Jet flow interference wind tunnel test method and system with continuously variable thrust

Abstract

The invention provides a continuous variable thrust jet flow interference wind tunnel test method and system. The method comprises the following steps: determining incoming flow conditions and test jet flow parameters; constructing a continuous variable thrust test system; performing a low-pressure environment spray pipe thrust calibration test on the continuous variable thrust test system; establishing a variable thrust jet flow force measurement test model; and carrying out a continuous variable thrust jet flow interference wind tunnel test to obtain a jet flow interference wind tunnel test result of the variable thrust jet flow force measurement test model under the continuous variable thrust condition. According to the invention, through the design and construction of the continuous variable thrust jet flow generation device and the jet flow control system, the correlation between the thrust of the nozzle and the jet flow obtained through calibration is combined, so that the continuous change of the thrust can be realized in the test process; data acquisition and test result acquisition of the jet flow interference wind tunnel test of the variable thrust jet flow force measurement test model under the continuous variable thrust condition are completed, and force measurement test research is carried out on the reverse jet flow interference effect of a main engine of a recoverable rocket and other continuous variable thrust aircrafts.

Description

Technical Field

[0001] The present disclosure relates to the technical field of wind tunnel testing, and in particular to a method and system for a jet interference wind tunnel test with continuously variable thrust. Background Art

[0002] Rocket engines generate high-temperature and high-pressure gas through fuel combustion, which is ejected at high speed through the nozzle to generate thrust. As the main engine, rocket engines are widely used in scenarios such as carrier rocket launches, deep space exploration, and various offensive and defensive missiles. With the development of aerospace technology and modern military combat needs, the recovery process requires rocket engines to have the ability to continuously adjust thrust to achieve the purpose of controlling flight attitude and precise control of landing points. During the recovery flight of the rocket sub-stage, complex aerodynamic interference occurs between the reverse jet of the main engine and the incoming flow, which significantly changes the aerodynamic characteristics of the aircraft surface and generates additional interference forces / torques. In addition, during the recovery process of the rocket sub-stage, due to the continuous adjustment of the thrust of the main engine, the strong interference flow field of the reverse jet caused by the continuous adjustment of the thrust of the main engine presents significant unsteady characteristics. In order to achieve precise control, it is necessary to carry out research on the unsteady aerodynamic characteristics of the main engine under the state of continuous thrust adjustment. Wind tunnel testing is an important technical approach to study the aerodynamic interference characteristics of the reverse jet of the continuous thrust adjustment of the main engine of the rocket sub-stage recovery.

[0003] At present, most wind tunnel tests for reverse jet interference force measurement of rocket substage recovery use steady-state force measurement test technology, which can only measure the aerodynamic characteristics of reverse jet interference of rocket substage under fixed thrust conditions, but cannot measure the unsteady reverse jet aerodynamic interference characteristics induced by continuous thrust adjustment. In view of this, it is urgent to develop a jet force measurement test system and test method for simulating the continuous thrust adjustment state of the rocket substage main engine. Summary of the invention

[0004] The purpose of the embodiments disclosed herein is to provide a continuously variable thrust jet interference wind tunnel test method and system to solve the problem in the prior art that it is impossible to perform continuously variable thrust jet interference aerodynamic characteristics of rocket sub-stages.

[0005] The embodiment of the present disclosure adopts the following technical scheme: a jet interference wind tunnel test method of continuous variable thrust, comprising: determining the incoming flow conditions and test jet parameters of the jet interference wind tunnel test based on actual flight conditions, jet interference wind tunnel test simulation criteria and variable thrust engine jet parameters; constructing a continuous variable thrust test system according to the test jet parameters, the continuous variable thrust test system at least comprising: a continuously variable thrust jet generating device, a jet control system and a dynamic force measurement and acquisition system; performing a low-pressure environment nozzle thrust calibration test on the continuously variable thrust test system to obtain the nozzle thrust and jet flow of the continuously variable thrust jet generating device under low-pressure environment without incoming flow conditions. a first correlation relationship between the total pressure of the jet and the jet flow rate of the jet control system; a variable thrust jet force measurement test model is established according to the wind tunnel blockage requirement and the structural design of the continuously variable thrust jet generating device; the variable thrust jet force measurement test model is arranged in a wind tunnel, and a continuous variable thrust jet interference wind tunnel test is carried out, and under the incoming flow condition, according to the first correlation relationship and the second correlation relationship, the nozzle thrust of the variable thrust jet force measurement test model is continuously changed by controlling the jet flow rate, and the jet interference wind tunnel test result of the variable thrust jet force measurement test model under the continuously variable thrust condition is obtained.

