, supporting the operation of test equipment and ensuring the safety of the test in the wind tunnel test.

[0042] Finally, under this condition, a no-jet test is carried out to test the angle of attack or sideslip angle of the wind tunnel test model one by one, and the no-jet dynamic data is recorded after each debugging. The no-jet dynamic data is the aerodynamic characteristic data of the model such as lift, drag, torque, etc. when there is incoming flow but no jet.

[0043] Step S2, further opening the jet flow, performing a jet test, and obtaining jet flow dynamic data.

[0044] In the embodiment of the present application, after the non-jet test is completed, the jet is further turned on on the basis of turning on the ejector and the main air source, and the parameters such as the flow rate, speed and direction of the jet are adjusted according to the test requirements; a jet test is carried out, and the angle of attack or sideslip angle of the wind tunnel test model is tested one by one, and the jet dynamic data is recorded after each debugging. Among them, the jet dynamic data is the aerodynamic characteristic data such as lift, drag, torque, etc. of the model under the action of the jet. Its jet can simulate the airflow effect generated by the engine of the aircraft in actual flight. Through the wind tunnel test, the interference of the jet on the outflow of the aircraft can be determined, so as to make full use of the favorable interference of the jet, reasonably arrange the components of the aircraft, reduce the resistance of the aircraft, and improve the maneuverability and stability of the aircraft; the interference of the outflow on the jet can also be determined, so as to reasonably arrange the position of the engine and the nozzle, and select the best nozzle form and size to obtain the maximum thrust of the engine; and the data affected by the jet are obtained by comparing the wind tunnel test with the jet and the test without the jet to ensure the accuracy of the flight data.

[0045] Step S3, closing the main air source, returning the angle of attack or sideslip angle to zero, performing a nozzle thrust calibration test, setting the ejector working time not to exceed a preset value, and obtaining nozzle thrust calibration data.

[0046] In the embodiment of the present application, after the completion of the spray test, the main air source is closed on the basis of opening the ejector and the jet, so as to eliminate the interference of the incoming air on the nozzle thrust measurement. Then adjust the angle of attack or sideslip angle of the model back to zero to ensure that the thrust measurement is carried out under the condition of no tilt and no lateral force. Then carry out the nozzle thrust calibration test. During the nozzle thrust calibration process, the wind tunnel ejector is kept working for generally not less than 5s to prevent the effective value from affecting the test results. Then use the thrust meter and other measuring equipment to accurately record the thrust value of the nozzle during the thrust injection process. The nozzle is connected to the wind tunnel test model in a fixed integrated manner to ensure that the force balance can directly and in real time measure the nozzle thrust calibration data to ensure the accuracy and integrity of the data. Among them, the nozzle thrust calibration data refers to the data obtained by experiment or simulation under specific conditions on the relationship between the thrust generated by the nozzle and its operating parameters, such as: total thrust, thrust coefficient, combustion chamber pressure, nozzle outlet pressure, etc.

[0047] Step S4, obtaining a jet aerodynamic interference factor according to the non-jet aerodynamic data, the jet aerodynamic data and the nozzle thrust calibration data.

[0048] In the embodiment of the present application, the same aerodynamic characteristic data needs to be measured and recorded during the non-jet test and the jet test. Using the same aerodynamic characteristic data, the difference between the measured values ​​of the jet aerodynamic data under the jet condition and the jet-free aerodynamic data under the non-jet condition is calculated to obtain the change data caused by the jet. The change caused by the jet is then compared with the thrust value of the nozzle to evaluate the relative influence of the jet on the aerodynamic performance, thereby obtaining the jet aerodynamic interference factor.

[0049] Using the same sequence of angle of attack or sideslip angle in this application can ensure that these parameters are measured under the same conditions, thereby facilitating subsequent comparison and analysis.

[0050] Preferably, the wind tunnel test is completed by an ejection-type temporary impulse wind tunnel.

[0051] An ejector-type temporary impulse wind tunnel refers to a temporary impulse supersonic wind tunnel with an ejection function. After the main air source is turned off, the ejector and the jet are still on to conduct nozzle thrust calibration tests. The ejector can be used to pump the wind tunnel to a relatively low pressure within a certain period of time, and then the thrust data of the jet itself can be obtained when only the jet is turned on, that is, the nozzle thrust calibration data.

