Method and device for creating fourteen faces of civil airport annex based on autonomous programming platform

Abstract

The present application relates to the method and device for creating the fourteen surfaces of the civil airport annex based on the autonomous programming platform, which is applied to the technical field of civil airport engineering building information model, and comprises the following steps: the whole process of modeling the fourteen surfaces is integrated in the same framework, runway linear and longitudinal section models are established in Civil3D to obtain basic geometric data, then the mathematical calculation rules of each surface are established by configuring the standard parameters, the local coordinate system is established, the boundary control point three-dimensional coordinates of each obstacle limiting surface are obtained, the local coordinate is converted to the world coordinate system without loss to ensure the correctness of the model space position, the triangular net curved surface is constructed according to the surface domain grouping to realize the mutual independence between the curved surfaces, and through the above steps, the designer only needs to input the runway category and the flight area index to automatically complete the creation of each limiting surface, and the tedious process of traditional manual point-by-point calculation is completely eliminated.

Description

Technical Field

[0001] This invention relates to the field of building information modeling technology for civil airport engineering, specifically to a method and apparatus for creating fourteen annexes of a civil airport based on an independent programming platform. Background Technology

[0002] Approach runway obstacle restriction surfaces are key three-dimensional spatial constraints for ensuring airport flight safety. According to Annex XIV of the Convention on International Civil Aviation and my country's Technical Standards for Civil Airport Flight Areas (MH5001), different types of runways require eight obstacle restriction surfaces, including the cone surface, inner horizontal surface, approach surface, transition surface, takeoff climb surface, inner approach surface, inner transition surface, and go-around surface. Section 4.2 of MH5001 further stipulates that the takeoff and landing strips should extend outwards at both ends of the runway by a certain distance (30m for non-instrument runways and 60m for instrument runways), and the transition surface and inner transition surface should be continuously generated along the entire length of the runway (including end extensions). Traditional manual calculation methods require designers to manually calculate the coordinates of the boundary control points of each restriction surface point by point, involving a large number of repetitive geometric calculations. This method is time-consuming, error-prone, and difficult to respond to the engineering needs of frequent runway design adjustments.

[0003] Civil3D, Autodesk's BIM platform for civil engineering, boasts powerful modeling capabilities for alignment, profile, surface, and pointgrouping. However, the native Civil3D environment lacks dedicated modeling tools for airport obstacle constraint surfaces. Traditional Civil3D secondary development requires COM component programming based on the .NET API, which, while powerful, has a long development cycle and high technical threshold, making it difficult for airport design engineers to master quickly. Dynamo, Autodesk's visual programming tool built into Civil3D, uses node-based graphical programming to lower the development threshold, but its native node library lacks a dedicated calculation module for airport obstacle constraint surfaces.

[0004] In existing technologies, attempts to use Dynamo for airport airspace modeling are mostly limited to simple geometric constructions of a single constraint surface, lacking a systematic computational architecture and failing to achieve integrated automatic generation and linked updates of all eight constraint surfaces. Furthermore, existing methods typically directly import the geometry generated by Dynamo into Civil3D, failing to generate native Civil3D TinSurface objects that can participate in subsequent airspace assessments.

[0005] Therefore, there is an urgent need to propose a method and apparatus for systematically transforming the geometric rules of Annex XIV into a parametric computational model, in order to fill the technological gap in this field within the industry. Summary of the Invention

[0006] In view of this, the purpose of the present invention is to provide a method and apparatus for creating fourteen-sided annexes of civil airports based on an autonomous programming platform, so as to solve the technical problems in the prior art, such as low efficiency in modeling airport obstacle restriction surfaces, slow response to parameter adjustment, and inability to achieve integrated automatic generation of all types of restriction surfaces.

[0007] According to a first aspect of the present invention, a method for creating fourteen annexes to a civil airport based on an autonomous programming platform is provided, the method comprising:

[0008] In Civil3D software, a planar alignment model and a corresponding longitudinal profile model of the runway are created, and the planar coordinates and elevation information of the runway centerline are extracted. Configure the parameter panel in the Dynamo platform, input the runway category and airspace level indicators, and obtain the geometric dimensions and slope parameters of each obstacle restriction surface; A local coordinate system is established with the runway entrance as the origin, the runway centerline as the positive X-axis, the Y-axis perpendicular to the X-axis, and the Z-axis perpendicular to the XY-axis in a horizontal plane. Based on the elevation information of the runway centerline and the geometric dimensions and slope parameters of each obstacle restriction surface, the three-dimensional coordinates of the boundary control points of each obstacle restriction surface are obtained in the local coordinate system. Using the planar coordinate information of the runway centerline as a reference, obtain the direction unit vector of the runway centerline. Based on the direction unit vector, transform the three-dimensional coordinates of the boundary control points of each obstacle restriction surface from the local coordinate system to the Civil3D world coordinate system to obtain the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the world coordinate system. The three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the world coordinate system are grouped according to the surface region of the obstacle restriction surface to obtain the three-dimensional coordinate group of the boundary control points of each obstacle restriction surface; based on the Dynamo surface generation node, the triangular mesh surface of each obstacle restriction surface is constructed according to the three-dimensional coordinate group of the boundary control points of each obstacle restriction surface to obtain the three-dimensional model of each obstacle restriction surface.

[0009] Preferably, The process of obtaining the three-dimensional coordinates of the boundary control points of each obstacle constraint surface in the local coordinate system includes: In the Dynamo platform, an independent calculation submodule is established for each obstacle constraint surface. Each independent calculation submodule contains a preset parameterized mathematical formula for the obstacle constraint surface. The independent calculation submodules are connected via Dynamo to transmit structured data lists; each independent calculation submodule uses the geometric dimensions and slope parameters of the obstacle restriction surface to calculate the three-dimensional coordinates of the boundary control points of the obstacle restriction surface using preset parametric mathematical formulas.

[0010] Preferably, The process involves obtaining the direction unit vector of the runway centerline based on the planar coordinate information of the runway centerline, and transforming the three-dimensional coordinates of the boundary control points of each obstacle constraint surface from the local coordinate system to the Civil3D world coordinate system based on the direction unit vector, thereby obtaining the three-dimensional coordinates of the boundary control points of each obstacle constraint surface in the world coordinate system, including: The starting coordinates P0(X0, Y0, Z0) and the ending coordinates Pn(Xn, Yn, Zn) of the runway are obtained based on the planar coordinate information of the runway centerline. Based on the runway start coordinates P0 and end coordinates Pn, the rotation angle theta of the direction unit vector in the XY plane is calculated using the four-quadrant arctangent function, and the expression is: theta = Atan2(Yn-Y0, Xn-X0); For any boundary control point with 3D coordinates P_local(x_local, y_local, z_local) in the local coordinate system, the boundary control point with 3D coordinates P_world(X_world, Y_world, Z_world) in the Civil3D world coordinate system is obtained based on the rotation angle theta, and the expression is: X_world = X0 + x_local Cos(theta) - y_local Sin(theta); Y_world = Y0 + x_local Sin(theta) + y_local Cos(theta); Z_world = z_local.

