A method for fast calculating transient thermal stress of ceramic radome along flight trajectory

Abstract

The application discloses a kind of ceramic radome transient thermal stress fast calculation method along flight trajectory, comprising: determining calculation input, including the aerodynamic thermal environment of ceramic radome and the structure scheme to be evaluated;Set the circumferential discrete strategy of ceramic radome, to determine the multiple meridional plane of ceramic radome;Interpolation model is constructed to aerodynamic thermal environment, determines the most severe meridional plane of ceramic radome aerodynamic heating in flight;Build the two-dimensional feature structure model of ceramic radome transient heat transfer and thermal stress analysis, and determine the external contour line of two-dimensional feature structure model;The axial thermal response calculation interval of ceramic radome is constructed and interpolation calculation is carried out, and the aerodynamic thermal environment parameter of each flight time of external contour line is obtained;The heat transfer calculation grid division is carried out to two-dimensional feature structure model, and the structure transient temperature distribution of two-dimensional feature structure model is calculated;Based on the structure transient temperature distribution, calculate structure temperature gradient;Utilize structure temperature gradient to calculate the transient thermal stress distribution of ceramic radome.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of high-speed aircraft thermal structure design, and particularly relates to a method for rapidly calculating transient thermal stress of a ceramic radome along a flight trajectory. BACKGROUND

[0002] The radome is located at the head of the aircraft body, and needs to have a reasonable aerodynamic shape to withstand the highest aerodynamic force and thermal load of the aircraft body. For high-speed aircraft with a maximum Mach number greater than 3, the radome is usually made of quartz ceramic material to achieve the requirements of heat protection, load bearing and thermal wave transmission during flight, and to create a good service environment for the radar seeker.

[0003] The quartz ceramic radome root is bonded with a low-expansion invar ring, which is the most widely used structure connection scheme for ceramic radomes. The invar ring increases the structural heat sink of the ceramic radome root connection part, which can effectively control the temperature of the bonding surface and ensure the reliability of the bonding structure. However, this scheme causes a sudden change in the structural heat sink and heat transfer path at the front end of the invar ring, which forms a sharp temperature gradient in a small range of the ceramic radome at this part, causing thermal stress concentration, and in extreme cases, it will lead to the destruction of the thermal structure of the radome, causing flight disasters.

[0004] The structural thermal strength of the radar radome under the action of aerodynamic force-thermal coupling is usually studied and designed by using finite element numerical simulation, and the calculation results can reflect the transient heat transfer and stress change law of the structure, providing strong support for the design and optimization of the radome. However, the transient thermal-mechanical coupling finite element numerical simulation requires a large amount of calculation, in order to ensure the stability of the calculation and capture the maximum stress value of the radome throughout the flight, the final design result is usually formed after several rounds of iteration, which takes a long time, seriously restricting the improvement of the efficiency of the aircraft development. How to quickly and accurately evaluate the thermal stress of the radome to provide reliable feasibility evaluation conclusions for the overall scheme optimization design of the aircraft is an important technical problem that needs to be solved in this field. SUMMARY

[0005] The purpose of the present application is to provide a method for rapidly calculating the transient thermal stress of a ceramic radome along a flight trajectory, in order to solve the problems of high time cost and low efficiency of the existing finite element numerical simulation method.

[0006] In order to achieve the above-mentioned task, the present application adopts the following technical scheme:

[0007] A method for rapidly calculating the transient thermal stress of a ceramic radome along a flight trajectory, comprising:

[0008] determining the calculation input, including the aerodynamic thermal environment of the ceramic radome and the structure scheme to be evaluated;

[0009] The structural scheme is used to construct a structural coordinate system, and a circumferential discrete strategy of the ceramic radome is set in the structural coordinate system to determine a plurality of meridional planes of the ceramic radome;

[0010] Based on the circumferential discrete strategy of the ceramic radome, a training sample data set is constructed in combination with feature points on an axial design section of the ceramic radome, and is used to establish an aerodynamic thermal environment interpolation model; based on aerodynamic thermal environment parameters of all feature points at each flight time obtained by the aerodynamic thermal environment interpolation model, a most severe meridional plane of the ceramic radome in the whole flight process is determined;

[0011] Based on the most severe meridional plane of the ceramic radome in the aerodynamic heating, a two-dimensional feature structure model for transient heat transfer and thermal stress analysis of the ceramic radome is constructed, and an external contour line of the two-dimensional feature structure model is determined;

[0012] An axial thermal response calculation interval of the ceramic radome is constructed, the axial thermal response calculation interval is discretized and mapped to the external contour line of the two-dimensional feature structure model, so as to construct a mapping grid point set; interpolation calculation is performed on the mapping grid point set to obtain aerodynamic thermal environment parameters of the external contour line at each flight time;

[0013] The two-dimensional feature structure model is subjected to heat transfer calculation grid division, and the aerodynamic thermal environment parameters of the external contour line at each flight time are combined to calculate the structural transient temperature distribution of the two-dimensional feature structure model;

[0014] Based on the structural transient temperature distribution, the structural temperature gradient is calculated;

[0015] The transient thermal stress distribution of the ceramic radome is calculated by using the structural temperature gradient.

[0016] Further, the aerodynamic thermal environment includes aerodynamic thermal environment parameters of grid nodes divided on the outer surface of the ceramic radome at different flight times; the aerodynamic thermal environment parameters include recovery enthalpy and cold wall heat flux;

[0017] The structure scheme to be evaluated includes a three-dimensional structure model of the ceramic radome; the ceramic radome includes a radome body and a steel ring, and an inner ring surface at the root of the radome body is fixed with the steel ring.

[0018] Further, the circumferential discrete strategy of the ceramic radome is set in the structural coordinate system to determine a plurality of meridional planes of the ceramic radome, including:

[0019] A semi-infinite length vector is defined in the reference plane of the structural coordinate system, the semi-infinite length vector starts from the origin of the structural coordinate system, and forms a semi-infinite length coordinate plane with the axis, which is defined as a discrete plane; the semi-infinite length vector is clockwise around the axis from the axis direction to The axis direction rotates to form a plurality of discrete surfaces; a plurality of discrete surfaces are uniformly selected as meridional surfaces from the plurality of discrete surfaces to discretely surround the ceramic radome in the circumferential direction;

[0020] The structure coordinate system is defined as follows: The axis is positive along the fuselage axis of the aircraft in the rear direction; The axis is perpendicular to the The axis is positive in the upward direction in the plane of symmetry of the fuselage; The axis is determined according to the right-hand rule.

