Method for assigning aerodynamic thermal boundary conditions in heat transfer simulation of variable sweep wing structure

Abstract

The application provides a method for assigning aerodynamic heat boundary conditions of variable sweep wing structure heat transfer simulation, which comprises defining a wing surface position with a first sweep angle in a whole trajectory as a reference position, rotating heat environment data to the reference position, and dividing a structure heat transfer grid at the reference position; then, creating a "point method" equation for the outer edge of a wing box, establishing a structure heat transfer grid surface grid point space position criterion based on the equation, and dividing the grid points into a set of aerodynamic heating points and a set of non-aerodynamic heating points; taking the set of aerodynamic heating points as an aerodynamic heat data interpolation target area, performing heat environment interpolation, and assigning 0Kw / m 2 to the cold wall heat flux of the set of non-aerodynamic heating points, restoring the constant value of enthalpy, and forming an adiabatic boundary condition. The method solves the problems that aerodynamic heat environment data cannot be directly interpolated to the structure heat transfer calculation grid surface due to the change of the spatial position of the variable sweep wing structure, and the structure heat transfer grid spatial position changes, resulting in that heat transfer analysis cannot be continuously performed along the whole trajectory.

Description

Technical Field

[0001] This invention belongs to the field of numerical simulation of heat transfer in structures under aerodynamic heating, and particularly relates to a method for assigning aerodynamic thermal boundary conditions for heat transfer simulation of variable sweep wing structures. Background Technology

[0002] The surface of the pneumatically heated structure is subjected to pneumatic heating. During the heat transfer numerical calculation, thermal environment data needs to be called up and assigned to the surface mesh of the structure at each time step as the boundary condition for the heat transfer numerical calculation.

[0003] Under the influence of high-speed airflow, the surface of the variable-sweep wing structure undergoes aerodynamic heating. Numerical calculations of heat transfer along the trajectory of the structure using existing technology employ a decoupled aerodynamic and heat transfer calculation method: First, thermal environment data of the structure surface is obtained, including cold wall heat flux data and regenerating enthalpy data. During the numerical calculation, the structure surface temperature is extracted at each time step, and the wall enthalpy is calculated. Simultaneously, cold wall heat flux data and regenerating enthalpy data from typical moments in the trajectory are retrieved. Linear interpolation is used to obtain the cold wall heat flux and regenerating enthalpy values ​​at the current calculation moment. The injected heat flux is obtained through cold and hot wall heat flux conversion, serving as the aerodynamic and thermal boundary conditions for the structure in the heat transfer analysis.

[0004] A portion of the variable-sweep wing surface is located in the high-speed incoming flow and is subjected to aerodynamic heating, while the remaining portion is housed within the fuselage wing box and does not directly contact the high-speed incoming flow, thus experiencing no aerodynamic heating effect. Numerical simulations of heat transfer in the swept-wing structure should apply aerodynamic boundary conditions to the surface in the high-speed incoming flow at each time step, and apply adiabatic boundary conditions to the portion housed within the wing box.

[0005] Existing technologies decouple the analysis of the airfoil thermal environment and structural heat transfer, suitable for cases where the spatial position of the structure remains constant. However, for variable-sweep wing structures, the spatial position changes with the sweep angle. Using existing technologies, the heat transfer calculation process is as follows: As the sweep angle changes, the spatial position of the airfoil changes accordingly. A separate flow field calculation grid needs to be defined for each spatial position to obtain thermal environment data. Similarly, a separate variable-sweep airfoil structure heat transfer grid needs to be defined for each spatial position. Two types of boundaries are set on the surface of the structural grid: aerodynamic heating boundaries and non-aerodynamic heating boundaries. The thermal environment at each spatial position is interpolated onto the aerodynamic heating region boundary of the structural grid at that position, forming a boundary condition dataset that can be used for heat transfer numerical simulation. Since the airfoil's spatial position changes, heat transfer numerical simulation cannot continue on the same structural grid. After the calculation is completed for a continuous time period at one spatial position, the airfoil structure temperature field data needs to be saved. The temperature field data is rotated according to the angle of change of the next spatial position relative to the current position and interpolated into the structural grid of the next spatial position to form the initial temperature field of this spatial volume. Then, heat transfer numerical simulation continues.

[0006] It is evident that, using existing technology, the number of sweep angles of the variable-sweep wing throughout the entire trajectory determines the number of structural meshes required. The heat transfer numerical calculation cannot be performed continuously along the entire trajectory. After the calculation is completed for a time period under a sweep angle attitude, the temperature field needs to be output and interpolated into the structural mesh under the new sweep angle attitude in order to continue calculating the heat transfer process under the new attitude angle.

[0007] Even if the thermal environment mesh is rotated to unify its spatial position to the airfoil position corresponding to the initial sweep angle, a separate structured mesh is still needed for each spatial position. This is because although the spatial position of the structured mesh can be consistent with the initial spatial position of the thermal environment mesh, the aerodynamic heating boundary and non-aerodynamic heating boundary regions are different at each position. Therefore, a separate structured mesh is still needed for each spatial position.

[0008] If only one structural mesh is used, the thermal environment data cannot be accurately interpolated onto the surface of the structural heat transfer mesh, thus making structural heat transfer simulation impossible.

[0009] In other words, traditional techniques for variable-sweep wings have two main problems: (1) they require a large number of structural meshes; (2) numerical simulations need to be interrupted as the wing surface position changes, and the temperature field of the structure space needs to be saved and interpolated onto a new structural mesh before calculations can continue. These two problems result in a large workload and low efficiency for traditional techniques. Summary of the Invention

[0010] The present invention aims to solve at least one of the technical problems existing in the prior art.

[0011] Therefore, this invention provides a method for assigning aerodynamic thermal boundary conditions in heat transfer simulation of variable sweep wing structures.

[0012] The technical solution of this invention is as follows: This invention provides a method for assigning aerodynamic thermal boundary conditions in heat transfer simulation of a variable sweep wing structure, the method comprising:

[0013] Establish the aircraft body axis coordinate system;

[0014] The spatial position of the wing surface corresponding to the first sweep angle in the entire trajectory is defined as the reference position, and the heat transfer grid of the wing surface structure and the thermal environment data grid are divided at the reference position.

