Lateral thermal jet interference wind tunnel test system and method

Abstract

The invention provides a lateral thermal jet interference wind tunnel test system and method. The system comprises a medium supply subsystem used for providing oxidant gas and fuel gas for a fuel gas combustion device, and the total pressure and flow of the oxidant gas and the fuel gas are adjustable; the fuel gas combustion device is used for carrying out mixed combustion on oxidant gas and fuel gas to generate fuel gas jet flow; the fuel gas parameter calibration subsystem is used for collecting the total pressure and the total temperature of fuel gas, sampling fuel gas jet flow generated by a fuel gas device, and analyzing and determining component parameters of the fuel gas. Based on the lateral thermal jet flow interference wind tunnel test method provided by the system, calculation results and test results of surface pressure distribution, aerodynamic force and torque of a wind tunnel test model under non-jet and jet test conditions can be obtained.

Description

Technical Field

[0001] The present invention belongs to the field of wind tunnel test methods, and particularly relates to a lateral hot jet interference wind tunnel test system and method. Background Technique

[0002] The direct force control technology of aircraft uses the reaction force generated by the lateral jet of the engine to change the motion attitude or orbit of the aircraft. Its function is to supplement the insufficient efficiency of the aerodynamic rudder surface and quickly change the flight state, and has been applied to various aircraft at home and abroad.

[0003] Under actual conditions, the controlled jet is usually a multi-component gas hot jet generated by a solid or liquid engine. The actual gas jet is a high-temperature mixed gas composed of multiple components with different thermodynamic characteristics. There is mass, momentum, and energy transport and exchange between these gas components. When the jet mixes with the external flow, the unburned jet products will undergo secondary combustion when encountering the external flow air. The hot jet interference effect of the jet makes the jet interference flow mechanism more complex.

[0004] Due to the immaturity of the hot jet wind tunnel test method, most current research uses cold jet simulation technology, that is, the gas jet is converted into a perfect gas (cold jet) for simulation under the condition of satisfying a limited number of similarity parameters, and it is impossible to simulate the characteristics of the real gas jet medium, the chemical non-equilibrium flow effect of secondary combustion, etc., resulting in a difference between the predicted results of the jet interference aerodynamic / thermal characteristics obtained and the real flight. Under certain conditions, the jet interference aerodynamic / thermal load may increase several times or more than ten times. This difference will seriously affect the low-redundancy design of flight control accuracy (it is very likely to cause control failure problems), and the accuracy of its data urgently needs the support of ground test data.

[0005] Currently, the simulation of hot jets mainly uses the method of generating high-temperature gas flow by hydrogen-oxygen combustion driving a Ludwig tube and the method of generating gas flow by a micro solid rocket engine. Due to poor stability or unclear chemical mechanism of the two hot jet implementation methods, it is difficult to use the test data as quantitative data to verify numerical methods. Currently, due to the complexity of the hot jet interference itself and the lack of ground test capabilities, there are no available quantitative test results so far, and the relevant numerical methods cannot be effectively verified. Summary of the Invention

[0006] The technical problem to be solved by the present invention: Overcoming the deficiencies of the prior art, providing a lateral hot jet interference wind tunnel test system and method, and quantitative hot jet interference test results of jet parameters can be obtained based on this method.

[0007] The technical solution of the present invention: A lateral hot jet interference wind tunnel test system, which includes a medium supply subsystem, a gas combustion device, and a gas parameter calibration subsystem;

[0008] A medium supply subsystem for providing oxidant gas and fuel gas to a gas combustion device, where the total pressure and flow rate of the oxidant gas and the fuel gas are adjustable;

[0009] A gas combustion device that mixes and burns the oxidant gas and the fuel gas to generate a fuel gas jet;

[0010] A fuel gas parameter calibration subsystem that collects the total pressure of the fuel gas, the total temperature of the fuel gas, samples the fuel gas jet generated by the fuel gas device, and analyzes and determines the component parameters of the fuel gas.

