Simulation and analysis method and system for thermal environment of multiple parallel engine nozzles of launch vehicles

Abstract

The present invention provides a method and system for simulating and analyzing the thermal environment of a multi-engine nozzle of a launch vehicle in parallel, the method comprising: obtaining simulation models of a rocket, a test bench and a single-sided guide groove, and meshing the simulation model; performing simulation calculation on the simulation model according to the jet parameters to obtain simulation calculation results; loading the surrounding fluid material parameters to perform simulation analysis on the simulation calculation results to obtain simulation analysis results, and determining the thermal environment data of the rocket, the single-sided guide groove and the test bench according to the simulation analysis results; judging whether the thermal environment data of the rocket, the single-sided guide groove and the test bench meet the design requirements, if not, redesigning the thickness, width and height of the test frame, the profile of the single-sided guide groove, and the thermal protection scheme of the rocket, and assigning them to the simulation model for resimulation calculation. The influence of the jet on the convection scouring and radiation heat flow of the single-sided guide groove, the test frame and the load-bearing frame can be obtained through an integrated design method.

Description

Technical Field

[0001] The invention relates to a rocket engine ground test, and in particular to a method and system for simulating and analyzing the thermal environment of multiple engine nozzles in parallel during a launch vehicle ground system test. Background Art

[0002] At present, relevant patents and literatures obtain the proportional relationship of radiation received at different positions on the bottom of the rocket based on the angle of jet expansion and the geometric relationship of the bottom of the rocket, through the radiation angle coefficient, and thus obtain the bottom heat flux distribution.

[0003] In the process of realizing the present invention, the inventors found that there are at least the following problems in the prior art: the prior art first simulates the flow field conditions, and then uses the radiation angle coefficient method to calculate the bottom thermal environment, which cannot accurately predict the thermal environment of the ground system test. Summary of the invention

[0004] In view of this, an embodiment of the present invention aims to provide a method and system for simulating and analyzing the thermal environment of multiple engine nozzles in parallel during a launch vehicle ground system test, so as to solve the problems in the prior art.

[0005] To achieve the above-mentioned purpose, in a first aspect, an embodiment of the present invention provides a method for simulating and analyzing the thermal environment of multiple engine nozzles in parallel during a launch vehicle ground system test, the method comprising:

[0006] Constructing simulation models of the rocket, the test bench and the single-sided guide trough, and meshing the simulation models;

[0007] Acquiring the rocket engine jet parameters, wherein the engine jet parameters include jet temperature, jet velocity and jet pressure;

[0008] Performing simulation calculation on the simulation model according to the engine jet parameters of the rocket to obtain simulation calculation results, wherein the simulation calculation results include the temperature, pressure and velocity of each grid in the simulation model;

[0009] Loading the simulation calculation results of the surrounding fluid material parameters to perform simulation analysis to obtain simulation analysis results, and determining the thermal environment data of the rocket, the single-sided guide groove and the test bench according to the simulation analysis results, wherein the simulation analysis results include the pressure, temperature, velocity and heat flow on each grid;

[0010] Determine whether the thermal environment data of the rocket, the single-sided guide groove and the test bench meet the design requirements. If the simulation design results do not meet the design requirements, redesign the thickness, width and height of the test frame, the profile of the single-sided guide groove, and the thermal protection scheme of the rocket, and assign them to the simulation model to re-simulate the calculation.

[0011] In some possible implementations, if the thermal environment data of the rocket, the single-sided guide groove, and the test bench meet the design requirements, the simulation analysis results are post-processed to obtain a pressure cloud map, a temperature cloud map, a velocity cloud map, and a heat flow cloud map of the rocket during takeoff;

[0012] Among them, the heat flow cloud map includes a single-sided guide groove heat flow cloud map, a test bench heat flow cloud map, a rocket body bottom heat flow cloud map and a rocket body tail section heat flow cloud map.

[0013] In some possible implementations, the simulation model is simulated and calculated according to the engine jet parameters of the rocket to obtain the simulation calculation results, specifically including:

[0014] The pressure, velocity and temperature of each grid point in the simulation model are obtained by solving the flow control equation by using the mass conservation equation, momentum conservation equation and energy conservation equation in combination with the viscosity coefficient; wherein,

[0015] The mass conservation equation is: ρ represents the density of the mixed gas at each grid point, and v represents the volume of the mixed gas at each grid point;

[0016] The momentum conservation equation is: f represents the remote external force on unit mass of fluid, and σ represents the stress;

[0017] The energy conservation equation is: ε represents the internal energy per unit mass of the fluid, D:σ represents the double dot product of the tensor, and k is the thermal conductivity.

[0018] In some possible implementations, before obtaining the simulation models of the rocket, the test bench, and the single-sided guide groove, the method further includes:

[0019] The three-dimensional structural models of the rocket, test bench and single-sided guide groove are preprocessed, and the preprocessing includes removing components that do not affect the simulation accuracy and components that are not concerned with the simulation, so as to obtain simulation models of the rocket, test bench and single-sided guide groove suitable for thermal simulation calculations.

[0020] In a second aspect, an embodiment of the present invention provides a launch vehicle ground system test multi-engine nozzle parallel thermal environment simulation and analysis system, the system comprising:

[0021] A simulation model acquisition and processing module is used to construct simulation models of the rocket, the test bench and the single-sided guide trough, and to perform meshing on the simulation models;

[0022] An engine jet parameter acquisition module is used to acquire the engine jet parameters of the rocket, wherein the engine jet parameters include jet temperature, jet velocity and jet pressure;

[0023] A simulation calculation module, used for performing simulation calculation on the simulation model according to the engine jet parameters of the rocket to obtain simulation calculation results, wherein the simulation calculation results include the temperature, pressure and velocity of each grid in the simulation model;

[0024] A simulation analysis module, used to load the surrounding fluid material parameters to perform simulation analysis on the calculation results, obtain simulation analysis results, and determine the thermal environment data of the rocket, the single-sided guide groove and the test bench according to the simulation calculation results, wherein the simulation analysis results include the pressure, temperature, velocity and heat flow on each grid;

[0025] A design requirement judgment module is used to judge whether the thermal environment data of the rocket, the single-sided guide groove and the test bench meet the design requirements;

[0026] The key parameter redesign module is used to redesign the thickness, width and height of the test frame, the profile of the single-sided guide groove, and the thermal protection scheme of the rocket if the simulation design results do not meet the design requirements, and assign them to the simulation model to re-simulate the calculation.

[0027] In some possible implementations, the system further includes:

[0028] A post-processing module, used for post-processing the simulation analysis results after the thermal environment data of the rocket, the single-sided guide groove and the test bench meet the design requirements, so as to obtain a pressure cloud map, a temperature cloud map, a velocity cloud map and a heat flow cloud map of the rocket during takeoff;

[0029] Among them, the heat flow cloud map includes a single-sided guide groove heat flow cloud map, a test bench heat flow cloud map, a rocket body bottom heat flow cloud map and a rocket body tail section heat flow cloud map.

