Method, device and equipment for predicting thermal jet interference in return deceleration section of aircraft

Abstract

The invention provides an aircraft return deceleration section thermal jet interference prediction method, device and equipment and a medium, and the method comprises the steps: determining design parameters of an aircraft, including aircraft profile parameters, nozzle profile parameters, nozzle outlet thermal state flow field parameters and engine combustion chamber gas parameters; modeling the shape of the aircraft and drawing a hybrid grid; based on the molded surface data of the spray pipe, the fuel gas parameters of the engine combustion chamber and the thermal state flow field parameters, fuel gas parameters of the combustion chamber required by calculation are determined; and according to the obtained design parameters of the aircraft, the design grid of the aircraft and the fuel gas parameters of the combustion chamber, various thermal jet flow states and jet flow-free states of the return section of the aircraft are simulated by adopting a steady numerical method, and aerodynamic characteristics and flow field characteristics of the aircraft in various jet flow interference states are obtained. According to the method, the thermal jet interference in the return jet deceleration section of the aircraft and the aerodynamic characteristics of the aircraft are predicted, and support is provided for aerodynamic design and stability evaluation of the vertical return aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of simulation experiments, and particularly relates to a method, device and equipment for predicting the thermal jet interference in the deceleration section of a vehicle return. Background Art

[0002] With the rapid growth of the demand for the scale of space access, lower costs, higher reliability and shorter launch preparation times are required for space transportation systems. Developing large-scale, low-cost and highly reliable reusable vehicles is an important development direction in the future space field.

[0003] The recovery method of the vehicle using the vertical return method adopts the configuration of a traditional launch vehicle, adds equipment such as a landing support mechanism, an aerodynamic deceleration and control mechanism, etc. During the return process, aerodynamic and engine reverse thrust deceleration are used, and finally it lands vertically relying on the landing support mechanism. This method has low requirements for the landing point, higher landing accuracy, a wider application range, and is particularly suitable for future landings and takeoffs on extraterrestrial bodies. Currently, most lunar and Martian landings basically adopt this method.

[0004] During the return process of the vehicle, in the engine jet deceleration section, the thermal jet collides with the high-speed oncoming flow, the thermal jet gas diffuses and wraps the vehicle, and the flow field velocity and temperature are unstable after the collision, that is, it has an obvious impact on the aerodynamic characteristics of the vehicle. When numerically simulating the return process of the vehicle, the prediction accuracy of the jet flow field is low, the calculation equation is relatively complex, the calculation amount is large, and it is relatively difficult to implement. The existing methods cannot provide support for the aerodynamic heat design of the vehicle.

[0005] In view of this, there is an urgent need to provide a method for realizing aerodynamic design and being able to evaluate the stability and having a smaller calculation amount for the thermal jet interference in the deceleration section of a vehicle return. Summary of the Invention

[0006] To overcome the problems existing in the related art, the present disclosure provides a method, device, equipment and medium for predicting the thermal jet interference in the deceleration section of a vehicle return, so as to solve the technical problems that in the numerical simulation of the vehicle return process in the related art, the prediction accuracy of the jet flow field is low, the calculation equation is relatively complex, the calculation amount is large, and it is relatively difficult to implement.

[0007] One or more embodiments of the present specification provide a method for predicting the thermal jet interference in the deceleration section of a vehicle return, including the following steps:

[0008] Determine the design parameters of the vehicle to be analyzed, including the vehicle shape parameters, the nozzle profile parameters, the hot flow field parameters at the nozzle exit and the gas parameters in the engine combustion chamber. Among them, the nozzle profile parameters include the combustion chamber diameter, the throat diameter, and the nozzle exit diameter, and the gas parameters in the engine combustion chamber include the combustion chamber total pressure, the combustion chamber total temperature, and the gas specific heat ratio;

[0009] Model the shape of the aircraft and draw a hybrid grid;

[0010] Based on the profile data of the nozzle, the hot flow field parameters at the nozzle exit, and the gas parameters of the engine combustion chamber, calculate the required gas parameters of the combustion chamber; among them, according to the total pressure, total temperature, and specific heat ratio of the combustion chamber gas, calculate and determine the static temperature, static pressure, and inlet Mach number of the combustion chamber based on the one-dimensional isentropic flow relationship, total pressure-static pressure relationship, and total temperature-static temperature relationship;

[0011] According to the obtained design parameters of the aircraft, the design grid of the aircraft, and the gas parameters of the combustion chamber, use the steady numerical method to numerically simulate the various hot jet states and non-jet states of the aircraft during the return phase through the airflow simulation software, and obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states.

