Engine jet flow thermal environment data determination method and system, medium and product

Abstract

The invention discloses an engine jet flow thermal environment data determination method and system, a medium and a product, and the method comprises the steps: collecting the actual heat flow data and actual temperature data of N target test small plates disposed at the side edge of an outlet of an engine jet pipe in the ground hot test process of an engine, the positions of the N target test small plates are obtained by simulating jet flow thermal environment data of the engine; determining a target heat flow correction parameter based on the calculated heat flow data and the actual heat flow data obtained by each target test small plate in the jet flow thermal environment data simulation process; and determining temperature response data of each target test small plate based on the actual heat flow data of each target test small plate, and determining a target temperature correction parameter based on the actual temperature data and the temperature response data of each target test small plate. According to the scheme, the simulation data can be corrected, so that the corrected data is close to the real environment data, and additional investment of relatively high cost is not needed.

Description

Technical Field

[0001] The present invention relates to the field of rocket thermal environment measurement, and particularly to a method, system, medium and product for determining engine jet flow thermal environment data. Background Art

[0002] In the process of designing the thermal protection scheme of a launch vehicle, the thickness selection of the thermal protection material highly depends on the predicted results of the thermal environment. If the thermal protection material is too thin, it will lead to the failure of thermal protection under the action of heat flux, resulting in the increase of the temperature of the rocket body structure and the decrease of strength. If the design is too conservative, it will reduce the carrying capacity of the rocket and its economy. To obtain the engine jet flow thermal environment, the traditional method is to arrange corresponding heat flux density and temperature measurement points near the engine nozzle at the bottom of the rocket to obtain the thermal environment data during flight. The position of the measurement points of this method is restricted by the layout of the on-board equipment, and the test cost is relatively high, the number of test samples is small, and the guidance for subsequent design work is limited. Therefore, how to conveniently and accurately measure the thermal environment of the rocket is a technical problem to be solved urgently. Summary of the Invention

[0003] Embodiments of the present invention provide a method, system, medium and product for determining engine jet flow thermal environment data.

[0004] In a first aspect, embodiments of the present invention provide a method for determining engine jet flow thermal environment data of a liquid rocket engine, which is characterized by including:

[0005] During the ground hot test of the engine, collect the actual heat flux data and actual temperature data of each of the N target test small plates arranged on the side of the engine nozzle outlet, where the positions of the N target test small plates are obtained through the simulation of the engine jet flow thermal environment data, and N is a positive integer;

[0006] Based on the calculated heat flux data obtained by each target test small plate during the simulation of the jet flow thermal environment data and the actual heat flux data of each target test small plate, determine the target heat flux correction parameter;

[0007] Based on the actual heat flux data of each target test small plate, determine the temperature response data of each target test small plate, and based on the actual temperature data and temperature response data of each target test small plate, determine the target temperature correction parameter;

[0008] Wherein, the target heat flux correction parameter and the target temperature correction parameter are used to correct the results of the simulation of the engine jet flow thermal environment data to obtain the final environment data.

[0009] In some embodiments, the positions of the N target test small plates are determined by the following method:

[0010] During the simulation process of the jet flow thermal environment data of the engine, an engine model of the engine is established;

[0011] On both sides of the nozzle outlet of the engine model, M rows of test small plate models are arranged, where the test small plate models in the same row have the same axial distance from the engine model, and the test small plate models in different rows have different axial distances from the engine model, and M is a positive integer;

[0012] Based on the engine model and the M rows of test small plate models, simulation calculations of the jet flow thermal environment data are carried out to obtain the calculated heat flux data of each test small plate model in the M rows of test small plate models;

[0013] Based on the heat flux data of each test small plate model, N target test small plate models are determined, where none of the N target test small plate models are located in the jet wake region, and the ratio of the heat flux data of two adjacent test small plate models among the N target test small plate models is greater than a preset ratio;

[0014] Take the positions of the N target test small plate models as the positions of the N target test small plates.

[0015] In some embodiments, each target test small plate includes a substrate, the substrate includes a first surface and a second surface opposite to the first surface, a thermal protection layer is formed on the first surface, temperature sensors are arranged on the surface of the thermal protection layer, the contact surface between the substrate and the thermal protection layer, and the second surface, and a heat flux sensor is further arranged on the surface of the thermal protection layer; Collecting the actual heat flux data and actual temperature data of each target test small plate among the N target test small plates arranged on the side of the engine nozzle outlet includes:

[0016] Obtain the actual temperature data through the temperature sensors on each target test small plate, and obtain the actual heat flux data through the heat flux sensors on each target test small plate.