[0030] In some possible implementations, the simulation calculation module is specifically used to:

[0031] The pressure, velocity and temperature of each grid point in the simulation model are obtained by solving the flow control equation by using the mass conservation equation, momentum conservation equation and energy conservation equation in combination with the viscosity coefficient; wherein,

[0032] The mass conservation equation is: ρ represents the density of the mixed gas at each grid point, and v represents the volume of the mixed gas at each grid point;

[0033] The momentum conservation equation is: f represents the remote external force on unit mass of fluid, and σ represents the stress;

[0034] The energy conservation equation is: ε represents the internal energy per unit mass of the fluid, D:σ represents the double dot product of the tensor, and k is the thermal conductivity.

[0035] In some possible implementations, the model acquisition and processing module is further used to:

[0036] The three-dimensional structural models of the rocket, test bench and single-sided guide groove are preprocessed, and the preprocessing includes removing components that do not affect the simulation accuracy and components that are not concerned with the simulation, so as to obtain simulation models of the rocket, test bench and single-sided guide groove suitable for thermal simulation calculations.

[0037] In a third aspect, an embodiment of the present invention provides an electronic device, including:

[0038] one or more processors;

[0039] A storage device for storing one or more programs. When the one or more programs are executed by the one or more processors, the one or more processors implement any one of the methods for simulating and analyzing the parallel thermal environment of multi-engine nozzles of a launch vehicle described in the first aspect.

[0040] In a fourth aspect, an embodiment of the present invention provides a computer-readable medium having a computer program stored thereon, which, when executed by a processor, implements a method for simulating and analyzing the parallel thermal environment of multiple engine nozzles of a launch vehicle as described in any one of the first aspects.

[0041] The beneficial technical effects of the above technical solution are:

[0042] The embodiment of the present invention provides a method and system for the thermal environment of an engine jet and the flow diversion of a single-sided flow guide groove. The method includes: constructing a simulation model of a rocket, a test bench and a single-sided flow guide groove, and meshing the simulation model; performing simulation calculation on the simulation model according to the engine jet parameters of the rocket, and obtaining the temperature, pressure and speed of each grid in the simulation model; loading the simulation calculation results of the surrounding fluid material parameters for simulation analysis, obtaining the simulation analysis results, and determining the thermal environment data of the rocket, the single-sided flow guide groove and the test bench according to the simulation analysis results; judging whether the thermal environment data of the rocket, the single-sided flow guide groove and the test bench meet the design requirements, if the simulation design results do not meet the design requirements, redesigning the thickness, width and height of the test bench, the profile of the single-sided flow guide groove, and the thermal protection scheme of the rocket, and assigning them to the simulation model for resimulation calculation. The embodiment of the present invention can accurately predict the thermal environment of the bottom of the rocket engine and quickly, efficiently and timely divert the gas jet by performing simulation analysis on the thermal environment of the engine jet and the flow diversion of the single-sided flow guide groove, thereby improving the success rate of rocket launch. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0044] Figure 1 This is a flow chart of a method for simulating and analyzing the thermal environment of multiple engine nozzles in parallel for a launch vehicle according to an embodiment of the present invention;

[0045] Figure 2 The thermal environment simulation analysis process of the launch vehicle ground system test run according to the embodiment of the present invention;

[0046] Figure 3 is a schematic diagram of a simulation grid according to an embodiment of the present invention;

[0047] Figure 4 is a pressure cloud diagram of a simulation result of an embodiment of the present invention;

[0048] Figure 5 is a density cloud diagram of simulation results of an embodiment of the present invention;

[0049] Figure 6 is a temperature cloud diagram of a simulation result of an embodiment of the present invention;

[0050] Figure 7 It is a speed cloud diagram of the simulation result of an embodiment of the present invention;

[0051] Figure 8 This is a heat flow cloud diagram of a load-bearing frame according to an embodiment of the present invention;

[0052] Fig. 9 is a heat flow cloud diagram of the bottom plate of an embodiment of the present invention;

[0053] Fig.10 is a heat flow cloud diagram of a test bench according to an embodiment of the present invention;

[0054] Fig.11 This is a heat flow cloud diagram of a single-sided guide groove according to an embodiment of the present invention;

[0055] Fig.12 is a pressure cloud diagram of a single-sided guide groove according to an embodiment of the present invention;

[0056] Fig.13 It is a functional block diagram of a launch vehicle multi-engine nozzle parallel thermal environment simulation and analysis system according to an embodiment of the present invention;

[0057] Fig.14 It is a functional block diagram of another launch vehicle multi-engine nozzle parallel thermal environment simulation and analysis system according to an embodiment of the present invention;

[0058] Fig.15 It is a functional block diagram of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0059] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0060] The embodiment of the present invention comprehensively considers the influence of multiple engines in parallel and turbine exhaust on the engine jet through an integrated design method. In addition, the influence of the jet on the convection and radiation heat flow of the single-sided guide groove, the test bench, and the load-bearing frame can be obtained. The test bench is used for testing to detect whether the rocket system, engine and other equipment are working properly. During the test run, the rocket will be fixed to the test bench to prevent the rocket from taking off. The launch pad is a device for the rocket to take off at the launch range after the test run is normal.

[0061] Definition of technical terms:

[0062] Thermal protection: The basic purpose of thermal protection is to ensure the safety of the aircraft and to keep the internal payload or equipment within the allowable temperature and pressure range.

[0063] Flight vehicle: A device that flies within the atmosphere or in space outside the atmosphere.

[0064] Steady state: Same as steady state, without considering the influence of time changes.

[0065] Transient state: Same as unsteady state, but taking into account the influence of time changes.

[0066] Thermal radiation: electromagnetic wave radiation caused by heat.

[0067] Thermal conduction: The process by which energy is transferred from the higher temperature part of an object to the lower temperature part due to the collision of a large number of molecules, atoms or electrons.

[0068] Thermal convection: The process of heat exchange between fluid and solid when the fluid flows over the solid surface.

[0069] Aerodynamic heat: The process in which the friction generated by an object moving relative to the air or other gas at high speed is converted into heat.

[0070] Trajectory: The motion of a projectile from the start of launch to the end point.

[0071] The test bench for the ground system test of the launch vehicle includes: a test frame and a load-bearing frame (commonly known as a basket, used to fix the rocket body and the test frame), as well as other ancillary equipment. The load-bearing frame is mainly responsible for providing stable support for the rocket during the rocket test or before launch, and bears the weight of the rocket. The load-bearing frame can serve as the bottom or base part of the launcher to provide stable support for the launcher. The load-bearing frame can be set above the rocket engine nozzle, where the rocket body and the test frame are connected. Ancillary equipment may include fuel supply systems, liquid oxygen supply systems, control systems, communication systems, safety systems, etc. These ancillary equipment are all designed to ensure the smooth progress of the test or launch process, while also ensuring the safety of personnel and equipment. For example, the fuel and liquid oxygen supply systems are responsible for providing the required fuel for the rocket, the control system is responsible for monitoring and adjusting the status and parameters of the rocket, and the safety system is responsible for taking timely countermeasures when abnormal situations occur.