[0012] Further, when using the steady numerical method to simulate various hot jet states and non-jet states of the aircraft during the return phase, use the multi-component hybrid NS equation to solve and obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states.

[0013] Further, the modeling of the aircraft shape and drawing of the hybrid grid are specifically as follows:

[0014] Use structured grids to draw the inside and the exit part of the nozzle, and use unstructured grids to draw the rest of the aircraft.

[0015] One or more embodiments of this specification provide a device for predicting hot jet interference during the deceleration phase of an aircraft's return, including:

[0016] An aircraft parameter determination module, used to determine the design parameters of the aircraft to be analyzed, including the aircraft shape parameters, the profile parameters of the nozzle, the hot flow field parameters at the nozzle exit, and the gas parameters of the engine combustion chamber; among them, the nozzle profile parameters include the combustion chamber diameter, the throat diameter, and the nozzle exit diameter, and the gas parameters of the engine combustion chamber include the total pressure of the combustion chamber, the total temperature of the combustion chamber, and the specific heat ratio of the gas;

[0017] An aircraft modeling module, used to model the aircraft shape and draw a hybrid grid;

[0018] A parameter determination module, used to calculate the required gas parameters of the combustion chamber based on the profile data of the nozzle, the hot flow field parameters at the nozzle exit, and the gas parameters of the engine combustion chamber; among them, according to the total pressure of the combustion chamber, the total temperature of the combustion chamber, and the specific heat ratio of the gas, calculate and determine the static temperature, static pressure, and inlet Mach number of the combustion chamber based on the one-dimensional isentropic flow relationship, the total pressure-static pressure relationship, and the total temperature-static temperature relationship;

[0019] A simulation module, which is used to numerically simulate various hot jet states and non-jet states of the return section of the aircraft by using a steady numerical method according to the design parameters of the aircraft, the design grid of the aircraft, and the gas parameters of the combustion chamber through an air flow simulation software, so as to obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states.

[0020] Furthermore, when the simulation module uses a steady numerical method to simulate various hot jet states and non-jet states of the return section of the aircraft, the multi-component hybrid Navier-Stokes (NS) equations are used for solution to obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states.

[0021] Furthermore, the specific process of the aircraft modeling module for modeling the aircraft shape and drawing the hybrid grid is as follows:

[0022] The structured grid is used to draw the inside and the outlet part of the nozzle, and the unstructured grid is used to draw the rest of the aircraft.

[0023] One or more embodiments of this specification provide a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the hot jet interference prediction method for the return deceleration section of the aircraft as described in any one of the above.

[0024] One or more embodiments of this specification provide a computer-readable storage medium. The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, it implements the hot jet interference prediction method for the return deceleration section of the aircraft as described in any one of the above.

[0025] The advantages of a hot jet interference prediction method, device, equipment, and medium for the return deceleration section of an aircraft provided by this disclosure are as follows: By using a structured grid for the inside and the outlet part of the nozzle and an unstructured grid for the rest of the aircraft for drawing, and based on the design parameters of the aircraft to be simulated and the gas parameters of the combustion chamber, a steady numerical method is used to simulate various hot jet states and non-jet states of the return section of the aircraft, so as to obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states. Thus, the hot jet interference and the aerodynamic characteristics of the aircraft in the return jet deceleration section can be predicted, and it is possible to accurately simulate the hot jet of the nozzle and the interference of the hot jet on the aircraft on the basis of reducing the amount of calculation, providing support for the aerodynamic design and stability evaluation of the vertical return aircraft. Brief Description of the Drawings

[0026] To more clearly illustrate the technical solutions in one or more embodiments of this specification or the prior art, the following will briefly introduce the accompanying drawings required for the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only some embodiments recorded in this specification. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0027] Figure 1 Flowchart of a method for predicting the thermal jet interference in the deceleration section of an aircraft return provided for one or more embodiments of this specification;

[0028] Figure 2 Simplified external shape diagram of an aircraft provided for one or more embodiments of this specification;

[0029] Figure 3 Schematic diagram of the computational domain grid and the grid near the nozzle drawn for one or more embodiments of this specification. Among them, Figure 3 (a) Schematic diagram of the computational domain grid, Figure 3 (b) Schematic diagram of the grid near the nozzle;