[0011] Preferably, The obstacle limiting surfaces include: a conical surface, an inner horizontal surface, an approach surface, a transition surface, a takeoff and climb surface, an inner approach surface, an inner transition surface, and a go-around surface; The acquisition of the three-dimensional coordinates of the boundary control points of the approach surface in the local coordinate system includes: The approach surface is divided into three segments along the runway centerline: a first segment, a second segment, and a horizontal segment. Using the runway entrance as a reference, eight boundary control points with three-dimensional coordinates are generated based on the geometric dimensions and slope parameters of the approach surface. These geometric dimensions and slope parameters include: the initial half-width of the approach surface B1, the length of the first segment AP_L1, the length of the second segment AP_L2, the spread rate of the first segment AP_S1, the spread rate of the second segment AP_S2, the slope of the first segment ρ1, and the slope of the second segment ρ2. The calculation expressions for the three-dimensional coordinates of the eight boundary control points are as follows: P1 = Point.ByCoordinates(-B, B1); P2 = Point.ByCoordinates(-B,-B1); P3 = Point.ByCoordinates(-(B+AP_L1),B1+AP_L1 AP_S1, AP_L1 ρ1); P4 = Point.ByCoordinates(-(B+AP_L1), -B1-AP_L1 AP_S1, AP_L1 ρ1); P5 = Point.ByCoordinates(-(B+AP_L1+AP_L2),B1+(AP_L1+AP_L2) AP_S1, AP_L1 ρ1+AP_L2 ρ2); P6 = Point.ByCoordinates(-(B+AP_L1+AP_L2),-B1-(AP_L1+AP_L2) AP_S1,AP_L1 ρ1+AP_L2 ρ2); P7 = Point.ByCoordinates(-(B+AP_LZ),B1+AP_LZ AP_S1, AP_L1 ρ1+AP_L2 ρ2); P8 = Point.ByCoordinates(-(B+AP_LZ), -B1-AP_LZ AP_S1, AP_L1 ρ1+AP_L2 ρ2); In the formula, B is the distance from the runway start point to the runway threshold; AP_LZ is the total length of the approach surface, which is obtained by summing the lengths of the first segment, the second segment, and the horizontal segment, as well as the distance B from the runway start point to the runway threshold.

[0012] Preferably, Obtaining the three-dimensional coordinates of the boundary control points of the inner horizontal plane in the local coordinate system includes: The coordinates of the runway midpoint are obtained based on the plane coordinate information of the runway centerline, and the average elevation of the runway centerline is obtained based on the elevation information of the runway centerline. Using the runway midpoint coordinates as the geometric center and the runway length as the major axis, a double-centered runway profile is constructed as the bottom boundary of the inner horizontal plane. This includes setting a first center and a second center on the runway centerline at half the runway length on each side. A near semicircular arc and a far semicircular arc are generated with a specified radius R_bottom. The endpoints of the two semicircular arcs are then connected to generate a common tangent on both sides, forming a closed double-centered runway profile. Discrete sampling is performed along the double-centered runway contour at equal angular intervals to generate N coordinates of bottom boundary control points; In the three-dimensional coordinates of the boundary control points of the inner horizontal plane, the plane coordinates are the coordinates of the bottom boundary control points, and the elevation is uniformly the sum of the specified height of the inner horizontal plane and the average elevation of the runway centerline. Obtaining the three-dimensional coordinates of the boundary control points of the conical surface in the local coordinate system includes: The three-dimensional coordinates of the boundary control points of the inner horizontal plane are used as the three-dimensional coordinates of the bottom control points of the conical surface; The bottom boundary radius of the conical surface is the same as the radius of the inner horizontal plane, both being R_bottom; the vertical height H_cone of the conical surface is obtained, as well as the angle Alpha_cone between the slope of the conical surface and the inner horizontal plane; the top boundary radius R_top of the conical surface is obtained based on the specified radius R_bottom, the vertical height H_cone of the conical surface, and the angle Alpha_cone, with the expression: R_top = R_bottom + H_cone / tan(Alpha_cone) Based on the top boundary radius R_top of the conical surface, for the coordinates of each bottom boundary control point, expand outward from the bottom boundary to the top boundary along its normal direction by a distance dL = H_cone / tan(Alpha_cone) to obtain the planar coordinates of the top control point. The elevation of the top control point is the sum of the elevation in the three-dimensional coordinates of the boundary control point of the inner horizontal plane and the vertical height H_cone of the conical surface. Based on the planar coordinates and elevation of the top control point, the three-dimensional coordinates of the top control point are obtained. The three-dimensional coordinates of the boundary control points of the conical surface are the set of the three-dimensional coordinates of the bottom control point and the top control point of the conical surface.

[0013] Preferably, Obtaining the three-dimensional coordinates of the boundary control points of the transition surface in the local coordinate system includes: The station numbers of each actual slope change point on the runway centerline are obtained based on the elevation information of the runway centerline; the end extension distance is obtained based on the geometric dimensions and slope parameters of the transition surface; virtual slope change points are generated at the runway start and end points according to the end extension distance; the elevation of the virtual slope change point is the extension value of the runway start or end elevation along the longitudinal slope of the runway; and the station number is the runway start station number minus the end extension distance or the end station number plus the end extension distance. The actual and virtual slope change points are merged and sorted in ascending order of station number to obtain a complete sequence of slope change points. The slope and height of the transition surface are obtained based on the geometric dimensions and slope parameters of the transition surface; Using the station number of each slope change point in the slope change point sequence as the base point, the three-dimensional coordinates of the bottom edge control point of the transition surface are generated by extrapolating along both sides of the runway centerline according to the slope of the transition surface; the bottom edge control point is moved upward along the elevation direction according to the height of the transition surface to generate the three-dimensional coordinates of the top edge control point of the transition surface. The three-dimensional coordinates of the boundary control points of the transition surface are the set of the three-dimensional coordinates of the bottom control points and the top control points of the transition surface.