[0006] The jet interference wind tunnel test simulation criteria at least include: the ratio of the variable thrust nozzle outlet static pressure that meets the wind tunnel test conditions to the wind tunnel incoming flow static pressure is equal to the ratio of the flight condition engine nozzle outlet static pressure to the flight condition incoming flow static pressure; the ratio of the nozzle outlet momentum that meets the wind tunnel test conditions to the wind tunnel incoming flow momentum is equal to the ratio of the flight condition control engine nozzle outlet momentum to the flight condition incoming flow momentum.

[0007] In some embodiments, the incoming flow conditions include at least: incoming flow Mach number and flight altitude; the test jet parameters include at least: nozzle profile parameters, nozzle outlet gas specific heat ratio, nozzle outlet Mach number, and combustion chamber total pressure change curve over time.

[0008] In some embodiments, the continuously variable thrust jet generating device comprises at least: a storage chamber, a Laval nozzle and a pressure sensor; wherein the convergent section of the Laval nozzle is connected to one end of the storage chamber, and the pressure sensor is arranged on the inner wall of the storage chamber to measure the total pressure of the jet of the variable thrust jet generating device.

[0009] In some embodiments, the number of the pressure sensors is N, where N is an integer greater than or equal to 2, all the pressure sensors are evenly distributed radially on the inner wall of the storage chamber, and the average pressure value of all the pressure sensors is used as the total pressure of the jet.

[0010] In some embodiments, the jet control system includes at least: a high-pressure resistant gas circuit and a shut-off valve, a pressure reducing valve, an air pressure sensor, a flow regulating valve and a flow sensor arranged in sequence on the high-pressure resistant gas circuit, wherein the high-pressure resistant gas circuit is connected to a high-pressure gas source near the upstream port of the shut-off valve, and the high-pressure resistant gas circuit is connected to the other end of the storage chamber near the downstream port of the flow sensor.

[0011] In some embodiments, the high pressure gas source is air at room temperature.

[0012] In some embodiments, the continuous change of the nozzle thrust of the variable thrust jet force measurement test model is achieved by controlling the jet flow rate according to the first association relationship and the second association relationship, including: determining a target jet total pressure according to the nozzle thrust required for the current test and the first association relationship; determining the jet flow rate of the jet control system according to the target jet total pressure, the second association relationship and the current jet total pressure collected by the pressure sensor, and achieving the output of the jet flow rate by adjusting the opening of the flow control valve.

[0013] In some embodiments, the dynamic force measurement and acquisition system comprises at least: a dynamic force measurement balance and an acquisition system for continuously acquiring the aerodynamic force of the variable thrust jet force measurement test model.

[0014] This embodiment also provides a continuously variable thrust jet interference wind tunnel test system, which is used to implement the jet interference wind tunnel test method as described above, and the jet interference wind tunnel test system at least includes: a wind tunnel; a variable thrust jet force measurement test model; and a host computer, wherein the host computer is communicatively connected with the jet control system and the dynamic force measurement and acquisition system.

[0015] The beneficial effects of the embodiments of the present disclosure are: providing a jet interference wind tunnel test method with continuously variable thrust, by designing and constructing a continuously variable thrust jet generating device and a jet control system, combined with the correlation between the calibrated nozzle thrust and the jet flow rate, a continuous change of thrust can be achieved during the test, and data collection and test result acquisition of the jet interference wind tunnel test of the variable thrust jet force measurement test model under continuously variable thrust conditions are completed, so as to carry out force measurement test research on the reverse jet interference effect of the main engine of continuously variable thrust aircraft such as recoverable rockets. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] 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.

