CN-122021388-A - CFD-based thermal spraying interference effect airspeed domain partitioning method and device

CN122021388ACN 122021388 ACN122021388 ACN 122021388ACN-122021388-A

Abstract

The embodiment of the specification provides a CFD-based thermal spraying interference effect airspeed domain partitioning method and device, wherein the method comprises the steps of establishing an aircraft jet interference CFD calculation model, selecting a plurality of discrete airspeed points in a target airspeed domain and attack angle range, completing progressive calculation of various working conditions for each discrete airspeed point based on the aircraft jet interference CFD calculation model, obtaining the influence quantity of a high Wen Yizhi effect on aerodynamic characteristics, the influence quantity of a component transport effect on the aerodynamic characteristics and the influence quantity of a chemical unbalance effect on the aerodynamic characteristics through incremental decomposition, determining the dominant thermal spraying interference effect of attack points of each airspeed domain according to the maximum value of the three influence quantities, and outputting an airspeed domain attack angle partitioning chart or a partitioning table.

Inventors

LIU YAOFENG
CAO NING
LI KANGKANG
LIU YUWEI
MA JIKUI

Assignees

中国航天空气动力技术研究院

Dates

Publication Date: 20260512
Application Date: 20251219

Claims (10)

1. The CFD-based thermal spraying interference effect airspeed domain partitioning method is characterized by comprising the following steps of: establishing an aircraft jet flow interference CFD calculation model, and selecting a plurality of discrete airspeed points in a target airspeed domain and an attack angle range; based on the aircraft jet flow interference CFD calculation model, finishing progressive calculation of various working conditions aiming at each discrete airspeed point, wherein the various working conditions only change jet flow definition, and the appearance of the aircraft is kept consistent with the incoming flow condition; The influence quantity of the high Wen Yizhi effect on the aerodynamic characteristics, the influence quantity of the component transport effect on the aerodynamic characteristics and the influence quantity of the chemical unbalance effect on the aerodynamic characteristics are obtained through incremental decomposition, the dominant thermal spraying interference effect of the attack points of each airspeed domain is determined according to the maximum value of the three influence quantities, and an airspeed domain attack angle partition map or a partition table is output.
2. The method of claim 1, wherein the plurality of operating conditions specifically comprises: The system comprises a normal temperature air jet working condition, a high temperature medium gas jet working condition, a high temperature multi-component gas jet working condition and a high Wen Duozu split chemical reaction jet working condition, wherein the specific heat ratio conditions of the high temperature medium gas jet working condition, the high temperature multi-component gas jet working condition and the high temperature multi-component split chemical reaction jet working condition are consistent, the gas constant conditions are consistent, the total temperature conditions are consistent and the total pressure conditions are consistent.
3. The method according to claim 2, wherein obtaining the high Wen Yizhi effect on aerodynamic properties, the component transport effect on aerodynamic properties, and the chemical unbalance effect on aerodynamic properties by incremental decomposition comprises: calculating the high-temperature medium effect, namely subtracting the aerodynamic characteristics under the normal-temperature air jet condition from the aerodynamic characteristics under the high Wen Yizhi jet condition according to formula 1 to obtain the influence delta C1 of the high Wen Yizhi effect on the aerodynamic characteristics: Equation 1; wherein, the characteristic (B) is the aerodynamic characteristic under the high Wen Yizhi jet flow condition, and the characteristic (A) is the aerodynamic characteristic under the normal temperature air jet flow condition; Calculating the component transport effect, namely subtracting the aerodynamic characteristics under the high Wen Yizhi jet flow condition from the aerodynamic characteristics under the multicomponent jet flow condition according to the formula 2 to obtain the influence quantity delta C2 of the component transport effect on the aerodynamic characteristics: equation 2; Wherein, the characteristic (C) is the aerodynamic characteristic under the condition of multicomponent jet flow, and the characteristic (B) is the aerodynamic characteristic under the condition of high Wen Yizhi jet flow; Calculating the chemical unbalance effect, namely subtracting the aerodynamic characteristics under the multicomponent jet flow condition from the aerodynamic characteristics under the chemical unbalance jet flow condition according to the formula 3 to obtain the influence delta C3 of the chemical unbalance effect on the aerodynamic characteristics: Equation 3; Wherein, the characteristic (D) is the aerodynamic characteristic under the chemical unbalanced jet flow condition, and the characteristic (C) is the aerodynamic characteristic under the multicomponent jet flow condition.
4. A method according to claim 3, wherein determining the dominant thermal spray interference effect for each airspeed domain attack point based on the maximum of the three impact quantities and outputting an airspeed domain attack angle partition map or table comprises: comparing the magnitudes of delta C1, delta C2 and delta C3 at each airspeed domain attack point, determining the effect corresponding to the maximum value delta CMax in delta C1, delta C2 and delta C3 as the dominant thermal spraying interference effect of the airspeed domain attack point, traversing all discrete flight conditions, outputting an airspeed domain attack angle partition map or a partition table, and determining the dominant thermal spraying interference mechanism under different airspeed domains and attack angles.