[0072] The ground system test of the launch vehicle can accurately assess the compatibility of the system and lay a solid foundation for the success of the flight test. During the ground test, the layout of multiple engines in parallel and the high-temperature, high-speed, and high-pressure gas generated by the engine nozzle jet will strongly wash the test bench, the single-sided guide groove, and generate strong radiation to nearby equipment and instruments. Therefore, accurately predicting the thermal environment of the ground system test is of great significance to the safety of the system test and the test process.

[0073] The embodiment of the present invention takes into account the impact of multiple engines in parallel and turbine exhaust on the engine jet flow of a launch vehicle through an integrated design method, and can obtain the impact of the jet flow on the convection scouring and radiation heat flow of the single-sided guide groove, the test frame and the load-bearing frame.

[0074] In some embodiments, multiple (e.g., 9) engine layouts use exhaust nozzle jets to reduce the thermal environment at the bottom of the rocket body. The main function of the single-sided guide groove is to guide or control the flow direction of the fluid to reduce the thermal impact on the rocket body. When multiple engine layouts are adopted, the gas jet guides the single-sided guide groove, and the thermal environment at the bottom of the rocket body and the launcher is more severe. The single-sided guide groove plays a key role in the rocket launch process, especially in the case of multiple engine layouts. The single-sided guide groove only needs to consider the exhaust flow on one side. When the rocket adopts a multiple engine (e.g., 9) layout, the exhaust / gas emissions and heat will greatly increase, and the design of the single-sided guide groove becomes more complex and critical. The exhaust nozzle of each engine will produce high-temperature and high-speed gas jets. If these gas jets directly impact the bottom of the rocket body or the launcher, they will not only cause serious thermal damage, but also may affect the stability and launch safety of the rocket. In order to reduce the thermal environment at the bottom of the rocket body, the design and adjustment of the exhaust nozzle are crucial. By precisely controlling the direction and angle of the nozzle, it is possible to ensure that the exhaust gas can diffuse quickly after leaving the rocket, reducing the thermal shock to the rocket body and the launch pad. The single-sided guide groove plays a guiding role in this process, ensuring that the exhaust gas can flow along the predetermined path and minimize the thermal impact on the rocket body and the launch pad. The high temperature and high speed characteristics of the gas jet mean that it will cause serious thermal damage to any object in direct contact. For the single-sided guide groove, the bottom of the rocket body and the launch pad, effective thermal protection measures should be taken, such as using high temperature resistant materials and applying thermal protective coatings. The design of the single-sided guide groove also needs to take into account the dynamic characteristics of the gas jet to ensure that the exhaust gas flow can be effectively guided under various possible launch conditions (such as changes in wind speed, temperature, air pressure, etc.). Therefore, the single-sided guide groove plays a vital role in the launch of rockets with a multi-engine layout. It can effectively guide and control the high-temperature and high-speed gas jet, protect the rocket body and the launch pad from serious thermal damage, and ensure the safety and success of the rocket launch.

[0075] In some embodiments, the temperature, pressure and velocity simulation analysis prediction of the impact position of the gas jet and the single-sided guide groove when the single-sided guide groove is single-sided guide groove is solved, as well as the accurate prediction of the harsh thermal environment. In the case of single-sided guide groove with single-sided guide groove, its flow characteristics and thermal environment are different from those of double-sided guide groove. Single-sided guide groove may cause problems such as uneven flow and uneven temperature distribution, which will put higher requirements on the thermal protection of the rocket body. The gas generated by the rocket engine is ejected at high speed through the nozzle, and a large amount of heat is generated in this process. These high-temperature gases will cause serious heat loads on the bottom of the rocket body and the single-sided guide groove. The position where the gas jet collides with the single-sided guide groove is an area with concentrated heat, large pressure changes and high flow speed. Accurately predicting the temperature, pressure and velocity changes at this position is crucial to the safety and stability of the rocket. During the launch and flight of the rocket, the rocket body will experience an extremely harsh thermal environment. Accurately predicting this thermal environment, especially the thermal environment at the impact position of the gas jet and the single-sided guide groove, can help engineers better design the thermal protection system of the rocket body and ensure the safety performance of the rocket under various extreme conditions.

[0076] In some embodiments, the single-sided guide groove profile is optimized, and different specifications of thermal protection schemes are carried out for the impact position, other positions of the single-sided guide groove, the side walls of the single-sided guide groove, and the second half of the single-sided guide groove. This embodiment focuses on optimizing the profile of the single-sided guide groove, and formulates different specifications of thermal protection schemes for different parts of the single-sided guide groove (such as the impact position, other positions of the single-sided guide groove, the side walls of the single-sided guide groove, and the second half of the single-sided guide groove). The single-sided guide groove profile optimization refers to improving the shape and structure of the single-sided guide groove to improve its diversion effect and thermal protection performance. The optimization goals may be to reduce the resistance of the fluid, improve the uniformity of the flow distribution, reduce the heat load, etc. The impact position is the area where the gas jet of the rocket engine is in direct contact with the single-sided guide groove, and is subject to extremely high heat loads. Therefore, it is necessary to specially design an efficient thermal protection scheme for the impact position, such as using high thermal conductivity materials, adding thermal barrier coatings, and using cooling systems to ensure that the area can withstand extreme high temperatures. In addition to the impact position, other parts of the single-sided guide groove will also be affected by heat to a certain extent. According to the heat load characteristics and requirements of the specific location, formulate corresponding thermal protection schemes, such as adding insulation layers, improving material heat resistance, etc. The side walls of the single-sided guide groove are the parts that are in contact with the external environment, and thermal protection also needs to be considered. The thermal protection scheme for the side walls of the single-sided guide groove may include the use of high-temperature resistant materials, the addition of insulation layers, and the design of a reasonable heat dissipation structure to reduce the transfer of heat to the rocket body. The second half of the single-sided guide groove may be affected by the aftermath and heat of the gas jet. For this area, corresponding thermal protection measures can be taken, such as adding thermal barrier coatings, improving material heat resistance, optimizing fluid dynamics design, etc. By formulating thermal protection schemes of different specifications for different locations, this embodiment aims to comprehensively improve the thermal protection performance of the single-sided guide groove and ensure the stability and safety of the rocket in various thermal environments.

[0077] In some embodiments, the preparation for predicting the radiant heat environment above the gas generated by the rocket engine is solved, and thermal protection work is carried out for the bottom of the rocket body, the launcher, and the attached test equipment on the launcher. Solving the prediction problem of the radiant heat environment above the gas generated by the rocket engine involves modeling and simulating the heat and radiation generated by the rocket engine gas to predict its impact on the surrounding environment. Thermal protection work is carried out at the bottom of the rocket body, which includes using insulation materials or taking other measures at the bottom of the body to reduce the impact of heat radiated from the engine gas on the body structure. Thermal protection work is carried out on the launcher. The launcher is a structure that supports the rocket and keeps it stable. It will also be affected by the radiant heat of the gas during the rocket launch process. Therefore, similar thermal protection measures need to be taken to protect the launcher. Thermal protection work is carried out on the attached equipment (test or detection equipment) on the launcher. These attached equipment may include sensors, cameras, etc., which are used to monitor various parameters during the rocket launch process. Similarly, these attached equipment also need to be protected to avoid being affected by the radiant heat of the gas. Therefore, the purpose of this embodiment is to reduce the impact of the radiant heat of the gas on the rocket body, the launcher and the attached test equipment during the rocket launch process through prediction and protective measures to ensure the safety and success of the rocket launch.