[0017] Figure 1 It is a flow chart of the jet interference wind tunnel test method with continuously variable thrust in the first embodiment of the present disclosure;

[0018] Figure 2 It is a schematic structural diagram of a continuously variable thrust jet generating device in the first embodiment of the present disclosure;

[0019] Figure 3 It is a schematic structural diagram of a jet flow control system in the first embodiment of the present disclosure;

[0020] Figure 4 Schematic diagram of a wind tunnel test of a continuously variable thrust jet interference in the first embodiment of the present disclosure. DETAILED DESCRIPTION

[0021] In order to enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the technical solutions in one or more embodiments of this specification will be clearly and completely described below in conjunction with the drawings in one or more embodiments of this specification. Obviously, the described embodiments are only part of the embodiments of this specification, not all of them. 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.

[0022] Rocket engines generate high-temperature and high-pressure gas through fuel combustion, which is ejected at high speed through the nozzle to generate thrust. As the main engine, rocket engines are widely used in scenarios such as carrier rocket launches, deep space exploration, and various offensive and defensive missiles. With the development of aerospace technology and modern military combat needs, the recovery process requires rocket engines to have the ability to continuously adjust thrust to achieve the purpose of controlling flight attitude and precise control of landing points. During the recovery flight of the rocket sub-stage, complex aerodynamic interference occurs between the reverse jet of the main engine and the incoming flow, which significantly changes the aerodynamic characteristics of the aircraft surface and generates additional interference forces / torques. In addition, during the recovery process of the rocket sub-stage, due to the continuous adjustment of the thrust of the main engine, the strong interference flow field of the reverse jet caused by the continuous adjustment of the thrust of the main engine presents significant unsteady characteristics. In order to achieve precise control, it is necessary to carry out research on the unsteady aerodynamic characteristics of the main engine under the state of continuous thrust adjustment. Wind tunnel testing is an important technical approach to study the aerodynamic interference characteristics of the reverse jet of the continuous thrust adjustment of the main engine of the rocket sub-stage recovery.

[0023] At present, most wind tunnel tests for reverse jet interference force measurement of rocket substage recovery use steady-state force measurement test technology, which can only measure the aerodynamic characteristics of reverse jet interference of rocket substage under fixed thrust conditions, but cannot measure the unsteady reverse jet aerodynamic interference characteristics induced by continuous thrust adjustment. In view of this, it is urgent to develop a jet force measurement test system and test method for simulating the continuous thrust adjustment state of the rocket substage main engine.

[0024] In order to solve the above problems, the first embodiment of the present disclosure provides a jet flow interference wind tunnel test method with continuously variable thrust, and the flow chart thereof is as follows: Figure 1 As shown, it mainly includes steps S10 to S50:

[0025] S10, determining the incoming flow conditions and test jet parameters of the jet interference wind tunnel test based on actual flight conditions, simulation criteria for the jet interference wind tunnel test, and variable thrust engine jet parameters.

[0026] Specifically, the simulation standard of the jet interference wind tunnel test is to ensure that the pressure ratio and momentum ratio of the ground and flight conditions are similar. In this embodiment, it mainly refers to the following two conditions: (1) the static pressure P of the variable thrust nozzle outlet that meets the wind tunnel test conditions 试验喷管j The static pressure P of the wind tunnel flow 风洞∞ Ratio P 试验喷管j / P 风洞∞ Equal to the static pressure P at the engine nozzle outlet under flight conditions 飞行喷管j The static pressure P of the flow under flight conditions 飞行∞ Ratio P 飞行喷管j / P 飞行∞ ; (2) Nozzle exit momentum M that meets wind tunnel test conditions 试验喷管j The wind tunnel flow momentum M 风洞∞ Ratio M 试验喷管j / M 风洞∞ Equal to the flight condition control engine nozzle exit momentum M 飞行喷管j The incoming momentum M under flight conditions 飞行∞ Ratio M 飞行喷管 / M 飞行∞ .