5. The method of claim 1, wherein performing progressive calculations for a plurality of operating conditions for each discrete airspeed point based on the aircraft jet disturbance CFD calculation model specifically comprises: Selecting a series of discrete airspeed points within the airspeed domain of interest, wherein the airspeed points include a flight Mach number, a flight altitude, and a flight angle of attack; Based on the aircraft jet flow interference CFD calculation model, CFD calculation of various working conditions is respectively completed at each airspeed point; extracting a pneumatic characteristic parameter of interest, wherein the pneumatic characteristic parameter specifically comprises at least one of an axial force coefficient, a normal force coefficient, a lateral force coefficient, a rolling moment coefficient, a yaw moment coefficient and a pitching moment coefficient.
6. CFD-based thermal spray interference effect airspeed domain partitioning device, comprising: the building module is used for building an aircraft jet flow interference CFD calculation model and selecting a plurality of discrete airspeed points in a target airspeed domain and an attack angle range; the computing module is used for completing progressive computation of various working conditions aiming at each discrete airspeed point based on the CFD computing model of the jet flow interference of the aircraft, wherein the jet flow definition is only changed by the various working conditions, and the appearance and the incoming flow condition of the aircraft are kept consistent; the determining module is used for obtaining the influence quantity of the high Wen Yizhi effect on the aerodynamic characteristics, the influence quantity of the component transport effect on the aerodynamic characteristics and the influence quantity of the chemical unbalance effect on the aerodynamic characteristics through incremental decomposition, determining the dominant thermal spraying interference effect of each airspeed domain attack point according to the maximum value of the three influence quantities, and outputting an airspeed domain attack angle partition map or a partition table.
7. The apparatus of claim 6, wherein the plurality of operating conditions specifically comprises: The system comprises a normal temperature air jet working condition, a high temperature medium gas jet working condition, a high temperature multi-component gas jet working condition and a high Wen Duozu split chemical reaction jet working condition, wherein the specific heat ratio conditions of the high temperature medium gas jet working condition, the high temperature multi-component gas jet working condition and the high temperature multi-component split chemical reaction jet working condition are consistent, the gas constant conditions are consistent, the total temperature conditions are consistent and the total pressure conditions are consistent.
8. The apparatus of claim 7, wherein the device comprises a plurality of sensors, The determining module is specifically configured to: calculating the high-temperature medium effect, namely subtracting the aerodynamic characteristics under the normal-temperature air jet condition from the aerodynamic characteristics under the high Wen Yizhi jet condition according to formula 1 to obtain the influence delta C1 of the high Wen Yizhi effect on the aerodynamic characteristics: Equation 1; wherein, the characteristic (B) is the aerodynamic characteristic under the high Wen Yizhi jet flow condition, and the characteristic (A) is the aerodynamic characteristic under the normal temperature air jet flow condition; Calculating the component transport effect, namely subtracting the aerodynamic characteristics under the high Wen Yizhi jet flow condition from the aerodynamic characteristics under the multicomponent jet flow condition according to the formula 2 to obtain the influence quantity delta C2 of the component transport effect on the aerodynamic characteristics: equation 2; Wherein, the characteristic (C) is the aerodynamic characteristic under the condition of multicomponent jet flow, and the characteristic (B) is the aerodynamic characteristic under the condition of high Wen Yizhi jet flow; Calculating the chemical unbalance effect, namely subtracting the aerodynamic characteristics under the multicomponent jet flow condition from the aerodynamic characteristics under the chemical unbalance jet flow condition according to the formula 3 to obtain the influence delta C3 of the chemical unbalance effect on the aerodynamic characteristics: Equation 3; Wherein, the characteristic (D) is the aerodynamic characteristic under the chemical unbalanced jet flow condition, and the characteristic (C) is the aerodynamic characteristic under the multicomponent jet flow condition; Comparing the magnitudes of delta C1, delta C2 and delta C3 at each airspeed domain attack point, determining the effect corresponding to the maximum value delta CMax in delta C1, delta C2 and delta C3 as the dominant thermal spraying interference effect of the airspeed domain attack point, traversing all discrete flight conditions, outputting an airspeed domain attack angle partition map or a partition table, and determining the dominant thermal spraying interference mechanism under different airspeed domains and attack angles; the computing module is specifically configured to: Selecting a series of discrete airspeed points within the airspeed domain of interest, wherein the airspeed points include a flight Mach number, a flight altitude, and a flight angle of attack; Based on the aircraft jet flow interference CFD calculation model, CFD calculation of various working conditions is respectively completed at each airspeed point; extracting a pneumatic characteristic parameter of interest, wherein the pneumatic characteristic parameter specifically comprises at least one of an axial force coefficient, a normal force coefficient, a lateral force coefficient, a rolling moment coefficient, a yaw moment coefficient and a pitching moment coefficient.
9. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, which when executed by the processor, implements the steps of the CFD-based thermal spray interference effect airspeed domain partitioning method of any one of claims 1 to 5.
10. A computer readable storage medium, characterized in that it has stored thereon a program for realizing information transfer, which when executed by a processor, realizes the steps of the CFD-based thermal spray interference effect airspeed domain partitioning method according to any one of claims 1 to 5.