[0014] Preferably, The acquisition of the three-dimensional coordinates of the boundary control points of the takeoff and climb surface in the local coordinate system includes: The initial width W0, spread rate E_takeoff, slope S_takeoff, and total length L_takeoff of the takeoff climb surface are obtained based on the geometric dimensions and slope parameters of the takeoff climb surface. Taking the runway end point as the starting position of the takeoff climb surface, the surface is linearly extended along the runway centerline at an extension rate E_takeoff until it reaches the total length L_takeoff. At the same time, the surface is continuously climbed along the runway centerline at a slope S_takeoff to obtain the end point of the takeoff climb surface. The half-width W_end and elevation Z of the section at a distance x from the runway finish line are obtained using the following formula: W_end = W0 + 2 L_takeoff E_takeoff; Z = x tan(S_takeoff) The three-dimensional coordinates of the boundary control point of the takeoff and climb surface in the local coordinate system are obtained based on the half-width W_end and the elevation Z.

[0015] Preferably, The acquisition of the three-dimensional coordinates of the boundary control points of the re-flight surface in the local coordinate system includes: The starting distance D_takeoff, starting width W_takeoff, expansion rate E_goaround, and total length L_goaround of the overflight are obtained based on the geometric dimensions and slope parameters of the overflight. Taking the distance D_takeoff from the runway threshold as the starting point of the go-around surface, extend it in the opposite direction along the runway centerline to the total length L_goaround to obtain the ending point of the go-around surface. Along the extension direction of the overflight surface, the initial width W_takeoff is linearly extended to the final width according to the expansion rate E_goaround; at the same time, the overflight surface is segmented and climbed along the extension direction according to the specified slope of each segment, and the elevation is determined by segmented linear interpolation. Within the extended range of the overflight surface, cross sections are sampled at equal intervals according to a preset sampling number to generate control points on the left and right sides of each cross section. The width and elevation of the control points on the left and right sides are obtained to obtain the three-dimensional coordinates of the boundary control points of the overflight surface in the local coordinate system.

[0016] According to a second aspect of the present invention, an apparatus for creating fourteen annexes to a civil airport based on an autonomous programming platform is provided, the apparatus comprising: Runway Model Building Module: Used to build the planar alignment model and corresponding longitudinal profile model of the runway in Civil3D software, and extract the planar coordinate information and elevation information of the runway centerline; Parameter configuration module: Used to configure the parameter panel in the Dynamo platform, input runway category and airspace level indicators, and obtain the geometric dimensions and slope parameters of each obstacle restriction surface; Local coordinate acquisition module: used to establish a local coordinate system with the runway entrance as the origin, the runway centerline direction as the positive X-axis, the Y-axis perpendicular to the X-axis in the horizontal plane, and the Z-axis perpendicular to the XY-axis; based on the elevation information of the runway centerline and the geometric dimensions and slope parameters of each obstacle restriction surface, to acquire the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the local coordinate system; Coordinate transformation module: used to obtain the direction unit vector of the runway centerline based on the planar coordinate information of the runway centerline, and transform the three-dimensional coordinates of the boundary control points of each obstacle restriction surface from the local coordinate system to the Civil3D world coordinate system according to the direction unit vector, so as to obtain the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the world coordinate system. Surface generation module: This module is used to group the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the world coordinate system according to the surface region of the obstacle restriction surface to obtain the three-dimensional coordinate group of the boundary control points of each obstacle restriction surface; based on the Dynamo surface generation node, it constructs the triangular mesh surface of each obstacle restriction surface according to the three-dimensional coordinate group of the boundary control points of each obstacle restriction surface to obtain the three-dimensional model of each obstacle restriction surface.

[0017] The technical solutions provided by the embodiments of the present invention may include the following beneficial effects: This application integrates the entire process of modeling the fourteen surfaces in Annex into a single framework: first, a runway alignment and longitudinal profile model is created in Civil3D to obtain basic geometric data; then, standard parameters are configured to establish the mathematical calculation rules for each surface; a local coordinate system is established, and the three-dimensional coordinates of the boundary control points of each obstacle restriction surface are obtained; the local coordinates are losslessly converted to the world coordinate system to ensure the correctness of the model's spatial position; triangular mesh surfaces are constructed by grouping by surface region to achieve mutual independence between surfaces; through the above interconnected steps, designers only need to input the runway category and flight area indicators to automatically complete the creation of each restriction surface, completely eliminating the tedious process of traditional manual point-by-point calculation; and each surface is generated independently by region, with surface decoupling; when parameters change, only the input needs to be modified to update the entire model, achieving efficient, accurate, and maintainable airport airspace obstacle restriction surface modeling.

[0018] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and are not intended to limit the invention. Attached Figure Description

[0019] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with the invention and, together with the description, serve to explain the principles of the invention.

[0020] Figure 1 This is a flowchart illustrating a method for creating fourteen annexes to a civil airport based on an autonomous programming platform, according to an exemplary embodiment. Figure 2 This is a flowchart illustrating runway cross-section information acquisition according to another exemplary embodiment. Figure 3 This is a flowchart illustrating the acquisition of obstacle constraint surface parameters according to another exemplary embodiment; Figure 4 This is a flowchart illustrating the process of obtaining the starting coordinates and rotation angle of a runway, according to another exemplary embodiment. Figure 5 This is a flowchart illustrating coordinate rotation and translation transformation according to another exemplary embodiment; Figure 6 This is a flowchart illustrating the approach surface control point generation process according to another exemplary embodiment; Figure 7 This is a flowchart illustrating the generation of inner horizontal plane control points according to another exemplary embodiment; Figure 8 This is a flowchart illustrating the generation of control points for a conical surface according to another exemplary embodiment; Figure 9 This is a flowchart illustrating the generation of transition surface control points according to another exemplary embodiment; Figure 10 This is a flowchart illustrating the generation of control points for the inner transition surface, according to another exemplary embodiment. Figure 11 This is a flowchart illustrating the control point generation process for a multiple flight surface according to another exemplary embodiment; Figure 12 This is a rendering of a three-dimensional clearance obstacle limiting surface model according to another exemplary embodiment; Figure 13 This is a schematic diagram of a system for creating fourteen civil airport annexes based on an autonomous programming platform, according to another exemplary embodiment. In the attached diagram: 1-Runway model construction module, 2-Parameter configuration module, 3-Local coordinate acquisition module, 4-Coordinate transformation module, 5-Surface generation module. Detailed Implementation

[0021] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numerals in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Rather, they are merely examples of apparatuses and methods consistent with some aspects of the invention as detailed in the appended claims.

