A continuously variable thrust jet interference wind tunnel test method and system

Abstract

The present disclosure provides a method and system for a continuously variable thrust jet interference wind tunnel test. The method includes: determining incoming flow conditions and test jet parameters; constructing a continuously variable thrust test system; conducting a low-pressure environment nozzle thrust calibration test on the continuously variable thrust test system; establishing a variable thrust jet force measurement test model; conducting a continuously variable thrust jet interference wind tunnel test, and obtaining jet interference wind tunnel test results for the variable thrust jet force measurement test model under continuously variable thrust conditions. The present disclosure, through the design and construction of 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, can achieve continuous thrust changes during the test process, complete data collection and test result acquisition for the jet interference wind tunnel test of the variable thrust jet force measurement test model under continuously variable thrust conditions, and conduct force measurement test research on the reverse jet interference effect of the main engine of continuously variable thrust aircraft such as reusable rockets.

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 continuously variable thrust jet interference wind tunnel testing. Background Art

[0002] Rocket engines generate high-temperature, high-pressure gases through fuel combustion, which are ejected at high speed through a nozzle to generate thrust. As the main engine, rocket engines are widely used in launch vehicles, deep space exploration, and various offensive and defensive missile applications. With the advancement of aerospace technology and the demands of modern warfare, the recovery process and re-entry trajectory change require rocket engines to have continuous thrust adjustment capabilities to achieve precise control of flight attitude and landing point. During the recovery flight of a rocket sub-stage, complex aerodynamic interference occurs between the main engine's reverse jet and the incoming flow, significantly changing the aerodynamic characteristics of the vehicle surface and generating additional interference forces / torques. Furthermore, the continuous thrust adjustment of the main engine during the recovery of a rocket sub-stage causes a strong interference flow field in the reverse jet, exhibiting significant unsteady characteristics. To achieve precise control, it is necessary to study the unsteady aerodynamic characteristics of the main engine under continuous thrust adjustment. Wind tunnel testing is an important technical approach to studying the aerodynamic interference characteristics of the reverse jet during continuous thrust adjustment of the main engine during rocket sub-stage recovery.

[0003] Currently, wind tunnel tests for measuring reverse jet flow during rocket stage recovery mostly use steady-state force measurement technology. This can only measure the aerodynamic characteristics of the reverse jet flow under fixed thrust conditions, but cannot measure the unsteady reverse jet flow aerodynamic characteristics induced by continuous thrust adjustment. Therefore, it is urgent to develop a jet flow force measurement test system and test method that can simulate the continuous thrust adjustment state of the rocket stage 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 solution: a continuously variable thrust jet interference wind tunnel test method, 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 continuously variable thrust test system based on the test jet parameters, the continuously variable thrust test system comprising at least: a continuously variable thrust jet generator, 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 generator under low-pressure environment conditions without incoming flow. A first correlation relationship between the total pressure of the jet and the jet flow rate of the jet control system is determined; 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. Under the incoming flow conditions, 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 results of the variable thrust jet force measurement test model under the continuously variable thrust conditions are obtained.

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

[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 includes 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 air 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 air circuit, wherein the high-pressure resistant air circuit is connected to the high-pressure air source near the upstream port of the shut-off valve, and the high-pressure resistant air 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 based on the first association relationship and the second association relationship, including: determining a target jet total pressure based on the nozzle thrust required for the current test and the first association relationship; determining the jet flow rate of the jet control system based on 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 includes 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 for implementing the jet interference wind tunnel test method as described above. 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 to 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 nozzle thrust and the jet flow rate obtained by calibration, the thrust can be continuously changed 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 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 following briefly introduces the drawings required for use in the embodiments or the description of the prior art. 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 any creative work.

[0017] Figure 1 This 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 This is a schematic structural diagram of a continuously variable thrust jet generating device in the first embodiment of the present disclosure;

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

[0020] Figure 4 Schematic diagram of the wind tunnel test of the 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 the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of this document.