Description

CFD-based thermal spraying interference effect airspeed domain partitioning method and device Technical Field The document relates to the technical field of aerospace and hydrodynamics, in particular to a thermal spraying interference effect airspeed domain partitioning method and device based on CFD. Background Under high-speed flight conditions, lateral control of the jet flow of the engine by the aircraft can cause significant interference to surrounding flow fields, thereby affecting the stability and maneuverability of the aircraft. The control engine is usually a gas engine, the jet flow and outflow interference of the gas engine will have thermal jet interference effects (high-temperature medium effect, component transportation effect, chemical unbalance effect and the like), compared with the jet flow with small flow, the thermal jet effect caused by the jet flow with large flow has more obvious influence on aerodynamic/thermal characteristics of the whole and parts of the aircraft. The core mechanisms of the thermal spray interference effect include: 1. high temperature medium effect, which is to jet high temperature gas to heat conduction and radiation effect of surrounding flow field; 2. Component transport effects, namely, the change of a flow field structure caused by diffusion and mixing of chemical components (such as CO 2、H2 O and the like) in jet flow; 3. Chemical imbalance effects, localized chemical reactions and energy release induced by mixing the jet with an external air stream. The traditional engineering method generally adopts cold spraying simulation based on normal temperature air and an experience correction coefficient to envelope real thermal spraying interference characteristics, if the method is adopted, the reliability of an established pneumatic database is not high and the precision is not enough, and if a chemical unbalanced simulation means based on real high temperature fuel gas is adopted, the problems of long acquisition period and high acquisition cost of the pneumatic characteristics are caused. The result of comprehensively meeting the reliability, precision and efficiency can be obtained by analyzing the internal core mechanism of the main heat conduction spray interference effect under different airspeed domain conditions on the basis of guaranteeing the simulation of the main core mechanism. Disclosure of Invention The invention aims to provide a thermal spraying interference effect airspeed domain partitioning method and device based on CFD, and aims to solve the problems in the prior art. The invention provides a CFD-based thermal spraying interference effect airspeed domain partitioning method, which comprises the following steps: establishing an aircraft jet flow interference CFD calculation model, and selecting a plurality of discrete airspeed points in a target airspeed domain and an attack angle range; based on the aircraft jet flow interference CFD calculation model, finishing progressive calculation of various working conditions aiming at each discrete airspeed point, wherein the various working conditions only change jet flow definition, and the appearance of the aircraft is kept consistent with the incoming flow condition; The influence quantity of the high Wen Yizhi effect on the aerodynamic characteristics, the influence quantity of the component transport effect on the aerodynamic characteristics and the influence quantity of the chemical unbalance effect on the aerodynamic characteristics are obtained through incremental decomposition, the dominant thermal spraying interference effect of the attack points of each airspeed domain is determined according to the maximum value of the three influence quantities, and an airspeed domain attack angle partition map or a partition table is output. The invention provides a CFD-based thermal spraying interference effect airspeed domain partitioning device, which comprises: the building module is used for building an aircraft jet flow interference CFD calculation model and selecting a plurality of discrete airspeed points in a target airspeed domain and an attack angle range; the computing module is used for completing progressive computation of various working conditions aiming at each discrete airspeed point based on the CFD computing model of the jet flow interference of the aircraft, wherein the jet flow definition is only changed by the various working conditions, and the appearance and the incoming flow condition of the aircraft are kept consistent; the determining module is used for obtaining the influence quantity of the high Wen Yizhi effect on the aerodynamic characteristics, the influence quantity of the component transport effect on the aerodynamic characteristics and the influence quantity of the chemical unbalance effect on the aerodynamic characteristics through incremental decomposition, determining the dominant thermal spraying interference effect of each airspeed domain attack point according