[0011] Preferably, the medium supply subsystem includes an oxidant gas source, an oxidant gas pipeline, a fuel gas source, and a fuel gas pipeline; the oxidant gas source is connected to the gas combustion device through the oxidant gas pipeline; the fuel gas source is connected to the gas combustion device through the fuel gas pipeline;

[0012] The oxidant gas pipeline is composed of an oxygen shut-off valve, a fuel gas filter, a first pressure sensor, a fuel gas mass flowmeter, a fuel gas pressure reducing valve, and a second pressure sensor connected in sequence;

[0013] The fuel gas pipeline is composed of a fuel gas shut-off valve, a fuel gas filter, a third pressure sensor, a fuel gas mass flowmeter, a fuel gas pressure reducing valve, and a fourth pressure sensor connected in sequence.

[0014] Preferably, the gas combustion device includes an injector, a combustion chamber, an igniter, and a nozzle;

[0015] The injector includes an inlet interface for fuel gas and oxidant gas, and an outlet. The inlet section of the combustion chamber is coaxially connected to the outlet of the injector, the outlet section is coaxially connected to the nozzle, and the axes of the inlet section and the outlet section are perpendicular to each other, forming an L shape; the igniter is installed on the side wall of the inlet section of the combustion chamber.

[0016] Preferably, the fuel gas parameter calibration subsystem includes a fifth pressure sensor, a thermocouple sensor, and a gas sampling device;

[0017] The fifth pressure sensor is arranged at the combustion chamber of the gas combustion device for collecting the total pressure of the fuel gas, and the thermocouple sensor is arranged at the combustion chamber of the gas combustion device for collecting the total temperature of the fuel gas;

[0018] The gas sampling device is arranged at the nozzle of the gas combustion device for sampling the fuel gas jet ejected from the nozzle.

[0019] Another technical solution of the present invention is: a method for a lateral hot jet interference wind tunnel test, the method comprising the following steps:

[0020] S1. Select fuel gas as the jet test medium for the lateral hot jet test;

[0021] S2. Determine the hot jet parameters for the wind tunnel test based on the lateral control engine jet parameters under the flight conditions of the aircraft, so as to ensure that the typical jet interference similarity parameters under the wind tunnel test conditions are the same as those under the flight conditions; the hot jet parameters for the wind tunnel test include the scaled nozzle size of the wind tunnel test, the total pressure and flow rate parameters of the hot jet.

[0022] S3. Construct a lateral hot jet interference wind tunnel test system, and design the specific parameters of the gas combustion device according to the scaled nozzle size of the wind tunnel test, the total pressure and mass flow rate of the hot jet, including the diameter of the combustion chamber, the outlet diameter of the nozzle, the throat diameter of the nozzle, and the Mach number at the nozzle outlet.

[0023] S4. Complete the measurement of the gas jet parameters of the gas combustion device under the total pressure and flow rate parameters of the test, and obtain the total gas temperature and gas component parameters under the specified test total pressure and flow rate conditions.

[0024] S5. Based on the geometric parameters of the wind tunnel test model, generate a computational grid for numerical calculation, and perform numerical simulations under the conditions of no jet and with jet according to the operating conditions of the wind tunnel and the total gas temperature and gas component parameters under the specified test total pressure and flow rate conditions, so as to obtain the calculation results of the surface pressure distribution of the wind tunnel test model and the calculation results of the aerodynamic force and moment under the conditions of no jet and with jet tests.

[0025] S6. Based on the size conditions of the gas combustion device and the numerical simulation results, determine the layout of the pressure measurement points and the balance load, complete the integrated design of the pressure measurement model - gas device and the integrated design of the force measurement model - gas device, and obtain the integrated structure of the pressure measurement model - gas device and the integrated structure of the force measurement model - gas device.

[0026] S7. Adopt the pressure measurement test method, and based on the integrated structure of the pressure measurement model - gas device, complete the hot jet interference wind tunnel pressure measurement test under the specified test total pressure and flow rate conditions, and obtain the test results of the pressure distribution of the surface pressure measurement points of the test model under the conditions of no jet and with jet tests; adopt the force measurement test method, and based on the integrated structure of the force measurement model - gas device, complete the hot jet interference wind tunnel force measurement test under the specified test total pressure and flow rate conditions, and obtain the test results of the aerodynamic force and moment of the test model under the conditions of no jet and with jet tests.

[0027] S8. Compare and analyze the numerical simulation results with the test results.

[0028] Preferably, the lateral control engine parameters under the flight conditions of the aircraft in step S1 include the outlet diameter of the control engine nozzle, the throat diameter, the specific heat ratio of the outlet gas, the outlet Mach number, and the total pressure of the combustion chamber.