[0015] The thermal environment data of the remaining sweep angles are converted to the reference position to obtain the converted thermal environment data of the remaining sweep angles;

[0016] Under the aforementioned aircraft body axis, establish the plane equation corresponding to the outer edge of the wing box at the first sweep angle;

[0017] Based on the plane equation of the outer edge of the wing box corresponding to the first sweep angle, establish the plane equations of the outer edges of the wing box corresponding to the remaining sweep angles respectively.

[0018] Construct a spatial position criterion for the heat transfer grid of the airfoil structure based on the plane equation corresponding to any sweep angle;

[0019] The positions of each grid point in the heat transfer grid of the airfoil structure are determined based on the criteria, and the positions of each grid point in the heat transfer grid of the airfoil structure at each sweep angle are obtained. The grid point positions include: a) the grid point is located in the positive direction of the normal vector and is subjected to aerodynamic heating in the high-speed airflow; b) the grid point is located in the negative direction of the normal vector and is contained within the airfoil box; c) the grid point is located in the outer edge plane of the airfoil box.

[0020] Perform thermal environment interpolation, including:

[0021] For any sweep angle, during interpolation, for grid points at position a, the thermal environment data grid is used as the source data grid, and the grid points at position a are used as the target grid for interpolation. The thermal environment data grids for the other sweep angles are the transformed thermal environment data grids. For grid points at positions b and c, the thermal environment data is directly assigned.

[0022] Furthermore, for any of the remaining sweep angles, their thermal environment data is converted to the reference position in the following manner to obtain the converted thermal environment data:

[0023] For any grid point in the thermal environment data, it is transformed to the reference position using the following formula:

[0024]

[0025] Where n = 0 when switching the left wing surface of the aircraft, and n = 1 when switching the right wing surface of the aircraft. The unit vector representing the direction of the rotation axis of the variable-sweep wing. Pointing in the negative Y-axis direction, (x q,m ,y q,m ,z q,m To convert the thermal environment data grid points on the forewing surface, the grid points are located in the vector... The projection of the point onto the straight line is point (x). p ,y p ,z p ), y q,m =y p Keeping the reference position corresponding to the first sweep angle λ1 of the entire trajectory unchanged, define the m-th sweep angle λ. m The angle θ with λ1 is λ m -λ1;(x q,m ′,y q,m ′,z q,m ′) represents the grid points of the converted thermal environment data.

[0026] Furthermore, the equation of the plane containing the outer edge of the wing box corresponding to the first sweep angle is established by the following formula;

[0027] A(x-x0)+B(y-y0)+C(z-z0)=0

[0028] in, Let the normal vector be... Point outward from the wing box; take three non-collinear points C0(x0,y0,z0), C1(x1,y1,z1), and C2(x2,y2,z2) in the plane containing the outer edge of the wing box, where x1 < x2. The three points form two intersecting straight lines with C0(x0,y0,z0) as the intersection point.

[0029] Furthermore, the normal vector is obtained using the following method:

[0030] Given points C0(x0,y0,z0), C1(x1,y1,z1), and C2(x2,y2,z2), construct two non-parallel vectors. but:

[0031]

[0032] in, Let x, y, z be the unit vectors in the directions of the three coordinate axes;

[0033] right Normalization to obtain the normal vector in:

[0034]

[0035]

[0036]

[0037]

[0038] Furthermore, the normal vector is obtained using the following method:

[0039] Select a point on the outer edge of the wing box and define it as point C0(x0,y0,z0). Starting from point C0, create a line segment l0 of unit length perpendicular to the plane of the outer edge of the wing box. The endpoint of the line segment is located outside the wing box. Translate the line segment l0 to the origin O of the body axis system. At this point, the coordinates of the endpoint of the line segment are (A,B,C). Obtain the normal vector coordinates.

[0040] Furthermore, based on the plane equation corresponding to the outer edge of the wing box for the first sweep angle, the plane equations corresponding to the outer edges of the wing box for the remaining sweep angles are established, specifically as follows:

[0041] Suppose the sweep angle of the variable-sweep wing of the aircraft changes from the first sweep angle λ1 to λ2. m The wing structure reaches a new spatial position. At this point, relative to the reference position, the sweep wing's unit vector around the rotation axis... Rotate (-1) n ·θ, θ=λ m -λ1, the spatial position of the structural heat transfer grid remains unchanged, and the outer edge plane of the wing box is rotated around the axis of rotation. Rotate (-1) n ·θ, when switching the left wing surface of the aircraft, n=0, and when switching the right wing surface, n=1. At this time, the plane equation is:

[0042] A'(x-x0')+B'(y-y0')+C'(z-z0')=0, normal vector

[0043] Wherein, point (x0',y0',z0') is the point corresponding to C0(x0,y0,z0) after the sweep angle changes.

[0044] Furthermore, the normal vector is obtained using the following formula. and (x0',y0',z0'):

[0045]

[0046]

[0047] Furthermore, the normal vector is obtained in the following manner.

[0048] The plane containing the outer edge of the wing box is rotated around the axis of rotation of the swept wing by a unit vector. Rotate (-1) n ·θ, when the left wing surface of the aircraft is transformed, n=0, and when the right wing surface of the aircraft is transformed, n=1, and a new plane is obtained. The point (x0,y0,z0) on the original plane is rotated to the new plane. The coordinates (x0',y0',z0') of the new point are read by computer geometric modeling software.

[0049] The variable sweep wing rotation axis Translate the vector to the origin O of the coordinate system to obtain the vector. Create a vector with point O as the origin. Around Rotation angle (-1) n ·θ, when the left wing surface of the aircraft is changed, n=0, and when the right wing surface of the aircraft is changed, n=1, to obtain the normal vector of the new plane.

[0050] Furthermore, the spatial position criterion for the heat transfer grid of the airfoil structure is constructed based on the plane equation corresponding to any sweep angle using the following method:

[0051] Let l = (-1) n ·[A″(x i -x0”)+B″(y i -y0”)+C″(z i -z0”)]·C″, where:

[0052] When l > 0, the grid point is located in the high-speed airflow and is subjected to aerodynamic heating, denoted as position a;

[0053] When l < 0, the grid point is located inside the wing surface storage box, denoted as position b;

[0054] When l = 0, the grid point is located in the outer edge plane of the wing box, denoted as position c;

[0055] For the first sweep angle, (x0″,y0″,z0″) is (x0,y0,z0), and (A″,B″,C″) is (x0,y0,z0). In the given information, (A, B, C) represents the sweep angles; for the remaining sweep angles, (x0″, y0″, z0″) represents the corresponding (x0', y0', z0') for each sweep angle, and (A″, B″, C″) represents the corresponding (x0', y0', z0') for each sweep angle. (A', B', C'); n = 0 when analyzing the left wing surface of the aircraft, and n = 1 when analyzing the right wing surface of the aircraft, (x i ,y i ,z i ) represents the coordinates of any grid point in the heat transfer grid of the airfoil structure.