[0021] Further, a training sample data set is constructed in combination with the feature points on the axial design section of the ceramic radome, and is used to establish an aerodynamic thermal environment interpolation model, including:

[0022] Each meridional surface intersects the outer surface of the ceramic radome to form a corresponding intersection line;

[0023] The cross section at the front end of the invar ring of the ceramic radome is selected as the axial design section of the ceramic radome;

[0024] The feature points on the axial design section of the ceramic radome are determined to construct a feature point set; wherein the feature points are the intersection points of the intersection lines and the axial design section;

[0025] A reference point set is constructed using the grid nodes divided on the outer surface of the ceramic radome, and the feature point set is used as a query point set; based on the The query point set is expanded by a The search point set is obtained by traversing search of the k nearest neighbors; the training sample data set is constructed based on the search point set;

[0026] The training sample data set is used to construct an aerodynamic thermal environment interpolation model using a radial basis function;

[0027] The aerodynamic thermal environment interpolation model is used to obtain the aerodynamic thermal environment parameters of each flight time of all feature points in the feature point set by interpolation.

[0028] Further, based on the aerodynamic thermal environment parameters of each flight time of all feature points obtained by the aerodynamic thermal environment interpolation model, the most severe meridional surface of the ceramic radome for aerodynamic heating during the entire flight is determined, including:

[0029] For each feature point, the maximum heat flux density during the entire flight is calculated by the aerodynamic thermal environment parameters using a linear scanning method;

[0030] The total heating amount at the feature point during the entire flight is calculated;

[0031] After obtaining the maximum heat flux density and total heating amount of all feature points, the maximum value in all maximum heat flux densities is selected, and the meridian plane where the feature point corresponding to the maximum value is located is the most severe meridian plane of the ceramic radome aerodynamic heating during the whole flight;

[0032] If there are multiple maximum values, then further select the feature point with the maximum total heating amount from all feature points corresponding to the maximum values, and the meridian plane where the feature point is located is the most severe meridian plane of the ceramic radome aerodynamic heating during the whole flight.

[0033] Further, based on the most severe meridian plane of the ceramic radome aerodynamic heating, a two-dimensional feature structure model for transient heat transfer and thermal stress analysis of the ceramic radome is constructed, and the external contour line of the two-dimensional feature structure model is determined, including:

[0034] The most severe meridian plane of the ceramic radome aerodynamic heating is taken as the reference plane, and the two-dimensional projection structure of the ceramic radome on the reference plane is the two-dimensional feature structure model for transient heat transfer and thermal stress analysis of the ceramic radome.

[0035] The intersection line of the most severe meridian plane of the ceramic radome aerodynamic heating and the outer surface of the ceramic radome is taken as the external contour line of the two-dimensional feature structure model.

[0036] Further, an axial thermal response calculation interval of the ceramic radome is constructed, the axial thermal response calculation interval is discretized and mapped onto the external contour line of the two-dimensional feature structure model, thereby constructing a set of mapping grid points; interpolation calculation is performed on the set of mapping grid points to obtain the aerodynamic thermal environment parameters of the external contour line at each flight time, including:

[0037] A plane coordinate system of the two-dimensional feature structure model is defined;

[0038] The axial thermal response calculation interval of the ceramic radome is determined in the plane coordinate system;

[0039] The plane coordinate system is discretized in the axial direction of the ceramic radome The discrete segments are obtained; all discrete segments are mapped onto the external contour line of the two-dimensional feature structure model to obtain corresponding mapping grid points, thereby forming a set of mapping grid points;

[0040] Aerodynamic thermal environment reconstruction interpolation calculation is performed on the mapping grid points in the set of mapping grid points to obtain the aerodynamic thermal environment parameters of the external contour line at each flight time.

[0041] Further, the two-dimensional feature structure model is subjected to heat transfer calculation grid division, and the aerodynamic thermal environment parameters of the external contour line at each flight time are combined to calculate the structure transient temperature distribution of the two-dimensional feature structure model, including:

[0042] The axial thermal response calculation interval is used for heat transfer calculation grid division of the two-dimensional feature structure model based on the ceramic radome;

[0043] The external contour line aerodynamic heat environment parameters at each flight time are applied to the heat transfer calculation grid division results of the two-dimensional feature structure model, and the structure transient temperature distribution is calculated.

[0044] Further, based on the structure transient temperature distribution, the structure temperature gradient is calculated, including:

[0045] For each heat transfer calculation grid, the second-order central difference method is used to traverse and calculate the partial derivative of the structure transient temperature at different flight times at the heat transfer calculation grid in the coordinate axis direction of the plane coordinate system, and then the partial derivative is used to calculate the structure temperature gradient at the heat transfer calculation grid.

[0046] Further, the structure temperature gradient is used to calculate the transient thermal stress distribution of the ceramic radome, including:

[0047] At flight time The transient thermal stress Caused by the structure temperature gradient At the heat transfer calculation grid , Is calculated according to the following formula:

[0048] ;

[0049] Wherein, 、 Elastic modulus and linear expansion coefficient of the ceramic radome material at flight time At the heat transfer calculation grid , ;

[0050] The transient thermal stress at the heat transfer calculation grid , Of the ceramic radome at each flight time is calculated to obtain the transient thermal stress sequence Of the heat transfer calculation grid , Along the flight path.

[0051] The transient thermal stress sequences of all heat transfer calculation grids are used to represent the transient thermal stress distribution of the ceramic radome.

[0052] A terminal device includes a processor, a memory, and a computer program stored in the memory; when the processor executes the computer program, the along-flight-path ceramic radome transient thermal stress rapid calculation method is implemented.

[0053] A computer-readable storage medium storing a computer program; when executed by a processor, the computer program implements the method for rapid calculation of transient thermal stress of a ceramic radome along a flight trajectory.