[0027] The actual flight conditions are the conditions set according to the actual usage scenarios and flight requirements of the aircraft. The variable thrust engine jet parameters refer to the equipment parameters of the variable thrust engine of the physical aircraft. By combining them with the jet interference wind tunnel test simulation criteria, the test incoming flow conditions and test jet parameters in the wind tunnel test environment can be obtained. That is, the test system constructed by the test needs to meet the test jet parameters and conduct wind tunnel tests under the above-mentioned incoming flow conditions to simulate the jet conditions of the variable thrust engine under actual flight conditions.

[0028] In this embodiment, the incoming flow conditions at least include: incoming flow Mach number and flight altitude; the test jet parameters at least include: nozzle profile parameters, nozzle outlet gas specific heat ratio, nozzle outlet Mach number, and combustion chamber total pressure change curve over time. It should be understood that other incoming flow conditions and test jet parameters can also be used according to actual needs. This embodiment does not impose specific restrictions, as long as the test rationality is guaranteed and the test requirements are met.

[0029] S20: construct a continuously variable thrust test system according to the test jet parameters.

[0030] According to the test jet parameters, a continuously variable thrust test system is constructed to achieve continuously variable thrust output. The continuously variable thrust test system of this embodiment at least includes: a continuously variable thrust jet generator, a jet control system, and a dynamic force measurement and acquisition system, wherein the continuously variable thrust jet generator is mainly used to simulate the engine to output the jet, the jet control system is mainly used to control the jet flow of the continuously variable thrust jet generator, and the dynamic force measurement and acquisition system is used to collect aerodynamic characteristics during the wind tunnel test.

[0031] Specifically, Figure 2 FIG. 1 shows a schematic diagram of the structure of the continuously variable thrust jet generator in this embodiment, which mainly includes: a storage chamber, a Laval nozzle and a pressure sensor. Figure 2 As shown, the convergent section of the Laval nozzle is connected to one end of the storage chamber, and the pressure sensor is arranged on the inner wall of the storage chamber to measure the total jet pressure of the variable thrust jet generating device. The specific model or size of the storage chamber and the Laval nozzle in the continuous variable thrust jet generating device is selected according to the test jet parameters. When the pressure sensor is arranged on the inner wall of the storage chamber, it should be arranged at one end close to the Laval nozzle and have a certain distance from the end of the storage chamber on this side to accurately measure the jet pressure inside the storage chamber. In some embodiments, the number of pressure sensors can be set to N, and N is a positive number greater than or equal to 2, that is, by arranging multiple pressure sensors and using the average pressure value of all pressure sensors as the total jet pressure to improve the accuracy of pressure detection, it is beneficial to improve the accuracy of subsequent variable thrust control. It should be noted that the multiple pressure sensors should be evenly distributed radially on the inner wall of the storage chamber, such as Figure 2 The two pressure sensors shown should be symmetrically distributed on the inner wall of the storage chamber. If the number of pressure sensors is 3, one pressure sensor can be set at an interval of 120° in the radial direction of the storage chamber.

[0032] Figure 3 The schematic diagram of the structure of the jet control system in this embodiment is shown, which mainly includes: a high-pressure resistant gas circuit and a stop valve, a pressure reducing valve, a pressure sensor, a flow regulating valve and a flow sensor arranged in sequence on the high-pressure resistant gas circuit, wherein the high-pressure resistant gas circuit is close to the upstream port of the stop valve ( Figure 3 The left side of the middle part) is connected to the high-pressure gas source, and the high-pressure gas path is close to the downstream port of the flow sensor ( Figure 3 The right side of the middle part) is connected to the other end of the storage chamber, that is, corresponding to Figure 2 The high-pressure gas circuit connected to the right side of the middle storage chamber. In actual use, the stop valve is opened, and the high-pressure gas output by the high-pressure gas source is reduced in pressure through the pressure reducing valve. The air pressure sensor is used to detect the gas pressure after the pressure reducing valve is reduced in pressure, and further adjust the pressure reducing valve when the air pressure is too high so that the gas pressure after the pressure reduction meets the adjustment range of the downstream flow regulating valve. The flow regulating valve and the flow sensor are used to adjust the jet flow output to the storage chamber according to the control requirements to meet the nozzle thrust requirements of the continuously variable thrust jet generating device.