[0022] Rocket engines generate high-temperature, high-pressure gases through fuel combustion, which are ejected at high speed through a nozzle to generate thrust. As the main engine, rocket engines are widely used in launch vehicles, deep space exploration, and various offensive and defensive missile applications. With the advancement of aerospace technology and the demands of modern warfare, the recovery process and re-entry trajectory change require rocket engines to have continuous thrust adjustment capabilities to achieve precise control of flight attitude and landing point. During the recovery flight of a rocket sub-stage, complex aerodynamic interference occurs between the main engine's reverse jet and the incoming flow, significantly changing the aerodynamic characteristics of the vehicle surface and generating additional interference forces / torques. Furthermore, the continuous thrust adjustment of the main engine during the recovery of a rocket sub-stage causes a strong interference flow field in the reverse jet, exhibiting significant unsteady characteristics. To achieve precise control, it is necessary to study the unsteady aerodynamic characteristics of the main engine under continuous thrust adjustment. Wind tunnel testing is an important technical approach to studying the aerodynamic interference characteristics of the reverse jet during continuous thrust adjustment of the main engine during rocket sub-stage recovery.

[0023] Currently, wind tunnel tests for measuring reverse jet flow during rocket stage recovery mostly use steady-state force measurement technology. This can only measure the aerodynamic characteristics of the reverse jet flow under fixed thrust conditions, but cannot measure the unsteady reverse jet flow aerodynamic characteristics induced by continuous thrust adjustment. Therefore, it is urgent to develop a jet flow force measurement test system and test method that can simulate the continuous thrust adjustment state of the rocket stage main engine.

[0024] In order to solve the above problems, the first embodiment of the present disclosure provides a continuously variable thrust jet interference wind tunnel test method, the flow chart of which 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 accuracy of the jet interference wind tunnel test is to ensure that the pressure ratio and momentum ratio under 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 and wind tunnel inflow static pressure P 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 and wind tunnel incoming 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 the wind tunnel test must be carried out 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 include at least the incoming flow Mach number and flight altitude; the test jet parameters include at least the nozzle profile parameters, the nozzle outlet gas specific heat ratio, the nozzle outlet Mach number, and the time-varying curve of the total pressure in the combustion chamber. It should be understood that other incoming flow conditions and test jet parameters may be used based on actual needs and are not specifically limited in this embodiment, as long as the test is reasonable and meets the test requirements.

[0029] S20: Construct a continuously variable thrust test system based on the test jet parameters.

[0030] Based on 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 includes at least a continuously variable thrust jet generator, a jet control system, and a dynamic force measurement and acquisition system. The continuously variable thrust jet generator is primarily used to simulate an engine to generate jet output, the jet control system is primarily used to control the jet flow rate of the continuously variable thrust jet generator, and the dynamic force measurement and acquisition system is used to collect aerodynamic characteristics during wind tunnel testing.

[0031] Specifically, Figure 2 The schematic diagram of the structure of the continuously variable thrust jet generator in this embodiment is shown, 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 continuously variable thrust jet generating device is selected according to the test jet parameters. When the pressure sensor is set on the inner wall of the storage chamber, it should be set at one end close to the Laval nozzle and at a certain distance from the end of the storage chamber on that 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 every 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 gas circuit and a stop valve, a pressure reducing valve, an air pressure sensor, a flow regulating valve and a flow sensor arranged in sequence on the high-pressure gas circuit, wherein the high-pressure 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 line is close to the downstream port of the flow sensor ( Figure 3 The right side of the middle chamber is connected to the other end of the storage chamber, which corresponds to Figure 2 The high-pressure gas line connected to the right side of the central storage chamber. During actual use, the shutoff valve is open, and the high-pressure gas output from the high-pressure gas source is reduced in pressure by the pressure reducing valve. The pressure sensor detects the pressure of the gas after the pressure reduction valve is used. If the pressure is too high, the pressure reducing valve is further adjusted to ensure that the pressure after the pressure reduction meets the adjustment range of the downstream flow control valve. The flow control valve and flow sensor are used to adjust the jet flow output to the storage chamber according to control requirements to meet the nozzle thrust requirements of the continuously variable thrust jet generator.

[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 includes at least a dynamic force measurement balance and an acquisition system. It 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 during the wind tunnel test, so as to facilitate the subsequent output of the 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 between the nozzle thrust of the continuously variable thrust jet generating device and the total jet pressure, and a second correlation between the total jet pressure and the jet flow rate of the jet control system under low-pressure environment and no incoming flow conditions.