[0030] Figure 4 Temperature contour map of the flow field symmetry plane of single-nozzle jet and three-nozzle jet at a flight altitude of 25 Km, Mach number of 2, and angle of attack of 10° provided for one or more embodiments of this specification. Among them, Figure 4 (a) Temperature contour map of the symmetry plane in the single-jet state, Figure 4 (b) Temperature contour map of the symmetry plane in the three-jet state;

[0031] Figure 5 Schematic diagram of the volume fraction of combustible gas and Mach number cloud map of the symmetry plane of the single-nozzle jet flow field and the three-nozzle jet flow field provided for one or more embodiments of this specification. Among them, Figure 5 (a) Schematic diagram of the volume fraction of combustible gas and Mach number cloud map of the symmetry plane of the single-nozzle jet, Figure 5 (b) Schematic diagram of the volume fraction of combustible gas and Mach number cloud map of the symmetry plane of the three-nozzle jet;

[0032] Figure 6 Block diagram of a device for predicting the thermal jet interference in the deceleration section of an aircraft return provided for one or more embodiments of this specification; and

[0033] Figure 7 Structural schematic diagram of a computer device provided for one or more embodiments of this specification. Detailed implementation manners

[0034] To enable those skilled in the art to better understand the technical solutions in one or more embodiments of this specification, the following will clearly and completely describe the technical solutions in one or more embodiments of this specification in conjunction with the accompanying drawings in one or more embodiments of this specification. Obviously, the described embodiments are only a part of the embodiments of this specification, rather than all the embodiments. Based on one or more embodiments of this specification, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0035] The following will make a detailed description of the present invention in combination with the specific implementation manners and the accompanying drawings of the specification.

[0036] Method Embodiment

[0037] According to an embodiment of the present invention, a method for predicting the thermal jet interference in the deceleration section of a vehicle return is provided. As Figure 1 shown, it is a flowchart of the method for predicting the thermal jet interference in the deceleration section of a vehicle return provided in this embodiment. The method for predicting the thermal jet interference in the deceleration section of a vehicle return according to an embodiment of the present invention includes the following steps:

[0038] Step S10: Determine the design parameters of the vehicle to be analyzed, including the vehicle shape parameters, the nozzle profile parameters, the hot flow field parameters at the nozzle outlet, and the gas parameters of the engine combustion chamber. Among them, the gas parameters of the engine combustion chamber include the combustion chamber total pressure and the combustion chamber total temperature, and the nozzle profile parameters include the nozzle inlet, outlet, and throat diameter values.

[0039] Step S20: Model the vehicle shape and draw a hybrid grid, where structured grids are used for the inside and the outlet part of the nozzle, and unstructured grids are used for the rest.

[0040] Step S30: Calculate the required gas parameters of the combustion chamber, including the combustion chamber static temperature, the combustion chamber static pressure, the inlet Mach number, the specific heat ratio of the gas, etc., based on the nozzle profile data, the hot flow field parameters at the nozzle outlet, and the gas parameters of the engine combustion chamber. Among them, the combustion chamber static temperature, static pressure, and inlet Mach number are calculated and determined based on the one-dimensional isentropic flow relationship, the total pressure-static pressure relationship, and the total temperature-static temperature relationship according to the combustion chamber total pressure and the combustion chamber total temperature.

[0041] Step S40: According to the design parameters of the aircraft, the design grid of the aircraft, and the gas parameters of the combustion chamber obtained in Steps S10 - S30, use the steady numerical method to perform numerical simulation calculations on various hot jet states and the non-jet state of the aircraft during the return phase through the airflow simulation software, and obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states. Among them, the aerodynamic characteristics of the aircraft include the aerodynamic forces of each component of the aircraft, the surface pressure distribution, the heat flux distribution, etc., and the flow field characteristics include data such as the pressure, temperature, and Mach number distribution of the flow field near the aircraft.

[0042] Finally, the aerodynamic characteristics and flow field characteristics of different jet states can be analyzed to obtain a relatively accurate prediction result of the hot jet interference during the return phase of the aircraft, providing data support for the aerodynamic heat design of the aircraft.

[0043] The method for predicting the hot jet interference during the return deceleration phase of the aircraft provided in this embodiment draws the aircraft by using structured grids for the internal and outlet parts of the nozzle and unstructured grids for the rest. Based on the design parameters of the aircraft to be simulated and the gas parameters of the combustion chamber, use the steady numerical method to simulate various hot jet states and the non-jet state of the aircraft during the return phase, and obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states, so as to realize the prediction of the hot jet interference and the aerodynamic characteristics of the aircraft during the return jet deceleration phase, and can accurately simulate the hot jet of the nozzle and the interference of the hot jet on the aircraft on the basis of reducing the calculation amount, providing support for the aerodynamic design and stability evaluation of the vertical return aircraft.