[0033] In actual implementation, the high-pressure gas source is room temperature air to simulate the high-temperature combustion gas of an actual engine.

[0034] The dynamic force measurement and acquisition system at least includes a dynamic force measurement balance and an acquisition system, which can be directly implemented using a conventional dynamic force measurement and acquisition system. It is mainly used to continuously acquire the aerodynamic force of the test model in a wind tunnel test, so as to facilitate the subsequent output of aerodynamic / torque wind tunnel test results based on the acquired aerodynamic data.

[0035] S30, performing a low-pressure environment nozzle thrust calibration test on the continuously variable thrust test system to obtain a first correlation relationship between the nozzle thrust of the continuously variable thrust jet generating device and the jet total pressure under low-pressure environment and no incoming flow conditions, and a second correlation relationship between the jet total pressure and the jet flow rate of the jet control system.

[0036] After the continuous variable thrust test system is built, it can be subjected to a low-pressure environment nozzle thrust calibration test under low-pressure and no-flow conditions to determine the correlation between the various links in the continuous variable thrust test system, including: the first correlation between the nozzle thrust of the continuous variable thrust jet generating device and the total jet pressure in the storage chamber, and the second correlation between the total jet pressure and the jet flow of the jet control system, wherein the jet flow is adjusted based on the opening of the flow control valve and detected and collected based on the flow sensor. In fact, through the low-pressure environment nozzle thrust calibration test, the total jet pressure in the storage chamber is used as an intermediate parameter to correlate the nozzle flow and the nozzle thrust. When the thrust needs to be continuously changed in subsequent tests, it can be carried out by adjusting the opening of the corresponding flow valve to achieve the test simulation of the continuous variable thrust.

[0037] In some embodiments, the first correlation relationship and the second correlation relationship may be presented in the form of a change curve, or by fitting corresponding functions.

[0038] S40, a variable thrust jet force measurement test model is established according to the wind tunnel blockage requirement and the structural design of the continuously variable thrust jet generating device.

[0039] The variable thrust jet dynamometer test model is a scaled rocket sub-stage model, that is, a model used for wind tunnel tests. When designing and implementing this model, it should be set in combination with the wind tunnel size and wind tunnel blockage requirements. At the same time, the structural design of the continuously variable thrust jet generating device needs to be implemented in the variable thrust jet dynamometer test model to achieve continuously variable thrust output.

[0040] S50, arranging the variable thrust jet dynamometer test model in a wind tunnel, carrying out a continuous variable thrust jet interference wind tunnel test, and achieving continuous change of the nozzle thrust of the variable thrust jet dynamometer test model by controlling the jet flow rate according to the first correlation relationship and the second correlation relationship under the incoming flow condition, and obtaining the jet interference wind tunnel test result of the variable thrust jet dynamometer test model under the condition of continuously variable thrust.

[0041] After the variable thrust jet force measurement test model is established, it can be placed in the wind tunnel to carry out the continuous variable thrust jet interference wind tunnel test. Figure 4 Specifically, under the incoming flow condition of the jet interference wind tunnel test, according to the thrust change requirement required by the test, based on the first correlation relationship and the second correlation relationship, the nozzle thrust of the variable thrust jet force measurement test model is continuously changed by controlling the jet flow rate, and the aerodynamic force of the variable thrust jet force measurement test model is continuously collected by using the dynamic force measurement and acquisition system, so as to obtain the jet interference wind tunnel test results of the variable thrust jet force measurement test model under the condition of continuous variable thrust.