[0017] In some embodiments, determining the target heat flux correction parameter based on the calculated heat flux data obtained by each target test small plate during the simulation process of the jet flow thermal environment data and the actual heat flux data of each target test small plate includes:

[0018] For each target test small plate, based on the actual heat flux data and calculated heat flux data of the target test small plate, determine the heat flux correction parameter corresponding to the target test small plate;

[0019] Take the average value of the heat flux correction parameters corresponding to each target test small plate as the target heat flux correction parameter.

[0020] In some embodiments, determining the temperature response data of each target test small board based on the actual heat flux data of each target test small board, and determining a target temperature correction parameter based on the actual temperature data and the temperature response data of each target test small board includes:

[0021] For each target test small board, dividing the target test small board into j layers along the thickness direction, where j is a positive integer;

[0022] Based on the actual heat flux data of each target test small board and a preset temperature response calculation strategy, determining the temperature response data of each layer of each target test small board, where the temperature response calculation strategy is determined based on the material emissivity of the thermal protection layer;

[0023] Based on the temperature response data of each layer of each target test small board and the actual temperature data of each target test small board, determining the target temperature correction parameter.

[0024] In some embodiments, determining the target temperature correction parameter based on the temperature response data of each layer of each target test small board and the actual temperature data of each target test small board includes:

[0025] For each target test small board, determining the first-layer temperature response data corresponding to the surface of the thermal protection layer, the second-layer temperature response data corresponding to the contact surface between the substrate and the thermal protection layer, and the third-layer temperature response data corresponding to the second surface from the temperature response data of each layer in the target test small board;

[0026] For each target test small board, based on the actual temperature data of the target test small board, determining the first temperature data corresponding to the surface of the thermal protection layer, the second temperature data corresponding to the contact surface between the substrate and the thermal protection layer, and the third temperature data corresponding to the second surface;

[0027] Based on the first-layer temperature response data, the second-layer temperature response data, the third-layer temperature response data of each target test small board and the corresponding first temperature data, second temperature data, and third temperature data, determining the target temperature correction parameter, where the target temperature correction parameter is a correction parameter for the material emissivity of the thermal protection layer.

[0028] In some embodiments, the method further includes:

[0029] During the ground hot test of the engine, controlling the difference between the thrust of the engine and a preset thrust to be less than a threshold value.

[0030] In a second aspect, an engine jet flow thermal environment data determination system provided by an embodiment of the present invention includes a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, the steps in the control method of the above electric pedal are implemented.

[0031] In a third aspect, an embodiment of the present invention provides a computer-readable storage medium, on which a computer program is stored. When the program is executed by a processor, the steps in the control method of the above electric pedal are implemented.

[0032] In a fourth aspect, an embodiment of the present invention provides a computer program product. The computer program product includes a computer program. When the computer program is executed by a processor, it is used to load and execute the steps in the control method of the above electric pedal.

[0033] One or at least one of the above technical solutions in the embodiments of the present application has at least the following technical effects:

[0034] The method for determining the liquid rocket engine jet flow thermal environment data provided by the embodiments of this specification, during the ground hot test of the engine, collects the actual heat flux data and actual temperature data of each of the N target test small plates arranged on the side of the engine nozzle outlet. Among them, the positions of the N target test small plates are obtained through the simulation of the engine jet flow thermal environment data, N is a positive integer. Based on the calculated heat flux data obtained by each target test small plate during the simulation of the jet flow thermal environment data and the actual heat flux data of each target test small plate, the target heat flux correction parameter is determined; based on the actual heat flux data of each target test small plate, the temperature response data of each target test small plate is determined, and based on the actual temperature data and temperature response data of each target test small plate, the target temperature correction parameter is determined. Among them, the target heat flux correction parameter and the target temperature correction parameter are used to correct the data obtained by the simulation of the engine jet flow thermal environment data to obtain the final environmental data. In this solution, by arranging test small plates near the jet flow, the actual heat flux data of the jet flow and the temperature response data of the test small plates are obtained, so as to determine the target heat flux correction parameter and the target temperature correction parameter, and then the simulation data is corrected by the correction parameters, so that the corrected data is close to the real environmental data, without the need to invest a large amount of additional cost, and the test cost is low. Description of the Drawings