[0078] Figure 1 FIG. 1 is a flow chart of a method for simulating and analyzing the thermal environment of multiple engine nozzles in parallel during a launch vehicle ground system test according to an embodiment of the present invention. Figure 1 As shown, the method comprises the following steps:

[0079] Step S11, constructing an (integrated) simulation model of the rocket, the test bench and the single-sided guide trough, and meshing the simulation model.

[0080] In this embodiment, constructing a simulation model of the rocket, test bench and single-sided guide trough refers to modeling the rocket, test bench and single-sided guide trough as a whole, and meshing refers to dividing the launch equipment and the space near it into small volumes, and using numerical simulation methods to couple the bottom thermal environment, instruments and equipment, and the rocket to solve the temperature, velocity and pressure values ​​on each small block (grid). Figure 3 It is a schematic diagram of the simulation body grid of a rocket, a test bench and a single-sided guide trough in an embodiment of the present invention. Through grid division, grids of different sizes are adopted for the rocket, the test bench and the single-sided guide trough, and boundary layer grids are added to better capture convection and radiation, which not only meets the calculation accuracy, but also takes into account the calculation time and calculation resource cost issues.

[0081] Step S12, obtaining the rocket's engine jet parameters.

[0082] In this embodiment, different engine models correspond to different engine jet parameters, and the engine jet parameters can be obtained by calculation, for example, the chemical reaction of gas combustion can be solved by simulation, and the engine jet parameters can be determined according to the chemical reaction formula (chemical reaction of gas combustion, such as CH4+0.5O2→CO+2H2, CH4+H2O→CO+3H2, CO+H2O→CO2+H2, H2+0.5O2→H2O, CO+0.5O2→CO2), and the engine jet parameters include jet temperature T, jet velocity V and jet pressure P. Among them, the jet temperature T, jet velocity V and jet pressure P can change with time, and transient simulation analysis can be performed at this time; the jet temperature T, jet velocity V and jet pressure P can also be the values ​​at a certain time t, and steady-state simulation analysis can be performed at this time.

[0083] Step S13, performing simulation calculation on the simulation model according to the rocket engine jet parameters to obtain simulation calculation results, wherein the simulation calculation results include the temperature, pressure and velocity of each grid in the simulation model.

[0084] Step S14, load the surrounding fluid material parameters to perform simulation analysis on the simulation calculation results, obtain simulation analysis results, and determine the thermal environment data of the rocket, single-sided guide groove and test bench according to the simulation analysis results, wherein the simulation analysis results include pressure, temperature, velocity and heat flow on each grid.

[0085] In this embodiment, the surrounding fluid material refers to the gas surrounding the rocket, including parameters such as gas temperature, gas pressure and gas viscosity. The temperature, pressure and velocity of each grid in the simulation model are calculated, and the gas surrounding the rocket is loaded for joint simulation analysis to determine the pressure, temperature, heat flow and velocity of the solid part and the fluid part during the rocket launch process. Among them, the solid refers to the part with physical structure such as the tail of the rocket, and the solid part includes pressure, temperature, and heat flow. The fluid refers to the jet of the engine and the surrounding air, and the fluid part includes pressure, temperature and velocity.

[0086] Step S15, determines whether the thermal environment data of the rocket, the single-sided guide groove and the test bench meet the design requirements. If the simulation design results do not meet the design requirements, redesign the thickness, width and height of the test frame, the profile of the single-sided guide groove, and the thermal protection scheme of the rocket, and assign them to the simulation model for re-simulation calculation.

[0087] In this embodiment, since there will be many monitoring and control instruments and equipment near the launch pad before launching at the target range, the rocket takeoff jet will greatly threaten its safety. Therefore, in this embodiment, by comprehensively considering the relationship between the thermal environment, instrument and equipment safety, single-sided guide groove diversion and safe launch of the carrier rocket, the thermal environment of the engine jet and the single-sided guide groove diversion are carried out to obtain the thermal environment parameters of the bottom of the rocket body, the environmental parameters of the single-sided guide groove, the environmental parameters of the test bench, and the flow field temperature and speed during the rocket takeoff process. The thickness, width and height of the test bench are designed appropriately, the profile of the single-sided guide groove, and the thermal protection scheme of the rocket are designed to accurately predict the thermal environment at the bottom of the engine and quickly, efficiently and timely divert the gas jet, so as to improve the success rate of safe and successful launch of the carrier rocket.

[0088] In addition, in this embodiment, the thermal protection scheme can propose high-temperature and medium-temperature zoned thermal control schemes based on the characteristics of the engine and its plume as high-temperature heat sources with different temperature ranges. For example, a hood is used to protect the convection generated by the gas flushing; an aluminum-plated film is used for reflection for radiation; and an air layer and thermal insulation materials (materials with low thermal conductivity such as plastic) are used for thermal control for heat conduction. For example, in the high-temperature area of ​​the engine nozzle, a heat shield is used for temperature control; and in the medium-temperature radiation of the plume, a polyimide aluminum-plated insulation component is used, where the insulation component refers to 15 to 20 layers of polyimide aluminum-plated foil film and polyester mesh alternately laid.

[0089] In some embodiments, if the thermal environment data of the rocket, the single-sided guide groove and the test bench meet the design requirements, the simulation analysis results are post-processed to obtain the pressure cloud map, temperature cloud map, velocity cloud map and heat flow cloud map of the rocket during takeoff; wherein the heat flow cloud map includes the heat flow cloud map of the single-sided guide groove, the heat flow cloud map of the test bench, the heat flow cloud map of the bottom of the rocket body and the heat flow cloud map of the tail section of the rocket body.

[0090] Figure 4 is a pressure cloud diagram of the simulation result of an embodiment of the present invention, Figure 5 is a density cloud diagram of the simulation results of an embodiment of the present invention, Figure 6 is a temperature cloud diagram of the simulation result of an embodiment of the present invention, Figure 7 is a velocity cloud diagram of the simulation result of an embodiment of the present invention, Figure 8 This is a heat flow cloud diagram of the load-bearing frame of an embodiment of the present invention. Fig. 9 This is a heat flow cloud diagram of the bottom plate of an embodiment of the present invention. Fig.10 This is a heat flow cloud diagram of the test bench of the embodiment of the present invention. Fig.11 This is a heat flow cloud diagram of a single-sided guide groove according to an embodiment of the present invention. Fig.12 is a pressure cloud diagram of a single-sided guide groove according to an embodiment of the present invention; Figures 4 to 12As shown, in this embodiment, through data analysis and visualization processing software (such as Tecplot), a pressure cloud map is drawn according to the pressure value on each grid, a velocity cloud map is drawn according to the velocity value on each grid, a temperature cloud map is drawn according to the temperature value on each grid, and a heat flow cloud map is obtained according to the heat flow value on each grid;

[0091] from Figure 4 Pressure cloud diagram and Figure 5 From the density cloud map, we can see that the high-temperature, high-speed, high-pressure gas is ejected from the nozzle, and after passing through the guide groove, a high-pressure area appears above the "V"-shaped front section. This indicates that some gas rolls over here, and its radiation will have a serious radiation impact on the test equipment and the rocket body. Therefore, it is necessary to carry out optimization design for the "V"-shaped front section, and carry out thermal protection design work for the test equipment affected by this.