[0036] Once the continuously variable thrust test system is constructed, it can be subjected to low-pressure, no-flow conditions to perform low-pressure nozzle thrust calibration tests. This will determine the relationships between the various components of the continuously variable thrust test system, including: a first relationship between the nozzle thrust of the continuously variable thrust jet generator and the total jet pressure within the reservoir, and a second relationship between the total jet pressure and the jet flow rate of the jet control system. The jet flow rate is adjusted based on the opening of the flow control valve and detected and collected by the flow sensor. In practice, through low-pressure nozzle thrust calibration tests, the relationship between nozzle flow rate and nozzle thrust is established using the total jet pressure within the reservoir as an intermediate parameter. When continuous thrust changes are required in subsequent tests, this can be achieved by adjusting the opening of the flow control valve accordingly, thus achieving a continuously variable thrust test simulation.

[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: Establish a variable thrust jet force measurement test model based on the wind tunnel blockage requirements 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, conducting a continuous variable thrust jet interference wind tunnel test, achieving continuous variation 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 incoming flow conditions, and obtaining jet interference wind tunnel test results of the variable thrust jet dynamometer test model under the continuously variable thrust condition.

[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, such as Figure 4 Specifically, under the incoming flow conditions of the jet interference wind tunnel test, according to the thrust change requirements of the test, based on 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 aerodynamic force of the variable thrust jet dynamometer test model is continuously collected using a dynamic force measurement and acquisition system to obtain the jet interference wind tunnel test results of the variable thrust jet dynamometer test model under continuously variable thrust conditions.

[0042] During actual variable thrust adjustment, the target total jet pressure can be determined based on the nozzle thrust required for the current test and the first correlation. Subsequently, the jet flow rate of the jet control system is determined based on the target total jet pressure, the second correlation, and the current total jet pressure collected by the pressure sensor. The jet flow rate is then output by adjusting the opening of the flow control valve. It should be noted that the jet control system should include a control unit for controlling the opening of the corresponding valve based on the parameters collected by various sensors.

[0043] This embodiment provides a continuously variable thrust jet interference wind tunnel test method. 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, continuous thrust variation can be achieved during the test process. Data collection and test result acquisition of the jet interference wind tunnel test of a variable thrust jet force measurement test model under continuously variable thrust conditions are completed, and force measurement test research is carried out for the reverse jet interference effect of the main engine of continuously variable thrust aircraft such as reusable 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, and is used 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 make 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] This embodiment provides a continuously variable thrust jet interference wind tunnel test system. 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, continuous thrust variation can be achieved during the test process. Data collection and test result acquisition of the jet interference wind tunnel test of a variable thrust jet force measurement test model under continuously variable thrust conditions are completed, and force measurement test research is carried out for the reverse jet interference effect of the main engine of continuously variable thrust aircraft such as reusable 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 with 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 continuously variable thrust jet interference wind tunnel test method, characterized in that: include: Based on actual flight conditions, simulation criteria for jet interference wind tunnel tests, and variable thrust engine jet parameters, determine the incoming flow conditions and test jet parameters for the jet interference wind tunnel test. According to the test jet parameters, a continuously variable thrust test system is constructed, wherein the continuously variable thrust test system comprises at least: a continuously variable thrust jet generating device, a jet control system, and a dynamic force measurement and acquisition system; Conducting a low-pressure environment nozzle thrust calibration test on the continuously variable thrust test system to obtain a first correlation between the nozzle thrust of the continuously variable thrust jet generating device and the total jet pressure, and a second correlation between the total jet pressure and the jet flow rate of the jet control system under low-pressure environment and no incoming flow conditions; According to the wind tunnel blockage requirement and the structural design of the continuously variable thrust jet generator, 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 conditions, 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 results of the variable thrust jet dynamometer test model under the continuously variable thrust conditions are 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 that meets the flight conditions to the static pressure of the inflow under the flight conditions; The ratio of the nozzle outlet momentum that meets the wind tunnel test conditions to the wind tunnel incoming momentum is equal to the ratio of the nozzle outlet momentum of the flight condition control engine to the flight condition incoming momentum.

3. The jet flow interference wind tunnel test method according to claim 1, characterized in that: 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 a curve of total pressure of the combustion chamber changing with time.

4. The jet flow interference wind tunnel test method according to claim 1, characterized in that: 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 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 air 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 air circuit, wherein the high-pressure resistant air circuit is connected to the high-pressure air source near the upstream port of the shut-off valve, and the high-pressure resistant air circuit is connected to the other end of the storage chamber near the downstream port of the flow sensor.

7. The jet flow 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 flow 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 based on 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 control 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 is 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: For implementing 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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