[0044] In this embodiment, the profile data of the nozzle is obtained by simplifying the specific research model, and the gas parameters at the outlet of the engine combustion nozzle and the hot flow field parameters at the nozzle outlet are the data obtained from the engine ground test;

[0045] The gas parameters and hot flow field parameters of the engine combustion chamber are calculated based on the total pressure and total temperature of the combustion chamber through the one-dimensional isentropic flow relation, the total pressure-static pressure relation, and the total temperature-static temperature relation. Refer to Figure 2 As shown, it is the simplified external shape diagram of the aircraft provided in this embodiment. In a specific embodiment, the reference length of the aircraft is 46m, and the reference cross-sectional area is 10.52m 2 ; the size of the nozzle profile data is (x) = Ax 2 + Bx + c, where A = 0.187051, B = 0.532439, C = 0.119, and A, B, and C are the equation coefficients; the total pressure of the combustion chamber is 108 bar, and the total temperature of the combustion chamber is 3883K.

[0046] In this embodiment, the corresponding simplified model of the aircraft shape is established and the hybrid grid is drawn. The internal and outlet parts of the nozzle are drawn using structured grids, and the rest are drawn using unstructured grids. Refer toFigure 3 As shown in the figure, it is a schematic diagram of the computational domain grid and the grid near the nozzle provided in this embodiment. Among them, Figure 3 (a) is a schematic diagram of the computational domain grid, Figure 3 (b) is a schematic diagram of the grid near the nozzle.

[0047] In one embodiment, when step S40 uses a steady numerical method to simulate various hot jet states and the non-jet state of the return section of the aircraft, the multi-component hybrid NS equation is used for solution to obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states, including the aerodynamic forces of each component of the aircraft, the surface pressure distribution, the heat flux distribution, and the pressure, temperature, Mach number distribution, etc. of the flow field near the aircraft.

[0048] In a specific embodiment, through step S40, simulation and comparative calculation and analysis are carried out under the conditions that the Mach number at the nozzle inlet of the aircraft is 1.2 - 4.45, the corresponding flight altitude range is 22 - 45 km, and the angle of attack α is 0° or 10° respectively. Numerical simulation calculations are carried out on the non-jet state, the single-nozzle jet state and the three-nozzle jet state respectively to obtain the aerodynamic characteristics and flow field characteristics of different jet states.

[0049] Refer to Figure 4 and 5 as shown, Figure 4 It is the temperature cloud diagram of the symmetry plane of the flow field of the single-nozzle jet and the three-nozzle jet at the state where the flight altitude is 25 Km, the Mach number is 2, and the angle of attack is 10° provided in this embodiment. Figure 5 It is the schematic diagram of the combustion gas volume fraction of the symmetry plane of the flow field of the corresponding single-nozzle jet and the three-nozzle jet. Among them, the red parts in the figure represent that the combustion gas volume fractions are 25%, 50% and 75% respectively. It can be found that by using the prediction method of this embodiment, the process of the hot jet expanding, diffusing and squeezing in the flow field and the data at different positions in the flow field can be obtained.

[0050] Device embodiment

[0051] According to the embodiment of the present invention, a device for predicting the hot jet interference in the return deceleration section of an aircraft is provided. As Figure 6 shown, it is the block diagram of the device for predicting the hot jet interference in the return deceleration section of the aircraft provided in this embodiment. The device for predicting the hot jet interference in the return deceleration section of the aircraft according to the embodiment of the present invention includes:

[0052] An aircraft parameter determination module 10, which is used to determine the design parameters of the aircraft to be analyzed, including the aircraft shape parameters, the nozzle profile parameters, the hot flow field parameters at the nozzle outlet and the gas parameters in the engine combustion chamber. Among them, the gas parameters in the engine combustion chamber include the total pressure in the combustion chamber, the total temperature in the combustion chamber and the specific heat ratio of the gas, and the nozzle profile parameters include the inlet, outlet and throat diameters of the nozzle.

[0053] An aircraft modeling module 20 is used to model the aircraft's outer shape and draw a hybrid grid. Among them, structured grids are used for the interior and outlet parts of the nozzle, and unstructured grids are used for the rest of the parts for drawing.