[0035] Figure 1 It is a flowchart of a method for determining the engine jet flow thermal environment data provided by the embodiments of this specification;

[0036] Figure 2 It is a schematic diagram of the arrangement of a test small plate model provided by the embodiments of this specification;

[0037] Figure 3 Schematic diagram of the structure of a target test small board provided by an embodiment of this specification;

[0038] Figure 4 Schematic diagram of the positional relationship between a target test small board provided by an embodiment of this specification and an engine;

[0039] Figure 5 Schematic diagram of a system for determining engine jet flow thermal environment data provided by an embodiment of this specification. Specific implementation manners

[0040] The general idea of the technical solution of the embodiments of this application is as follows: During the ground hot test of the engine, collect the actual heat flux data and actual temperature data of each of the N target test small boards arranged on the side of the engine nozzle outlet, where the positions of the N target test small boards are obtained through simulation of the engine jet flow thermal environment data, and N is a positive integer; Based on the calculated heat flux data obtained by each target test small board during the simulation of the jet flow thermal environment data and the actual heat flux data of each target test small board, determine the target heat flux correction parameter; Based on the actual heat flux data of each target test small board, determine the temperature response data of each target test small board, and based on the actual temperature data and temperature response data of each target test small board, determine the target temperature correction parameter; Among them, the target heat flux correction parameter and the target temperature correction parameter are used to correct the results of the simulation of the engine jet flow thermal environment data to obtain the final environmental data.

[0041] In the solution of the embodiments of this specification, by arranging test small boards near the jet flow, the actual heat flux data of the jet flow and the temperature response data of the test small boards are obtained, so as to determine the target heat flux correction parameter and the target temperature correction parameter, and then the simulation data is corrected by the correction parameters, so that the corrected data is close to the real environmental data, without the need to invest a large amount of additional cost, and the test cost is low.

[0042] In order to better understand the above technical solution, the technical solution of the embodiments of this specification will be described in detail below through the drawings and specific embodiments. It should be understood that the specific features in the embodiments of this specification and the embodiments are detailed descriptions of the technical solution of the embodiments of this specification, rather than limitations on the technical solution of this specification. Without conflict, the technical features in the embodiments of this specification and the embodiments can be combined with each other.

[0043] First, it should be noted that the term "and / or" appearing in this article is merely a description of the association relationship between associated objects, indicating that there can be three relationships. For example, A and / or B can represent three situations: A exists alone, A and B exist simultaneously, and B exists alone. Additionally, the character " / " in this article generally represents an "or" relationship between the preceding and following associated objects.

[0044] As Figure 1 shown, it is a flowchart of a method for determining the jet heat environment data of a liquid rocket engine provided by an embodiment of this specification. This method includes the following steps:

[0045] Step S101: During the ground hot-fire test of the engine, collect the actual heat flux data and actual temperature data of each of the N target test small plates arranged on the side of the engine nozzle outlet. Among them, the positions of the N target test small plates are obtained through simulation of the jet heat environment data of the engine, and N is a positive integer;

[0046] Step S102: Based on the calculated heat flux data obtained by each target test small plate during the simulation of the jet heat environment data and the actual heat flux data of each target test small plate, determine the target heat flux correction parameter;

[0047] Step S103: Based on the actual heat flux data of each target test small plate, determine the temperature response data of each target test small plate, and based on the actual temperature data and temperature response data of each target test small plate, determine the target temperature correction parameter;

[0048] Among them, the target heat flux correction parameter and the target temperature correction parameter are used to correct the results of the simulation of the jet heat environment data of the engine to obtain the final environment data.

[0049] The method provided by the embodiment of this specification can be applied to a liquid rocket engine jet heat environment measurement system, or to a server communicatively connected to the engine jet heat environment measurement system, or can also be implemented through the interaction between the engine jet heat environment measurement system and the server, which is not limited here.

[0050] In step S101, in order to obtain the jet heat environment data of the liquid rocket engine, N target test small plates are arranged on the side of the engine nozzle outlet. The number of N can be determined according to actual needs. For example, N is 3, 4, etc. Temperature sensors and heat flux sensors can be arranged on the target test small plates. When the engine conducts a ground hot-fire test, the high-temperature gas during the test will act on the target test small plates, and thus the actual heat flux data and actual temperature data of each target test small plate can be obtained through the heat flux sensors and temperature sensors.

[0051] In the embodiments of this specification, in order to enable the data collected by the target test small board to accurately reflect the engine jet heat environment, the setting position of the target test small board can be screened.