[0042] When variable thrust adjustment is actually performed, the target jet total pressure can be determined according to the nozzle thrust required for the current test and the first correlation, and then the jet flow rate of the jet control system is determined according to the target jet total pressure, the second correlation, and the current jet total pressure collected by the pressure sensor, and the output of the jet flow rate is achieved by adjusting the opening of the flow control valve. It should be noted that the jet control system should have a control unit for controlling the opening of the corresponding valve according to the parameters collected by various sensors.

[0043] The present embodiment provides a jet interference wind tunnel test method for continuously variable thrust. By designing and constructing a continuously variable thrust jet generating device and a jet control system, combined with the correlation between the nozzle thrust and the jet flow rate obtained by calibration, the continuous change of thrust can be achieved during the test, and the data collection and test result acquisition of the jet interference wind tunnel test of the variable thrust jet force measurement test model under the condition of continuously variable thrust are completed, so as to carry out force measurement test research on the reverse jet interference effect of the main engine of continuously variable thrust aircraft such as recoverable rockets.

[0044] Based on the same inventive concept, the second embodiment of the present disclosure provides a continuously variable thrust jet interference wind tunnel test system, which is mainly used to implement the jet interference wind tunnel test method of the first embodiment of the present disclosure. The jet interference wind tunnel test system at least includes: a wind tunnel for conducting the test; a variable thrust jet force measurement test model established in the first embodiment of the present disclosure, the variable thrust jet force measurement test model can be fixed in the wind tunnel by an angle of attack mechanism, and the wind tunnel is started in combination with the incoming flow conditions determined in the first embodiment to carry out a continuously variable thrust jet interference wind tunnel test. During the test, the nozzle thrust of the continuously variable thrust jet generating device can be adjusted by the jet control system. When the variable thrust adjustment is actually performed, the nozzle thrust required for the current test and the first correlation relationship can be determined. The target jet total pressure is then determined, and the jet flow rate of the jet control system is determined according to the target jet total pressure, the second correlation relationship and the current jet total pressure collected by the pressure sensor, and the output of the jet flow rate is achieved by adjusting the opening of the flow control valve; the jet interference wind tunnel test system also includes a host computer, which can be communicated with the jet control system and the dynamic force measurement and acquisition system to issue corresponding thrust adjustment instructions to the jet control system, and obtain the aerodynamic conditions collected by the dynamic force measurement and acquisition system, and finally output the aerodynamic / torque wind tunnel test results; the host computer can also be used to adjust the angle of attack mechanism and the wind tunnel settings, and can also perform other settings required in the test process, and can provide an operation interface for operators to perform real-time control and view test results.

[0045] The present embodiment provides a jet interference wind tunnel test system with continuously variable thrust. By designing and constructing a continuously variable thrust jet generating device and a jet control system, combined with the correlation between the nozzle thrust and the jet flow rate obtained by calibration, continuous change of thrust can be achieved during the test, and data collection and test result acquisition of the jet interference wind tunnel test of the variable thrust jet force measurement test model under the condition of continuously variable thrust are completed, so as to carry out force measurement test research on the reverse jet interference effect of the main engine of continuously variable thrust aircraft such as recoverable rockets.

[0046] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present disclosure, rather than to limit them. Although the present disclosure has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein by equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present disclosure.

Claims

1. A jet flow interference wind tunnel test method with continuously variable thrust, characterized in that: include: Based on actual flight conditions, simulation criteria for jet interference wind tunnel tests, and variable thrust engine jet parameters, the incoming flow conditions and test jet parameters for the jet interference wind tunnel test are determined; According to the test jet parameters, a continuously variable thrust test system is constructed, wherein the continuously variable thrust test system at least comprises: a continuously variable thrust jet generating device, a jet control system, and a dynamic force measurement and acquisition system; A low-pressure environment nozzle thrust calibration test is performed on the continuously variable thrust test system to obtain a first correlation relationship between the nozzle thrust of the continuously variable thrust jet generating device and the jet total pressure under a low-pressure environment without incoming flow, and a second correlation relationship between the jet total pressure and the jet flow rate of the jet control system; According to the wind tunnel blockage requirement and the structural design of the continuously variable thrust jet generating device, a variable thrust jet force measurement test model is established; The variable thrust jet dynamometer test model is arranged in a wind tunnel, and a continuous variable thrust jet interference wind tunnel test is carried out. Under the incoming flow condition, according to the first correlation relationship and the second correlation relationship, the nozzle thrust of the variable thrust jet dynamometer test model is continuously changed by controlling the jet flow rate, and the jet interference wind tunnel test result of the variable thrust jet dynamometer test model under the continuously variable thrust condition is obtained.