[0056] Furthermore, when assigning values ​​to the thermal environment data: the cold wall heat flux is assigned a value of 0 kW / m. 2 The enthalpy is restored to a constant value.

[0057] The aforementioned technical solution first defines the wing surface spatial position corresponding to the first sweep angle in the entire trajectory as the reference position. After rotation, all aerodynamic and thermal data, i.e., thermal environment data, are rotated to the reference position, and a structural heat transfer mesh is generated at the reference position. Before interpolating the aerodynamic and thermal data to the structural heat transfer surface mesh, the outer edge plane equation of the wing box is established. Based on the plane equation, a criterion is established to determine the position of the wing structural surface mesh relative to the plane containing the outer edge of the wing box. The outer side of the plane is located in the airflow, and the inner side is contained within the wing box. The set of points located outside the plane is used as the target mesh points for aerodynamic and thermal environment interpolation, and the aerodynamic and thermal environment data is interpolated to these points. Therefore, by applying this invention, only one set of structural meshes needs to be generated, without naming the outer wall regions, to achieve accurate thermal environment interpolation, solving the problems of large workload and low efficiency in heat transfer simulation of variable sweep wing structures. Attached Figure Description

[0058] The accompanying drawings, which form part of this specification, are provided to further illustrate embodiments of the invention and, together with the textual description, explain the principles of the invention. It is obvious that the drawings described below are merely some embodiments of the invention, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0059] In this embodiment, the wing surface is located on the left side of the aircraft. In the established aircraft body axis system, the Y-axis points to the upper surface of the wing surface, and the variable sweep wing rotation axis... Pointing in the negative direction of the Y-axis.

[0060] Figure 1 This is the wing surface sweep angle of 65° in an embodiment of the present invention;

[0061] Figure 2 This is the wing surface sweep angle of 85° in an embodiment of the present invention;

[0062] Figure 3 The embodiment of the present invention is a 85° swept-back aerodynamic thermal mesh. Comparison of positions before and after rotating -20°;

[0063] Figure 4 The 85° swept-back angle mesh of this embodiment of the invention Comparison of the positions of the grid (reference position) after rotating -20° and sweeping back 65°;

[0064] Figure 5In this embodiment of the invention, the wing surface maintains a 65° sweepback spatial position, and the outer edge plane of the wing box rotates around... Rotation -20°;

[0065] Figure 6 The surface mesh of the wing structure in an embodiment of the present invention;

[0066] Figure 7 This is a schematic diagram of the method flow of an embodiment of the present invention;

[0067] Figure 8 This is a schematic diagram of the aerodynamic thermal data of the 85° sweep angle in an embodiment of the present invention being rotated and interpolated to a reference position. Detailed Implementation

[0068] The embodiments of the technical solution of the present invention will now be described in detail with reference to the accompanying drawings. These embodiments are merely illustrative of the technical solution of the present invention and are therefore intended to limit the scope of protection of the present invention.

[0069] It should be noted that, unless otherwise stated, the technical or scientific terms used in this application should have the ordinary meaning as understood by those skilled in the art to which this invention pertains.

[0070] In the description of this application, it should be understood that the terms "horizontal", "vertical", "up", "down", "front", "back", "X-axis", "Y-axis", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the present invention.

[0071] Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly defined.

[0072] In this application, unless otherwise expressly specified and limited, the terms "connected," "linked," "inserted," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0073] This invention aims to solve the problems of large workload and low efficiency in heat transfer simulation of variable sweep wing structures. It reduces the number of variable airfoil structure meshes required for heat transfer calculation to one set, and the calculation process is continuous and does not require interruption.

[0074] like Figure 7 As shown, in one embodiment of the present invention, a method for assigning aerodynamic thermal boundary conditions for heat transfer simulation of a variable-sweep wing structure is provided, the method comprising:

[0075] Step 1: Establish the aircraft's body axis coordinate system;

[0076] Step 2: Define the wing surface spatial position corresponding to the first sweep angle in the entire trajectory as the reference position, and divide the wing surface structure heat transfer grid at the reference position;

[0077] Step 3: Convert the thermal environment data of the remaining sweep angles to the reference position to obtain the converted thermal environment data of the remaining sweep angles;

[0078] Step 4: Under the aircraft body axis, establish the plane equation corresponding to the outer edge of the wing box at the first sweep angle;

[0079] Step 5: Based on the plane equation of the outer edge of the wing box corresponding to the first sweep angle, establish the plane equations of the outer edges of the wing box corresponding to the remaining sweep angles.

[0080] Step 6: Construct the spatial position criterion for the heat transfer grid of the airfoil structure based on the plane equation corresponding to any sweep angle;

[0081] Step 7: Determine the position of each grid point of the heat transfer grid of the airfoil structure according to the aforementioned criteria, and obtain the position of each grid point of the heat transfer grid of the airfoil structure at each sweep angle. The grid point positions include: position a, the grid point is located in the positive direction of the normal vector and is subjected to aerodynamic heating in the high-speed airflow; position b, the grid point is located in the negative direction of the normal vector and is contained within the airfoil box; position c, the grid point is located in the outer edge plane of the airfoil box.

[0082] Step 8: Perform thermal environment interpolation, including:

[0083] For any sweep angle, during interpolation, for grid points at position 'a', the thermal environment data grid is used as the source data grid, and the grid points at position 'a' are used as the target grid for interpolation. The thermal environment data grids for other sweep angles are the transformed thermal environment data grids. For grid points at positions 'b' and 'c', the thermal environment data is directly assigned (i.e., interpolation and assignment of thermal environment data: for any sweep angle, during interpolation, for grid points at position 'a', the thermal environment data grid is used as the source data grid, and the grid points at position 'a' are used as the target grid for interpolation. The thermal environment data grids for other sweep angles are the transformed thermal environment data grids; for grid points at positions 'b' and 'c', the thermal environment data is directly assigned).

[0084] That is, for the first sweep angle, the corresponding plane equation and criterion are obtained, and the grid point coordinates of the heat transfer grid are used to determine the grid point position. For each change in the sweep angle of the variable sweep wing, the grid point position needs to be determined again based on the grid point coordinates of the heat transfer grid.