[0052] In some embodiments, the positions of the N target test small boards can be determined through the following simulation process: in the simulation process of the jet heat environment data of the engine, an engine model of the engine is established; M columns of test small board models are arranged on both sides of the nozzle outlet of the engine model, where the test small board models in the same column have the same distance from the axis of the engine model, and the test small board models in different columns have different distances from the axis of the engine model, and M is a positive integer; based on the engine model and the M columns of test small board models, simulation calculations of the jet heat environment data are carried out to obtain the calculated heat flux data of each test small board model in the M columns of test small board models; based on the heat flux data of each test small board model, N target test small board models are determined, where none of the N target test small board models are located in the jet wake region, and the ratio of the heat flux data of two adjacent test small board models among the N target test small board models is greater than a preset ratio; the positions of the N target test small board models are used as the positions of the N target test small boards.

[0053] Specifically, the simulation of the engine jet environment data can be realized through CFD (Computational Fluid Dynamics). In the simulation process, an engine model can be established. In order to determine the position of the target test small board, multiple test small board models can also be established. The size of the test small board model can be set according to actual needs and is not limited here. In some embodiments, in order to make the test small board model cover the jet action area as much as possible, M columns of test small board models can be arranged on both sides of the nozzle of the engine model. M can be set according to actual needs. For example, M is 2, 3, 6, 8, etc. The M columns of test small board models can be all completed in one simulation process or in multiple simulation processes. For example, in the first simulation process, the first and second columns of test small board models are simulated, and in the second simulation process, the third and fourth columns of test small board models are simulated.

[0054] The distance of each column of test small board models from the axis of the engine model is the same, and the distances of different columns of test small board models from the axis of the engine model are different. The distance of each column of test small board models from the axis of the engine model can be set according to actual needs. In some embodiments, the nozzle outlet diameter is D, and the distances of the M columns of test small board models from the axis of the engine model can be D, 2D, 3D,..., MD in sequence. As Figure 2 shown, it is a schematic diagram of the arrangement of the test small board models. As Figure 2Two columns of test small plate models are shown, located on both sides of the nozzle respectively. The distances between the two columns of test small plate models and the axis are D1 and D2 respectively. It should be noted that D1 and D2 can be different or the same. In some embodiments, for each column of test small plate models, they can be equally spaced. For example, the distance between two adjacent test small plate models is D.

[0055] During the simulation of the jet flow thermal environment data of the engine, the calculated heat flux data of each test small plate model can be obtained. To ensure that there is a certain heat flux difference between the selected test small plates, the calculated heat flux data between any two test small plate models can be compared, and the test small plate model with the heat flux difference meeting the preset conditions is used as the model corresponding to the target test small plate.

[0056] In some embodiments, the ratio between the calculated heat flux data of any two test small plate models can be determined. Among the finally determined N target test small plate models, if the calculated heat flux data of the N target test small plate models are arranged from high to low, the heat flux ratio between each adjacent two target test small plate models is greater than the preset ratio. The preset ratio can be set according to actual needs. For example, the preset ratio can be 1.1, 1.2, etc. In addition, to eliminate the influence of high-temperature gas heat convection, in the embodiments of this specification, the target test small plate models are not located in the jet wake region.

[0057] In some embodiments, if the number of target test small plates determined based on the above method is relatively large, further screening can be performed in combination with the distance between the test small plates to make the interval between the small plates as large as possible. For example, the interval between any two finally selected target test small plates is greater than the preset interval.

[0058] After screening out the N target test small plate models, the positions of the N target test small plate models can be used as the positions of the N target test small plates, and during the test run, the N target test small plates are set at the corresponding positions.

[0059] It should be noted that the specific size and structure of the target test small plate can be selected according to actual needs. In some embodiments, each target test small plate may include a substrate, the substrate includes a first surface and a second surface opposite to the first surface, a thermal protection layer is formed on the first surface, temperature sensors are arranged on the surface of the thermal protection layer, the contact surface between the substrate and the thermal protection layer, and the second surface, and a heat flux sensor is also arranged on the thermal protection layer. Among them, the material of the substrate, the material of the thermal protection layer, the thickness of the substrate and the thermal protection layer can all be set according to actual needs, and the positions of the temperature sensor and the heat flux sensor can also be selected according to actual needs.