[0054] Compared with the prior art, the present invention has the following technical features:

[0055] This invention, by rationally selecting a two-dimensional characteristic structural model of the aerodynamic thermal environment of the radome, can accurately characterize the transient temperature field and thermal stress changes of the radome under strongly nonlinear time-varying aerodynamic heating. Compared with traditional three-dimensional finite element analysis, this invention has significant efficiency advantages. Specifically, in terms of mesh generation, this invention only requires a few thousand mesh nodes to obtain fine calculation results, reducing the number of mesh points by two orders of magnitude compared to three-dimensional finite element analysis. This not only allows the calculation process to be completed within minutes in a single-core environment, but also greatly reduces the requirements for computer hardware. Using this invention can effectively shorten the design iteration cycle, significantly reduce the cost of numerical simulation, and achieve the goal of efficient joint design with the overall aerodynamics of the aircraft. This invention provides important theoretical guidance for the thermal structure demonstration, optimization selection, and stress control of radomes, and has significant engineering practical value. Attached Figure Description

[0056] Figure 1 This is a schematic flowchart of the method of the present invention;

[0057] Figure 2 This is a schematic diagram of the aerodynamic thermal environment input for the ceramic antenna radome, where ( a ( ) represents the shape and surface grid node distribution of the ceramic radome; b )and( c ) are grid nodes The changes in recovery enthalpy and cold wall heat flux with flight time;

[0058] Figure 3 This is a schematic diagram of the structure of a ceramic radome, in which ( a (This refers to the side view and its corresponding...) D - D Cross-sectional view, ( b )for( a Enlarged view of the circled area in the image;

[0059] Figure 4 A schematic diagram defining the coordinate system of the ceramic radome structure, wherein ( a (This is a side view of the ceramic radome.) b (This is a rear view of the ceramic radome.)

[0060] Figure 5 As described in the embodiments of the present invention A schematic diagram of the nearest neighbor search method;

[0061] Figure 6 A schematic diagram of a two-dimensional characteristic structural model for transient heat transfer and thermal stress analysis of a ceramic radome;

[0062] Figure 7 This is a schematic diagram of the heat transfer calculation mesh generation for a two-dimensional feature structure model;

[0063] Figure 8 This is a schematic diagram showing the structural transient temperature calculation results of the four heat transfer calculation grids of the ceramic radome throughout the flight in the embodiment; wherein ( a ) represents the location of the four heat transfer calculation grids, ( b () represents the transient temperature of the structure;

[0064] Figure 9 This is a schematic diagram showing the structural temperature gradient calculation results of the four heat transfer calculation grids of the ceramic radome throughout the flight in the embodiment.

[0065] Figure 10 For the example A schematic diagram comparing the transient thermal stress calculation results of the same parts using the method of the present invention with the transient thermal stress calculation results of three-dimensional finite element force-thermal coupling analysis.

[0066] Figure 11 This is a schematic diagram comparing the performance of the method of the present invention and the three-dimensional finite element force-thermal coupling analysis method in the embodiments, wherein ( a (This is a comparison of the heat transfer calculation grid and grid nodes.) b (Comparison is performed on a computer.)

[0067] The labels in the diagram are: 1. Cover body, 2. Indium steel ring. Detailed Implementation

[0068] This invention provides a rapid calculation method for transient thermal stress of ceramic radomes along flight trajectories. Based on the meridional plane identification results of the most severe aerodynamic heating of ceramic radomes, a two-dimensional characteristic structural model for transient heat conduction and thermal stress calculation is constructed. This method rapidly analyzes the local thermal stress change process of the ceramic radome at the front end of the Invar ring throughout the flight, providing efficient and powerful theoretical guidance and data support for the thermal structure design and optimization of ceramic radomes.

[0069] This invention provides a method for rapid calculation of transient thermal stress of a ceramic radome along a flight trajectory, specifically including the following steps:

[0070] Step 1: Determine the calculation inputs, including the aerodynamic and thermal environment of the ceramic radome and the structural scheme to be evaluated; specifically including:

[0071] Step 1.1, the aerodynamic thermal environment includes aerodynamic thermal environment parameters of the ceramic radome outer surface divided grid nodes at different flight time; the aerodynamic thermal environment parameters include recovery enthalpy and cold wall heat flux.

[0072] First, the aerodynamic thermal environment calculation coordinate system is constructed for the ceramic radome; then, for the coordinates[ , , ] of the ceramic radome outer surface in the aerodynamic thermal environment calculation coordinate system, the recovery enthalpy , , and the cold wall heat flux , , are functions of the flight time and the coordinates[ , , ], and are specifically expressed as:

[0073] , , ;

[0074] , , ;

[0075] Wherein: characterizes the functional relationship between the recovery enthalpy , , and the Mach number , height , angle of attack and sideslip angle of the flight time and the coordinates[ , , ]; characterizes the functional relationship between the cold wall heat flux , , and the Mach number , height , angle of attack and sideslip angle of the flight time and the coordinates[ , , ].

[0076] Then, for a grid node used for aerodynamic thermal environment calculation of the ceramic radome outer surface, at flight time The corresponding recovery enthalpy and cold wall heat flux are and ; wherein is the coordinate of the grid node .

[0077] Step 1.2, the structure scheme to be evaluated, specifically: obtaining the assembly three-dimensional structure numerical model of the ceramic radome; the ceramic radome includes a radome body and a steel ring, and the inner ring surface of the root of the radome body is fixed with the steel ring, as shown in Figure 3 .

[0078] Step 2, for the ceramic radome, a structure coordinate system is constructed using the structure scheme, and a circumferential discretization strategy of the ceramic radome is set in the structure coordinate system to determine a plurality of meridian planes of the ceramic radome.

[0079] Step 2.1, the definition of the structure coordinate system based on the assembly three-dimensional structure numerical model of the ceramic radome; as shown in Figure 4 , the origin of the structure coordinate system is the theoretical top point of the head of the radome body; the axis is positive along the fuselage axis of the aircraft; the axis is perpendicular to the axis, located in the symmetry plane of the fuselage, and positive upward; the axis is determined by the right-hand rule, perpendicular to the coordinate plane.

[0080] Then the relationship of coordinate mapping transformation of the outer surface of the ceramic radome in the aerodynamic thermal environment calculation coordinate system to the structure coordinate system is:

[0081] The coordinates , , of the outer surface of the ceramic radome in the aerodynamic thermal environment calculation coordinate system are known inputs of step 1.1; it is assumed that the coordinates in the structure coordinate system are , , Z ; then the transformation from , , to , , Z includes translation and rotation:

[0082] Step 2.1.1, translation conversion:

[0083] ; ; ;

[0084] wherein , , ] is a coordinate translation vector, , , ] is a coordinate after translation. , , ] is a coordinate after translation.

[0085] As shown in Figure 2 , in an embodiment of the present application, the translation vector is , , ] = [0, 0, 0].

[0086] Step 2.1.2, the coordinates after translation , , ] are subjected to a rotation transformation, and the conversion order is to rotate by an angle around the axis, then rotate by an angle around the axis, and finally rotate by an angle around the axis; the corresponding three rotation transformation matrices are respectively:

[0087] ; ; ;

[0088] After the rotation transformation, the final mapping transformation relationship of the coordinates , , ] to , , Z ] is:

[0089] .