[0085] Specifically, in this embodiment of the invention, a numerical simulation grid for heat transfer of the variable-sweep wing structure is further divided at the reference position. At this time, the rotated aerodynamic heat data grid (i.e., the thermal environment data grid, i.e., the thermal environment numerical simulation grid) is in the same spatial position as the structural heat transfer grid.

[0086] For example, in this embodiment of the invention, the coordinate system is the aircraft body axis system. The origin O of the coordinate system is located at the leading edge of the aircraft's nose, the X-axis points to the rear of the aircraft, the Y-axis coincides with the direction of the variable sweep wing rotation axis and points downwards from the aircraft, and the Z-axis points to the right side of the aircraft when viewed from above.

[0087] This invention differs from existing technologies. Existing methods, to accurately interpolate thermal environment data onto the surface mesh of a variable-sweep wing, require partitioning and naming the surface mesh into aerodynamically heated and non-aerodynamically heated regions. The aerodynamically heated region mesh is used as the target interpolation mesh, while the non-aerodynamically heated region is assigned constant values. Since the variable-sweep wing's spatial position changes with the sweep angle throughout flight, the aerodynamically heated and non-aerodynamically heated regions will change. Therefore, each spatial position requires a separate heat transfer calculation mesh before thermal environment interpolation. This results in a large workload for mesh generation, discontinuous heat transfer calculations, and the calculation must be stopped after a change in spatial position, with the temperature field interpolated onto a new mesh before resuming. However, this invention eliminates the need to distinguish between aerodynamically heated and non-aerodynamically heated regions during mesh generation. Only one structural mesh is needed to complete the calculations for the entire flight process, reducing the number of structural heat transfer mesh divisions. The heat transfer calculation process is not interrupted by changes in the spatial position of the variable-sweep wing, allowing for continuous calculation.

[0088] As can be seen, this embodiment of the invention first defines the wing surface spatial position corresponding to the first sweep angle in the entire trajectory as the reference position. After rotation, all aerodynamic and thermal data, i.e., thermal environment data, are rotated to the reference position, and a structural heat transfer mesh is divided at the reference position. Before interpolating the aerodynamic and thermal data to the structural heat transfer surface mesh, the outer edge plane equation of the wing box is established. Based on the plane equation, a criterion is established to determine the position of the wing structural surface mesh relative to the plane containing the outer edge of the wing box. The outer side of the plane is located in the airflow, and the inner side is contained within the wing box. The set of points located outside the plane is used as the target mesh points for aerodynamic and thermal environment interpolation, and the aerodynamic and thermal environment data is interpolated to these points. Therefore, by applying this invention, only one set of structural meshes needs to be divided, without naming the outer wall regions, to achieve accurate thermal environment interpolation, solving the problem of large workload and low efficiency in heat transfer simulation of variable sweep wing structures.

[0089] In the above embodiments, for any of the remaining sweep angles, the thermal environment data is converted to the reference position using the following formula to obtain the converted thermal environment data:

[0090] For any grid point in the thermal environment data, it is transformed to the reference position using the following formula:

[0091]

[0092] When switching the left wing surface of the aircraft, n = 0; when switching the right wing surface of the aircraft, n = 1. The unit vector representing the direction of the rotation axis of the variable-sweep wing. Pointing in the negative Y-axis direction, (x q,m ,y q,m ,z q,m To convert the thermal environment data grid points on the forewing surface, the grid points are located in the vector... The projection of the point onto the straight line is point (x). p ,y p ,z p ), y q,m =y p Keeping the reference position corresponding to the first sweep angle λ1 of the entire trajectory unchanged, define the m-th sweep angle λ. m The angle θ with λ1 is λ m -λ1;(x q,m ′,y q,m ′,z q,m ′) represents the grid points of the converted thermal environment data.

[0093] That is, define the unit vector in the direction of the rotation axis of the variable sweep wing. Surface thermal environment grid points (x) q,m ,y q,m ,z q,m ), grid points in vector The projection of the point onto the straight line is point (x). p ,y p ,z p ). Pointing in the negative Y-axis direction. Keeping the reference position corresponding to the first sweep angle λ1 of the entire trajectory unchanged, define the m-th sweep angle λ... m The angle θ with λ1 is λ m -λ1. The sweep angle λ m Corresponding thermal environment data grid around Rotate (-1) n ·θ, when switching the left wing surface of the aircraft, n=0, and when switching the right wing surface, n=1. Unify to the reference position, ensuring the variable-sweep wing's rotation axis and leading edge coincide. The rotation formula is shown above. Since the Y-axis coincides with the direction of the variable-sweep wing's rotation axis, therefore y q,m =y p .

[0094] The above formula allows for the rotation of the thermal environment grid in Tecplot software, enabling the rotation of any point (x) on the thermal environment data grid. q,m ,y q,m ,z q,m Rotate to the reference position (x) q,m ',y q,m ',z q,m ').

[0095] In the above embodiment, the equation of the plane containing the outer edge of the wing box corresponding to the first sweep angle can be established by the following formula:

[0096] A(x-x0)+B(y-y0)+C(z-z0)=0

[0097] in, Let x be the normal vector; take three non-collinear points C0(x0,y0,z0), C1(x1,y1,z1), and C2(x2,y2,z2) in the plane containing the outer edge of the wing box, where x1 < x2. The three points form two intersecting lines with C0(x0,y0,z0) as the intersection point.

[0098] That is, the plane equation is the "point-normal" plane equation.

[0099] There are two methods to obtain the normal vector corresponding to the plane equation:

[0100] Optionally, the normal vector can be constructed using the following method:

[0101] Take three non-collinear points C0(x0,y0,z0), C1(x1,y1,z1), and C2(x2,y2,z2) within the plane containing the outer edge of the wing box, where x1 < x2. These points intersect at C0(x0,y0,z0), forming two non-parallel vectors. but:

[0102]

[0103] in, Let x, y, z be the unit vectors in the directions of the three coordinate axes;

[0104] right Normalization to obtain the normal vector in:

[0105]

[0106]

[0107]

[0108]

[0109] Alternatively, it can be achieved using computer geometric modeling software:

[0110] (In the modeling software) Select a point on the outer edge of the wing box and define it as point C0(x0,y0,z0). Starting from point C0, create a line segment l0 of unit length perpendicular to the plane of the outer edge of the wing box (using a tool in the modeling software). The endpoint of the line segment is located outside the wing box. Translate the line segment l0 to the origin O of the body axis system. At this point, the coordinates of the endpoint of the line segment are (A,B,C). Obtain the normal vector coordinates.