[0022] Example 1 Figure 1 This is a flowchart illustrating a method for creating fourteen annexes to a civil airport based on an autonomous programming platform, according to an exemplary embodiment. Figure 1 As shown, the method includes: S1. In Civil3D software, create a planar alignment model of the runway and its corresponding longitudinal profile model, and extract the planar coordinates and elevation information of the runway centerline. S2, configure the parameter panel in the Dynamo platform, input the runway category and flight zone level indicators, and obtain the geometric dimensions and slope parameters of each obstacle restriction surface; S3. Establish a local coordinate system with the runway entrance as the origin, the runway centerline as the positive X-axis, the Y-axis perpendicular to the X-axis, and the Z-axis perpendicular to the XY-axis in a horizontal plane. Based on the elevation information of the runway centerline and the geometric dimensions and slope parameters of each obstacle restriction surface, obtain the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the local coordinate system. S4. Based on the planar coordinate information of the runway centerline, obtain the direction unit vector of the runway centerline. According to the direction unit vector, transform the three-dimensional coordinates of the boundary control points of each obstacle restriction surface from the local coordinate system to the Civil3D world coordinate system to obtain the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the world coordinate system. S5, group the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the world coordinate system according to the surface region of the obstacle restriction surface to obtain the three-dimensional coordinate group of the boundary control points of each obstacle restriction surface; based on the Dynamo surface generation node, construct the triangular mesh surface of each obstacle restriction surface according to the three-dimensional coordinate group of the boundary control points of each obstacle restriction surface to obtain the three-dimensional model of each obstacle restriction surface. It is understood that this embodiment specifically includes: As attached Figure 2As shown, a planar alignment model and corresponding longitudinal profile model of the runway are built in Civil3D. The planar coordinate information and elevation information of the runway centerline are extracted. The planar coordinate information includes at least the planar coordinates of the runway start and end points, and the elevation information includes at least the elevations of the runway start and end points and the station numbers and elevation data of each slope change point on the runway centerline. The station numbers and elevation data of each slope change point are obtained by reading the station numbers and elevation information of each slope change point of the runway line through the Civil3D API and outputting the PVI array. As attached Figure 3 As shown, in the Dynamo visual programming environment, design parameters such as runway category and flight area classification are input through the configuration parameter panel. The parameters are determined according to Table 5.2.4 of the "Civil Airport Flight Area Technical Standard" (MH5001) to specify the geometric dimensions and slope parameters of each obstacle restriction surface. For example: App_InnerEdgeDist (inner edge distance from the entrance B), App_InnerEdgeWidth (inner edge full width, B1 is half this value), App_FirstSection (first segment length AP_L1), App_FirstSlope (first segment slope ρ1, tan value), App_SecondSection (second segment length AP_L2), App_SecondSlope ... The specific values ​​of parameters such as slope ρ2 (tan value), Horizontal Section (horizontal section length), Divergence (spread rate, percentage, e.g., 15 represents 15%), and LZ (total length of the approach surface) are obtained from Table 5.2.4 of MH5001, depending on the runway category (non-instrument runway, non-precision approach runway, Category I / II / III precision approach runway) and airfield indicators (1~4). For a Category I precision approach runway, the typical configuration of airfield indicator 4 is as follows: B is approximately 60m, B1 is approximately 150m (inner edge full width 300m), AP_L1 is approximately 3000m, AP_L2 is approximately 3600m, ρ1 is approximately 0.02, ρ2 is approximately 0.025, and the spread rate is approximately 15%.

[0023] With the runway entrance point (local coordinate origin) as the reference, the local coordinate system's X-axis points along the runway centerline towards the runway finish line, the Y-axis is perpendicular to the X-axis in the horizontal plane (positive on the left), and the Z-axis is vertically upward, forming a right-handed coordinate system. To support bidirectional approach surfaces at the start and finish, the program controls the extension direction through the fromThreshold parameter: true extends in the negative L direction (start), and false extends in the positive L direction (finish).

[0024] Using the runway threshold as the origin of the local coordinate system, the direction of the runway centerline as the positive X-axis, the Y-axis perpendicular to the X-axis in the horizontal plane (positive on the left), and the Z-axis vertically upward, a right-hand rectangular coordinate system is formed. Under this local coordinate system, the three-dimensional coordinates of the boundary control points of the eight obstacle restriction surfaces are calculated using preset parametric mathematical formulas. It should be noted that: in the Dynamo platform, independent calculation submodules are established for each obstacle constraint surface, and each independent calculation submodule contains a preset parametric mathematical formula for the obstacle constraint surface; the independent calculation submodules are connected to each other through Dynamo to transfer structured data lists; each independent calculation submodule uses the geometric dimensions and slope parameters of the obstacle constraint surface to calculate the three-dimensional coordinates of the boundary control points of the obstacle constraint surface using the preset parametric mathematical formula.

[0025] All control points of the constrained surfaces are output in PtLocal(L, T, Z) structure, and then batch converted to world coordinates using CoordTransform, specifically including: As attached Figure 4 As shown, the starting coordinates P0(X0, Y0, Z0) and the ending coordinates Pn(Xn, Yn, Zn) of the runway are obtained based on the planar coordinate information of the runway centerline. Based on the runway start coordinates P0 and end coordinates Pn, the rotation angle theta of the unit vector in the XY plane is calculated using the four-quadrant arctangent function. The expression is: theta = Atan2(Yn-Y0, Xn-X0); As attached Figure 5 As shown, for any boundary control point's 3D coordinates P_local(x_local, y_local, z_local) in the local coordinate system, the 3D coordinates P_world(X_world, Y_world, Z_world) of the boundary control point in the Civil3D world coordinate system are obtained based on the rotation angle theta. The expression is as follows: X_world = X0 + x_local Cos(theta) - y_local Sin(theta); Y_world = Y0 + x_local Sin(theta) + y_local Cos(theta); Z_world = z_local.

[0026] After grouping the control points of each restricted surface in the obtained world coordinate system by surface region, a triangular mesh surface is automatically constructed using Dynamo surface generation nodes (naming rule: OLS_{surface name}). The generated result is shown in the attached figure. Figure 12 As shown, complete the creation of the 3D model for all 8 obstacle constraint surfaces.

[0027] All the Dynamo program nodes mentioned above are encapsulated into a custom node library, providing a unified parameter input interface to enable one-click generation of obstacle constraint surfaces under different runway design parameter inputs.

[0028] It is important to emphasize that the batch coordinate transformation function (implemented by CoordTransform.LocalToWorldBatch) receives a list of control points in the local coordinate system and the runway bearing heading angle. It uses matrix operations to complete the orthogonal transformation of the coordinates of all control points in one go, which is significantly more efficient than calculating point by point in a loop. The bearing is represented in degrees, and the rotation matrix is ​​constructed according to (Ux, Uy) = (sinθ, cosθ). All of the above functions are encapsulated in the Dynamo program diagram. Airport design engineers can load it through the Dynamo player and run it with one click without writing any code.