[0054] A parameter determination module 30 is used to calculate the required gas parameters of the combustion chamber based on the profile data of the nozzle, the hot flow field parameters at the nozzle outlet, and the gas parameters of the engine combustion chamber. Among them, according to the total pressure of the combustion chamber, the total temperature of the combustion chamber, and the specific heat ratio of the gas, the static temperature, static pressure, and inlet Mach number of the combustion chamber are calculated and determined based on the one-dimensional isentropic flow relationship, the total pressure-static pressure relationship, and the total temperature-static temperature relationship.

[0055] A simulation module 40 is used to numerically simulate and calculate various hot jet states and non-jet states during the return section of the aircraft by using a steady numerical method according to the design parameters of the aircraft, the design grid of the aircraft, and the gas parameters of the combustion chamber through an air flow simulation software, and obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states.

[0056] The hot jet interference prediction device for the return deceleration section of the aircraft provided in this embodiment can predict the hot jet interference and the aerodynamic characteristics of the aircraft during the return jet deceleration section, and can accurately simulate the hot jet of the nozzle and the interference of the hot jet on the aircraft on the basis of reducing the calculation amount, providing support for the aerodynamic design and stability evaluation of the vertical return aircraft.

[0057] In this embodiment, the profile data of the nozzle is obtained by simplifying a specific research model, and the gas parameters and hot flow field parameters at the outlet of the engine combustion nozzle are calculated from the data obtained from the engine ground test run.

[0058] In this embodiment, when the simulation module 40 uses a steady numerical method to simulate various hot jet states and non-jet states during the return section of the aircraft, the multi-component hybrid NS equation is used for solution to obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states.

[0059] The embodiment of the present invention is a device embodiment corresponding to the above method embodiment. The specific operations of each module processing step can be understood with reference to the description of the method embodiment, and will not be elaborated here.

[0060] As Figure 7 shown, the present invention also provides a computer device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, it implements the method for predicting hot jet interference in the return deceleration section of the aircraft in the above embodiment.

[0061] The present invention also provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, it implements the method for predicting the thermal jet interference in the return deceleration section of the aircraft in the above embodiments, or when the computer program is executed by the processor, it implements the method for predicting the thermal jet interference in the return deceleration section of the aircraft in the above embodiments. When the computer program is executed by the processor, the following method steps are implemented:

[0062] Step S10: Determine the design parameters of the aircraft to be analyzed, including the aircraft shape parameters, the nozzle profile parameters, the hot flow field parameters at the nozzle outlet, and the gas parameters of the engine combustion chamber. Among them, the gas parameters of the engine combustion chamber include the total pressure and total temperature of the combustion chamber, and the nozzle profile parameters include the nozzle inlet, outlet, and throat diameter values.

[0063] Step S20: Model the aircraft shape and draw a hybrid grid. Among them, structured grids are used for the inside and outlet part of the nozzle, and unstructured grids are used for the rest.

[0064] Step S30: Based on the nozzle profile data, the hot flow field parameters at the nozzle outlet, and the gas parameters of the engine combustion chamber, calculate the required gas parameters of the combustion chamber, including the static temperature, static pressure, inlet Mach number, specific heat ratio of the gas, etc. Among them, according to the total pressure and total temperature of the combustion chamber, the static temperature, static pressure, and inlet Mach number of the combustion chamber are calculated and determined based on the one-dimensional isentropic flow relation, the total pressure-static pressure relation, and the total temperature-static temperature relation.

[0065] Step S40: According to the design parameters of the aircraft, the design grid of the aircraft, and the gas parameters of the combustion chamber obtained in steps S10 - S30, use a steady numerical method to perform numerical simulation calculations on various thermal jet states and the non-jet state in the return section of the aircraft through a flow simulation software, and obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states. Among them, the aerodynamic characteristics of the aircraft include the aerodynamic forces of each component of the aircraft, the surface pressure distribution, the heat flux distribution, etc., and the flow field characteristics include the data such as the pressure, temperature, and Mach number distribution of the flow field near the aircraft.

[0066] Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above embodiments can be completed by instructing relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above methods. Among them, any reference to a memory, storage, database, or other medium used in the various embodiments provided in this application can include non-volatile and / or volatile memories. Non-volatile memory can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memory can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDR SDRAM), enhanced SDRAM (ESDRAM), synchronous link DRAM (SLDRAM), Rambus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and Rambus dynamic RAM (RDRAM), etc.

[0067] The various embodiments in this specification are described in a progressive manner. For the same or similar parts among the various embodiments, reference can be made to each other. Each embodiment focuses on the differences from other embodiments. In particular, for the device or system embodiments, since they are basically similar to the method embodiments, they are described relatively simply. For the relevant parts, reference can be made to the partial description of the method embodiments. The device and system embodiments described above are merely illustrative. The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed to multiple network units. Some or all of the modules can be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art can understand and implement it without creative efforts.