[0111] For the first sweep angle, based on the outer edge plane equation of the wing box, the spatial position criterion for the heat transfer grid of the wing structure is constructed as follows:

[0112] Let l = (-1) n ·[A(x i -x0)+B(y i -y0)+C(z i -z0)]·C, where n=0 when analyzing the left wing surface of the aircraft and n=1 when analyzing the right wing surface of the aircraft;

[0113] When l > 0, the grid point is located in the high-speed airflow and is subjected to aerodynamic heating, denoted as position a;

[0114] When l < 0, the grid point is located inside the wing surface storage box, denoted as position b;

[0115] When l = 0, the grid point is located in the outer edge plane of the wing box, denoted as position c.

[0116] That is, based on the coordinates (x, y) of the heat transfer grid points of the airfoil structure i ,y i ,z i The wing structure grid points are divided into three categories: those in the high-speed incoming flow, those contained within the wing box, and those located on the outer edge plane of the wing box.

[0117] Furthermore, when the sweep angle changes, it is necessary to re-obtain the plane equation and corresponding criteria, specifically:

[0118] Based on the plane equation of the outer edge of the wing box corresponding to the first sweep angle, establish the plane equations of the outer edges of the wing box corresponding to the remaining sweep angles, specifically:

[0119] Suppose the sweep angle of the variable-sweep wing of the aircraft changes from the first sweep angle λ1 to λ2. m The wing structure reaches a new spatial position. At this point, relative to the reference position, the sweep wing's unit vector around the rotation axis... Rotate (-1) n ·θ, when switching the left wing surface of the aircraft, n=0, and when switching the right wing surface, n=1. The spatial position of the structural heat transfer grid remains unchanged. The outer edge plane of the wing box is rotated around the axis of rotation. Rotate (-1) n ·θ, when switching the left wing surface of the aircraft, n=0, and when switching the right wing surface, n=1. At this time, the plane equation is:

[0120] A'(x-x0')+B'(y-y0')+C'(z-z0')=0, normal vector

[0121] Wherein, point (x0',y0',z0') is the point corresponding to C0(x0,y0,z0) after the sweep angle changes.

[0122] Similarly, the normal vector can be obtained using the following formula. and (x0',y0',z0'):

[0123]

[0124]

[0125] Alternatively, this can be achieved using computer geometric modeling software, by obtaining the normal vector in the following manner.

[0126] The plane containing the outer edge of the wing box is rotated around the axis of rotation of the swept wing by a unit vector. Rotate (-1) n·θ, when the left wing surface of the aircraft is transformed, n=0, and when the right wing surface of the aircraft is transformed, n=1, and a new plane is obtained. The point (x0,y0,z0) on the original plane is rotated to the new plane. The coordinates (x0',y0',z0') of the new point are read by computer geometric modeling software.

[0127] The variable sweep wing rotation axis Translate the vector to the origin O of the coordinate system to obtain the vector. Create a vector with point O as the origin. Around Rotation angle (-1) n ·θ, when the left wing surface of the aircraft is changed, n=0, and when the right wing surface of the aircraft is changed, n=1, to obtain the normal vector of the new plane.

[0128] Regarding the corresponding criterion:

[0129] Let l = (-1) n ·[A′(x i -x0')+B′(y i -y0')+C′(z i -z0')]·C′, where n = 0 when analyzing the left wing surface of the aircraft and n = 1 when analyzing the right wing surface of the aircraft;

[0130] When l > 0, the grid point is located in the high-speed airflow and is subjected to aerodynamic heating, denoted as position a;

[0131] When l < 0, the grid point is located inside the wing surface storage box, denoted as position b;

[0132] When l = 0, the grid point is located in the outer edge plane of the wing box, denoted as position c.

[0133] Furthermore, during thermal environment interpolation: When performing thermal environment calculations, it is necessary to divide the mesh according to the changes in the airfoil position, with each airfoil position corresponding to a separate mesh. After completing the numerical simulation of the flow field, the thermal environment data of the airfoil portion in the high-speed airflow is output. The thermal environment data mesh is then rotated to the initial airfoil position.

[0134] During interpolation, the rotated thermal environment data grid (i.e., the thermal environment data at the reference location) is used as the source data grid, and the grid in the high-speed airflow, as determined by the criteria, is used as the target grid. Conventional methods such as inverse distance interpolation can be used for interpolation.

[0135] Based on the criteria determined that the grid points contained within the wing box and the planar grid points on the outer edge of the wing box, due to the lack of aerodynamic heating, have a cold wall heat flux of 0 kW / m². 2 The enthalpy is restored to a constant. In this case, it is equivalent to an adiabatic boundary condition in actual calculations.

[0136] In addition, after the above interpolation and assignment process, the thermal environment data at each sweep angle are output as a new thermal environment dataset, which is a thermal environment data grid file that can be called when performing numerical calculations of heat transfer in the airfoil structure. The grid spatial position of these files is uniform, which enables the heat transfer calculation to proceed continuously along the entire trajectory without interruption due to changes in the grid spatial position.