[0060] For ease of explanation, an embodiment of this specification provides a target test small board. As Figure 3 shown, it is a schematic structural diagram of a target test small board. The target test small board is a heat - resistant small board. Figure 3 In it, the size of the small board is 100mm×100mm. The small board can use carbon steel with a thickness of d2 as the substrate. A heat - protection layer with a thickness of d1 is sprayed on the first surface of the substrate. Two temperature measurement points and one heat - flux measurement point are arranged on the front surface of the heat - protection layer. Two temperature measurement points are also arranged on the contact surface between the heat - protection layer and the carbon - steel substrate. On the inner wall of the substrate, that is, the second surface opposite to the first surface of the substrate, two temperature measurement points are arranged. Temperature sensors are set at the temperature measurement points, and a heat - flux sensor is set at the heat - flux measurement point. Then, a total of six temperature sensors and one heat - flux sensor are set on the target test small board. Among them, the temperature measurement points of the heat - protection layer, the contact surface between the heat - protection layer and the substrate, and the inner wall of the substrate are the same. In Figure 3 In it, for the two temperature measurement points of each layer, one temperature measurement point is located at the center position of the small board, and the other temperature measurement point is located at the quarter - diagonal position. For the heat - flux measurement point of the heat - protection layer, the heat - flux measurement point is located at the quarter - diagonal position. It should be noted that for the sensors set for each layer, it is necessary to ensure that the distance between any two sensors is greater than the first preset distance, and the distance between each sensor and the boundary of the small board is greater than the second preset distance. Among them, the first preset distance and the second preset distance can be set according to actual needs.

[0061] In addition, to reduce the heat conduction from the carbon - steel substrate to the tooling, a heat - protection layer with a thickness of d3 can be added to the inner wall of the carbon - steel substrate. As Figure 3 shown, the height of the added heat - protection layer on the inner wall can be 20mm, which is used to isolate the solid heat conduction between the substrate and the tooling. In the embodiment of this specification, the small board can be connected to the support tooling with multiple bolts. As Figure 3 shown, it is connected to the tooling with 3 bolts, and the opening diameter is 7mm.

[0062] It should be understood that the size of the above - mentioned small board, the thickness of each layer, and other parameters can all be adjusted according to actual needs. The above - mentioned parameters are only for illustration and do not limit the parameters.

[0063] In the embodiment of this specification, the target test small board is arranged on the side of the engine nozzle according to the corresponding position. In some embodiments, the center height of the target test small board can be made to be at the same height as the axis of the engine nozzle by setting the height of the support tooling. As Figure 4 shown, it is a schematic diagram of the positional relationship between the target test small board and the engine. Figure 4 In it, the number of target test small boards is 3, and the distances of the three target test boards from the outlet of the engine nozzle are L1, L2, and L3 in sequence.

[0064] After setting up the target test small board, the ground hot test run of the engine can be carried out. Step S101 can be implemented in the following manner: obtaining the actual temperature data through the temperature sensors on each of the target test small boards, and obtaining the actual heat flux data through the heat flux sensors on each of the target test small boards.

[0065] Specifically, during the ground hot test run of the engine, in order to avoid the influence of the unstable factors of the engine jet flow itself on the results during the test, the test can select the steady-state test run condition of the engine, and control the difference between the thrust of the engine and the preset thrust to be less than the threshold value, that is, keep the engine thrust constant during the test run, and the engine does not perform a swaying action. Among them, the preset thrust and the threshold value can both be set according to actual needs and are not limited here.

[0066] During the test run, the data collected by the temperature sensors on the target test small board is used as the actual temperature data, and the data collected by the heat flux sensors is used as the actual heat flux data.

[0067] In step S102, during the above-mentioned simulation process of the jet flow heat environment data, the calculated heat flux data of each test small board model can be simulated, and the calculated heat flux data of the small board models corresponding to the N target test small boards can be screened out and compared with the corresponding actual heat flux data respectively, so as to obtain the target heat flux correction parameter.

[0068] In some embodiments, step S102 can be implemented in the following manner: for each of the target test small boards, based on the actual heat flux data and the calculated heat flux data of the target test board, determine the heat flux correction parameter corresponding to the target test small board; take the average value of the heat flux correction parameters corresponding to each of the target test small boards as the target heat flux correction parameter.

[0069] Specifically, for each target test small board, the actual heat flux data corresponding to the target test small board can be represented by q 1 denoted, and the calculated heat flux data obtained during the simulation process can be represented by q 2 denoted. The heat flux correction parameter A 1 corresponding to the target test small board can be q 1 / q 2 . Further, the heat flux correction parameters corresponding to each target test small board are averaged, and the obtained average value is used as the target heat flux correction parameter.