[0090] In an embodiment of the present application, , , .

[0091] Step 2.2, a circumferential discrete strategy of the ceramic radome is set in the structural coordinate system, specifically:

[0092] As shown in Figure 4 , a semi-infinite long vector is defined in the reference plane of the structural coordinate system , and the semi-infinite long vector starts from the origin of the structural coordinate system and forms a semi-infinite long coordinate plane with the axis, which is defined as a discrete surface; a semi-infinite long vector Around Axis self axial direction clockwise to Rotation along the axis to form several discrete surfaces, wherein each discrete surface is... Angle formed by the reference plane , is defined as a discrete angle.

[0093] since Rotate the axis clockwise to Uniform selection within the axis range The discrete surfaces are used as meridional surfaces to discretize the ceramic radome circumferentially, and the corresponding discrete angles are used as meridional angles; where the th discrete surface is the meridional surface. The meridian angle is:

[0094] ;

[0095] Among them, using Simultaneously characterize the first Each meridian angle and its corresponding meridian plane; when When, a semi-infinite vector point to Axial direction, When, a semi-infinite vector Point to + Y direction.

[0096] In one embodiment of the present invention, a selection is made. A single-course noodle dish.

[0097] Step 3: Based on the circumferential discretization strategy of the ceramic radome, a training sample dataset is constructed using feature points on the axial design section of the ceramic radome to establish an aerodynamic thermal environment interpolation model. Based on the aerodynamic thermal environment parameters obtained from the aerodynamic thermal environment interpolation model at each flight time for all feature points, the meridional plane with the most severe aerodynamic heating of the ceramic radome throughout the flight is determined. Specifically, this includes:

[0098] Step 3.1, each meridian plane The lines of intersection with the outer surface of the ceramic radome form a corresponding line of intersection. ; Calculate the intersection line The mapping relationship between the coordinates of each point and the structural coordinate system is as follows:

[0099] Intersection The coordinates of each point in the structural coordinate system are [ It can be calculated using the following formula:

[0100] ; ; ;

[0101] in Intersection the outer surface of the ceramic radome cross section, is the meridian plane corresponding axial coordinate.

[0102] Step 3.2, defining the axial design section of the ceramic radome, specifically: the front end structure of the invar ring heat sink mutation, the ceramic radome is prone to form thermal stress concentration, which can characterize the local structure thermal strength; selecting the cross section where the front end of the invar ring is located as the axial design section, the axial coordinate of the axial design section in the structural coordinate system is .

[0103] As shown in Figure 3 , in an embodiment of the present application, m .

[0104] Step 3.3, determining the feature points on the axial design section of the ceramic radome, and constructing the feature point set; specifically:

[0105] the corresponding axial coordinate of the axial design section, the corresponding intersection point on each intersection line can be uniquely determined, and the intersection point is taken as a feature point; based on the mapping relationship of step 3.1, the calculation formula of the coordinates , , of the feature point is:

[0106] ; ; ;

[0107] wherein, is the outer surface of the ceramic radome cross section , which is measured by the assembly three-dimensional structure model of the ceramic radome in step 1.2.

[0108] For all the meridian planes discretely obtained in step 2.2, the feature point set on the intersection line at axial coordinate is constructed , , ; wherein, , , are the coordinates of the feature points of the th intersection line .

[0109] ​In the embodiments of the present invention, there are a total of 41 feature points, which can be obtained. Axis coordinates are The radius of gyration can be obtained by measurement. =0.17, then there are 41 feature points. axis, Axis coordinates are and .

[0110] Step 3.4: Construct a reference point set using the grid nodes divided on the outer surface of the ceramic radome, and use the feature point set as the query point set; based on The nearest neighbor search method expands the query point set. A search is performed by traversing the nearest neighbor points to obtain the corresponding search point set; a training sample dataset is then constructed based on the search point set; specifically:

[0111] Step 3.4.1, Setting The reference point set, query point set, and number of nearest neighbors for the nearest neighbor search method.

[0112] First, define the reference point set. ; Reference point set Reference points The coordinates are represented as The reference point uses the grid nodes used in the aerodynamic and thermal environment calculation of the outer surface of the ceramic radome; the total number of grid nodes is denoted as [reference point name]. The result is obtained from the calculation input in step 1. .

[0113] Then define the query point set. ; The first query point in the set Query points The coordinates are represented as The query point uses the feature point set constructed in step 3.3. Feature points in, i.e. ; .

[0114] Redefine the nearest neighbor number: Nearest neighbor number It is a positive integer.

[0115] In one embodiment of the present invention, the total number of grid nodes The number of feature points is 10296. The nearest neighbor number is 41. It is 20.

[0116] Step 3.4.2, Calculate the query point set Coordinates of each feature point and reference point set Euclidean distance between the coordinates of each grid node ;in, , Each represents a query point set. The Middle Coordinates and reference point set of each grid node The Middle The coordinates of the feature points.

[0117] Step 3.4.3 involves spatial partitioning based on the reference point set, query point set, and nearest neighbor number defined in Step 3.4.1, and the Euclidean distance calculated in Step 3.4.2, to construct the nearest neighbor search algorithm. K - D Tree"( K - Dimensional Tree Specifically:

[0118] Firstly Axis as a dividing dimension Select the current reference point set The coordinates of each reference point in the dimension median on The median As a dividing point The split point divides the space into two semi-space subtrees, including the left subtree. and right subtree That is, for all reference points, such as its The axis coordinates are less than the dividing point. Then the grid node is assigned to the left subtree. Otherwise, it will be assigned to the right subtree. ; Remember the left subtree and right subtree In the segmentation dimension The upper boundary is and The segmented space is a hyperrectangular region. Spatial dimension =3, including The dimensions of the three axes.

[0119] Step 3.4.4, based on the left subtree constructed in step 3.4.3 and right subtree For the query point set Each query point in the middle The traversal search of the nearest neighbors is as follows:

[0120] First, regarding the first Query points Define its first The distance between the nearest neighbors is This parameter It will be updated dynamically;

[0121] Secondly, by segmentation dimension Compare path selection; if query point In the segmentation dimension coordinates on Less than the dividing point If the path is right, then the left subtree is selected; otherwise, the right subtree is selected.

[0122] Finally, based on the path selection results, the process recursively calculates the path from the root node to the leaf node, iteratively calculating the internal nodes of the leaf nodes to the query point. The distance, where the hyperrectangular region arrive minimum distance The specific calculation method used to determine the pruning criteria for the current search is as follows:

[0123] (1) If ;

[0124] (2) If ;

[0125] (3) Other situations. ;

[0126] in, Indicated by Axis as a dividing dimension left subtree and right subtree In the segmentation dimension The upper boundary is and Spatial dimension is .