[0052] In the ejection-type temporary wind tunnel, the main air source, ejector and jet components can work together in the experimental sequence, so that the wind tunnel test can complete the non-jet test, the jet test and the nozzle thrust calibration test in one wind run, so as to measure the non-jet dynamic data, the jet dynamic data and the nozzle thrust calibration data at one time, thus forming a complete wind tunnel test. The synergy between them enables the wind tunnel to simulate various complex airflow conditions, thus meeting the needs of aircraft design and optimization.

[0053] For example: fix the test model in the wind tunnel test section to ensure that it is firm and can adjust its posture freely, then assemble the wind tunnel test model on the ground, connect the force balance, sensor, support rod and other components; then use the calibration instrument to calibrate the model and test equipment, ensure that all measuring equipment has been calibrated, and connect to the data acquisition system to prepare to record the experimental data. First, open the control valve of the ejector to gradually reduce the pressure in the test chamber to the predetermined value. When the pressure in the test chamber reaches the predetermined value, start the main gas source and set the predetermined pressure, temperature and other operating parameters (such as 30 bar pressure and 300K temperature) for the main gas source; ensure that the gas provided by the main gas source can stably enter the wind tunnel test section to form a uniform and consistent incoming flow field to meet the speed and density conditions required by the test. Secondly, conduct a non-spray test, gradually increase the angle of attack or sideslip angle according to the predetermined sequence, wait for enough time for the airflow to stabilize after each adjustment, and then record the corresponding aerodynamic parameters; for each angle point, perform multiple independent measurements to ensure the consistency and reliability of the data. Then conduct a jet test, gradually start the jet gas source, ensure that the jet transitions smoothly and reaches the predetermined working state; under the jet condition, retest the angle of attack or sideslip angle and record the corresponding data. Then conduct a nozzle thrust calibration test, gradually close the main gas source, ensure a smooth transition, and avoid sudden air outage causing shock to the system; adjust the model's angle of attack and sideslip angle back to 0 degrees to ensure that the model returns to the initial attitude; keep the ejector working, but for no less than the preset time (such as 5 seconds), and record the thrust data generated by the nozzle at the same time. The thrust data can be averaged in the future, with more valid values, improving the accuracy of the test. Finally, combine the jet aerodynamic data and non-jet aerodynamic data under the same sequence and the nozzle thrust calibration data to calculate the jet aerodynamic interference factor and evaluate the impact of the jet on the performance of the aircraft.

[0054] Preferably, in the non-injection test and the injection test, the sequence of preset attack angles or preset sideslip angles is the same.

[0055] The angle of attack and sideslip angle are the inclination angles of the aircraft model relative to the incoming flow direction. In the non-spray test and the spray test, maintaining the same sequence of angles of attack or sideslip angles can ensure that the aerodynamic performance of the model under both conditions is measured at the same attitude and angle, thereby eliminating the interference of attitude changes on the aerodynamic performance evaluation. In addition to the angle of attack or sideslip angle, it is also necessary to ensure that the incoming flow velocity, temperature, pressure and other conditions remain consistent in the non-spray and spray tests to further ensure the consistency of the test conditions.

[0056] For example: set a series of attack angles, such as 0°, 5°, 10°, 15°, 20°, etc. In the non-jet experiment, adjust the model's attitude according to the attack angle sequence, and measure the corresponding non-jet aerodynamic data. In the jet test, also adjust the model's attitude according to the attack angle sequence, turn on the jet, and then measure the jet aerodynamic data. Among them, the non-jet aerodynamic data and the jet aerodynamic data include key aerodynamic performance parameters such as lift, drag, and lateral force. Compare the aerodynamic data in the non-jet and jet tests, evaluate the impact of the jet on the aerodynamic performance of the model, and analyze the trends and laws of the impact of the jet on the aerodynamic performance of the model at different attack angles.

[0057] Preferably, the calculation formula of the jet aerodynamic interference factor is as follows:

[0058] K i =(C i有喷 -C i无喷 ) / C i喷流

[0059] Among them, K i represents the jet aerodynamic disturbance factor;

[0060] C i有喷 Indicates that there is jet data;

[0061] C i无喷 Indicates no jet data; and

[0062] C i喷流 Indicates nozzle thrust calibration data.