[0137] As can be seen, the key features of this invention are: (1) Establishing a Cartesian coordinate system, with the origin located at the leading edge of the aircraft, the X-axis pointing to the rear of the aircraft, the Y-axis pointing to the direction of the variable sweep wing rotation axis, and looking down at the aircraft, the Y-axis pointing to the bottom of the aircraft, and the Z-axis pointing to the right side of the aircraft. In this coordinate system, the spatial position of the wing surface corresponding to the first sweep angle in the entire trajectory is defined as the reference position, and the aerodynamic thermal data corresponding to other sweep angles are rotated to the reference position to form an aerodynamic thermal dataset that can be used as interpolation source data. The variable sweep wing structure heat transfer numerical simulation grid is divided at the reference position, and at this time the spatial position of the rotated aerodynamic thermal dataset grid is consistent with that of the structural heat transfer grid. (2) Establishing the plane equation of the plane where the outer edge of the variable sweep wing housing box is located, and defining the plane normal vector pointing to the outside side of the wing box as the positive direction, and based on this, establishing the surface grid spatial position criterion in the structured grid used for the variable sweep wing heat transfer numerical simulation: the grid point coordinates (x i ,y i ,z i Substituting the equation of the plane into the "point-normal" form: Let l = (-1) n ·[A″(x i -x0”)+B″(y i -y0”)+C″(z i -z0”)]·C″,where n=0 when analyzing the left wing surface of the aircraft, and n=1 when analyzing the right wing surface of the aircraft. When l>0, the grid points are located in the high-speed airflow and are subject to aerodynamic heating. When l=0, the grid points are located in the plane and are subject to aerodynamic heating. When l<0, the grid points are contained in the wing box and are not subject to aerodynamic heating. Based on the criterion, the grid points on the surface of the structural heat transfer grid are divided into two parts: the set of points subject to aerodynamic heating and the set of points not subject to aerodynamic heating. (3) When the sweep angle of the variable sweep wing changes by angle θ, the spatial position changes. At this time, the spatial position of the structured grid used for the numerical simulation of heat transfer of the fixed variable sweep wing remains unchanged, and the plane where the outer edge of the wing box is located is rotated, that is, around the rotation axis of the variable sweep wing. Rotate (-1) n ·θ, when the left wing surface of the aircraft is transformed, n=0; when the right wing surface is transformed, n=1, resulting in a new plane equation. The corresponding criterion is then used to determine the grid coordinates (x, y) at this point. i ,y i ,z i(5) Using the thermal environment data of the unified spatial location as the source data, the set of points heated by aerodynamics is determined by the criterion as the interpolation target area, and thermal environment interpolation is performed. The set of points not heated by aerodynamics is assigned a value, and the cold wall heat flux is assigned 0Kw / m 2 The enthalpy value is assigned as the static enthalpy, typically between 280 and 320 kJ / kg. In this case, the region without aerodynamic heating is essentially an adiabatic boundary condition. After interpolation and assignment, the thermal environment boundary conditions are obtained and can be directly used for numerical calculations of heat transfer in variable-sweep wings.

[0138] The specific implementation of the present invention is illustrated by taking the numerical simulation process of the temperature of the variable sweep wing structure of a high-speed variable sweep wing aircraft as an example.

[0139] This high-speed aircraft has two sweep angle states: an initial sweep angle of 65°, which changes to 85° after a period of flight. The outer edge plane of the wing box makes an angle of 3.5° with the XOY coordinate plane. According to the definition of this invention, the 65° sweep angle position of the variable-sweep wing is taken as the reference position.

[0140] In the numerical simulation of the thermal environment, two sets of numerical simulation grids for the thermal environment were divided at 65° sweep angle and 85° sweep angle. In accordance with the conventional practice of numerical simulation of the thermal environment, typical moments in the entire trajectory were selected for calculation to obtain thermal environment datasets for the 65° sweep angle and 85° sweep angle attitudes—cold wall heat flux and recovery enthalpy datasets.

[0141] In this embodiment, the wing surface is located on the left side of the aircraft. In the established aircraft body axis system, the Y-axis points to the upper surface of the wing surface, and the variable sweep wing rotation axis... Pointing in the negative direction of the Y-axis.

[0142] The following is the implementation process of an embodiment of the present invention:

[0143] (1) The thermal environment data of the 85° sweep angle is used to rotate around the axis of the swept wing. Rotate (-1) 0 ×20°, so that it is in the same attitude as the 65° swept-back wing surface.

[0144] Figure 1 This is a schematic diagram of the wing surface swept back at 65°.

[0145] The X-axis coordinate of the intersection of the rotation axis and the wing is x p =2806.268, the Z-axis coordinate is z p =48.4007, unit vector of rotation axis The Y-axis coordinate y0 of any point on the wing surface is projected onto the rotation axis, and the Y-axis coordinate y0 is projected onto the rotation axis. p,0 Satisfy y p,0 =y0, the X-axis and Z-axis coordinates satisfy: x p,0 =x p , zp,0 =z p .

[0146] Figure 3 The thermal environment data grid of the 85° swept wing is rotated around the axis of rotation. Rotate (-1) 0 Comparison of positions before and after ×20°. The rotation formula is as follows:

[0147] (x0',y0',z0')=(x0-x p,0 ,y0-y p,0 ,z0-z p,0 )·cos((-1) 0 ×20°)

[0148] +[(0,-1,0)×(x0-x p,0 ,y0-y p,0 ,z0-z p,0 )]·sin((-1) 0 ×20°)

[0149] +(0,-1,0)[(0,-1,0)·(x0-x p,0 ,y0-y p,0 ,z0-z p,0 )](1-cos((-1) 0 ×20°))

[0150] +(x0,y0,z0)

[0151] The above formula can be transformed into:

[0152] x0'=(x0-x p )·cos((-1) 0 ×20°)-(z0-z p sin((-1)) 0 (×20°)+x0

[0153] y0'=y0

[0154] z0'=(z0-z p )·cos((-1) 0 ×20°)+(x0-x p sin((-1)) 0 ×20°)+z0

[0155] The rotation process is implemented through programming. It can also be done using the Tecplot software.

[0156] (2) Establish the equation of the plane containing the outer edge of the wing box at a sweep angle of 65°.

[0157] Three points are selected on the outer edge plane of the wing box when swept back at 65°: C0(3708.070776137, 0, 226.795324372), C1(3585.799263331, 0, 219.316878279), and C2(3759.935381647, 30, 229.967499538).

[0158]

[0159] After normalization, the normal vector is obtained:

[0160] (0.06104854, 0, -0.998134798).

[0161] The normal vector can also be obtained using computer geometric modeling software. In this embodiment, UG software is selected, and the process is as follows:

[0162] Select point C0 (3708.070776137, 0, 226.795324372) on the outer edge plane of the wing box when swept back by 65°. Using UG, create a line segment of length 1 perpendicular to the outer edge plane of the wing box. The endpoint of the line segment is located outside the wing box, and the coordinates of the endpoint of the line segment are (3708.009727598, 0, 227.79345917). Translate the line segment to the origin so that C0 coincides with the origin O, and obtain the endpoint of the line segment (0.06104854, 0, -0.998134798), which is the plane normal vector. (0.06104854, 0, -0.998134798).

[0163] After obtaining the plane normal vector, the "point normal form" plane equation can be created:

[0164] 0.06104854(x-3708.070776137)-0.998134798(z-226.795324372)=0;

[0165] Normal vector: (0.06104854, 0, -0.998134798).

[0166] (3) Use the criterion to determine the spatial position of the grid wing surface points used for structural heat transfer when the sweep angle is 65°.