[0127] The pruning conditions are: when When the current search term is reached, skip the left or right subtree and enter the backtracking process. Specifically, first update the current search term using a max-heap. Distance of a nearest neighbor Next, calculate the minimum possible distance between sibling nodes. ,like If the left or right sibling subtree is not found, then a recursive search is performed on the left or right sibling subtree.

[0128] After completing the above steps, backtrack upwards to the root node to obtain the query point. of The search results of the nearest neighbor points are used to form the search point set of the query point. ;in, For the first Query points of k Group search points, search point set It isk An array of 3 × 1000.

[0129] Step 3.4.5: The functional relationship between the aerodynamic thermal environment and the coordinates of the outer surface of the ceramic radome can be considered as a multiple-input multiple-output system; based on the search point set obtained in step 3.4.4... Construct a feature point set The training sample dataset for the aerodynamic thermal environment interpolation model at each feature point within the interior is as follows:

[0130] query point search point set As input, flight time This search point set All search points Aerodynamic thermal environment parameters (at which search point is also the reference point) For output, a set of flight times can be constructed. The training sample data for the interpolation prediction model, including aerodynamic thermal environment parameters. Including recovery enthalpy and cold wall heat flux; then query the point set. The training sample dataset consists of all the training sample data corresponding to each flight moment during the flight of the aircraft, representing the training sample dataset as follows:

[0131] { } ;

[0132] in This indicates the number of flight times.

[0133] In one embodiment of the present invention, the 13th query point is used. For example, its corresponding search point set A sequence of 20 × 3 can be represented as follows:

[0134] ;

[0135] in The units of each element in the text are: m .

[0136] Correspondingly, aerothermal environment parameters A sequence of 20 × 2 can be represented as follows:

[0137] .

[0138] Among them, the number of aerodynamic thermal environment parameters The first column is the recovery enthalpy; the second column is the cold wall heat flow.

[0139] Step 3.5: Using the training sample dataset, construct an aerodynamic thermal environment interpolation model using radial basis functions; specifically:

[0140] First, at the flight moment , an aerodynamic thermal environment interpolation model is constructed based on a sample data set Radial Basis Function , RBF using a radial basis function ; wherein the basis function in the radial basis function is in the form of a thin plate spline Thin Plate Spline function.

[0141] The aerodynamic thermal environment interpolation model is expressed as follows:

[0142] ;

[0143] In the above formula, is a query point in a query point set , is an aerodynamic thermal environment parameter obtained by interpolation of the query point ; is an aerodynamic thermal environment parameter of a search point in a search point set ; is an aerodynamic thermal environment parameter of a search point in a search point set ; is a basis function, is a basis function matrix, is a pseudo-inverse matrix of the basis function matrix .

[0144] Step 3.6, using the aerodynamic thermal environment interpolation model, the aerodynamic thermal environment parameters of each query point in the query point set are obtained by interpolation, which are also the aerodynamic thermal environment parameters of all feature points in the feature point set at each flight moment.

[0145] Step 3.7, according to the aerodynamic thermal environment parameters of all feature points at each flight moment, the most severe meridian plane of aerodynamic heating of the ceramic radome during the entire flight is identified, which specifically includes:

[0146] Step 3.7.1, for the i-th feature point in the feature point set j , the maximum heat flux during the entire flight is calculated using the linear scanning method through the aerodynamic thermal environment parameters.

[0147] Step 3.7.2, the total heating amount of the feature point during the entire flight is calculated, which can be obtained by integrating the cold wall heat flux with respect to time.

[0148] Step 3.7.3, according to the methods of steps 3.7.1 and 3.7.2, the aerodynamic thermal environment parameters of all feature points in the feature point set are obtained ​Maximum heat flux density at each characteristic point Total heating capacity ; at all maximum heat flux densities Select the maximum value; the meridian plane containing the feature point corresponding to this maximum value is the meridian plane where the aerodynamic heating of the ceramic radome is most demanding throughout the flight. Specifically, if there are multiple maximum values, then the total heating amount is further selected from all feature points corresponding to the maximum values. The largest feature point, located on the meridional plane, is the meridional plane where the aerodynamic heating of the ceramic radome is most demanding throughout the flight. .

[0149] Step 4: Based on the meridional plane where aerodynamic heating of the ceramic radome is most demanding, construct a two-dimensional characteristic structural model for transient heat transfer and thermal stress analysis of the ceramic radome, and determine the external contour line of the two-dimensional characteristic structural model, specifically:

[0150] The most demanding meridional plane for aerodynamic heating of the ceramic radome. Using the reference plane as a reference, the two-dimensional projection structure of the ceramic radome on this reference plane is the two-dimensional characteristic structural model for transient heat transfer and thermal stress analysis of the ceramic radome, such as... Figure 6 As shown.

[0151] The ceramic radome is aerodynamically heated to the most demanding meridional plane. The line of intersection with the outer surface of the ceramic radome serves as the outer contour line of the two-dimensional feature structure model. .

[0152] Step 5: Construct the axial thermal response calculation interval of the ceramic radome, discretize the axial thermal response calculation interval and map it onto the outer contour line of the two-dimensional feature structure model, thereby constructing a set of mapped grid points; perform interpolation calculation on the set of mapped grid points to obtain the aerodynamic thermal environment parameters of the outer contour line at each flight time.

[0153] This process prepares the groundwork for transient heat transfer and thermal stress analysis of the structure, and specifically includes:

[0154] Step 5.1, define the planar coordinate system of the two-dimensional feature structure model, specifically as follows:

[0155] According to the definition of the structural coordinate system in step 2, the planar coordinate system... Axis and structural coordinate system axis y Consistent; Plane coordinate system Axis is defined as , by the structural coordinate system Rotate the axis clockwise by the meridian angle Obtain and satisfy The planar coordinate system of the two-dimensional feature structure model is then... Coordinate system, where the origin is... It coincides with the theoretical apex of the ceramic antenna radome's head.

[0156] Step 5.2, determine the axial thermal response calculation range of the ceramic radome in the planar coordinate system, specifically as follows:

[0157] In the planar coordinate system of the two-dimensional feature structure model, the axial coordinate of the rear end face of the ceramic radome is: The axial coordinate of the front end of the Invar ring is All values ​​are obtained from the three-dimensional structural digital model measurement of the ceramic radome assembly described in step 1.2; therefore, the axial thermal response calculation range of the ceramic radome is taken as […]. To prevent the calculation interval from being too small and affecting the axial heat transfer calculation results, its specific value must satisfy:

[0158] ; ;

[0159] For ease of calculation, this scheme takes... for:

[0160] .