[0063] Embodiment 2

[0064] In order to study the aerodynamic effect of aircraft jet interference through wind tunnel tests and obtain the aerodynamic interference factor of jet interference, a jet interference force measurement test method suitable for pressure-injection wind tunnels was established. The specific steps are as follows:

[0065] (1) Assemble the wind tunnel test model, force balance, support rod and other components on the ground, and install the wind tunnel support rod on the wind tunnel angle of attack mechanism;

[0066] (2) After the model and test system are debugged, they are ready to enter the wind tunnel test process;

[0067] (3) Turn on the ejector. After the pressure in the test chamber drops to about 6000 Pa, turn on the main gas source to establish an incoming flow field with predetermined parameters;

[0068] (4) Keep the jet air source closed and complete the no-jet wind test under the attack angle sequence of α = -4°, -2°, 0°, 2°, and 4° to obtain the no-jet air data C under each attack angle condition. i无喷 ;

[0069] (5) Open the jet gas source and adjust the total jet pressure P 0j =1.0MPa, complete the jet wind test under the attack angle sequence conditions of α=-4°, -2°, 0°, 2°, 4°, and obtain the jet dynamic data C under each attack angle condition i有喷 ;

[0070] (6) After completing the blowing test of the angle of attack sequence, the angle of attack returns to zero and the total pressure P of the jet opening is maintained. 0j =1.0MPa, turn off the main air source of the wind tunnel, and keep the wind tunnel ejector working. At this time, the pressure in the test chamber is about 6000Pa, and P is completed. 0j = Nozzle thrust calibration test under 1.0MPa total pressure condition, obtain nozzle thrust calibration data C i喷流 ;

[0071] (7) Turn off the ejector and complete the wind tunnel test;

[0072] (8) Obtain the jet aerodynamic interference factor K under various attack angle conditions i =(C i有喷 -C i无喷 ) / C i喷流 .

[0073] The method of the present application can complete the non-jet, jet and nozzle thrust calibration tests in one blower trip, and obtain the nozzle thrust data, non-jet aerodynamic data and jet aerodynamic data required for calculating the aerodynamic interference factor at one time, which is convenient for the implementation of the direct force measurement method of jet interference. In the nozzle thrust calibration test, the nozzle thrust calibration data is measured under the condition of the ejector being turned on, and the ambient back pressure is relatively stable, which is conducive to obtaining more reliable nozzle thrust.

[0074] Embodiment 3

[0075] The present application embodiment provides a wind tunnel jet interference force measurement test device, such as Figure 2 As shown, including:

[0076] The non-spray test module 101 is used to pre-set the angle of attack or sideslip angle of the wind tunnel test model, turn on the ejector and the main air source, perform the non-spray test, and obtain the non-spray pneumatic data;

[0077] A spray test module 102 is used to further open the spray flow, perform a spray test, and obtain spray dynamic data;

[0078] The nozzle thrust calibration test module 103 is used to close the main air source, return the angle of attack or sideslip angle to zero, perform a nozzle thrust calibration test, and obtain nozzle thrust calibration data; and

[0079] The calculation module 104 is used to obtain the jet aerodynamic interference factor according to the non-jet aerodynamic data, the jet aerodynamic data and the nozzle thrust calibration data.

[0080] Furthermore, the wind tunnel test was completed through an ejection-type temporary impulse wind tunnel.

[0081] Furthermore, the nozzle in the wind tunnel test model is connected to the wind tunnel test model in a fixed integrated manner.

[0082] Further, in the non-injection test and the injection test, the sequence of preset attack angles or preset sideslip angles is the same.

[0083] An embodiment of the present application provides a storage medium for storing computer-executable instructions, wherein the computer-executable instructions, when executed, implement the steps of the wind tunnel jet interference force measurement test method described in any one of the above embodiments.

[0084] It should be noted that the embodiments of the storage medium in this specification and the embodiments of the blockchain-based service provision method in this specification are based on the same inventive concept. Therefore, the specific implementation of this embodiment can refer to the aforementioned corresponding implementation of the blockchain-based service provision method, and the repeated parts will not be repeated.

