Heat flow control system for coupling test of solid rocket engine

Abstract

The invention provides a heat flow control system for a solid rocket engine test. A silicon controlled rectifier control power supply in the heating module supplies power to the heater. The silicon controlled rectifier trigger board triggers the silicon controlled rectifier to control the heater. The heat flux and temperature sensor transmits a detected heat flux signal and a detected temperature signal of the heater to the data acquisition module. The upper computer reads heat flux density and temperature data from the data acquisition module, and performs closed-loop control on heat flux density and temperature parameters. And the signal output module converts the heating control signal into an analog signal for controlling the silicon controlled trigger board. The heater comprises two layers of quartz lamps, lamp tubes are arranged in a staggered and parallel mode, and the upper computer judges a heat flux density value and can output selected heater arrangement parameters meeting requirements. According to the invention, the optimal heater arrangement parameters can be selected according to different heating temperature requirements before the test, so that the thermal control requirements of the solid rocket engine thermal environment simulation test bed on radiation heat flow distribution and large heating power are met.

Description

Technical Field

[0001] The invention belongs to the technical field of thermal environment simulation of solid rocket engines, and in particular relates to a thermal flow control system for solid rocket engine tests. Background Art

[0002] As the flight speed of solid rockets continues to increase, their engines are subjected to harsh aerodynamic thermal environments when flying at high speeds in the atmosphere. The aerodynamic heating problem of solid rocket engine casings will become more serious. The various properties of steel and composite materials used as engine casings will degrade under the action of aerodynamic heating. Therefore, the need to conduct aerodynamic thermal analysis of solid rocket engine casings and corresponding thermal protection research is becoming more urgent.

[0003] At present, there are two ways to study the aerodynamic heating of engines. One is airflow heating, which mainly has two test methods, namely flight test and ground wind tunnel test; the other is radiation heating. Flight test is costly, the number of flights is limited, the test data is small, and in practice, the measuring instruments inevitably have errors, so it is impossible to obtain complete and accurate data. The thermal environment parameters of ground wind tunnel tests can be directly measured, and the measurement accuracy is controllable, but due to the limitations of model scale and incoming flow conditions, it cannot simulate real flight conditions, so accurate aerodynamic data cannot be obtained.

[0004] Compared with the airflow heating method, the construction and operation costs of the radiation heating method equipment are more economical, and it has unique advantages in solving the heat transfer, thermal deformation, thermal matching and structural integrity of the solid rocket engine structure under a composite environment. This heating method is mainly based on a computer-controlled infrared radiation heating system. The use of quartz lamps, graphite and other radiation heating devices can reproduce the heat transfer characteristics of the outer surface of the structure under the actual working conditions of the solid rocket engine. At the same time, according to the load size and temperature distribution of the actual flight aerodynamic heating, the test piece can be divided into sections and regions in the ground test to simulate the thermal environment according to the actual flight aerodynamic heat conditions. Therefore, the radiation heating test that closely combines computers and ground simulation equipment is the only test method to achieve multi-temperature zones, changes over time, and full-scale / whole machine thermal tests.

[0005] However, existing ground simulation equipment, whether using a single constant temperature heating or constant heat flux heating mode, or an adaptive heating mode, is difficult to meet the thermal control requirements of the solid rocket engine thermal environment simulation test bench for uniform radiation heat flux distribution and large heating power. Summary of the invention

[0006] In order to solve the problem that the existing solid rocket engine thermal environment ground simulation equipment is difficult to meet the thermal control requirements of the solid rocket engine thermal environment simulation test bench when conducting radiation heating tests, the present invention proposes a heat flux control system for solid rocket engine coupling tests, which can realize the temperature and heat flux density acquisition and processing of the surface of the heated object and feedback control, and gradually meet the solid rocket engine's uniform radiation heat flux distribution and high heating rate test capability requirements.