[0092] from Figure 6 It can be concluded from the temperature cloud map that by optimizing the single-sided guide groove profile, the gas can fit the single-sided guide groove better, and the gas can be quickly exported to meet the needs of rapid and safe rocket launch. Through the optimization simulation between the top of the single-sided guide groove and the rocket nozzle, the engine gas reflux at the high point of the single-sided guide groove can be reduced, and the wall gas reflux affects the normal operation of the engine.

[0093] from Figure 7 It can be concluded from the velocity cloud diagram that by using the exhaust nozzle jet for the nine-nozzle engine, the low temperature environment and jet velocity of the exhaust jet can suppress the gas reflux and reduce the thermal environment at the bottom of the rocket body.

[0094] from Figures 8 to 11 It can be concluded from multiple heat flow cloud diagrams that through surface optimization and exhaust jet parameter design, the gas can be quickly discharged, greatly reducing the thermal environment on the equipment, optimizing the thermal protection scheme, reducing costs and supporting the rapid launch of the rocket. And through the surface optimization of the single-sided guide groove, the heat flow on the launch platform shelf is also significantly reduced.

[0095] from Fig.12 From the pressure cloud diagram of the single-sided guide groove, it can be seen that a high-pressure area appears directly below the nozzle, where targeted flushing and high-temperature thermal protection solutions should be designed. At the same time, through optimization of the diversion, the range and pressure of the secondary high-pressure area at the front of the nozzle and the bottom of the "V"-shaped guide groove are reduced.

[0096] In this embodiment, through data analysis and visualization processing software (such as Tecplot), a pressure cloud map is drawn according to the pressure value on each grid, a velocity cloud map is drawn according to the velocity value on each grid, a temperature cloud map is drawn according to the temperature value on each grid, and a heat flow cloud map is obtained according to the heat flow value on each grid; subsequent improvement plans can be made based on the simulation cloud map, and downstream professionals can also carry out production work based on this cloud map, such as selecting materials that can meet the temperature.

[0097] In some embodiments, the simulation model is simulated and calculated according to the rocket engine jet parameters to obtain the simulation calculation results, specifically including:

[0098] Activate the energy equation, which includes the mass conservation equation, momentum conservation equation and energy conservation equation. Combine the viscosity coefficient to jointly solve the flow control equation through the mass conservation equation, momentum conservation equation and energy conservation equation to obtain the pressure, velocity and temperature of each grid point in the upper stage thermal control simulation model; where,

[0099] The mass conservation equation is: ρ represents the density of the mixed gas at each grid point, and v represents the volume of the mixed gas at each grid point; wherein the mixed gas includes water, carbon dioxide, oxygen, and carbon monoxide.

[0100] The momentum conservation equation is: f represents the remote external force on unit mass of fluid, and σ represents the stress;

[0101] The energy conservation equation is: ε represents the internal energy per unit mass of the fluid, D:σ represents the double dot product of the tensor, and k is the thermal conductivity.

[0102] In this embodiment, the viscosity coefficient is combined to take into account the influence of air viscosity in the calculation, and the pressure P, velocity V and temperature T parameters on each grid are solved through simulation calculation. By solving the flow control equation, namely Navier-Stokes (NS equation for short), the parameter value on each grid can be obtained. This calculation is similar to setting the engine nozzle throat as the gas parameter, the calculation domain boundary is the atmospheric parameter, and the solution is the relevant value of each grid after the calculation from the engine nozzle throat to the calculation boundary is stable.

[0103] In some embodiments, before obtaining the simulation models of the rocket, the test bench, and the single-sided guide groove, the method further includes:

[0104] The three-dimensional structural models of the rocket, test bench and single-sided guide groove are preprocessed, which includes removing small-sized components that do not affect the simulation accuracy and components that are not of concern in the simulation, so as to obtain simulation models of the rocket, test bench and single-sided guide groove suitable for thermal simulation calculations.

[0105] In this embodiment, a three-dimensional structural model integrating a rocket, a single-sided guide trough and a test bench must first be drawn. After the three-dimensional structural model is obtained, the three-dimensional structural model can be preprocessed and simplified to make it a model suitable for thermal simulation calculations. For example, small-sized components that do not affect the simulation accuracy and components that are not of concern to the simulation can be removed. The model is then meshed using computational fluid dynamics (CFD) pre-processing mesh generation software (such as pointwise software) to divide the simulation model into multiple grids.

[0106] In order to enable those skilled in the art to better understand the technical solution provided by the embodiment of the present invention, an engine jet thermal environment and a single-sided guide groove guide method provided by the embodiment of the present invention are described in detail below. Figure 3 A flow diagram of a rocket engine jet thermal environment and a single-sided guide groove flow guide provided in an embodiment of the present invention, specifically:

[0107] In this embodiment, firstly, a three-dimensional structural model integrating a rocket, a single-sided guide trough and a test bench is drawn, and then the three-dimensional structural model is preprocessed to make it a simulation model suitable for thermal simulation calculation.

[0108] In this embodiment, the simulation analysis method includes a simulation preparation stage, a simulation design stage, and a result post-processing stage. In the simulation design stage, a three-dimensional structural model integrating a rocket, a single-sided guide groove, and a test bench is first drawn, and then the three-dimensional structural model is preprocessed to make it a simulation model suitable for thermal simulation calculation, and the simulation model is meshed, and the simulation model is divided into multiple grids, and then the rocket jet parameters are obtained, which include jet pressure tP, jet temperature tT, and jet velocity tV. T, P, and V can be transient parameters that change with time t, or they can be steady-state parameters. After completing the simulation preparation work, the simulation design stage is carried out. If it is found that the current design does not meet the requirements in the simulation design stage, it is necessary to redesign key parameters, such as the thickness, width, and height of the test bench, the profile of the single-sided guide groove, and the thermal protection scheme of the rocket, and re-assign them to the simulation model, and re-simulate the calculation.

[0109] In the simulation design stage, after activating the energy equation, the viscosity coefficient is loaded and selected to calculate the parameter values ​​on each grid in the simulation model, including pressure, temperature and speed. Finally, the fluid material parameters (i.e., the air around the rocket) are loaded for simulation analysis to obtain the pressure, temperature and speed of the solid during the rocket flight, as well as the pressure, temperature and heat flow of the fluid. Based on the data obtained from the previous simulation analysis, the thickness, width and height of the test frame, the profile of the single-sided guide groove, and the rocket's thermal protection scheme and other key parameters are evaluated to see if they meet the design requirements. If they do not meet the design requirements, it is necessary to return to the simulation preparation stage to readjust these key parameter designs and re-perform simulation calculation analysis until they meet the design requirements. If they meet the design requirements, the result post-processing stage is entered.