[0070] After obtaining the target heat flux correction parameter, during the subsequent simulation process of the environmental data, after obtaining the heat flux data during the simulation process, the heat flux data obtained by simulation is corrected by the target heat flux correction parameter, so that the corrected heat flux data can be closer to the real heat flux data.

[0071] In step S103, after obtaining the actual heat flux data of the target small plate, the corresponding temperature response data can be inferred based on the heat flux data. Taking the test small plate composed of the above heat insulation layer and carbon steel as an example, using the collected actual heat flux data, the temperature response of the combination of the heat insulation layer and carbon steel can be calculated. By comparing the calculation result with the actually measured temperature data, the target temperature correction parameter can be obtained.

[0072] In some embodiments, step S103 can be implemented through the following steps: for each target test small plate, divide the target test small plate into j layers along the thickness direction, where j is a positive integer; based on the actual heat flux data of each target test small plate and a preset temperature response calculation strategy, determine the temperature response data of each layer of each target test small plate, where the temperature response calculation strategy is determined based on the material emissivity of the thermal protection layer; based on the temperature response data of each layer of each target test small plate and the actual temperature data of each target test small plate, determine the target temperature correction parameter.

[0073] Specifically, continuing with the above Figure 3 target test small plate, the target test small plate includes a thermal protection layer with a thickness of d1 and a substrate with a thickness of d2, then the total thickness of the target test small plate is d1 + d2. Divide d1 + d2 into j layers, and each layer can correspond to a unit. Among them, the thickness stratification can be evenly divided into j layers or randomly divided into j layers in terms of thickness. Here, it is not limited, and the specific value of j can also be set according to actual needs.

[0074] In the embodiments of this specification, since the temperature sensor and the heat flux sensor are respectively arranged on the surface of the thermal protection layer, the contact surface between the thermal protection layer and the substrate, and the inner wall of the substrate, therefore, the layers where the sensors are located can be screened out from the j layers. Among them, the layer where the inner wall is located can be used as the first layer, and the layer where the surface of the thermal protection layer is located can be used as the jth layer.

[0075] In some embodiments, calculating the temperature response through the heat flux data can be achieved through the following formula:

[0076]

[0077] where ρ is the material density, c is the specific heat capacity of the material, δ is the thickness of the differential unit, T n is the temperature of the nth unit, ε is the emissivity of the outer surface of the material, σ is the Boltzmann constant, and its value is 5.67×10 -8 , λ is the thermal conductivity of the material, and q 1 is the actual heat flux data.

[0078] Among the above three formulas, formula (1) corresponds to the outermost layer, that is, the temperature response of the layer where the thermal protection layer is located, formula (2) corresponds to the innermost layer, that is, the temperature response of the layer where the second surface of the substrate is located, and formula (3) corresponds to the temperature response of the middle nth layer. Through the above formulas, the temperature response of each layer in the jth layer can be determined.

[0079] In some embodiments, after obtaining the temperature response of each layer, the target temperature correction parameter can be determined through the following steps: for each target test small board, determine the first-layer temperature response data corresponding to the surface of the thermal protection layer, the second-layer temperature response data corresponding to the contact surface between the substrate and the thermal protection layer, and the third-layer temperature response data corresponding to the second surface from the temperature response data of each layer in the target test small board; for each target test small board, based on the actual temperature data of the target test small board, determine the first temperature data corresponding to the surface of the thermal protection layer, the second temperature data corresponding to the contact surface between the substrate and the thermal protection layer, and the third temperature data corresponding to the second surface; based on the first-layer temperature response data, second-layer temperature response data, third-layer temperature response data of each target test small board and the corresponding first temperature data, second temperature data, and third temperature data, determine the target temperature correction parameter, and the target temperature correction parameter is the correction parameter for the material emissivity of the thermal protection layer.

[0080] Specifically, if the above example is followed, taking the layer number where the inner wall is located as the first layer and the layer number where the surface of the thermal protection layer is located as the jth layer, then the first-layer temperature response data can correspond to the temperature response data of the jth layer, the second-layer temperature response data can correspond to the temperature response data of the first layer, and the third temperature response data can correspond to the temperature response data of the nth layer where the contact surface is located. Thus, three temperature response data of the target test small board can be obtained. In some embodiments, the temperature response data can be a temperature response curve. At the same time, since temperature sensors are provided on all these three layers, the actual temperature data of these three layers can be collected through the temperature sensors. Then, three actual temperature response curves of these three layers can be obtained.