[0007] Furthermore, during the simulation design and experiment of the heater, the applicant analyzed the influence of different parameters on the distribution of radiation heat flux and the power density of the heater based on the simulation calculation results of the distribution of radiation heat flux density on the surface of the specimen, and found that the three parameters of the lamp tube layer spacing, the spacing between adjacent quartz lamps, and the distance between the heater and the specimen and their relationship have a great influence on the distribution of radiation heat flux and the power density of the heater. When these parameters are within a certain range, a higher heat flux density can be achieved. At the same time, when the distance between the heater and the specimen is greater than the spacing between adjacent quartz lamps, the spacing between quartz lamps mainly affects the power density of the heater, but has little effect on the radiation distribution; when the spacing between quartz lamps is close to or even greater than the distance between the heater and the specimen, it will cause a radiation valley phenomenon between the quartz lamps. This phenomenon needs to be avoided to ensure that a certain radiation uniformity is maintained when the heater power density is high. In response to this discovery, the applicant designed and determined the appropriate range of these parameters. During the simulation test, these parameters can be adjusted within the designed range according to the heat flux control target to select the optimal parameters to meet the thermal control requirements of the solid rocket engine thermal environment simulation test bench.

[0008] To achieve the above purpose, the technical solution provided by the present invention is:

[0009] A heat flow control system for solid rocket engine testing, comprising a host computer, a heating module, a thyristor trigger board, a heat flux density sensor, a temperature sensor, a data acquisition module, a signal output module and an interaction module;

[0010] The heating module includes a heater, a thyristor and a power supply, and the thyristor controls the power supply to supply power to the heater to heat the engine test piece;

[0011] The thyristor trigger board is used to trigger the thyristor to control the heater;

[0012] The heat flux density sensor is used to detect the heat flux density of the heater and transmit the detected heat flux density signal to the data acquisition module, and one is arranged at the center of each layer of quartz lamps;

[0013] The temperature sensor is used to detect the heating temperature of the heater and transmit the detected temperature signal to the data acquisition module;

[0014] The host computer reads the heat flux density data and temperature data from the data acquisition module, calculates and processes the temperature data, and outputs a heating control signal;

[0015] The signal output module converts the heating control signal into an analog signal for controlling the thyristor trigger board;

[0016] The heater includes two layers of quartz lamps, the quartz lamps in the two layers are staggered and arranged in parallel. The heater is arranged according to the selected heater layout parameters, which include the distance between lamp tube layers, the distance between adjacent quartz lamps in each layer, and the distance between the heater and the engine test piece. The upper computer determines the read heat flux density value. If it does not meet the requirements, the selected heater layout parameters that meet the requirements are output through the interactive module under the following constraints: the range of the distance between lamp tube layers is 0-20mm, the range of the distance between adjacent quartz lamps in each layer is 10-30mm, and the range of the distance between the heater and the engine test piece is 90-110mm.

[0017] Furthermore, the host computer adopts an intelligent PID control method based on deep reinforcement learning to achieve real-time temperature control.

[0018] Furthermore, the interactive module can be used to set the heating temperature and the time to stably maintain the heating temperature.

[0019] Furthermore, the interactive module can be used to set the required heat flux density.

[0020] Furthermore, the interactive module can display the curve of heat flux density changing with time.

[0021] The advantages of the present invention are:

[0022] 1. The heat flux control system for solid rocket engine testing of the present invention is provided with a heat flux density sensor for collecting the heat flux density of the heater and a temperature sensor for collecting the heating temperature of the heater. Whether the heating temperature meets the expected temperature requirement can be known through the temperature sensor. Suitable layout parameters of the heater can be selected through the heat flux density sensor. Meanwhile, constraints on the structure and layout parameters of the heater are also defined. Before the test, the optimal layout parameters of the heater can be selected under the constraints according to different heating temperature requirements, thereby meeting the thermal control requirements of the solid rocket engine thermal environment simulation test bench for radiation heat flux distribution and large heating power.

[0023] 2. By adopting the intelligent PID control method based on deep reinforcement learning to realize temperature control, fast and stable temperature rise control can be achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The above and / or other features and advantages of the present invention will become more easily understood through the following description with reference to the accompanying drawings, which are not drawn to scale and some features are exaggerated or reduced to show details of specific components. In the accompanying drawings:

[0025] Figure 1 It is a composition diagram of a heat flow control system for solid rocket engine testing of the present invention;

[0026] Figure 2 is a three-dimensional diagram of the heater in the present invention;

[0027] Figure 3 is a front view of the heater of the present invention;

[0028] Figure 4 : are simulated cloud diagrams of the radiation heat flux density distribution under different lamp tube layer spacings in the present invention, wherein the lamp tube layer spacing in (a) is 0 mm, the lamp tube layer spacing in (b) is 10 mm, the lamp tube layer spacing in (c) is 20 mm, and the lamp tube layer spacing in (d) is 40 mm;