[0029] Preferably, the similarity parameters adopted in the hot jet interference wind tunnel test are the pressure ratio and the momentum ratio.

[0030] Preferably, the similarity parameter of the wind tunnel test conditions being the same as that of the flight conditions for jet interference means that: the static pressure P at the nozzle outlet of the gas combustion device satisfying the wind tunnel test conditions 燃烧装置j and the static pressure P of the wind tunnel incoming flow 风洞∞ The ratio P 燃烧装置j / P 风洞∞ is equal to the static pressure P at the nozzle outlet of the control engine under flight conditions 控制发动机j and the static pressure P of the incoming flow under flight conditions 飞行∞ The ratio P 控制发动机j / P 飞行∞ , the momentum M at the nozzle outlet of the gas combustion device under wind tunnel test conditions 燃烧装置j and the incoming flow momentum M of the wind tunnel 风洞∞ The ratio M 燃烧装置j / M 风洞∞ is equal to the momentum M at the nozzle outlet of the control engine under flight conditions 控制发动机j and the incoming flow momentum M under flight conditions 飞行∞ The ratio M 控制发动机 / M 飞行∞ .

[0031] Preferably, the total gas temperature calibrated in the combustion chamber of the gas combustion device is determined by taking the average of the measured values of two or more thermocouple sensors arranged at the inlet of the nozzle contraction section.

[0032] The beneficial effects of the present invention are as follows:

[0033] (1). The present invention provides a method for a lateral hot jet interference wind tunnel test. Using this method, quantitative hot jet interference test results of jet parameters can be obtained, and the chemical reaction mechanism of the gas medium used is relatively clear, which is beneficial to the verification of numerical methods for hot jet interference.

[0034] (2). The test system involved in the present invention is simple in form, and the gas combustion device can achieve long-term stable combustion, which is beneficial to the measurement of interference flow field characteristics and aerodynamic characteristics.

[0035] (3). The method for a lateral hot jet interference wind tunnel test provided by the present invention is applicable to low-speed, subsonic / transonic / supersonic and hypersonic wind tunnel tests. Description of the Drawings

[0036] Figure 1 is a schematic diagram of the test method of the embodiment of the present invention;

[0037] Figure 2 is a schematic diagram of the hot jet flow test system of the embodiment of the present invention;

[0038] Figure 3 is a schematic diagram of the gas combustion device of the embodiment of the present invention. Detailed Embodiments

[0039] The present invention will be further described in detail below with reference to the accompanying drawings, so that those skilled in the art can implement it according to the text of the specification.

[0040] As Figure 1 shown, the present invention provides a method for a lateral hot jet interference wind tunnel test, and the method includes the following steps:

[0041] S1. Select gas as the jet test medium for the lateral hot jet test; the jet test medium can be high-temperature gas generated by using methane, ethylene or acetylene as fuel and air (or a mixed gas with different oxygen contents) as oxidant.

[0042] S2. Determine the hot jet parameters of the wind tunnel test according to the lateral control engine jet parameters under the flight conditions of the aircraft, so as to ensure that the typical jet interference similarity parameters of the wind tunnel test conditions are the same as those of the flight conditions; the hot jet parameters of the wind tunnel test include the scale nozzle size of the wind tunnel test, the total pressure of the hot jet and the flow rate parameters; the lateral control engine parameters under the flight conditions of the aircraft include the outlet diameter of the control engine nozzle, the throat diameter, the specific heat ratio of the outlet gas, the outlet Mach number, and the total pressure of the combustion chamber.

[0043] The similarity parameters adopted in the hot jet interference wind tunnel test are the pressure ratio and the momentum ratio. The same jet interference similarity parameters between the wind tunnel test conditions and the flight conditions mean that: the static pressure P 燃烧装置j at the outlet of the nozzle of the gas combustion device under the wind tunnel test conditions and the static pressure P 风洞∞ of the wind tunnel incoming flow ratio P 燃烧装置j / P 风洞∞ is equal to the static pressure P 控制发动机j at the outlet of the control engine nozzle under the flight conditions and the static pressure P 飞行∞ of the flight condition incoming flow ratio P 控制发动机j / P 飞行∞ , the momentum M 燃烧装置j at the outlet of the nozzle of the gas combustion device under the wind tunnel test conditions and the momentum M 风洞∞ of the wind tunnel incoming flow ratio M 燃烧装置j / M 风洞∞ is equal to the momentum M 控制发动机j at the outlet of the control engine nozzle under the flight conditions and the momentum M 飞行∞ of the flight condition incoming flow ratio M 控制发动机 / M 飞行∞ .