[0081] Furthermore, for each layer, compare the calculated temperature response curve and the actual temperature response curve of this layer to obtain the target temperature correction parameter. It should be noted that since the density, specific heat capacity, and thermal conductivity of the material in engineering practice can be measured through corresponding material-level tests, the data accuracy is relatively high, while the emissivity data of the material is often difficult to determine. When performing temperature correction, the emissivity of the material can be used as the target temperature correction parameter to make the corrected temperature curve closer to the measured curve.

[0082] In the embodiments of this specification, after obtaining the target temperature correction parameter, when calculating the temperature response subsequently, the target temperature correction parameter can be used to correct the material emissivity, so as to obtain a more accurate temperature response.

[0083] Based on the same inventive concept, the embodiments of the present invention further provide an engine jet flow thermal environment data determination system, as Figure 5 described, including a memory 504, a processor 502, and a computer program stored on the memory 504 and executable on the processor 502. When the processor 502 executes the program, it implements any one of the implementation manners of the engine jet flow thermal environment data determination method.

[0084] Among them, in Figure 5 , the bus architecture (represented by bus 500), bus 500 may include any number of interconnected buses and bridges. Bus 500 links together various circuits including one or more processors represented by processor 502 and a memory represented by memory 504. Bus 500 can also link together various other circuits such as peripheral devices, voltage regulators, and power management circuits, which are well known in the art, and thus will not be further described herein. Bus interface 505 provides an interface between bus 500 and receiver 501 and transmitter 503. Receiver 501 and transmitter 503 can be the same element, i.e., a transceiver, which provides a unit for communicating with various other devices on the transmission medium. Processor 502 is responsible for managing bus 500 and general processing, while memory 504 can be used to store data used by processor 502 when executing operations.

[0085] Based on the same inventive concept, the embodiments of this specification provide a computer-readable storage medium, on which a computer program is stored. When the program is executed by a processor, it implements the steps of the above-mentioned engine jet flow thermal environment data determination method.

[0086] Based on the same inventive concept, the embodiments of this specification provide a computer program product. The computer program product includes a computer program, and when the computer program is executed by a processor, it is used to load and execute the steps of the engine jet flow thermal environment data determination method.

[0087] The functions described herein can be implemented in hardware, software executed by a processor, firmware, or any combination thereof. If implemented in software executed by a processor, the functions can be stored on or transmitted via a computer-readable medium as one or more instructions or codes. Other examples and implementations are within the scope and spirit of the present invention and the appended claims. For example, due to the nature of software, the functions described above can be implemented using software executed by a processor, hardware, firmware, hardwiring, or any combination of these. In addition, each functional unit can be integrated in one processing unit, or each unit can exist physically alone, or two or more units can be integrated in one unit.

[0088] In several embodiments provided in the present application, it should be understood that the disclosed technical content can be implemented in other ways. Among them, the device embodiments described above are merely illustrative. For example, the division of the units can be a logical function division. In actual implementation, there can be other division methods. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the couplings or direct couplings or communication connections shown or discussed with each other can be through some interfaces. The indirect couplings or communication connections of the units or modules can be in electrical or other forms.

[0089] The units described as separate components may or may not be physically separated. The components serving as control devices may or may not be physical units, that is, they can be located in one place or distributed to multiple units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0090] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or all or part of this technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions for causing a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes: USB flash drives, read-only memories (ROMs), random access memories (RAMs), mobile hard disks, magnetic disks, or optical discs, etc., which can store program codes.

[0091] The above are only embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the scope of the claims of the present invention.

Claims

1. A method for determining the jet thermal environment data of a liquid rocket engine, characterized in that: include: During the ground hot test of the engine, actual heat flow data and actual temperature data of each target test plate among N target test plates arranged on the side of the engine nozzle outlet are collected, wherein the positions of the N target test plates are obtained by simulating the jet thermal environment data of the engine, and N is a positive integer; Determine a target heat flux correction parameter based on the calculated heat flux data of each target test platelet obtained during the jet thermal environment data simulation process and the actual heat flux data of each target test platelet; Determine the temperature response data of each target test platelet based on the actual heat flow data of each target test platelet, and determine the target temperature correction parameter based on the actual temperature data and the temperature response data of each target test platelet; The target heat flow correction parameter and the target temperature correction parameter are used to correct the result of the simulation of the jet thermal environment data of the engine to obtain the final environment data.