[0029] Figure 5 : are simulated cloud diagrams of the radiation heat flux density distribution under different lamp spacings in the present invention, wherein the quartz lamp spacing in (a) is 20 mm, the quartz lamp spacing in (b) is 40 mm, the quartz lamp spacing in (c) is 60 mm, and the quartz lamp spacing in (d) is 80 mm;

[0030] Figure 6 It is a schematic cloud diagram of the trough of radiation heat flow between quartz lamps in the present invention;

[0031] Figure 7 : are simulated cloud diagrams of the radiation heat flux density distribution at different heater-specimen distances in the present invention, wherein the heater-specimen distance in (a) is 50 mm, the heater-specimen distance in (b) is 100 mm, the heater-specimen distance in (c) is 150 mm, and the heater-specimen distance in (d) is 200 mm;

[0032] Figure 8 It is a control software panel diagram of the present invention;

[0033] Fig. 9 1 is a test site diagram of the present invention in an example, wherein (a) and (b) are diagrams of the heater before and during the test, respectively;

[0034] Fig.10 1 is the test data curve of the present invention in the example, wherein (a) and (b) are the data curves of two tests respectively, wherein the black line is the heat flux density curve, and the other lines are the temperature monitoring points at different positions. DETAILED DESCRIPTION

[0035] The present invention will be described in detail below with reference to the accompanying drawings by means of exemplary embodiments of the present invention. It should be noted that the following detailed description of the present invention is only for the purpose of illustration, and is not intended to limit the present invention.

[0036] First refer to Figure 1 The thermal flux control system for solid rocket engine testing provided by the present invention includes a host computer, a heating module, a thyristor trigger board, a heat flux density sensor, a temperature sensor, a data acquisition module, a signal output module and an interaction module.

[0037] The heating module includes a heater, a thyristor and a power supply, which are connected in series to form the heating part of the system. The thyristor controls the power supply to supply power to the heater to heat the engine test piece. The thyristor can be used to linearly control the output voltage of the heater to control its output power.

[0038] The thyristor trigger board is used to trigger the thyristor to control the heater. The heat flux density sensor is used to detect the heat flux density of the heater and transmit the detected heat flux density signal to the data acquisition module, and one is arranged at the center of each layer of quartz lamp. The temperature sensor is used to detect the heating temperature of the heater and transmit the detected temperature signal to the data acquisition module. The host computer reads the heat flux density data and temperature data from the data acquisition module, calculates and processes the temperature data, and outputs the heating control signal. The signal output module converts the heating control signal into an analog signal for controlling the thyristor trigger board.

[0039] The closed-loop control part consists of a thyristor trigger board, a data acquisition module, a signal output module, and a host computer (industrial computer or desktop computer). The voltage signal output by the heat flux density sensor is collected by the data acquisition module and read in the host computer; after calculation and processing, the host computer outputs the target signal, which is converted into an analog signal (voltage signal) of a certain specification through the signal output module to control the thyristor trigger board; after receiving this voltage signal, the thyristor trigger board outputs a control signal to the thyristor to control the voltage of the heater. As Figure 1 As shown, the heat flow control system forms a closed loop.

[0040] The interactive module can be used to set the heating temperature, the time to maintain the heating temperature, and can also display the current heating temperature. The interactive module can also be used to set the required heat flux density. The interactive module can also display the change curve of heat flux density over time.

[0041] like Figure 2 and Figure 3As shown, the heater includes two layers of quartz lamps, each layer of lamp arrays may include multiple, for example, more than 10 quartz lamp tubes, the quartz lamp tubes in the two layers are staggered and arranged in parallel, and the heater is arranged according to the selected heater arrangement parameters at different temperatures in different heating stages. The heater arrangement parameters include the lamp tube layer spacing, the spacing between adjacent quartz lamps in each layer, and the distance between the heater and the engine test piece. The host computer can judge the read heat flux density value. If it does not meet the requirements, the interactive module outputs the selected heater arrangement parameters that meet the requirements under the constraints. If it meets the requirements, it means that the heater arrangement parameters are appropriate, and a compliance prompt can be output to prompt the operator to conduct the test.

[0042] The constraints of the above-mentioned structure and arrangement parameters of the heater are determined by simulation calculations for the following heat radiation distribution.