[0044] S3. Construct a lateral hot jet interference wind tunnel test system, and design the specific parameters of the gas combustion device according to the scale nozzle size of the wind tunnel test, the total pressure of the hot jet and the mass flow rate, including the diameter of the combustion chamber, the outlet diameter of the nozzle, the throat diameter of the nozzle, and the outlet Mach number of the nozzle;

[0045] S4. Complete the measurement of the high-temperature gas jet parameters of the gas combustion device under the total pressure and flow rate parameters of the test, and obtain the total gas temperature and gas component parameters under the specified test total pressure and flow rate conditions.

[0046] S5. Based on the geometric parameters of the wind tunnel test model, generate a computational grid for numerical calculation. According to the operating conditions of the wind tunnel and the total gas temperature and gas component parameters under the specified test total pressure and flow rate conditions, conduct numerical simulations under non-injection and injection conditions to obtain the calculation results of the surface pressure distribution and the aerodynamic forces and moments of the wind tunnel test model under non-injection and injection test conditions.

[0047] In the numerical simulation, the jet boundary conditions are set according to the calibrated actual total pressure, total temperature, and component parameters for the jet conditions.

[0048] S6. Based on the size conditions of the gas combustion device and the numerical simulation results, determine the layout of the pressure measurement points and the balance load, complete the integrated design of the pressure measurement model - gas device and the integrated design of the force measurement model - gas device, and obtain the integrated structure of the pressure measurement model - gas device and the integrated structure of the force measurement model - gas device.

[0049] S7. Adopt the pressure measurement test method. Based on the integrated structure of the pressure measurement model - gas device, complete the hot jet interference wind tunnel pressure measurement test under the specified test total pressure and flow rate conditions to obtain the pressure distribution test results of the surface pressure measurement points of the test model under non-injection / injection test conditions; adopt the force measurement test method. Based on the integrated structure of the force measurement model - gas device, complete the hot jet interference wind tunnel force measurement test under the specified test total pressure and flow rate conditions to obtain the test results of the aerodynamic forces and moments of the test model under non-injection and injection test conditions.

[0050] S8. After the above wind tunnel tests are completed, the calculated results of the surface pressure distribution of the test model under non-injection / injection test conditions can be compared and analyzed with the pressure distribution test results of the surface pressure measurement points of the test model, and the calculated results of the aerodynamic forces and moments of the test model and the test results of the aerodynamic forces and moments of the test model under non-injection and injection test conditions can be compared and analyzed.

[0051] Preferably, the lateral hot jet interference wind tunnel test system includes a medium supply subsystem, a gas combustion device, and a gas parameter calibration subsystem.

[0052] The medium supply subsystem is used to provide oxidant gas and fuel gas for the gas combustion device, and the total pressure and flow rate of the oxidant gas and fuel gas are adjustable.

[0053] The gas combustion device mixes and burns the oxidant gas and fuel gas to generate a gas jet.

[0054] The gas parameter calibration subsystem collects the total gas pressure, total gas temperature, samples the gas jet generated by the gas device, and analyzes and determines the component parameters of the gas.

[0055] As Figure 2 shown, the medium supply subsystem has two gas paths. The upstream is connected to the fuel gas source and the oxidant gas source respectively through high-pressure resistant pipelines. Both gas paths are equipped with stop valves, pressure reducing valves, pressure sensors, mass flow meters, etc. The downstream of both gas paths is connected to the fuel gas inlet and the oxidant gas inlet of the gas combustion device respectively through high-pressure resistant pipelines. The supply pressure and flow rate of the fuel gas and the oxidant gas are controlled by the pressure reducing valves. Specifically, the medium supply subsystem includes an oxidant gas source, an oxidant gas pipeline, a gas source, and a gas pipeline; the oxidant gas source is connected to the gas combustion device through the oxidant gas pipeline; the gas source is connected to the gas combustion device through the gas pipeline;

[0056] The oxidant gas pipeline consists of an oxygen stop valve, a gas filter, a first pressure sensor, a gas mass flow meter, a gas pressure reducing valve, and a second pressure sensor connected in sequence;

[0057] The gas pipeline consists of a gas stop valve, a gas filter, a third pressure sensor, a gas mass flow meter, a gas pressure reducing valve, and a fourth pressure sensor connected in sequence.