[0110] In the post-processing stage of the results, when the key parameters such as the thickness, width and height of the designed test frame, the profile of the single-sided guide groove, and the thermal protection scheme of the rocket meet the requirements, the simulation analysis results are also post-processed in this embodiment to obtain the pressure cloud map, temperature cloud map, velocity cloud map and heat flow cloud map of the rocket during takeoff; wherein, the heat flow cloud map includes the heat flow cloud map of the single-sided guide groove, the heat flow cloud map of the test bench, the heat flow cloud map of the bottom of the rocket body and the heat flow cloud map of the tail section of the rocket body. The temperature rises sharply where the gas hits the profile of the guide groove. At the impact point, there is a sharp increase in temperature and pressure, and the high-speed gas washes the profile here, often causing large pits on the profile. Accurately predict the position, temperature, and flow rate parameters here to provide support for downstream professional thermal protection schemes.

[0111] In this embodiment, Tecplot data analysis and visualization software can be used to draw a pressure cloud map according to the pressure value on each grid, draw a velocity cloud map according to the velocity value on each grid, draw a temperature cloud map according to the temperature value on each grid, and obtain a heat flow cloud map according to the heat flow value on each grid; subsequent improvement plans can be made based on the simulation cloud map, and downstream professionals can also carry out production work based on this cloud map, such as selecting materials that can meet the temperature requirements.

[0112] Fig.13 The present invention is a system for guiding the thermal environment of an engine jet and a single-sided guide groove, such as Fig.13 As shown, the system 100 includes:

[0113] The simulation model acquisition and processing module 110 is used to construct simulation models of the rocket, the test bench and the single-sided guide trough, and to mesh the simulation models.

[0114] In this embodiment, constructing a simulation model of the rocket, test bench and single-sided guide trough refers to modeling the rocket, test bench and single-sided guide trough as a whole, and meshing refers to dividing the launch equipment and the space near it into small volumes, and using numerical simulation methods to couple the bottom thermal environment, instruments and equipment, and the rocket to solve the temperature, velocity and pressure values ​​on each small block (grid).

[0115] The engine jet parameter acquisition module 120 is used to obtain the engine jet parameters of the rocket.

[0116] In this embodiment, different engine models correspond to different engine jet parameters, and the engine jet parameters can be calculated in advance, and the engine jet parameters include jet temperature T, speed V and pressure P, and then the acquisition module 120 can directly acquire the calculated engine jet parameters. Among them, the temperature T, speed V and pressure P can change with time, and transient simulation analysis can be performed at this time; the temperature T, speed V and pressure P can also be the value at a certain moment, and steady-state simulation analysis can be performed at this time.

[0117] A simulation calculation module 130 is used to perform simulation calculation on the simulation model according to the rocket engine jet parameters to obtain simulation calculation results, wherein the simulation calculation results include the temperature, pressure and velocity of each grid in the simulation model;

[0118] The simulation analysis module 140 is used to load the surrounding fluid material parameters to perform simulation analysis on the calculation results, obtain simulation analysis results, and determine the thermal environment data of the rocket, single-sided guide groove and test bench according to the simulation calculation results, wherein the simulation analysis results include pressure, temperature, velocity and heat flow on each grid.

[0119] In this embodiment, the surrounding fluid material refers to the gas surrounding the rocket. The simulation analysis module 140 loads the gas surrounding the rocket for joint simulation analysis based on the temperature, pressure and velocity of each grid in the simulation model to determine the pressure, temperature, heat flow and velocity of the solid part and the fluid part during the rocket launch process. Among them, the solid refers to the part with physical structure such as the tail of the rocket, and the solid part includes pressure, temperature, and heat flow. The fluid refers to the jet of the engine and the surrounding air, and the fluid part includes pressure, temperature and velocity.

[0120] The design requirement judgment module 150 is used to judge whether the thermal environment data of the rocket, the single-sided guide groove and the test bench meet the design requirements;

[0121] The key parameter redesign module 160 is used to redesign the thickness, width and height of the test frame, the profile of the single-sided guide groove, and the thermal protection scheme of the rocket if the simulation design results do not meet the design requirements, and assign them to the simulation model to re-simulate the calculation.

[0122] In this embodiment, since there will be many monitoring and control instruments and equipment near the launch pad before launching at the target range, the rocket takeoff jet will greatly threaten its safety. Therefore, in this embodiment, by comprehensively considering the relationship between the thermal environment, instrument and equipment safety, single-sided guide groove diversion and safe launch of the carrier rocket, the thermal environment of the engine jet and the single-sided guide groove diversion are carried out to obtain the thermal environment parameters of the bottom of the rocket body, the environmental parameters of the single-sided guide groove, the environmental parameters of the test bench, and the flow field temperature and speed during the rocket takeoff process. The thickness, width and height of the test bench are designed appropriately, the profile of the single-sided guide groove, and the thermal protection scheme of the rocket are designed to accurately predict the thermal environment at the bottom of the engine and quickly, efficiently and timely divert the gas jet, so as to improve the success rate of safe and successful launch of the carrier rocket.

[0123] Fig.14 Another embodiment of the present invention is a system for guiding the flow of an engine jet thermal environment and a single-sided guide groove, such as Fig.14 As shown, in some embodiments, the system 100' further includes:

[0124] The post-processing module 170 is used to post-process the simulation analysis results after the thermal environment data of the rocket, the single-sided guide groove and the test bench meet the design requirements, so as to obtain the pressure cloud map, temperature cloud map, velocity cloud map and heat flow cloud map of the rocket during takeoff; wherein the heat flow cloud map includes the heat flow cloud map of the single-sided guide groove, the heat flow cloud map of the test bench, the heat flow cloud map of the bottom of the rocket body and the heat flow cloud map of the tail section of the rocket body.

[0125] In this embodiment, the post-processing module 160 uses data analysis and visualization processing software (such as Tecplot) to draw a pressure cloud map according to the pressure value on each grid, draw a velocity cloud map according to the velocity value on each grid, draw a temperature cloud map according to the temperature value on each grid, and obtain a heat flow cloud map according to the heat flow value on each grid.

[0126] In some embodiments, the simulation calculation module 130 is specifically used to:

[0127] Activate the energy equation, which includes the mass conservation equation, momentum conservation equation and energy conservation equation, and then solve the flow control equation by combining the mass conservation equation, momentum conservation equation and energy conservation equation in combination with the viscosity coefficient to obtain the pressure, velocity and temperature of each grid point in the upper stage thermal control simulation model; wherein,

[0128] The mass conservation equation is: ρ represents the density of the mixed gas at each grid point, and v represents the volume of the mixed gas at each grid point; the mixed gas includes water, carbon dioxide, oxygen, carbon monoxide

[0129] The momentum conservation equation is: f represents the remote external force on unit mass of fluid, and σ represents the stress;

[0130] The energy conservation equation is: ε represents the internal energy per unit mass of the fluid, D:σ represents the double dot product of the tensor, and k is the thermal conductivity.