[0043] Reference Figure 4 , which shows the distribution cloud diagram of radiation heat flux density under different lamp tube layer spacing. The heat flux density range of the four figures is the same, all 30~38.5kW / m2. Figure 4 (a) shows the radiation heat flux distribution when the interlayer spacing is 0 mm, and the radiation is relatively uniform on the main heating surface. Figure 4 (b) shows the distribution of radiant heat flux generated by the heater when the interlayer spacing is 10 mm. The heat flux density on the specimen surface is mainly concentrated in the range of 34 to 38 kW / m2, and the maximum unevenness is about 10%. Figure 4 As shown in (c) and (d) in the figure, when the interlayer spacing of the lamp tubes increases, the edge effect between the heater layers begins to become prominent, and the overall radiation efficiency decreases, which is manifested as a decrease in the average heat flux density; especially when the interlayer spacing is as high as 40mm, the local radiation heat flux density at the center of the plate is about 31kW / m2, which is quite different from the peak heat flux density. In fact, the 40mm interlayer spacing of the lamp tubes is only twice the length of the ceramic head of a general quartz lamp. Therefore, if the quartz lamps are aligned and arranged according to their actual length (not the luminous length, or the filament length), a large radiation valley area will be formed in the middle of the plate, seriously affecting the uniformity of the radiation heat flux density distribution. For the radiation distribution of multi-layer quartz lamp heaters, the size of the interlayer spacing of the lamp tubes is a very sensitive influencing factor. To this end, the light-emitting sections of the two layers of quartz lamps, that is, the ends of the filaments, need to be as close as possible (to ensure that the distance between the filament end layers is between 0 and 20 mm) to avoid the generation of radiation troughs caused by edge effects; considering the tooling and wiring issues of quartz lamps, in order to minimize the distance between the lamp tube layers, the two layers of lamp tubes usually need to be staggered.

[0044] Reference Figure 5, shows the radiation distribution cloud map under different quartz lamp spacing. Except for the different quartz lamp spacing, other arrangement parameters are the same, namely: the distance between the heater and the flat specimen is 100mm, and the distance between the lamp tubes is 10mm; the number of quartz lamps varies with the distance between the lamp tubes, so that the heater area is similar. It can be seen from the figure that when the distance between the heater and the flat specimen is the same and the distance is greater than the quartz lamp spacing, the quartz lamp spacing mainly affects the heater power density, but has little effect on the radiation distribution. Figure 5 As shown in (a), (b) and (d) in the figure, the density of quartz lamp arrangement is halved, resulting in the radiant heat flux density on the surface of the specimen being approximately halved, while the distribution is similar. Therefore, when the distance between the heater and the heated specimen is greater than the spacing between the quartz lamps, the spacing between the quartz lamps mainly affects the radiant power density of the heater, and the relationship is approximately inversely proportional. In actual experiments, if the spacing between quartz lamps is too small, such as 10mm, the quartz lamps are close to each other (the outer diameter of the lamp tube cross section is 10mm), which will cause the quartz lamps to overheat and be damaged due to excessive power density. If the quartz lamp is damaged as a result, the heater needs to be cooled by air or even water.

[0045] In addition, if Figure 6 As shown in the figure, when the distance between the quartz lamps is close to or even greater than the distance between the heater and the flat specimen, a radiation valley phenomenon will occur between the quartz lamps. At this time, the distance between the quartz lamps is 80mm, and the distance between the heater and the flat specimen is 50mm. The radiation heat flux density in the area facing the quartz lamps is high, while the radiation heat flux density between the lamps is low. Although the heat flux density value in the radiation valley area shown in the figure is not much different from the heat flux peak value (about 3kW / m2), this phenomenon usually needs to be avoided to ensure that a certain degree of radiation uniformity is maintained when the heater power density is high.