[0029] All the core calculation processes described above are implemented using Dynamo's C# Script nodes, which can be tested independently or called within the main program diagram. The main program flow passes control points to the surface generation node according to Dynamo's data flow method, automatically constructing TinSurface triangular mesh surfaces, thus seamlessly integrating with the Civil3D BIM model. After debugging all program nodes, select all nodes in Dynamo and create a custom node named ObstacleLimitationSurfaces_Generator using the Edit-Create Custom Node function. Input parameters include: alignment (route selector, type Civil3D Alignment), CodeNumber (flight area indicator, 1~4 integers), ApproachType (approach type string, such as NPA, CAT_I, CAT_II, etc.), and slope / length correction coefficients for each surface (Double type). Output parameters are a list of 8 control points and the generated triangular mesh surface object. After encapsulation, save it to the local node library path through Dynamo's node library manager. Other team members can directly load and use this node in Civil3D through Dynamo without opening the underlying program diagram.

[0030] The acquisition of the three-dimensional coordinates of the boundary control points of the eight limiting surfaces in the local coordinate system includes: (1) Approach plane: As attached Figure 6 As shown, the approach face is divided into three sections along the runway centerline: the first section, the second section, and the horizontal section. Taking the runway entrance as the reference, eight boundary control points are generated in three dimensions based on the geometric dimensions and slope parameters of the approach face. The geometric dimensions and slope parameters of the approach face include: the initial half-width of the approach face B1, the length of the first section AP_L1, the length of the second section AP_L2, the spread rate of the first section AP_S1, the spread rate of the second section AP_S2, the slope of the first section ρ1, and the slope of the second section ρ2. The formula for calculating the three-dimensional coordinates of the eight boundary control points is as follows: P1 = Point.ByCoordinates(-B, B1); P2 = Point.ByCoordinates(-B,-B1); P3 = Point.ByCoordinates(-(B+AP_L1),B1+AP_L1 AP_S1, AP_L1 ρ1); P4 = Point.ByCoordinates(-(B+AP_L1), -B1-AP_L1 AP_S1, AP_L1 ρ1); P5 = Point.ByCoordinates(-(B+AP_L1+AP_L2),B1+(AP_L1+AP_L2) AP_S1, AP_L1 ρ1+AP_L2 ρ2); P6 = Point.ByCoordinates(-(B+AP_L1+AP_L2),-B1-(AP_L1+AP_L2) AP_S1,AP_L1 ρ1+AP_L2 ρ2); P7 = Point.ByCoordinates(-(B+AP_LZ),B1+AP_LZ AP_S1, AP_L1 ρ1+AP_L2 ρ2); P8 = Point.ByCoordinates(-(B+AP_LZ), -B1-AP_LZ AP_S1, AP_L1 ρ1+AP_L2 ρ2); In the formula, B is the distance from the runway start point to the runway threshold; AP_LZ is the total length of the approach surface, which is obtained by summing the lengths of the first segment, the second segment, and the horizontal segment, as well as the distance B from the runway start point to the runway threshold. (2) Inner horizontal plane: As attached Figure 7 As shown, the coordinates of the runway midpoint are obtained based on the plane coordinates of the runway centerline, and the average elevation of the runway centerline is obtained based on the elevation information of the runway centerline. Using the runway midpoint coordinates as the geometric center and the runway length as the major axis, a double-centered runway profile is constructed as the bottom boundary of the inner horizontal plane. This includes setting a first center and a second center on the runway centerline at half the runway length on each side. A near semicircular arc and a far semicircular arc are generated with a specified radius R_bottom. The endpoints of the two semicircular arcs are then connected to generate a common tangent on both sides, forming a closed double-centered runway profile. Discrete sampling is performed along the double-centered runway contour at equal angular intervals to generate the coordinates of N bottom boundary control points; In the three-dimensional coordinates of the boundary control points of the inner horizontal plane, the plane coordinates are the coordinates of the bottom boundary control points, and the elevation is uniformly the sum of the specified height of the inner horizontal plane and the average elevation of the runway centerline; It should be noted that the radius R of the inner horizontal plane is determined according to the flight area indicators (4000m for flight area indicator 4, 3500m for indicator 3, 2500m for indicator 2, and 2000m for indicator 1), and the elevation of each control point on the inner horizontal plane is Z_avg + 45m (as specified in Article 5.1.2 of MH5001).

[0031] (3) Conical surface: As attached Figure 8 As shown, the three-dimensional coordinates of the boundary control points of the inner horizontal plane are used as the three-dimensional coordinates of the bottom control points of the conical surface; The bottom boundary radius of the conical surface is the same as the radius of the inner horizontal plane, both being R_bottom; the vertical height H_cone of the conical surface is obtained, as well as the angle Alpha_cone between the slope of the conical surface and the inner horizontal plane; the top boundary radius R_top of the conical surface is obtained based on the specified radius R_bottom, the vertical height H_cone of the conical surface, and the angle Alpha_cone, with the expression: R_top = R_bottom + H_cone / tan(Alpha_cone) Based on the top boundary radius R_top of the conical surface, for the coordinates of each bottom boundary control point, expand outward from the bottom boundary to the top boundary along its normal direction by a distance dL = H_cone / tan(Alpha_cone) to obtain the planar coordinates of the top control point. The elevation of the top control point is the sum of the elevation in the three-dimensional coordinates of the boundary control point of the inner horizontal plane and the vertical height H_cone of the conical surface. Based on the planar coordinates and elevation of the top control point, the three-dimensional coordinates of the top control point are obtained. The three-dimensional coordinates of the boundary control points of the conical surface are the set of the three-dimensional coordinates of the bottom control point and the top control point of the conical surface.

[0032] It should be noted that: The bottom boundary profile of the conical surface is consistent with the inner horizontal surface profile, both being R_bottom (double-centered runway shape: semicircles at both ends + common tangents on both sides). The top boundary profile of the conical surface is obtained by expanding each control point on the bottom surface outward along the radial (semicircular segment) or perpendicular to the runway direction (common tangent segment) by dL = H_cone / Con_Slope (H_cone is the vertical height of the conical surface, Con_Slope is the slope of the conical surface, 1:20 corresponds to Con_Slope=0.05, and the angle between its slope and the horizontal plane Alpha_cone =arctan(0.05) ≈ 2.86 degrees); Top surface elevation = bottom surface elevation + H_cone.