[0161] Step 5.3, within the axial thermal response calculation range of the ceramic radome [ [On] Spatial discretization along the axial direction yields discrete segments; specifically:

[0162] The axial thermal response calculation range of the ceramic radome is [ Evenly divided into There are discrete segments; the distance between each segment is:

[0163] ;

[0164] Calculate the first interval discrete segments The axis coordinates are:

[0165] .

[0166] In embodiments of the present invention, taking There are a total of 51 discrete segments.

[0167] Step 5.4, calculate the axial thermal response range of the ceramic radome [ The discrete segments within are mapped to the outer contour lines of the two-dimensional feature structure model described in step 4. The corresponding mapped grid points are obtained, thus forming a set of mapped grid points. Among them, the first imapping grid points coordinates are:

[0168] ; ; ;

[0169] wherein, is the meridian plane is the axial coordinate is the outer surface revolution radius of the cover cross section, which is obtained by measuring the structure model input described in step 1.2; .

[0170] In the embodiment of the application, the coordinate calculation results of part of the 51 mapping grid points are as follows:

[0171] Table 1: Coordinate calculation results of mapping grid points in the embodiment

[0172]

[0173] Step 5.5, aerodynamic heat environment reconstruction interpolation calculation is carried out on the mapping grid points in the mapping grid point set , to obtain the aerodynamic heat environment parameters of all mapping grid points of the external contour line at each flight time; the specific interpolation method is the same as step 3.

[0174] Step 6, heat transfer calculation grid division is carried out on the two-dimensional feature structure model, and the structure transient temperature distribution of the two-dimensional feature structure model is calculated in combination with the aerodynamic heat environment parameters of the external contour line at each flight time; specifically including:

[0175] Step 6.1, based on the axial heat response calculation interval of the ceramic antenna cover, heat transfer calculation grid division is carried out on the two-dimensional feature structure model, specifically:

[0176] In the plane coordinate system , the discrete segment division scheme of step 5.3 is adopted in the axial direction, that is, it is divided into discrete segments; in the plane coordinate system , it is divided into thickness sections along the thickness direction of the cover and the steel ring, wherein the cover part contains thickness sections, and the discrete step length is ; the steel ring part contains thickness sections, and the discrete step length is: ; wherein, ; is the thickness of the cover, The thickness of the invar ring is measured by the three-dimensional structure model of the ceramic radome assembly in step 1.2; all discrete segments and thickness segments are measured in the plane coordinate system axis, all quadrilateral meshes composed of the axis direction are the heat transfer calculation meshes, as shown in Figure 7 .

[0177] In the embodiments of the present application, 51 discrete segments in the axis direction, the invar ring part in the axis direction contains thickness segments, and the radome part contains thickness segments, finally forming a quadrilateral mesh as shown in Figure 7 . The heat transfer calculation mesh of the radome part has a total of 806, and the heat transfer calculation mesh of the invar ring part has a total of 546, a total of 1352 heat transfer calculation meshes.

[0178] Step 6.2, after applying the aerodynamic heat environment parameters of each flight time of the external contour line in step 5.5 to the heat transfer calculation mesh division result of the two-dimensional feature structure model, the structure transient temperature distribution is calculated; specifically including:

[0179] Step 6.2.1, the structure temperature field control equation adopts the two-dimensional transient heat conduction equation, specifically:

[0180] ;

[0181] Wherein, is the material density of the ceramic radome; is the specific heat capacity of the material at constant pressure; Lambda is the thermal conductivity of the material; is the structure temperature; is the flight time; x is the axis direction coordinate; is the axis direction coordinate.

[0182] Step 6.2.2, the outer surface of the ceramic radome is a gas-solid coupling heat exchange boundary, ignoring the influence of body radiation, the heat conducted to the inside of the ceramic radome axis is equal to the aerodynamic heating and the external radiation heat of the high-temperature surface, specifically:

[0183] ;

[0184] Wherein and are the specific heat capacity of the material at constant pressure; is the structure transient temperature of the outer surface of the ceramic radome under the action of aerodynamic heating; For wall enthalpy, It is the specific heat capacity of the gas at constant pressure on the outer surface of the ceramic radome. , is the Stefan-Boltzmann constant; The emissivity of the ceramic radome material surface.

[0185] Step 6.2.3, the inner wall of the ceramic radome structure is assumed to be an ideal thermally insulating wall surface, specifically:

[0186] ;

[0187] in, The coordinates represent the thickness of the inner wall of the ceramic radome structure.

[0188] Step 6.2.4: The two-dimensional transient heat conduction equation is numerically solved using the second-order central difference method to obtain the structural transient temperature distribution of the two-dimensional characteristic structure model of the ceramic radome throughout the flight.

[0189] In one embodiment of the present invention, such as Figure 8 As shown, P Point 1 (heat transfer calculation grid) is on the outer surface of the outer shell. The wall temperature at this point exhibits a strong nonlinear change with flight time, reaching a maximum of approximately 1083℃. P Point 2 is located on the inner wall of the enclosure, approximately 0.106 axially from the front end of the Invar ring. m The temperature rise and fall slope of this part over flight time is significantly lower than that of the outer wall, with a maximum temperature of about 560°C. P Point 3 is located at the interface between the cover and the Invar ring, approximately 0.03816 mm from the rearward direction of the front end of the Invar ring. m Due to the heat sink and axial heat conduction of the Invar ring structure, the temperature change in this part is more gradual, with the highest temperature being about 172℃. P Point 4 is located on the inner wall of the cover at the front end of the Invar ring. This point is at a location of abrupt structural heat sink change. The temperature response process is affected by the aerodynamic heating of the outer wall and the heat transfer within the cover and Invar ring structure. The heating and cooling rates are between P 2 points and P Between the three points, the radome structure exhibits a characteristic of alternating cold and hot temperatures.

[0190] In this embodiment, the calculation of the transient temperature distribution of the structure takes only about 257 seconds. s (processor is) Intel Xeon CPU E 5-1603, 2.8GHz GHz (single-core computing).

[0191] Step 7: Calculate the structural temperature gradient based on the transient temperature distribution of the structure; specifically including:

[0192] Based on the transient temperature distribution of the structure, the second-order central difference method is used to traverse and calculate the heat transfer calculation grid for each heat transfer calculation grid. , The transient temperature of the structure at different flight times at point ) in a plane coordinate system shaft and Partial derivatives in the axial direction and Then, partial derivatives are used to calculate the heat transfer computational grid ( , Structural temperature gradient at ) .