[0046] Reference Figure 7 , which shows the distribution of radiant heat flux density at different heater-specimen distances. The lamp arrangement and other parameters remain the same, that is, the distance between adjacent quartz lamps is 40mm, and the distance between lamp layers is 10mm. Properly increasing the distance between the heater and the specimen can optimize the uniformity of the radiant heat flux, but it will lead to a decrease in the heat flux density at the flat plate. Figure 7As shown in (a), when the heater is 50 mm away from the specimen, the 10 mm gap between the lamp layers (non-luminous section) causes the interlayer radiation trough. Although the value of this trough is close to the peak value, this result still shows that when the heater is close to the flat specimen, the radiation trough caused by the distance between the lamp layers and the distance between adjacent quartz lamps will be prominent. Only when the heater-specimen distance is greater than the above two, the radiation trough phenomenon can be eliminated. Therefore, in actual design, it is necessary to comprehensively consider the two factors of the distance between the lamp layers and the distance between the quartz lamps, and the heater-specimen distance should not be too small; and as mentioned above, the size of the distance between the lamp layers is limited by the actual assembly and wiring conditions, and the distance between the quartz lamps is determined by the target heating power density and the heat resistance of the quartz lamps. The distribution of the radiation heat flux density shown in the figure is relatively uniform, but the increase in the distance between the heater and the specimen leads to a more obvious decrease in the average radiation heat flux density.

[0047] According to the above simulation results, the layout parameter constraints of the heater can be determined as follows: the range of the distance between the lamp tube layers is 0-20mm, the range of the distance between adjacent quartz lamps in each layer is 10-30mm, and the range of the distance between the heater and the engine test piece is 90-110mm, preferably 100mm. Before the test, when the target heating temperature of the engine is known, the heater layout parameters can be adjusted to obtain the optimal heat flux density at the expected heating temperature, thereby meeting the test's thermal control requirements for radiation heat flux distribution and large heating rate.

[0048] The setting, control and display of the software part of the closed-loop system can be realized by LabVIEW. Among them, the control algorithm can be based on the intelligent PID control method of deep reinforcement learning, interact with the external environment through the reinforcement learning algorithm, adjust the PID parameters according to the system state, and realize real-time control of temperature. The function of time-segment control and stable heating is realized in LabVIEW, which can achieve the target, timed and stable heating effect quickly.

[0049] Reference Figure 8 , which shows the front panel of LabVIEW, which is used to set the heat flow control target and monitor the collected heat flow in real time. The front panel of the software consists of two parts: "Settings" and "Display". In the "Settings" part, users can set the required heat flow or temperature value according to the test requirements, as well as the time to maintain the value stably; in the "Display" part, the current heating stage number (current heating temperature) and its target value and stabilization time are displayed in the value box, the heat flow or temperature change over time is displayed in the curve chart, and the heat flow or temperature control curve chart is displayed in the white box.

[0050] As described above, the present invention is provided with a heat flux density sensor for collecting the heat flux density of the heater and a temperature sensor for collecting the heating temperature of the heater. The temperature sensor can be used to determine whether the heating temperature meets the expected temperature requirement. The heat flux density sensor can be used to select appropriate layout parameters of the heater. At the same time, the structural and layout parameter constraints of the heater are also limited. Before the test, the optimal heater layout parameters can be selected under the constraints according to different heating temperature requirements, thereby meeting the thermal control requirements of the solid rocket engine thermal environment simulation test bench for radiation heat flux distribution and large heating power.

[0051] The solid engine coupling test heat flux control system provided by the present invention has been verified by test measurement data. The quartz lamp array radiation model has strong adaptability and accuracy. It can be quickly and conveniently modified for heaters with different geometric arrangements and different quartz lamps (size, power, etc.) to obtain accurate simulation heat flux density results. The idea of ​​the multi-domain coupling calculation method of the specimen temperature field is also universal, and the specimen surface temperature field can be accurately calculated based on the above radiation distribution results. The goal of using a computer to control the quartz lamp heating power in real time, quickly and accurately is achieved, thereby achieving uniform heat flow or temperature, as well as fast and stable temperature rise control goals.

[0052] The system and its design scheme can also provide design and test experience for ground simulated thermal loading of various high-speed aircraft shells; the simulation calculation scheme also provides solutions for the design of heaters for similar problems, and the simulation results and analysis play an important guiding role in the design of heaters.

[0053] Next, the thermal flow control system for solid rocket engine testing provided by the present invention is further explained by way of examples.

[0054] Reference Fig. 9 In this example, the upper and lower layers of the heater are composed of 15 quartz lamps, and the spacing between adjacent lamps is 30 mm; the length of the quartz lamp light segment is 380 mm, the spacing between the light segments between layers is 10 mm, and the lamps need to be staggered; the size of the flat specimen is 500×600 mm; the intelligent PID control method based on deep reinforcement learning is used to achieve temperature control.