[0131] In this embodiment, combining the viscosity coefficient means that the influence of air viscosity is taken into account in the calculation, and the pressure P, velocity V and temperature T parameters on each grid are solved through simulation calculation. By solving the flow control equation, namely Navier-Stokes (NS equation for short), the parameter value on each grid can be obtained. This calculation is similar to setting the engine nozzle throat as the gas parameter, the calculation domain boundary is the atmospheric parameter, and the solution is the relevant value (pvt) of each grid after the calculation is stable from the engine nozzle throat to the calculation boundary. In some embodiments, the model acquisition and processing module 110 is also used to:

[0132] The three-dimensional structural models of the rocket, test bench and single-sided guide groove are preprocessed, and the preprocessing includes removing components that do not affect the simulation accuracy and components that are not concerned with the simulation, so as to obtain simulation models of the rocket, test bench and single-sided guide groove suitable for thermal simulation calculations.

[0133] In this embodiment, it is necessary to first draw a three-dimensional structural model that integrates a rocket, a single-sided guide trough and a test bench. After obtaining the three-dimensional structural model, the model can be preprocessed and simplified to make it a model suitable for thermal simulation calculations. For example, small-sized components that do not affect the simulation accuracy and components that are not of concern to the simulation are removed, and then the model is meshed using pointwise software.

[0134] If the integrated module / module is implemented in the form of a software function module and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the present invention implements all or part of the processes in the above-mentioned embodiment method, and can also be completed by instructing the relevant hardware through a computer program. The computer program can be stored in a computer-readable storage medium, and the computer program can implement the steps of the above-mentioned various method embodiments when executed by the processor. Among them, the computer program includes computer program code, and the computer program code can be in source code form, object code form, executable file or some intermediate form. The computer-readable medium may include: any entity or device capable of carrying the computer program code, recording medium, U disk, mobile hard disk, disk, optical disk, computer memory, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), electric carrier signal, telecommunication signal and software distribution medium. Of course, there are other ways of readable storage media, such as quantum memory, graphene memory, etc. It should be noted that the content contained in the computer-readable medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, computer-readable media does not include electrical carrier signals and telecommunication signals.

[0135] The design method implemented by the present invention adopts pointwise for mesh pre-processing, fluent for simulation calculation, and tecplot for post-processing.

[0136] The simulation software implemented in the present invention can be replaced by, for example, C++ or Python.

[0137] The implementation of the present invention only specifies a calculation process for realizing the technical requirements, and the same effect can be achieved by adding or replacing some steps.

[0138] The embodiment of the present invention takes into account the impact of multiple engines in parallel and turbine exhaust on the engine jet flow of a launch vehicle through an integrated design method, and can obtain the impact of the jet flow on the convection scouring and radiation heat flow of the single-sided guide groove, the test frame, and the load-bearing frame.

[0139] Those skilled in the art can clearly understand that, for the convenience and simplicity of description, only the division of the above-mentioned functional modules and modules is used as an example for illustration. In actual applications, the above-mentioned function allocation can be completed by different functional modules and modules as needed, that is, the internal structure of the system can be divided into different functional modules or modules to complete all or part of the functions described above. The functional modules and modules in the embodiment can be integrated into a processing module, or each module can exist physically alone, or two or more modules can be integrated into one module. The above-mentioned integrated modules can be implemented in the form of hardware or in the form of software functional modules. In addition, the specific names of the functional modules and modules are only for the convenience of distinguishing each other, and are not used to limit the scope of protection of this application. The specific working process of the modules and modules in the above-mentioned system can refer to the corresponding process in the aforementioned method embodiment, which will not be repeated here.

[0140] An embodiment of the present invention also provides a computer-readable storage medium, in which a computer program is stored. When the computer program is executed by a processor, each step of the above-mentioned launch vehicle multi-engine nozzle parallel thermal environment simulation analysis method is implemented.

[0141] If the integrated module / module is implemented in the form of a software function module and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the present invention implements all or part of the processes in the above-mentioned embodiment method, and can also be completed by instructing the relevant hardware through a computer program. The computer program can be stored in a computer-readable storage medium, and the computer program can implement the steps of the above-mentioned various method embodiments when executed by the processor. Among them, the computer program includes computer program code, and the computer program code can be in source code form, object code form, executable file or some intermediate form. The computer-readable medium may include: any entity or device capable of carrying the computer program code, recording medium, U disk, mobile hard disk, disk, optical disk, computer memory, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), electric carrier signal, telecommunication signal and software distribution medium. Of course, there are other ways of readable storage media, such as quantum memory, graphene memory, etc. It should be noted that the content contained in the computer-readable medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, computer-readable media does not include electrical carrier signals and telecommunication signals.

[0142] The embodiment of the present invention also provides a computer device, such as Fig.15As shown, it includes one or more processors 301 , a communication interface 302 , a memory 303 and a communication bus 304 , wherein the processor 301 , the communication interface 302 , and the memory 303 communicate with each other via the communication bus 304 .

[0143] Memory 303, used for storing computer programs;

[0144] The processor 301 is used to implement each step of the above-mentioned launch vehicle multi-engine nozzle parallel thermal environment simulation analysis method when executing the program stored in the memory 303.

[0145] The processor 301 can be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it can also be a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field programmable gate array (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components.

[0146] The memory 303 may include a large capacity memory for data or instructions. For example, but not limitation, the memory 303 may include a hard disk drive (HDD), a floppy disk drive, a flash memory, an optical disk, a magneto-optical disk, a magnetic tape or a universal serial bus (USB) drive or a combination of two or more of these. In appropriate cases, the memory 303 may include a removable or non-removable (or fixed) medium. In a specific embodiment, the memory 303 is a non-volatile solid-state memory. In a specific embodiment, the memory 303 includes a read-only memory (ROM). In appropriate cases, the ROM may be a mask-programmed ROM, a programmable ROM (PROM), an erasable PROM (EPROM), an electrically erasable PROM (EEPROM), an electrically rewritable ROM (EAROM) or a flash memory or a combination of two or more of these.

[0147] Communication bus 304 includes hardware, software or both, for coupling the above-mentioned components to each other.For example, bus may include accelerated graphics port (AGP) or other graphics bus, enhanced industrial standard architecture (EISA) bus, front side bus (FSB), hypertransport (HT) interconnection, industrial standard architecture (ISA) bus, infinite bandwidth interconnection, low pin count (LPC) bus, memory bus, micro channel architecture (MCA) bus, peripheral component interconnection (PCI) bus, PCI-Express (PCI-X) bus, serial advanced technology attachment (SATA) bus, video electronics standard association local (VLB) bus or other suitable bus or two or more of these combinations.In suitable cases, bus may include one or more buses.Although the embodiment of the present invention describes and shows a specific bus, the present invention considers any suitable bus or interconnection.

[0148] The above is a description of a specific embodiment of the specification. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recorded in the claims can be performed in an order different from that in the embodiments and still achieve the desired results. In addition, the processes depicted in the drawings do not necessarily require the specific order or continuous order shown to achieve the desired results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0149] Although the present application provides method operation steps such as embodiments or flow charts, more or fewer operation steps may be included based on conventional or non-creative labor. The order of steps listed in the embodiments is only one way of executing the order of many steps and does not represent the only execution order. When the actual system or client product is executed, it can be executed in the order of the method shown in the embodiments or the drawings or in parallel (for example, in a parallel processor or multi-threaded processing environment).