[0167] The coordinates of the grid points on the wing surface are successively substituted into the criteria to classify the spatial positions of the grid points. Here, the judgment process is illustrated using three points W1, W2, and W3 on the grid as an example. The coordinates of the three points are as follows:

[0168] W1(3796.972509802, 0, 629.141587503),

[0169] W2(3829.58545475, 0, 328.491681274),

[0170] W3(3829.58545475, 0, 46.632394184).

[0171] Substituting the three points into the criterion, we get: 395.4295509, 93.91288514, and -186.8959336, which are greater than 0, greater than 0, and less than 0, respectively. Therefore, points W1 and W2 are located outside the wing box, in the area with aerodynamic heating, while point W3 is located inside the wing box, in the area without aerodynamic heating.

[0172] (4) Increase the sweep angle by 20°, rotate the plane containing the outer edge of the wing box, and establish a new plane equation.

[0173] The sweep angle is increased by 20°, that is, the variable sweep wing rotates around the axis Rotate -20° to reach the new position. In this embodiment, the heat transfer grid of the variable sweep wing structure remains spatially unchanged, and the outer edge plane of the wing box rotates around the axis. Rotate (-1) 0 ×20°.

[0174] Calculate the normal vector after rotation using the formula:

[0175]

[0176]

[0177] The coordinates of point C0 (3708.070776137, 0, -226.795324372) after rotation are calculated using the formula; alternatively, computer geometric modeling software can be used to rotate the plane containing the outer edge of the wing box. In this embodiment, UG software is used. The plane is rotated around... Rotation of the axis (-1) 0 After a 20° rotation, point C0 moves to point C0', with coordinates (3592.670962, 0, 524.4715449). A line segment of length 1 is created with point C0' as its endpoint, ending outside the wing box. The line segment is translated, moving point C0' to the origin O of the body axis, with the endpoint coordinates (0.398749069, 0, 0.958819735), meaning the normal vector is:

[0178]

[0179] Therefore, the equation of the rotated plane in "point normal form" is:

[0180] 0.398749069(x-3592.670962)-0.958819735(z-524.4715449)=0;

[0181]

[0182] (5) For the state where the sweep angle increases by 20°, determine the spatial position of the points on the surface of the heat transfer grid of the structure.

[0183] A criterion is used to determine the spatial location of points on the airfoil surface of the mesh used for structural heat transfer. The coordinates of the airfoil surface mesh points are sequentially substituted into the criterion to classify the spatial locations of the mesh points. The judgment process is illustrated using three points W1, W2, and W3 on the mesh, with their coordinates remaining unchanged:

[0184] W1(3796.972509802, 0, 629.141587503),

[0185] W2(3829.58545475, 0, 328.491681274),

[0186] W3(3829.58545475, 0, 46.632394184).

[0187] Substituting the three points into the criterion, we get: 18.11656381, -270.7503607, and -529.8735486, which are greater than 0, less than 0, and less than 0, respectively. Therefore, point W1 is located outside the wing box, in the area with aerodynamic heating, while points W2 and W3 are located inside the wing box, in the area without aerodynamic heating.

[0188] (6) Based on the judgment results, interpolate the thermal environment data.

[0189] In this embodiment, only two wing surface spatial position states are shown: 65° sweep angle and 85° sweep angle. After the above five steps, the thermal environment data has been rotated to the reference position, and the surface grid points of the structural heat transfer grid in the 65° sweep angle and 85° sweep angle states have been spatially determined according to the criteria, dividing them into aerodynamic heating areas and non-aerodynamic heating areas. Therefore, the conditions for interpolation and conducting full-trajectory continuous heat transfer numerical simulation are met.

[0190] At this point, using the thermal environment data from the reference location as the source data, interpolation is performed on the aerodynamic heating area, and the cold wall heat flux in the non-aerodynamic heating area is assigned 0 Kw / m. 2 The recovery enthalpy is 300 KJ / Kg.

[0191] The process of assigning aerodynamic thermal boundary conditions is complete. Figure 8This is a schematic diagram of the result of interpolating the thermal environment data (cold wall heat flow) at an 85° sweep angle to the reference position onto the heat transfer grid of the reference position structure.

[0192] The features described and / or illustrated above with respect to one embodiment may be used in the same or similar manner in one or more other embodiments, and / or in combination with or in lieu of features in other embodiments.

[0193] It should be emphasized that the term "including / comprises" as used herein refers to the presence of a feature, whole, step, or component, but does not exclude the presence or addition of one or more other features, wholes, steps, components, or combinations thereof.

[0194] The methods described above in this invention can be implemented in hardware or in combination with software. This invention relates to computer-readable programs that, when executed by a logic component, enable the logic component to implement the aforementioned apparatus or constituent parts, or to implement the various methods or steps described above. This invention also relates to storage media for storing the above programs, such as hard disks, magnetic disks, optical disks, DVDs, flash memory, etc.

[0195] Many features and advantages of these embodiments are apparent from this detailed description, and therefore the appended claims are intended to cover all such features and advantages of these embodiments that fall within their true spirit and scope. Furthermore, since many modifications and alterations will readily occur to those skilled in the art, the embodiments of the invention are not intended to be limited to the precise structures and operations illustrated and described, but rather to encompass all suitable modifications and equivalents falling within their scope.

[0196] The parts of this invention not described in detail are techniques known to those skilled in the art.

Claims

1. A method for assigning aerodynamic thermal boundary conditions in heat transfer simulation of a variable sweep wing structure, characterized in that, The method includes: Establish the aircraft body axis coordinate system; The spatial position of the wing surface corresponding to the first sweep angle in the entire trajectory is defined as the reference position, and the heat transfer grid of the wing surface structure and the thermal environment data grid are divided at the reference position. The thermal environment data of the remaining sweep angles are converted to the reference position to obtain the converted thermal environment data of the remaining sweep angles; Under the aforementioned aircraft body axis, establish the plane equation corresponding to the outer edge of the wing box at the first sweep angle; Based on the plane equation of the outer edge of the wing box corresponding to the first sweep angle, establish the plane equations of the outer edges of the wing box corresponding to the remaining sweep angles respectively. Construct a spatial position criterion for the heat transfer grid of the airfoil structure based on the plane equation corresponding to any sweep angle; The positions of each grid point in the heat transfer grid of the airfoil structure are determined based on the criteria, and the positions of each grid point in the heat transfer grid of the airfoil structure at each sweep angle are obtained. The grid point positions include: a) the grid point is located in the positive direction of the normal vector and is subjected to aerodynamic heating in the high-speed airflow; b) the grid point is located in the negative direction of the normal vector and is contained within the airfoil box; c) the grid point is located in the outer edge plane of the airfoil box. Perform thermal environment interpolation, including: For any sweep angle, during interpolation, for grid points at position a, the thermal environment data grid is used as the source data grid, and the grid points at position a are used as the target grid for interpolation. The thermal environment data grids for the other sweep angles are the transformed thermal environment data grids. For grid points at positions b and c, the thermal environment data is directly assigned.