[0033] The program actually samples N=50 points (25 points for each semicircle + 2 endpoints of the common tangent) to ensure surface smoothness. The near semicircle (center L=L_C1=0) is scanned from angle π / 2 to 3π / 2, totaling 25 points (covering the semicircle in the direction L<0); the far semicircle (center L=L_C2=RunwayLength) is scanned from angle -π / 2 to π / 2, totaling 25 points (covering the semicircle in the direction L>L_C2). The normal direction (radial unit vector) of each point is recorded simultaneously to generate the top control point. For each sampling angle, the coordinates of the bottom control point (L, T, Z_bot) and the coordinates of the top control point (L + nL·dL, T + nT·dL, Z_top) are calculated respectively, where nL and nT are the normal direction components of that point.

[0034] (4) Transition surface: As attached Figure 9 As shown, the station numbers of each actual slope change point on the runway centerline are obtained based on the elevation information of the runway centerline; the end extension distance is obtained based on the geometric dimensions and slope parameters of the transition surface; virtual slope change points are generated at the runway start and end points according to the end extension distance; the elevation of the virtual slope change point is the extension value of the runway start or end elevation along the longitudinal slope of the runway; the station number is the runway start station number minus the end extension distance or the end station number plus the end extension distance. The actual and virtual slope change points are merged and sorted in ascending order of station number to obtain a complete sequence of slope change points. The slope and height of the transition surface are obtained based on its geometric dimensions and slope parameters. Using the station number of each slope change point in the slope change point sequence as the base point, the three-dimensional coordinates of the bottom control point of the transition surface are generated by extrapolating along both sides of the runway centerline according to the slope of the transition surface; the bottom control point is moved up along the elevation direction according to the height of the transition surface to generate the three-dimensional coordinates of the top control point of the transition surface. The three-dimensional coordinates of the boundary control points of the transition surface are the set of the three-dimensional coordinates of the bottom control point and the top control point of the transition surface; It should be noted that the acquisition of the three-dimensional coordinates of the boundary control points of the transition surface (implemented through Dynamo C# Script nodes) uses the PVI array as input. At each PVI position, the bottom control point is generated by extrapolating along the vertical direction of the runway centerline according to the transition surface slope Trans_Slope. The distance from the bottom edge to the RSF of the runway centerline is taken as 60 / 75 / 150m according to the MH5001 4.4.5 table (width of each side of the rise and fall zone). Then, the top control point is generated by expanding radially outward (zIH - Z_bottom) / Trans_Slope (zIH is the inner horizontal plane elevation). The bottom edge extension is extended by 60m (instrument runway) or 30m (non-instrument runway) at each end of the runway according to MH5001 4.2 to form a virtual PVI, so as to ensure that the transition surface covers the entire rise and fall zone (including the end extension).

[0035] (5) Inner approach face: The inner approach surface is applicable to precision approach runways. Its geometric parameters are obtained from Table 5.2.4 of MH5001 based on the runway category and flight zone indicators. The inner approach surface extends along the approach direction of the runway centerline with the runway threshold as the reference. The initial inner edge is located at the runway threshold, and the initial width is equal to the initial width of the approach surface. It extends outward and rises according to the specified spread rate and slope. The calculation method of each control point in the local coordinate system is consistent with the calculation logic of the first segment control points (P1~P4) of the approach surface. That is, with the runway threshold as the starting point, the position and elevation of the end section are determined by the length and slope of the inner approach surface, and the width of the end section is determined by the initial half width and spread rate. The outer edge of the inner approach surface is the first segment of the bottom edge of the inner transition surface.

[0036] (6) Inner transition surface: As attached Figure 10As shown, the inner transition surface is suitable for precision approach runways, and its bottom edge is constructed from three segments. The first segment is the sequence of control points along the outer edge of the inner approach surface, extending from the beginning to the end. The second segment is the sequence of control points along the runway elevation, extending from the end of the inner approach surface along the runway length to the start of the miss approach surface. The third segment is the sequence of control points along the outer edge of the miss approach surface, extending from the start of the miss approach surface along its extension direction to the end. Connecting these three control point sequences sequentially forms the bottom edge control point sequence of the inner transition surface. For each bottom edge control point, the slope is adjusted to the inner horizontal plane elevation along a direction perpendicular to the runway centerline and pointing outwards, according to the inner transition surface slope, to generate the top edge control point. The bottom and top edges together constitute the boundary control point set of the inner transition surface.

[0037] (7) Takeoff climb surface: The initial width W0, spread rate E_takeoff, slope S_takeoff, and total length L_takeoff of the takeoff climb surface are obtained based on the geometric dimensions and slope parameters of the takeoff climb surface. Taking the runway end point as the starting position of the takeoff climb surface, the surface is linearly extended along the runway centerline at an extension rate E_takeoff until it reaches the total length L_takeoff. At the same time, the surface is continuously climbed along the runway centerline at a slope S_takeoff to obtain the end point of the takeoff climb surface. The half-width W_end and elevation Z of the section at a distance x from the runway finish line are obtained using the following formula: W_end = W0 + 2 L_takeoff E_takeoff; Z = x tan(S_takeoff) The three-dimensional coordinates of the boundary control points of the takeoff and climb surface in the local coordinate system are obtained based on the half-width W_end and the elevation Z.

[0038] (8) Go-around surface: As attached Figure 11 As shown, the starting distance D_takeoff, starting width W_takeoff, expansion rate E_goaround, and total length L_goaround of the bypass surface are obtained based on the geometric dimensions and slope parameters of the bypass surface. Taking the distance D_takeoff from the runway threshold as the starting point of the go-around surface, extend it in the opposite direction along the runway centerline to the total length L_goaround to obtain the ending point of the go-around surface. Along the extension direction of the overflight surface, the initial width W_takeoff is linearly extended to the final width according to the expansion rate E_goaround; at the same time, the overflight surface is segmented and climbed along the extension direction according to the specified slope of each segment, and the elevation is determined by segmented linear interpolation. Within the extended range of the bypass surface, cross sections are collected at equal intervals according to the preset sampling quantity, generating control points on the left and right sides of each cross section. The width and elevation of the control points on the left and right sides are obtained, and the three-dimensional coordinates of the boundary control points of the bypass surface in the local coordinate system are obtained.