[0150] The present invention is described with reference to flowcharts and / or block diagrams of methods, devices (systems), and computer program products according to embodiments of the present invention. It should be understood that each process and / or block in the flowchart and / or block diagram, as well as the combination of processes and / or blocks in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 A process or multiple processes and / or boxes Figure 1 A system that specifies the functions of a box or multiple boxes.

[0151] These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer-readable memory produce a product including an instruction system, which is implemented in the process Figure 1 A process or multiple processes and / or boxes Figure 1 A function specified in one or more boxes.

[0152] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operating steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing instructions for implementing the process. Figure 1 A process or multiple processes and / or boxes Figure 1 The steps for the functions specified in one or more boxes.

[0153] The present invention uses specific embodiments to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. At the same time, for those skilled in the art, according to the idea of ​​the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as a limitation on the present invention.

Claims

1. A simulation and analysis method for the thermal environment of multiple parallel engine nozzles of a launch vehicle, characterized in that: The method comprises: Acquire simulation models of a rocket, a test bench and a single-sided guide trough, and mesh the simulation models; the test bench includes a test frame and a load-bearing frame; Acquiring the rocket engine jet parameters, wherein the engine jet parameters include jet temperature, jet velocity and jet pressure; Performing simulation calculation on the simulation model according to the engine jet parameters of the rocket to obtain simulation calculation results, wherein the simulation calculation results include the temperature, pressure and velocity of each grid in the simulation model; Loading surrounding fluid material parameters to perform simulation analysis on the simulation calculation results to obtain simulation analysis results, and determining thermal environment data of the rocket, the single-sided guide groove and the test bench according to the simulation analysis results, wherein the simulation analysis results include pressure, temperature, velocity and heat flow on each grid; Determine whether the thermal environment data of the rocket, the single-sided guide groove and the test bench meet the design requirements. If the simulation calculation results do not meet the design requirements, redesign the thickness, width and height of the test bench, the profile of the single-sided guide groove, and the thermal protection scheme of the rocket, and assign them to the simulation model to re-simulate the calculation; The step of performing simulation calculation on the simulation model according to the engine jet parameters of the rocket to obtain simulation calculation results specifically includes: The pressure, velocity and temperature of each grid point in the simulation model are obtained by solving the flow control equation by using the mass conservation equation, momentum conservation equation and energy conservation equation in combination with the viscosity coefficient; wherein, The mass conservation equation is: ρ represents the density of the mixed gas at each grid point, and v represents the volume of the mixed gas at each grid point; The momentum conservation equation is: f represents the remote external force on unit mass of fluid, and σ represents the stress; The energy conservation equation is: ε represents the internal energy per unit mass of fluid, D:σ represents the double dot product of the tensor, and k is the thermal conductivity; Before obtaining the simulation models of the rocket, the test bench and the single-sided guide groove, the following steps are also included: The three-dimensional structural models of the rocket, test bench and single-sided guide groove are preprocessed, and the preprocessing includes removing components that do not affect the simulation accuracy and components that are not concerned with the simulation, so as to obtain simulation models of the rocket, test bench and single-sided guide groove suitable for thermal simulation calculations.

2. The method according to claim 1, characterized in that If the thermal environment data of the rocket, the single-sided guide groove and the test bench meet the design requirements, the simulation analysis results are post-processed to obtain a pressure cloud map, a temperature cloud map, a velocity cloud map and a heat flow cloud map of the rocket during takeoff; Among them, the heat flow cloud map includes a single-sided guide groove heat flow cloud map, a test bench heat flow cloud map, a rocket body bottom heat flow cloud map and a rocket body tail section heat flow cloud map.

3. A launch vehicle multi-engine nozzle parallel thermal environment simulation and analysis system, characterized in that: The system comprises: A simulation model acquisition and processing module is used to acquire simulation models of the rocket, the test bench and the single-sided guide groove, and to perform grid division on the simulation models; the test bench includes a test frame and a load-bearing frame; An engine jet parameter acquisition module is used to acquire the engine jet parameters of the rocket, wherein the engine jet parameters include jet temperature, jet velocity and jet pressure; A simulation calculation module, used for performing simulation calculation on the simulation model according to the engine jet parameters of the rocket to obtain simulation calculation results, wherein the simulation calculation results include the temperature, pressure and velocity of each grid in the simulation model; A simulation analysis module, used to load the surrounding fluid material parameters to perform simulation analysis on the calculation results, obtain simulation analysis results, and determine the thermal environment data of the rocket, the single-sided guide groove and the test bench according to the simulation calculation results, wherein the simulation analysis results include the pressure, temperature, velocity and heat flow on each grid; A design requirement judgment module is used to judge whether the thermal environment data of the rocket, the single-sided guide groove and the test bench meet the design requirements; A key parameter redesign module is used to redesign the thickness, width and height of the test frame, the profile of the single-sided guide groove, and the thermal protection scheme of the rocket if the simulation calculation results do not meet the design requirements, and assign them to the simulation model to re-simulate the calculation; The simulation calculation module is specifically used for: The pressure, velocity and temperature of each grid point in the simulation model are obtained by solving the flow control equation by using the mass conservation equation, momentum conservation equation and energy conservation equation in combination with the viscosity coefficient; wherein, The mass conservation equation is: ρ represents the density of the mixed gas at each grid point, and v represents the volume of the mixed gas at each grid point; The momentum conservation equation is: f represents the remote external force on unit mass of fluid, and σ represents the stress; The energy conservation equation is: ε represents the internal energy per unit mass of fluid, D:σ represents the double dot product of the tensor, and k is the thermal conductivity; The model acquisition and processing module is also used for: The three-dimensional structural models of the rocket, test bench and single-sided guide groove are preprocessed, and the preprocessing includes removing components that do not affect the simulation accuracy and components that are not concerned with the simulation, so as to obtain simulation models of the rocket, test bench and single-sided guide groove suitable for thermal simulation calculations.

4. The system according to claim 3, characterized in that The system further comprises: A post-processing module, used for post-processing the simulation analysis results after the thermal environment data of the rocket, the single-sided guide groove and the test bench meet the design requirements, so as to obtain a pressure cloud map, a temperature cloud map, a velocity cloud map and a heat flow cloud map of the rocket during takeoff; Among them, the heat flow cloud map includes a single-sided guide groove heat flow cloud map, a test bench heat flow cloud map, a rocket body bottom heat flow cloud map and a rocket body tail section heat flow cloud map.

5. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the program is executed by a processor, the parallel thermal environment simulation analysis method for multiple engine nozzles of a launch vehicle as described in claim 1 or 2 is implemented.

6. A computer device, characterized in that: It includes: one or more processors; A storage device for storing one or more programs; When the one or more programs are executed by the one or more processors, the one or more processors implement the launch vehicle multi-engine nozzle parallel thermal environment simulation analysis method as described in claim 1 or 2.

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