[0058] As Figure 3 shown, the gas combustion device includes an injector, a combustion chamber, an igniter, and a nozzle;

[0059] The injector includes fuel gas and oxidant gas inlet interfaces, as well as an outlet. The inlet section of the combustion chamber is coaxially connected to the outlet of the injector, and the outlet section is coaxially connected to the nozzle. The axes of the inlet section and the outlet section are perpendicular to each other, forming an L shape, that is, the axis of the nozzle is perpendicular to the axis of the combustion chamber; the igniter is installed on the side wall of the inlet section of the combustion chamber, and pressure sensor and temperature sensor interfaces are arranged below the nozzle contraction section of the combustion device.

[0060] The gas parameter calibration subsystem includes a fifth pressure sensor, a thermocouple sensor, and a gas sampling device;

[0061] The fifth pressure sensor is arranged at the combustion chamber of the gas combustion device and is used to collect the total gas pressure. The thermocouple sensor is arranged at the combustion chamber of the gas combustion device and is used to collect the total gas temperature;

[0062] The gas sampling device is arranged at the nozzle of the gas combustion device and is used to sample the high-temperature gas jet ejected from the nozzle.

[0063] The total gas temperature calibrated in the combustion chamber of the gas combustion device is determined by taking the average of the measured values of two or more thermocouple sensors arranged at the inlet of the nozzle contraction section.

[0064] Embodiment

[0065] In order to study the hot jet interference effect of an aircraft by means of wind tunnel tests, obtain quantitative test results with clear jet conditions and reaction mechanisms, and verify the numerical simulation method of hot jet interference, a lateral hot jet interference wind tunnel test method was established, a hot jet interference test system was constructed, and the relevant test designs were completed. The specific steps are as follows:

[0066] (1) Methane was selected as the fuel gas and air as the oxidant gas, with a mass mixing ratio of methane:air of 1:20. The high-temperature combustion gas of methane and air was used as the jet test medium.

[0067] (2) Based on the flight conditions of the aircraft and the jet parameters of the lateral control engine, ensuring that the pressure ratio, momentum ratio, and jet interference similarity parameters of the wind tunnel test conditions are the same as those of the flight conditions, the hot jet parameters of the wind tunnel test were determined to be the scaled nozzle size of the wind tunnel test, the total pressure of the hot jet, and the flow rate parameters. In this embodiment, the jet total pressure is 3.0 MPa, and the flow rate parameter is the mass flow rate, which can be taken as 50 g / s.

[0068] (3) The medium supply subsystem of the constructed hot jet interference test system has two gas paths for methane and air. Upstream, they are respectively connected to the methane high-pressure gas cylinder and the air gas cylinder through high-pressure-resistant pipelines. Both gas paths are equipped with stop valves, pressure reducing valves, pressure sensors, mass flow meters, etc. Downstream, the two gas paths are respectively connected to the methane gas inlet and the air gas inlet of the gas combustion device through high-pressure-resistant pipelines. The supply pressure and flow rate of the fuel gas and the oxidant gas are controlled by the pressure reducing valve to meet the total pressure and flow rate conditions of the test.

[0069] (4) A gas combustion device was designed. The injector adopts a premixed form, and the igniter uses a conventional spark plug. Two temperature sensors and one pressure sensor are arranged below the nozzle to measure the total temperature and total pressure of the combustion chamber. The main parameters of the gas combustion device are shown in Table 1.

[0070] Table 1 Main parameters of the gas device

[0071] Parameter Name Parameter Value Combustion Chamber Diameter (mm) 32 Combustion Chamber Length (mm) 168 Nozzle Exit Diameter (mm) 10 Nozzle Throat Diameter (mm) 4.77 <![CDATA[Mach number M at the nozzle exit j > 2.7785

[0072] (5) The measurement of high-temperature gas jet parameters of the gas combustion device under the total pressure and flow rate parameters of the test was completed. The total pressure of the gas was collected by a pressure sensor arranged at the combustion chamber of the gas combustion device, the total temperature of the gas was collected by a thermocouple sensor arranged at the combustion chamber of the gas combustion device, and the component parameters of the gas were determined by gas chromatography after sampling with a gas sampling device arranged at the nozzle of the gas combustion device. Table 2 gives the data of the total temperature of the gas and the gas component parameters under the specified test total pressure and flow rate conditions, where the water vapor content was calculated according to the carbon monoxide and carbon dioxide contents in the components, so as to determine the molar content of each component in the high-temperature gas.