[0039] Example 2 Figure 13 This is a system schematic diagram illustrating an apparatus for creating fourteen civil airport annexes based on an autonomous programming platform, according to another exemplary embodiment. The apparatus includes: Runway Model Building Module 1: Used to build the planar alignment model and corresponding longitudinal profile model of the runway in Civil3D software, and extract the planar coordinate information and elevation information of the runway centerline; Parameter configuration module 2: Used to configure the parameter panel in the Dynamo platform, input the runway category and flight zone level indicators, and obtain the geometric dimensions and slope parameters of each obstacle restriction surface; Local coordinate acquisition module 3: used to establish a local coordinate system with the runway entrance as the origin, the runway centerline direction as the positive X-axis, the Y-axis perpendicular to the X-axis in the horizontal plane, and the Z-axis perpendicular to the XY-axis; based on the elevation information of the runway centerline and the geometric dimensions and slope parameters of each obstacle restriction surface, to acquire the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the local coordinate system; Coordinate transformation module 4: used to obtain the direction unit vector of the runway centerline based on the planar coordinate information of the runway centerline, and transform the three-dimensional coordinates of the boundary control points of each obstacle restriction surface from the local coordinate system to the Civil3D world coordinate system according to the direction unit vector, so as to obtain the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the world coordinate system. Surface generation module 5: It is used to group the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the world coordinate system according to the surface region of the obstacle restriction surface to obtain the three-dimensional coordinate group of the boundary control points of each obstacle restriction surface; based on the Dynamo surface generation node, it constructs the triangular mesh surface of each obstacle restriction surface according to the three-dimensional coordinate group of the boundary control points of each obstacle restriction surface to obtain the three-dimensional model of each obstacle restriction surface.

[0040] It is understood that the same or similar parts in the above embodiments can be referred to each other, and the contents not described in detail in some embodiments can be referred to the same or similar contents in other embodiments.

[0041] It should be noted that in the description of this invention, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, in the description of this invention, unless otherwise stated, "a plurality of" means at least two.

[0042] Any process or method description in the flowchart or otherwise herein can be understood as representing a module, segment, or portion of code comprising one or more executable instructions for implementing a particular logical function or process, and the scope of the preferred embodiments of the invention includes additional implementations in which functions may be performed not in the order shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as will be understood by those skilled in the art to which embodiments of the invention pertain.

[0043] It should be understood that various parts of the present invention can be implemented in hardware, software, firmware, or a combination thereof. In the above embodiments, multiple steps or methods can be implemented in software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware, as in another embodiment, it can be implemented using any one or a combination of the following techniques known in the art: discrete logic circuits having logic gates for implementing logical functions on data signals, application-specific integrated circuits (ASICs) having suitable combinational logic gates, programmable gate arrays (PGAs), field-programmable gate arrays (FPGAs), etc.

[0044] Those skilled in the art will understand that all or part of the steps of the methods in the above embodiments can be implemented by a program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, the program includes one or a combination of the steps of the method embodiments.

[0045] Furthermore, the functional units in the various embodiments of the present invention can be integrated into a processing module, or each unit can exist physically separately, or two or more units can be integrated into a module. The integrated module can be implemented in hardware or as a software functional module. If the integrated module is implemented as a software functional module and sold or used as an independent product, it can also be stored in a computer-readable storage medium.

[0046] The storage media mentioned above can be read-only memory, disk, or optical disk, etc.

[0047] In the description of this specification, references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0048] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A method for creating fourteen annexes to a civil airport based on an independent programming platform, characterized in that: The method includes: In Civil3D software, a planar alignment model and a corresponding longitudinal profile model of the runway are created, and the planar coordinates and elevation information of the runway centerline are extracted. Configure the parameter panel in the Dynamo platform, input the runway category and airspace level indicators, and obtain the geometric dimensions and slope parameters of each obstacle restriction surface; A local coordinate system is established with the runway entrance as the origin, the runway centerline as the positive X-axis, the Y-axis perpendicular to the X-axis, and the Z-axis perpendicular to the XY-axis in a horizontal plane. Based on the elevation information of the runway centerline and the geometric dimensions and slope parameters of each obstacle restriction surface, the three-dimensional coordinates of the boundary control points of each obstacle restriction surface are obtained in the local coordinate system. Using the planar coordinate information of the runway centerline as a reference, obtain the direction unit vector of the runway centerline. Based on the direction unit vector, transform the three-dimensional coordinates of the boundary control points of each obstacle restriction surface from the local coordinate system to the Civil3D world coordinate system to obtain the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the world coordinate system. The three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the world coordinate system are grouped according to the surface region of the obstacle restriction surface to obtain the three-dimensional coordinate group of the boundary control points of each obstacle restriction surface; based on the Dynamo surface generation node, the triangular mesh surface of each obstacle restriction surface is constructed according to the three-dimensional coordinate group of the boundary control points of each obstacle restriction surface to obtain the three-dimensional model of each obstacle restriction surface.

2. The method for creating fourteen annexes to a civil airport based on an autonomous programming platform according to claim 1, characterized in that, The process of obtaining the three-dimensional coordinates of the boundary control points of each obstacle constraint surface in the local coordinate system includes: In the Dynamo platform, an independent calculation submodule is established for each obstacle constraint surface. Each independent calculation submodule contains a preset parameterized mathematical formula for the obstacle constraint surface. The independent calculation submodules are connected via Dynamo to transmit structured data lists; each independent calculation submodule uses the geometric dimensions and slope parameters of the obstacle restriction surface to calculate the three-dimensional coordinates of the boundary control points of the obstacle restriction surface using preset parametric mathematical formulas.

3. The method for creating fourteen annexes to a civil airport based on an autonomous programming platform according to claim 1, characterized in that, The process involves obtaining the direction unit vector of the runway centerline based on the planar coordinate information of the runway centerline, and transforming the three-dimensional coordinates of the boundary control points of each obstacle constraint surface from the local coordinate system to the Civil3D world coordinate system based on the direction unit vector, thereby obtaining the three-dimensional coordinates of the boundary control points of each obstacle constraint surface in the world coordinate system, including: The starting coordinates P0(X0, Y0, Z0) and the ending coordinates Pn(Xn, Yn, Zn) of the runway are obtained based on the planar coordinate information of the runway centerline. Based on the runway start coordinates P0 and end coordinates Pn, the rotation angle theta of the direction unit vector in the XY plane is calculated using the four-quadrant arctangent function, and the expression is: theta = Atan2(Yn-Y0, Xn-X0); For any boundary control point with 3D coordinates P_local(x_local, y_local, z_local) in the local coordinate system, the boundary control point with 3D coordinates P_world(X_world, Y_world, Z_world) in the Civil3D world coordinate system is obtained based on the rotation angle theta, and the expression is: X_world = X0 + x_local Cos(theta) - y_local Sin(theta); Y_world = Y0 + x_local Sin(theta) + y_local Cos(theta); Z_world = z_local.