[0193] In one embodiment of the present invention, with reference to the appendix Figure 8 As shown P Taking 4 points as an example, the entire flight path is given. P Temperature at 4 points x , y The structural temperature gradient calculation results were obtained; the calculation of all 806 heat transfer computational grids was completed at all flight times, taking only about 112 seconds. s (processor is) Intel Xeon CPU E 5-1603, 2.8GHz GHz (single-core computing).

[0194] Step 8: Calculate the transient thermal stress distribution of the ceramic radome using the structural temperature gradient, specifically including:

[0195] Step 8.1: The transient thermal stress of the ceramic radome is calculated using a one-dimensional linear approximation formula:

[0196] ;

[0197] in, Transient thermal stress; The elastic modulus of the ceramic radome material; In response to the situation; is the coefficient of linear expansion of the material. Here are the temperature gradient parameters.

[0198] Step 8.2, using the formula from Step 8.1, at the flight time The heat transfer computational grid of the ceramic radome ( , Transient thermal stress caused by structural temperature gradient at point ) It can be calculated using the following formula:

[0199] ;

[0200] in, , Flight times Heat transfer computational grid ( , The elastic modulus and coefficient of linear expansion of the ceramic radome material at () are provided by test data of the material's parametric performance at different temperatures.

[0201] Step 8.3, repeat step 8.2, traverse and calculate the heat transfer calculation grid of the ceramic radome at each moment of flight throughout the entire flight ( , The transient thermal stress at point () is obtained from the heat transfer calculation grid () , Transient thermal stress sequence throughout the flight .

[0202] Step 8.4: Repeat step 8.3 for all heat transfer calculation grids to obtain the transient thermal stress sequence of all heat transfer calculation grids. When the interval between flight times and the distance between the heat transfer calculation grids are sufficiently small (less than a set threshold), the calculation results of the transient thermal stress sequence of all heat transfer calculation grids can represent the transient thermal stress distribution of the ceramic radome under nonlinear aerodynamic heating throughout the flight.

[0203] One embodiment of the present invention uses Figure 8 As shown Taking a point as an example, the transient thermal stress generated by the nonlinear aerodynamic heating of the ceramic radome, changes in the structural heat sink, and internal heat transfer coupling is given, such as Figure 10 As shown; the temperature gradient calculation for all 806 heat transfer computational grids at all discrete time points was completed, and the time taken using matrix operations was only about 15 seconds. s (processor is) Intel Xeon CPU E 5-1603, 2.8GHz GHz (single-core computing).

[0204] In contrast to the embodiments of the present invention, Figure 10 The variation process of the first principal stress at the same location of the radome with flight time, obtained by three-dimensional finite element force-thermal coupling calculation, is also presented.

[0205] In terms of computational accuracy, the transient thermal stress variation trend calculated by this invention is basically consistent with that of the finite element analysis. Specifically, the maximum transient thermal stress of the ceramic radome calculated in the embodiment is approximately 32.1 kJ. MPa The finite element calculation yields approximately 29.8. MPa The difference between the two is only about 7%, which can meet the error requirements of engineering design.

[0206] In terms of computational efficiency, the heat transfer calculation grid in this embodiment of the invention consists of 1352 grids, and the calculation of the transient temperature distribution, temperature gradient, and transient thermal stress of the structure takes approximately 6.4 seconds. Min ( Intel Xeon CPU E 5-1603, 2.8GHz GHz, single-core computing); the grid nodes of three-dimensional finite element calculation are 102,000, and the time consumption of transient heat transfer and thermal stress sequential coupling calculation is 25.17 h ( Intel Xeon CPU E 5-1603, 2.8 GHz , 4-core parallel computing, and the total machine time is 6040.8 Min ). The number of heat transfer calculation grids required by the embodiment of the application is only 1.32% of the grid nodes used in three-dimensional finite element analysis, and more than 100 h , which has an incomparable computing efficiency advantage over the latter.

[0207] The above embodiments are only used to illustrate the technical solutions of the present application, but not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should be included in the protection scope of the present application.

Claims

1. A method for fast calculation of transient thermal stress of a ceramic radome along a flight trajectory, characterized in that, The method comprises the following steps: determining the calculation input, including the aerodynamic thermal environment of the ceramic radome and the structure scheme to be evaluated; constructing a structure coordinate system for the ceramic radome using the structure scheme, and setting a circumferential discretization strategy for the ceramic radome in the structure coordinate system to determine a plurality of meridians of the ceramic radome; based on the circumferential discretization strategy of the ceramic radome, constructing a training sample data set in combination with feature points on the axial design section of the ceramic radome, for establishing an aerodynamic thermal environment interpolation model; based on the aerodynamic thermal environment parameters of all feature points at each flight time obtained by the aerodynamic thermal environment interpolation model, determining the most severe meridian of the ceramic radome subjected to aerodynamic heating throughout the flight; based on the most severe meridian of the ceramic radome subjected to aerodynamic heating, constructing a two-dimensional feature structure model for transient heat transfer and thermal stress analysis of the ceramic radome, and determining the external contour line of the two-dimensional feature structure model; constructing an axial thermal response calculation interval of the ceramic radome, discretizing and mapping the axial thermal response calculation interval to the external contour line of the two-dimensional feature structure model, thereby constructing a set of mapped grid points; performing interpolation calculation on the set of mapped grid points to obtain the aerodynamic thermal environment parameters of the external contour line at each flight time; performing heat transfer calculation grid division on the two-dimensional feature structure model, and combining the aerodynamic thermal environment parameters of the external contour line at each flight time to calculate the structure transient temperature distribution of the two-dimensional feature structure model; based on the structure transient temperature distribution, calculating the structure temperature gradient; using the structure temperature gradient to calculate the transient thermal stress distribution of the ceramic radome.

2. The method for fast calculation of transient thermal stress of ceramic radome along flight trajectory according to claim 1, characterized in that, The aerodynamic thermal environment includes the aerodynamic thermal environment parameters of the grid nodes divided on the outer surface of the ceramic radome at different flight times; the aerodynamic thermal environment parameters include recovery enthalpy and cold-wall heat flux; the structure scheme to be evaluated includes a three-dimensional structure numerical model of the ceramic radome; the ceramic radome includes a radome body and a steel ring, and the inner ring surface of the radome body root is fixed with the steel ring.