2. The method according to claim 1, characterized in that The positions of the N target test boards are determined by: In the process of simulating the jet thermal environment data of the engine, establishing an engine model of the engine; M rows of test plate models are arranged on both sides of the nozzle outlet of the engine model, wherein the test plate models in the same row have the same axial distance from the engine model, and the test plate models in different rows have different axial distances from the engine model, and M is a positive integer; Performing jet thermal environment data simulation calculation based on the engine model and the M rows of test plate models to obtain calculated heat flow data of each test plate model in the M rows of test plate models; Based on the heat flow data of each test platelet model, N target test platelet models are determined, wherein none of the N target test platelet models is located in the jet wake region, and a ratio of heat flow data of two adjacent test platelet models among the N target test platelet models is greater than a preset ratio; The positions of the N target test platelet models are used as the positions of the N target test platelets.

3. The method according to claim 1, characterized in that Each target test platelet includes a substrate, the substrate includes a first surface and a second surface opposite to the first surface, a heat protection layer is formed on the first surface, a temperature sensor is arranged on the surface of the heat protection layer, a contact surface between the substrate and the heat protection layer, and the second surface, and a heat flux sensor is also arranged on the surface of the heat protection layer; the actual heat flux data and actual temperature data of each target test platelet among the N target test plates arranged on the side of the engine nozzle outlet are collected, including: The actual temperature data is acquired through a temperature sensor on each target test board, and the actual heat flow data is acquired through a heat flow sensor on each target test board.

4. The method according to claim 1, characterized in that Determining the target heat flux correction parameter based on the calculated heat flux data of each target test platelet obtained during the jet thermal environment data simulation process and the actual heat flux data of each target test platelet comprises: For each target test board, based on the actual heat flow data and calculated heat flow data of the target test board, determine the heat flow correction parameter corresponding to the target test board; The average value of the heat flux correction parameter corresponding to each target test platelet is used as the target heat flux correction parameter.

5. The method according to claim 3, characterized in that The step of determining the temperature response data of each target test platelet based on the actual heat flow data of each target test platelet, and determining the target temperature correction parameter based on the actual temperature data and the temperature response data of each target test platelet comprises: For each target test platelet, the target test platelet is divided into j layers along the thickness direction, where j is a positive integer; Determine the temperature response data of each layer of each target test platelet based on the actual heat flow data of each target test platelet and a preset temperature response calculation strategy, wherein the temperature response calculation strategy is determined based on the material emissivity of the thermal protection layer; The target temperature correction parameter is determined based on the temperature response data of each layer of each target test platelet and the actual temperature data of each target test platelet.

6. The method according to claim 5, characterized in that The determining the target temperature correction parameter based on the temperature response data of each layer of each target test platelet and the actual temperature data of each target test platelet comprises: For each target test board, determine, from each layer of temperature response data in the target test board, a first layer of temperature response data corresponding to the surface of the thermal protection layer, a second layer of temperature response data corresponding to the contact surface between the substrate and the thermal protection layer, and a third layer of temperature response data corresponding to the second surface; For each target test platelet, based on actual temperature data of the target test platelet, determine first temperature data corresponding to the surface of the heat protection layer, second temperature data corresponding to the contact surface between the substrate and the heat protection layer, and third temperature data corresponding to the second surface; Based on the first layer temperature response data, the second layer temperature response data, the third layer temperature response data and the corresponding first temperature data, second temperature data and third temperature data of each target test plate, the target temperature correction parameter is determined, wherein the target temperature correction parameter is a correction parameter for the material emissivity of the thermal protection layer.

7. The method according to any one of claims 1 to 6, characterized in that: The method further comprises: During the ground hot test of the engine, the difference between the thrust of the engine and the preset thrust is controlled to be smaller than a threshold.

8. An engine jet thermal environment data determination system, characterized in that: The method comprises a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor implements the method according to any one of claims 1 to 7 when executing the program.

9. A computer-readable storage medium, characterized in that: A computer program is stored thereon, and when the program is executed by a processor, the steps of the method according to any one of claims 1 to 7 are implemented.

10. A computer program product, characterized in that The computer program product comprises a computer program, and when the computer program is executed by a processor, the computer program is used to load and execute the method according to any one of claims 1 to 7.

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