2. The method according to claim 1, characterized in that, For any of the remaining sweep angles, the thermal environment data is converted to the reference position using the following formula to obtain the converted thermal environment data: For any grid point in the thermal environment data, it is transformed to the reference position using the following formula: Where n = 0 when switching the left wing surface of the aircraft, and n = 1 when switching the right wing surface of the aircraft. The unit vector representing the direction of the rotation axis of the variable-sweep wing. Pointing in the negative Y-axis direction, (x q,m ,y q,m ,z q,m To convert the thermal environment data grid points on the forewing surface, the grid points are located in the vector... The projection of the point onto the straight line is point (x). p ,y p ,z p ), y q,m =y p Keeping the reference position corresponding to the first sweep angle λ1 of the entire trajectory unchanged, define the m-th sweep angle λ. m The angle θ with λ1 is λ m -λ1;(x q,m ′,y q,m ′,z q,m ′) represents the grid points of the converted thermal environment data.

3. The method according to claim 1 or 2, characterized in that, The equation for the plane containing the outer edge of the wing box corresponding to the first sweep angle is established by the following formula: A(x-x0)+B(y-y0)+C(z-z0)=0 in, Let x be the normal vector; take three non-collinear points C0(x0,y0,z0), C1(x1,y1,z1), and C2(x2,y2,z2) in the plane containing the outer edge of the wing box, where x1 < x2. The three points form two intersecting lines with C0(x0,y0,z0) as the intersection point.

4. The method according to claim 3, characterized in that, The normal vector is obtained using the following method: Given points C0(x0,y0,z0), C1(x1,y1,z1), and C2(x2,y2,z2), construct two non-parallel vectors. but: in, Let x, y, z be the unit vectors in the directions of the three coordinate axes; right Normalization to obtain the normal vector in:

5. The method according to claim 3, characterized in that, The normal vector is obtained using the following method: Select a point on the outer edge of the wing box and define it as point C0(x0,y0,z0). Starting from point C0, create a line segment l0 of unit length perpendicular to the plane of the outer edge of the wing box. The endpoint of the line segment is located outside the wing box. Translate the line segment l0 to the origin O of the body axis system. At this point, the coordinates of the endpoint of the line segment are (A,B,C). Obtain the normal vector coordinates.

6. The method according to any one of claims 3-5, characterized in that, Based on the plane equation of the outer edge of the wing box corresponding to the first sweep angle, establish the plane equations of the outer edges of the wing box corresponding to the remaining sweep angles, specifically: Suppose that the sweep angle of the variable-sweep wing of the aircraft changes from the first sweep angle λ1 to the m-th sweep angle λ. m Define the m-th sweep angle λ m The angle θ with λ1 is λ m -λ1, the wing structure reaches a new spatial position. At this point, the variable-sweep wing, relative to the reference position, rotates around the rotation axis by a unit vector. Rotate (-1) n •θ, the spatial position of the structural heat transfer grid remains unchanged, and the outer edge plane of the wing box is rotated around the axis of rotation. Rotate (-1) n ·θ, when switching the left wing surface of the aircraft, n=0, and when switching the right wing surface, n=1. At this time, the plane equation is: A'(x-x0')+B'(y-y0')+C'(z-z0')=0, normal vector Wherein, point (x0',y0',z0') is the point corresponding to C0(x0,y0,z0) after the sweep angle changes.

7. The method according to claim 6, characterized in that, The normal vector is obtained using the following formula. and (x0',y0',z0'): When analyzing the left wing surface of the aircraft, n = 0; when analyzing the right wing surface of the aircraft, n = 1.

8. The method according to claim 6, characterized in that, Obtain the normal vector in the following manner The plane containing the outer edge of the wing box is rotated around the axis of rotation of the swept wing by a unit vector. Rotate (-1) n ·θ, when analyzing the left wing surface of the aircraft, n=0, and when analyzing the right wing surface of the aircraft, n=1, a new plane is obtained. The point (x0,y0,z0) on the original plane is rotated to the new plane. The coordinates (x0',y0',z0') of the new point are read by computer geometric modeling software. The variable sweep wing rotation axis Translate the vector to the origin O of the coordinate system to obtain the vector. Create a vector with point O as the origin. Around Rotation angle (-1) n ·θ, where n=0 when analyzing the left wing surface of the aircraft and n=1 when analyzing the right wing surface of the aircraft, to obtain the normal vector of the new plane.

9. The method according to claim 6, characterized in that, The spatial position criterion for the heat transfer grid of the airfoil structure is constructed based on the plane equation corresponding to any sweep angle using the following method: Let l = (-1) n ·[A″(x i -x0”)+B″(y i -y0”)+C″(z i -z0”)]·C″, where: When l > 0, the grid point is located in the high-speed airflow and is subjected to aerodynamic heating, denoted as position a; When l < 0, the grid point is located inside the wing surface storage box, denoted as position b; When l = 0, the grid point is located in the outer edge plane of the wing box, denoted as position c; For the first sweep angle, (x0″,y0″,z0″) is (x0,y0,z0), and (A″,B″,C″) is (x0,y0,z0). In the given information, (A, B, C) represents the sweep angles; for the remaining sweep angles, (x0″, y0″, z0″) represents the corresponding (x0', y0', z0') for each sweep angle, and (A″, B″, C″) represents the corresponding (x0', y0', z0') for each sweep angle. (A', B', C'); n = 0 when analyzing the left wing surface of the aircraft, and n = 1 when analyzing the right wing surface of the aircraft, (x i ,y i ,z i ) represents the coordinates of any grid point in the heat transfer grid of the airfoil structure.

10. The method according to claim 1, characterized in that, When assigning values ​​to the thermal environment data, the cold wall heat flux was assigned a value of 0 kW / m. 2 The enthalpy is restored to a constant value.

Images