3. The method of claim 1, wherein, In the structure coordinate system, the circumferential discretization strategy of the ceramic radome is set to determine a plurality of meridians of the ceramic radome, which comprises: In the structural coordinate system, a semi-infinite length vector is defined in the reference plane, the semi-infinite length vector starts from the origin of the structural coordinate system, and forms a semi-infinite length coordinate plane with the axis, which is defined as a discrete surface; the semi-infinite length vector rotates around the axis from the axis direction to the axis direction to form a plurality of discrete surfaces; a plurality of discrete surfaces are uniformly selected from the plurality of discrete surfaces as meridional surfaces, which are used to disperse the ceramic radome circumferentially; and the ceramic radome is formed by the plurality of meridional surfaces. axis direction to form a plurality of discrete surfaces; a plurality of discrete surfaces are uniformly selected from the plurality of discrete surfaces as meridional surfaces, which are used to disperse the ceramic radome circumferentially; and the ceramic radome is formed by the plurality of meridional surfaces. wherein the structural coordinate system has The z-axis is positive along the fuselage axis of the aircraft; The x-axis is positive along the longitudinal axis of the aircraft; The y-axis is positive along the vertical axis of the aircraft; The z-axis is determined using the right-hand rule.

4. The method for fast calculation of transient thermal stress of ceramic radome along flight trajectory according to claim 1, characterized in that, combining the feature points on the axial design section of the ceramic radome to construct a training sample data set for establishing an aerodynamic thermal environment interpolation model, which comprises: each meridian intersects with the outer surface of the ceramic radome to form a corresponding intersection line; selecting the cross section where the front end of the steel ring of the ceramic radome is located as the axial design section of the ceramic radome; determining the feature points on the axial design section of the ceramic radome to construct a feature point set; wherein the feature points are the intersection points of the intersection lines and the axial design section; A reference point set is constructed by using grid nodes divided on the outer surface of the ceramic radome, and the feature point set is taken as a query point set; based on The neighbor search method expands the query point set The traversal search of one neighbor point obtains a corresponding search point set; a training sample data set is constructed based on the search point set; using the training sample data set, constructing an aerodynamic thermal environment interpolation model using a radial basis function; using the aerodynamic thermal environment interpolation model, obtaining the aerodynamic thermal environment parameters of all feature points in the feature point set at each flight time by interpolation.

5. The method for rapid calculation of transient thermal stress of ceramic radome along flight trajectory according to claim 1, characterized in that, Based on the aerodynamic thermal environment parameters of all feature points at each flight time obtained by the aerodynamic thermal environment interpolation model, the most severe meridian of the ceramic radome subjected to aerodynamic heating throughout the flight is determined, which comprises: for each feature point, the maximum heat flux density throughout the flight is calculated by the aerodynamic thermal environment parameters using the linear scanning method; calculating the total heating amount at the feature point throughout the flight; After obtaining the maximum heat flux density and the total heating amount of all feature points, the maximum value in all maximum heat flux densities is selected, and the meridian plane where the feature point corresponding to the maximum value is located is the most severe meridian plane of the ceramic radome aerodynamic heating during the whole flight; If there are multiple maximum values, then further select the feature point with the maximum total heating amount from all feature points corresponding to the maximum values, and the meridian plane where the feature point is located is the most severe meridian plane of the ceramic radome aerodynamic heating during the whole flight.

6. The method for rapid calculation of transient thermal stress of ceramic radome along flight trajectory according to claim 1, characterized in that, Based on the most severe meridian plane of the ceramic radome aerodynamic heating, a two-dimensional feature structure model for transient heat transfer and thermal stress analysis of the ceramic radome is constructed, and the external contour line of the two-dimensional feature structure model is determined, including: Taking the most severe meridian plane of the ceramic radome aerodynamic heating as the reference plane, the two-dimensional projection structure of the ceramic radome on the reference plane is the two-dimensional feature structure model for transient heat transfer and thermal stress analysis of the ceramic radome; The intersection line of the most severe meridian plane of the ceramic radome aerodynamic heating and the outer surface of the ceramic radome is the external contour line of the two-dimensional feature structure model.

7. The method of claim 1, wherein, An axial thermal response calculation interval of the ceramic radome is constructed, the axial thermal response calculation interval is discretized and mapped onto the external contour line of the two-dimensional feature structure model, thereby constructing a set of mapped grid points; An interpolation calculation is performed on the set of mapped grid points to obtain the aerodynamic thermal environment parameters of the external contour line at each flight time, including: Defining a plane coordinate system of the two-dimensional feature structure model; Determining the axial thermal response calculation interval of the ceramic radome in the plane coordinate system; The axial thermal response calculation interval of the ceramic radome is divided into a plurality of subintervals The space is discretized in the axial direction to obtain discrete segments; all the discrete segments are respectively mapped to the external contour line of the two-dimensional feature structure model to obtain corresponding mapping grid points, thereby forming a mapping grid point set; Performing aerodynamic thermal environment reconstruction interpolation calculation on the mapped grid points in the set of mapped grid points to obtain the aerodynamic thermal environment parameters of the external contour line at each flight time.

8. The method of claim 1, wherein, The two-dimensional feature structure model is subjected to heat transfer calculation grid division, and the structure transient temperature distribution of the two-dimensional feature structure model is calculated in combination with the aerodynamic thermal environment parameters of the external contour line at each flight time, including: The two-dimensional feature structure model is subjected to heat transfer calculation grid division based on the axial thermal response calculation interval of the ceramic radome; For the heat transfer calculation grid division result of the two-dimensional feature structure model, after applying the aerodynamic thermal environment parameters of the external contour line at each flight time, the structure transient temperature distribution is calculated.

9. The method of claim 1, wherein, The structure temperature gradient is used to calculate the transient thermal stress distribution of the ceramic radome, including: At the time of flight The heat transfer calculation grid , ) is caused by the transient thermal stress of the structural temperature gradient is obtained by the following formula: ； wherein , are the flight times the elastic modulus and the linear expansion coefficient of the ceramic radome material at the heat transfer calculation grid , ​ The heat transfer calculation grid of the ceramic radome at each flight moment is traversed and calculated. , The transient thermal stress at point () is obtained from the heat transfer calculation grid () , Transient thermal stress sequence throughout the flight ; The transient thermal stress sequence of all heat transfer calculation grids is used to represent the transient thermal stress distribution of the ceramic radome.

10. A terminal device comprising a processor, a memory, and a computer program stored in the memory; characterized in that, When the processor executes the computer program, the method for rapidly calculating the transient thermal stress of the ceramic radome along the flight trajectory according to any one of claims 1-9 is realized.

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