[0073] Table 2 Measurement results of high-temperature gas jet parameters under test total pressure and flow rate conditions

[0074]

[0075]

[0076] (6) Based on the test model, the generation of the computational grid for numerical calculation was completed. The incoming flow and jet conditions of the numerical calculation were set according to the actual wind tunnel operating conditions and the parameters in Table 2 respectively, and the numerical simulation of the test conditions was completed to obtain the numerical simulation results of the jet interference pressure distribution under the test conditions.

[0077] (7) Based on the flat plate shape and the methane / air gas device, a flat plate jet interference pressure measurement test model was designed. The measurement test of the thermal jet interference pressure distribution was completed in a supersonic wind tunnel under the conditions of a jet total pressure of 3.0 MPa and a mass flow rate of 50 g / s, and the typical point pressure data of the thermal jet interference on the flat plate surface were obtained. Based on the cone-cylinder-skirt axisymmetric body shape and the methane / air gas device, an axisymmetric body jet interference force measurement test model was designed. The thermal jet interference force measurement test was completed in a hypersonic wind tunnel under the conditions of a jet total pressure of 2.0 MPa and a mass flow rate of 280 g / s, and the test data of the thermal jet interference aerodynamic force / moment were obtained.

[0078] After completing the above experiments, the comparative analysis of the numerical simulation pressure distribution results and the test pressure distribution results can be carried out.

[0079] The unpublicized content of the present invention is common general knowledge in the art. Although the embodiments of the present invention have been disclosed as above, it is not limited to only the applications listed in the specification and the embodiments. It can be fully applied to various fields suitable for the present invention. For those familiar with the art, other modifications can be easily made. Therefore, without departing from the general concept defined by the claims and the equivalent scope, the present invention is not limited to the specific details and the illustrated examples here.

Claims

1. A lateral thermal jet interference wind tunnel test system, characterized in that It includes medium supply subsystem, gas combustion device and gas parameter calibration subsystem; A medium supply subsystem is used to provide oxidant gas and fuel gas to the fuel gas combustion device, and the total pressure and flow rate of the oxidant gas and fuel gas are adjustable; A gas combustion device, which mixes and burns the oxidant gas and the fuel gas to produce a fuel gas jet; The gas parameter calibration subsystem collects the total gas pressure, total gas temperature, samples the gas jet generated by the gas device, and analyzes and determines the component parameters of the gas.

2. A lateral thermal jet interference wind tunnel test system according to claim 1, characterized in that The medium supply subsystem includes an oxidant gas source, an oxidant gas pipeline, a fuel gas source, and a fuel gas pipeline; the oxidant gas source is connected to the fuel gas combustion device through the oxidant gas pipeline; the fuel gas source is connected to the fuel gas combustion device through the fuel gas pipeline; The oxidant gas pipeline is composed of an oxygen shut-off valve, a fuel gas filter, a first pressure sensor, a fuel gas mass flow meter, a fuel gas pressure reducing valve, and a second pressure sensor connected in sequence; The gas pipeline is composed of a gas shut-off valve, a gas filter, a third pressure sensor, a gas mass flow meter, a gas pressure reducing valve, and a fourth pressure sensor which are connected in sequence.

3. A lateral thermal jet interference wind tunnel test system according to claim 1, characterized in that The gas combustion device comprises an injector, a combustion chamber, an igniter and a nozzle; The injector includes fuel gas and oxidant gas inlet interfaces, as well as an outlet. The inlet section of the combustion chamber is coaxially connected to the outlet of the injector, and the outlet section is coaxially connected to the nozzle. The axes of the inlet section and the outlet section are perpendicular to each other to form an L shape. The igniter is installed on the side wall of the inlet section of the combustion chamber.

4. A lateral thermal jet interference wind tunnel test system according to claim 1, characterized in that The gas parameter calibration subsystem includes a fifth pressure sensor, a thermocouple sensor, and a gas sampling device; A fifth pressure sensor is arranged at the combustion chamber of the gas combustion device and is used to collect the total pressure of the gas. A thermocouple sensor is arranged at the combustion chamber of the gas combustion device and is used to collect the total temperature of the gas. The gas sampling device is arranged at the nozzle of the gas combustion device and is used to sample the gas jet ejected from the nozzle.