[0055] The key point of this design is that the interlayer spacing of the quartz lamp light-emitting segment should be controlled at about 10mm. For this reason, since the length of the quartz lamp ceramic head is about 2cm, the quartz lamps are usually required to be arranged in a staggered manner. Second, the distance from the edge of the quartz lamp heater beyond the flat plate is approximately the distance from the heater plane to the surface of the specimen to avoid the influence of the heater edge effect on the radiation uniformity. For example, in this design, the two ends of the lamp tube exceed the specimen by 85mm, and the distance between the heater and the specimen surface is 100mm, and the difference between the two should not be too large. The power of a single quartz lamp is 1500W, and the distance between the lamp tubes is 40mm. At this time, the radiation heat flux density of the flat plate can be as high as 50kW / m2; if the heat flux density of the heat load needs to be increased, the distance between the lamp tubes can be appropriately reduced, or the power of the lamp tubes can be increased. However, when the power density of the heater is too large, it is necessary to consider taking cooling measures for the heater. According to the simulation results analysis and experimental experience, the structural design of the heater can meet the goal of less than 10% uniformity of radiation heat flux on the surface of the flat specimen; when the flat plate is placed horizontally, due to the heat conduction inside the flat plate, the temperature uniformity will be better than the radiation heat flux uniformity.

[0056] like Fig.10 As shown in the heat flux density curve data in the two test curves (a) and (b), the heat flux density rises rapidly during control, is stable in the plateau section, and does not show large fluctuations in the descending section. The test results show that the control program of the heat flux control system of the present invention responds quickly, the heat flux control is precise and stable, and can achieve the expected control target, verifying the effectiveness of the heat flux control system provided by the present invention.

[0057] Finally, it should be noted that the features mentioned and / or shown in the above description of the exemplary embodiments of the present invention may be combined in the same or similar manner into one or more other embodiments, combined with the features in other embodiments or substituted for the corresponding features in other implementations. The technical solutions obtained by these combinations or substitutions shall also be deemed to be included in the protection scope of the present invention.

Claims

1. A thermal flow control system for solid rocket engine testing, characterized in that: It includes a host computer, a heating module, a thyristor trigger board, a heat flux density sensor, a temperature sensor, a data acquisition module, a signal output module and an interaction module; The heating module comprises a heater, a thyristor and a power supply, wherein the thyristor controls the power supply to supply power to the heater so as to heat the engine test piece; The thyristor triggering board is used to trigger the thyristor to control the heater; The heat flux density sensor is used to detect the heat flux density of the heater and transmit the detected heat flux density signal to the data acquisition module, and one heat flux density sensor is arranged at the center of each layer of quartz lamps; The temperature sensor is used to detect the heating temperature of the heater and transmit the detected temperature signal to the data acquisition module; The host computer reads the heat flux data and temperature data from the data acquisition module, calculates and processes the temperature data, and outputs a heating control signal; The signal output module converts the heating control signal into an analog signal for controlling the thyristor trigger board; The heater includes two layers of quartz lamps, the quartz lamps in the two layers are staggered and arranged in parallel. The heater is arranged according to the selected heater arrangement parameters, which include the lamp tube layer spacing, the spacing between adjacent quartz lamps in each layer, and the distance between the heater and the engine test piece. The host computer determines the read heat flux density value. If it does not meet the requirements, the selected heater arrangement parameters that meet the requirements are output through the interactive module under the following constraints: the range of the lamp tube layer spacing is 0-20mm, the range of the spacing between adjacent quartz lamps in each layer is 10-30mm, and the range of the distance between the heater and the engine test piece is 90-110mm.

2. The thermal flow control system for solid rocket engine testing according to claim 1, characterized in that: The host computer adopts an intelligent PID control method based on deep reinforcement learning to achieve real-time temperature control.

3. The thermal flow control system for solid rocket engine testing according to claim 1 or 2, characterized in that: The interactive module can be used to set the heating temperature and the time to stably maintain the heating temperature.

4. The thermal flow control system for solid rocket engine testing according to claim 1 or 2, characterized in that: The interactive module can be used to set the desired heat flux density.

5. The thermal flow control system for solid rocket engine testing according to claim 1 or 2, characterized in that: The interactive module can display the curve of heat flux density changing with time.

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