2. The jet interference wind tunnel test method according to claim 1, characterized in that: The simulation criteria for the jet interference wind tunnel test at least include: The ratio of the static pressure at the variable thrust nozzle outlet that meets the wind tunnel test conditions to the static pressure of the wind tunnel inflow is equal to the ratio of the static pressure at the engine nozzle outlet under flight conditions to the static pressure of the inflow under flight conditions; The ratio of the nozzle exit momentum that meets the wind tunnel test conditions to the wind tunnel incoming momentum is equal to the ratio of the nozzle exit momentum of the flight condition control engine to the flight condition incoming momentum.

3. The jet interference wind tunnel test method according to claim 1, characterized in that: The incoming flow conditions at least include: incoming flow Mach number and flight altitude; The test jet parameters at least include: nozzle profile parameters, nozzle outlet gas specific heat ratio, nozzle outlet Mach number, and a curve of total pressure of the combustion chamber changing with time.

4. The jet interference wind tunnel test method according to claim 1, characterized in that: The continuously variable thrust jet generating device at least comprises: a storage chamber, a Laval nozzle and a pressure sensor; wherein, The convergent section of the Laval nozzle is communicated with one end of the storage chamber, and the pressure sensor is arranged on the inner wall of the storage chamber to measure the total pressure of the jet of the variable thrust jet generating device.

5. The jet interference wind tunnel test method according to claim 4, characterized in that: The number of the pressure sensors is N, where N is an integer greater than or equal to 2. All the pressure sensors are evenly distributed radially on the inner wall of the storage chamber, and the average pressure value of all the pressure sensors is used as the total pressure of the jet.

6. The jet interference wind tunnel test method according to claim 4, characterized in that: The jet control system includes at least: a high-pressure resistant gas circuit and a shut-off valve, a pressure reducing valve, an air pressure sensor, a flow regulating valve and a flow sensor arranged in sequence on the high-pressure resistant gas circuit, wherein the high-pressure resistant gas circuit is connected to a high-pressure gas source near the upstream port of the shut-off valve, and the high-pressure resistant gas circuit is connected to the other end of the storage chamber near the downstream port of the flow sensor.

7. The jet interference wind tunnel test method according to claim 6, characterized in that: The high-pressure gas source is air at room temperature.

8. The jet interference wind tunnel test method according to claim 6, characterized in that: The method of achieving continuous change of the nozzle thrust of the variable thrust jet force measurement test model by controlling the jet flow rate according to the first association relationship and the second association relationship includes: determining a target jet total pressure according to the nozzle thrust required for the current test and the first correlation relationship; The jet flow rate of the jet control system is determined according to the target jet total pressure, the second association relationship and the current jet total pressure collected by the pressure sensor, and the output of the jet flow rate is achieved by adjusting the opening of the flow regulating valve.

9. The jet interference wind tunnel test method according to any one of claims 1 to 8, characterized in that: The dynamic force measurement and acquisition system at least includes: a dynamic force measurement balance and an acquisition system, which are used to continuously acquire the aerodynamic force of the variable thrust jet force measurement test model.

10. A continuously variable thrust jet interference wind tunnel test system, characterized in that: Used to implement the jet interference wind tunnel test method according to any one of claims 1 to 9, the jet interference wind tunnel test system at least comprises: Wind tunnel; Variable thrust jet force measurement test model; A host computer is communicatively connected with the jet control system and the dynamic force measurement and acquisition system.

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