[0068] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some or all of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention, and the content not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.

Claims

1. A method for predicting thermal jet interference during the return deceleration phase of an aircraft, characterized in that The following steps are involved: Determine the design parameters of the aircraft to be analyzed, including aircraft shape parameters, nozzle profile parameters, hot flow field parameters at the nozzle outlet, and engine combustion chamber gas parameters, wherein the nozzle profile parameters include combustion chamber diameter, throat diameter, nozzle outlet diameter, and engine combustion chamber gas parameters include combustion chamber total pressure, combustion chamber total temperature, and gas specific heat ratio; Model the aircraft shape and draw the hybrid mesh; Based on the nozzle profile data, the hot flow field parameters at the nozzle outlet and the combustion chamber gas parameters of the engine, the required combustion chamber gas parameters are calculated; wherein, according to the total pressure of the combustion chamber, the total temperature of the combustion chamber and the specific heat ratio of the gas, the combustion chamber static temperature, static pressure and inlet Mach number are calculated and determined based on the one-dimensional isentropic flow relationship, the total pressure-static pressure relationship and the total temperature-static temperature relationship; According to the obtained design parameters of the aircraft, the design grid of the aircraft and the gas parameters of the combustion chamber, the steady numerical method is used to perform numerical simulation calculations on various hot jet states and no-jet states in the return section of the aircraft through airflow simulation software, and the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states are obtained.

2. The method for predicting thermal jet interference during the return deceleration phase of an aircraft according to claim 1, characterized in that: When the steady-state numerical method is used to simulate various thermal jet states and non-jet states in the return phase of the aircraft, the multi-component mixed NS equations are used to solve the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states.

3. The method for predicting thermal jet interference during the return deceleration phase of an aircraft according to claim 1, characterized in that: The specific steps of modeling the aircraft shape and drawing the mixed grid are as follows: The structured grid is used to draw the interior and exit of the nozzle, and the unstructured grid is used to draw the rest of the aircraft.

4. A device for predicting thermal jet interference during the return deceleration phase of an aircraft, characterized in that: include: The aircraft parameter determination module is used to determine the design parameters of the aircraft to be analyzed, including aircraft shape parameters, nozzle profile parameters, hot flow field parameters at the nozzle outlet, and engine combustion chamber gas parameters, wherein the nozzle profile parameters include the combustion chamber diameter, throat diameter, and nozzle outlet diameter, and the engine combustion chamber gas parameters include the combustion chamber total pressure, the combustion chamber total temperature, and the gas specific heat ratio; Aircraft modeling module, used to model the aircraft shape and draw hybrid meshes; A parameter determination module is used to calculate the required combustion chamber gas parameters based on the nozzle profile data, the hot flow field parameters at the nozzle outlet and the engine combustion chamber gas parameters; wherein, according to the combustion chamber total pressure, the combustion chamber total temperature and the gas specific heat ratio, the combustion chamber static temperature, static pressure and inlet Mach number are calculated and determined based on the one-dimensional isentropic flow relationship, the total pressure-static pressure relationship and the total temperature-static temperature relationship; The simulation module is used to perform numerical simulation calculations on various hot jet states and no-jet states in the return section of the aircraft through airflow simulation software based on the design parameters of the aircraft, the design grid of the aircraft and the gas parameters of the combustion chamber, using a steady numerical method to obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states.

5. The device for predicting thermal jet interference during the return deceleration phase of an aircraft according to claim 3, characterized in that: The simulation module uses a constant numerical method to simulate various thermal jet states and non-jet states in the return phase of the aircraft, and uses a multi-component mixed NS equation to solve to obtain the aerodynamic characteristics and flow field characteristics of the aircraft under various jet interference states.

6. The device for predicting thermal jet interference during the return deceleration phase of an aircraft according to claim 3, characterized in that: The aircraft modeling module models the aircraft shape and draws the mixed grid specifically as follows: The structured grid is used to draw the interior and exit of the nozzle, and the unstructured grid is used to draw the rest of the aircraft.

7. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, the method for predicting thermal jet interference in the return deceleration phase of an aircraft as described in any one of claims 1 to 3 is implemented.

8. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the method for predicting thermal jet interference in the return deceleration phase of an aircraft as claimed in any one of claims 1 to 3 is implemented.

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