5. A lateral thermal jet interference wind tunnel test method based on the wind tunnel test system of claim 1, characterized in that The steps include: S1. Select gas as the jet test medium for the lateral thermal jet test; S2. Determine the thermal jet parameters of the wind tunnel test according to the lateral control engine jet parameters under the flight conditions of the aircraft to ensure that the wind tunnel test conditions and the typical jet interference similarity parameters under the flight conditions are the same; the thermal jet parameters of the wind tunnel test include the wind tunnel test scaled nozzle size, thermal jet total pressure and flow parameters; S3. Construct the lateral thermal jet interference wind tunnel test system as described in claim 1, and design the specific parameters of the gas combustion device according to the wind tunnel test scale nozzle size, thermal jet total pressure and mass flow rate, including the diameter of the combustion chamber, nozzle outlet diameter, nozzle throat diameter, and nozzle outlet Mach number; S4. Complete the measurement of the gas jet parameters of the gas combustion device under the total pressure and flow parameters of the test, and obtain the total temperature and gas component parameters of the gas under the specified test total pressure and flow conditions; S5. Generate a computational grid for numerical calculation based on the geometric parameters of the wind tunnel test model, perform numerical simulations with and without injection according to the wind tunnel operating conditions and the total temperature and gas component parameters of the gas under the specified test total pressure and flow conditions, and obtain the calculation results of the surface pressure distribution of the wind tunnel test model and the calculation results of the aerodynamic force and moment under the test conditions with and without injection; S6. Based on the size conditions of the gas combustion device and the numerical simulation results, the layout of the pressure measuring points and the balance load are determined, and the integrated design of the pressure measuring model-gas device and the integrated design of the force measuring model-gas device are completed to obtain the integrated structure of the pressure measuring model-gas device and the integrated structure of the force measuring model-gas device; S7. Using the pressure test method, based on the integrated structure of the pressure test model and the gas device, complete the hot jet interference wind tunnel pressure test under the specified test total pressure and flow conditions, and obtain the pressure distribution test results of the pressure measuring points on the test model surface under the conditions of no-spray and spray test conditions; Using the force measurement test method, based on the integrated structure of the force measurement model gas device, the thermal jet interference wind tunnel force measurement test under the specified test total pressure and flow conditions was completed, and the test results of the test model aerodynamic force and torque under the conditions of no-jet and with-jet test were obtained; S8. Compare and analyze the numerical simulation results with the experimental results.

6. A lateral thermal jet interference wind tunnel test method according to claim 5, characterized in that In step S1, the aircraft flight condition lateral control engine parameters include controlling the engine nozzle outlet diameter, throat diameter, outlet gas specific heat ratio, outlet Mach number, and combustion chamber total pressure.

7. A lateral thermal jet interference wind tunnel test method according to claim 5, characterized in that Similar parameters used in the thermal spray interference wind tunnel test are pressure ratio and momentum ratio.

8. A lateral thermal jet interference wind tunnel test method according to claim 5, characterized in that The wind tunnel test conditions and the flight conditions have the same jet flow interference similarity parameters, which means that the static pressure P at the nozzle outlet of the gas combustion device that meets the wind tunnel test conditions is 燃烧装置j The static pressure P of the wind tunnel flow 风洞∞ Ratio P 燃烧装置j / P 风洞∞ Equal to the static pressure P at the engine nozzle outlet under flight conditions 控制发动机j The static pressure P of the flow under flight conditions 飞行∞ Ratio P 控制发动机j / P 飞行∞ , the momentum M of the nozzle outlet of the gas combustion device under wind tunnel test conditions 燃烧装置j The wind tunnel flow momentum M 风洞∞ Ratio M 燃烧装置j / M 风洞∞ Equal to the flight condition control engine nozzle exit momentum M 控制发动机j The incoming momentum M under flight conditions 飞行∞ Ratio M 控制发动机 / M 飞行∞ .

9. A lateral thermal jet interference wind tunnel test method according to claim 5, characterized in that: The total temperature of the gas calibrated in the combustion chamber of the gas combustion device is determined by averaging the measured values ​​of two or more thermocouple sensors arranged at the inlet of the nozzle contraction section.

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