[0085] The above is a description of a specific embodiment of the specification. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recorded in the claims can be performed in an order different from that in the embodiments and still achieve the desired results. In addition, the processes depicted in the drawings do not necessarily require the specific order or continuous order shown to achieve the desired results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0086] In the 1930s, improvements to a technology could be clearly distinguished as hardware improvements (for example, improvements to the circuit structure of diodes, transistors, switches, etc.) or software improvements (improvements to the method flow). However, with the development of technology, many improvements to the method flow today can be regarded as direct improvements to the hardware circuit structure. Designers almost always obtain the corresponding hardware circuit structure by programming the improved method flow into the hardware circuit. Therefore, it cannot be said that an improvement in a method flow cannot be implemented using a hardware entity module. For example, a programmable logic device (PLD) (such as a field programmable gate array (FPGA)) is such an integrated circuit whose logical function is determined by the user's programming of the device. Designers can "integrate" a digital system on a PLD by programming it themselves, without having to ask a chip manufacturer to design and produce a dedicated integrated circuit chip. Moreover, nowadays, instead of manually making integrated circuit chips, this kind of programming is mostly implemented by "logic compiler" software, which is similar to the software compiler used when developing and writing programs, and the original code before compilation must also be written in a specific programming language, which is called hardware description language (HDL). There is not only one HDL, but many kinds, such as ABEL (Advanced Boolean Expression Language), AHDL (Altera Hardware Description Language), Confluence, CUPL (Cornell University Programming Language), HDCal, JHDL (Java Hardware Description Language), Lava, Lola, MyHDL, PALASM, RHDL (Ruby Hardware Description Language), etc. The most commonly used ones are VHDL (Very-High-Speed ​​Integrated Circuit Hardware Description Language) and Verilog. Those skilled in the art should also know that it is only necessary to program the method flow slightly in the above-mentioned hardware description languages ​​and program it into the integrated circuit, and then it is easy to obtain the hardware circuit that implements the logic method flow.

[0087] The controller can be implemented in any appropriate manner, for example, the controller can take the form of a microprocessor or processor and a computer-readable medium storing a computer-readable program code (such as software or firmware) that can be executed by the (micro)processor, a logic gate, a switch, an application-specific integrated circuit (ASIC), a programmable logic controller, and an embedded microcontroller. Examples of controllers include, but are not limited to, the following microcontrollers: ARC 625D, Atmel AT91SAM, Microchip PIC18F26K20, and Silicone Labs C8051F320. The memory controller can also be implemented as part of the control logic of the memory. Those skilled in the art also know that in addition to implementing the controller in a purely computer-readable program code manner, the controller can be implemented in the form of a logic gate, a switch, an application-specific integrated circuit, a programmable logic controller, and an embedded microcontroller by logically programming the method steps. Therefore, this controller can be considered as a hardware component, and the devices included therein for implementing various functions can also be regarded as structures within the hardware component. Or even, the devices for implementing various functions can be regarded as both software modules for implementing the method and structures within the hardware component.

[0088] The systems, devices, modules or units described in the above embodiments may be implemented by computer chips or entities, or by products with certain functions. A typical implementation device is a computer. Specifically, the computer may be, for example, a personal computer, a laptop computer, a cellular phone, a camera phone, a smart phone, a personal digital assistant, a media player, a navigation device, an email device, a game console, a tablet computer, a wearable device, or a combination of any of these devices.

[0089] For the convenience of description, the above devices are described in terms of functions and are divided into various units. Of course, when implementing the embodiments of this specification, the functions of each unit can be implemented in the same or multiple software and / or hardware.

[0090] It should be understood by those skilled in the art that one or more embodiments of this specification may be provided as a method, system or computer program product. Therefore, one or more embodiments of this specification may take the form of a complete hardware embodiment, a complete software embodiment, or an embodiment combining software and hardware. Moreover, this specification may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0091] This specification is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of this specification. It should be understood that each process and / or box in the flowchart and / or block diagram, as well as the combination of the processes and / or boxes in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 A process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0092] These computer program instructions may also be stored in a computer-readable memory capable of directing a computer or other programmable data processing device to operate in a specific manner, so that the instructions stored in the computer-readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 A process or multiple processes and / or boxes Figure 1 A function specified in one or more boxes.

[0093] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operating steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing instructions for implementing the process. Figure 1 A process or multiple processes and / or boxes Figure 1 The steps for the functions specified in one or more boxes.

[0094] In a typical configuration, a computing device includes one or more processors (CPU), input / output interfaces, network interfaces, and memory.

[0095] The memory may include non-permanent storage in a computer-readable medium, random access memory (RAM) and / or non-volatile memory in the form of read-only memory (ROM) or flash RAM. The memory is an example of a computer-readable medium.

[0096] Computer readable media include permanent and non-permanent, removable and non-removable media that can be implemented by any method or technology to store information. Information can be computer readable instructions, data structures, program modules or other data. Examples of computer storage media include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technology, compact disk read-only memory (CD-ROM), digital versatile disk (DVD) or other optical storage, magnetic cassettes, magnetic tape magnetic disk storage or other magnetic storage devices or any other non-transmission media that can be used to store information that can be accessed by a computing device. As defined herein, computer readable media does not include temporary computer readable media (transitory media), such as modulated data signals and carrier waves.

[0097] It should also be noted that the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, commodity or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, commodity or device. In the absence of more restrictions, the elements defined by the sentence "comprises a ..." do not exclude the existence of other identical elements in the process, method, commodity or device including the elements.

[0098] One or more embodiments of the present specification may be described in the general context of computer-executable instructions executed by a computer, such as program modules. Generally, program modules include routines, programs, objects, components, data structures, etc. that perform specific tasks or implement specific abstract data types. One or more embodiments of the present specification may also be practiced in distributed computing environments where tasks are performed by remote processing devices connected through a communication network. In a distributed computing environment, program modules may be located in local and remote computer storage media, including storage devices.

[0099] Each embodiment in this specification is described in a progressive manner, and the same or similar parts between the embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the system embodiment, since it is basically similar to the method embodiment, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiment.

[0100] The above description is only an embodiment of this document and is not intended to limit this document. For those skilled in the art, this document may have various changes and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of this document should be included in the scope of the claims of this document.

Claims

1. A wind tunnel jet interference force measurement test method, characterized in that include: Pre-set the angle of attack or sideslip angle of the wind tunnel test model, turn on the ejector and main air source, conduct a no-jet test, and obtain no-jet dynamic data; The jet is further opened to conduct a jet test to obtain jet dynamic data; Turn off the main air source, return the angle of attack or sideslip angle to zero, perform a nozzle thrust calibration test, set the ejector working time not to exceed a preset value, and obtain nozzle thrust calibration data; and A jet aerodynamic interference factor is obtained according to the jet-free aerodynamic data, the jet-with aerodynamic data and the nozzle thrust calibration data.

2. The method according to claim 1, characterized in that The wind tunnel test was completed through an ejection-type temporary wind tunnel.

3. The method according to claim 2, characterized in that Also includes, The nozzle in the wind tunnel test model is connected to the wind tunnel test model in a fixed integrated manner.

4. The method according to claim 1, characterized in that Also includes, In the non-injection test and the injection test, the sequence of preset attack angles or preset sideslip angles is the same.

5. The method according to claim 1, characterized in that The calculation formula of the jet aerodynamic interference factor is as follows: K i =(C i有喷 -C i无喷 ) / C i喷流 Among them, K i represents the jet aerodynamic disturbance factor; C i有喷 Indicates that there is jet data; C i无喷 Indicates no jet data; and C i喷流 Indicates nozzle thrust calibration data.

6. A wind tunnel jet interference force test device, characterized in that include: The non-jet test module is used to pre-set the angle of attack or sideslip angle of the wind tunnel test model, turn on the ejector and main air source, conduct a non-jet test, and obtain non-jet dynamic data; The spray test module is used to further open the spray flow, conduct the spray test, and obtain the spray dynamic data; A nozzle thrust calibration test module is used to shut down the main air source, return the angle of attack or sideslip angle to zero, perform a nozzle thrust calibration test, and obtain nozzle thrust calibration data; and The calculation module is used to obtain the jet aerodynamic interference factor according to the non-jet aerodynamic data, the jet aerodynamic data and the nozzle thrust calibration data.

7. The device according to claim 6, characterized in that The wind tunnel test was completed through an ejection-type temporary wind tunnel.

8. The device according to claim 6, characterized in that The nozzle in the wind tunnel test model is connected to the wind tunnel test model in a fixed integrated manner.

9. The device according to claim 6, characterized in that In the non-injection test and the injection test, the sequence of preset attack angles or preset sideslip angles is the same.

10. A storage medium for storing computer executable instructions, characterized in that: When the computer executable instructions are executed, the steps of the wind tunnel jet interference force measurement test method according to any one of claims 1 to 5 are implemented.

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