4. The method for creating fourteen annexes to a civil airport based on an autonomous programming platform according to claim 2, characterized in that, The obstacle limiting surfaces include: a conical surface, an inner horizontal surface, an approach surface, a transition surface, a takeoff and climb surface, an inner approach surface, an inner transition surface, and a go-around surface; The acquisition of the three-dimensional coordinates of the boundary control points of the approach surface in the local coordinate system includes: The approach surface is divided into three segments along the runway centerline: a first segment, a second segment, and a horizontal segment. Using the runway entrance as a reference, eight boundary control points with three-dimensional coordinates are generated based on the geometric dimensions and slope parameters of the approach surface. These geometric dimensions and slope parameters include: the initial half-width of the approach surface B1, the length of the first segment AP_L1, the length of the second segment AP_L2, the spread rate of the first segment AP_S1, the spread rate of the second segment AP_S2, the slope of the first segment ρ1, and the slope of the second segment ρ2. The calculation expressions for the three-dimensional coordinates of the eight boundary control points are as follows: P1 = Point.ByCoordinates(-B, B1); P2 = Point.ByCoordinates(-B,-B1); P3 = Point.ByCoordinates(-(B+AP_L1),B1+AP_L1 AP_S1,AP_L1 ρ1); P4 = Point.ByCoordinates(-(B+AP_L1), -B1-AP_L1 AP_S1,AP_L1 ρ1); P5 = Point.ByCoordinates(-(B+AP_L1+AP_L2),B1+(AP_L1+AP_L2) AP_S1, AP_L1 ρ1+AP_L2 ρ2); P6 = Point.ByCoordinates(-(B+AP_L1+AP_L2),-B1-(AP_L1+AP_L2) AP_S1, AP_L1 ρ1+AP_L2 ρ2); P7 = Point.ByCoordinates(-(B+AP_LZ),B1+AP_LZ AP_S1, AP_L1 ρ1+AP_L2 ρ2); P8 = Point.ByCoordinates(-(B+AP_LZ), -B1-AP_LZ AP_S1, AP_L1 ρ1+AP_L2 ρ2); In the formula, B is the distance from the runway start point to the runway threshold; AP_LZ is the total length of the approach surface, which is obtained by summing the lengths of the first segment, the second segment, and the horizontal segment, as well as the distance B from the runway start point to the runway threshold.

5. The method for creating fourteen annexes to a civil airport based on an autonomous programming platform according to claim 4, characterized in that, Obtaining the three-dimensional coordinates of the boundary control points of the inner horizontal plane in the local coordinate system includes: The coordinates of the runway midpoint are obtained based on the plane coordinate information of the runway centerline, and the average elevation of the runway centerline is obtained based on the elevation information of the runway centerline. Using the runway midpoint coordinates as the geometric center and the runway length as the major axis, a double-centered runway profile is constructed as the bottom boundary of the inner horizontal plane. This includes setting a first center and a second center on the runway centerline at half the runway length on each side. A near semicircular arc and a far semicircular arc are generated with a specified radius R_bottom. The endpoints of the two semicircular arcs are then connected to generate a common tangent on both sides, forming a closed double-centered runway profile. Discrete sampling is performed along the double-centered runway contour at equal angular intervals to generate N coordinates of bottom boundary control points; In the three-dimensional coordinates of the boundary control points of the inner horizontal plane, the plane coordinates are the coordinates of the bottom boundary control points, and the elevation is uniformly the sum of the specified height of the inner horizontal plane and the average elevation of the runway centerline. Obtaining the three-dimensional coordinates of the boundary control points of the conical surface in the local coordinate system includes: The three-dimensional coordinates of the boundary control points of the inner horizontal plane are used as the three-dimensional coordinates of the bottom control points of the conical surface; The bottom boundary radius of the conical surface is the same as the radius of the inner horizontal plane, both being R_bottom; the vertical height H_cone of the conical surface is obtained, as well as the angle Alpha_cone between the slope of the conical surface and the inner horizontal plane; the top boundary radius R_top of the conical surface is obtained based on the specified radius R_bottom, the vertical height H_cone of the conical surface, and the angle Alpha_cone, with the expression: R_top = R_bottom + H_cone / tan(Alpha_cone) Based on the top boundary radius R_top of the conical surface, for the coordinates of each bottom boundary control point, expand outward from the bottom boundary to the top boundary along its normal direction by a distance dL = H_cone / tan(Alpha_cone) to obtain the planar coordinates of the top control point. The elevation of the top control point is the sum of the elevation in the three-dimensional coordinates of the boundary control point of the inner horizontal plane and the vertical height H_cone of the conical surface. Based on the planar coordinates and elevation of the top control point, the three-dimensional coordinates of the top control point are obtained. The three-dimensional coordinates of the boundary control points of the conical surface are the set of the three-dimensional coordinates of the bottom control point and the top control point of the conical surface.

6. The method for creating fourteen annexes to a civil airport based on an autonomous programming platform according to claim 4, characterized in that, Obtaining the three-dimensional coordinates of the boundary control points of the transition surface in the local coordinate system includes: The station numbers of each actual slope change point on the runway centerline are obtained based on the elevation information of the runway centerline; the end extension distance is obtained based on the geometric dimensions and slope parameters of the transition surface; virtual slope change points are generated at the runway start and end points according to the end extension distance; the elevation of the virtual slope change point is the extension value of the runway start or end elevation along the longitudinal slope of the runway; and the station number is the runway start station number minus the end extension distance or the end station number plus the end extension distance. The actual and virtual slope change points are merged and sorted in ascending order of station number to obtain a complete sequence of slope change points. The slope and height of the transition surface are obtained based on the geometric dimensions and slope parameters of the transition surface; Using the station number of each slope change point in the slope change point sequence as the base point, the three-dimensional coordinates of the bottom control point of the transition surface are generated by extrapolating along both sides of the runway centerline according to the slope of the transition surface; the bottom control point is moved upward along the elevation direction according to the height of the transition surface to generate the three-dimensional coordinates of the top control point of the transition surface. The three-dimensional coordinates of the boundary control points of the transition surface are the set of the three-dimensional coordinates of the bottom control points and the top control points of the transition surface.

7. The method for creating fourteen annexes to a civil airport based on an autonomous programming platform according to claim 4, characterized in that, The acquisition of the three-dimensional coordinates of the boundary control points of the takeoff and climb surface in the local coordinate system includes: The initial width W0, spread rate E_takeoff, slope S_takeoff, and total length L_takeoff of the takeoff climb surface are obtained based on the geometric dimensions and slope parameters of the takeoff climb surface. Taking the runway end point as the starting position of the takeoff climb surface, the surface is linearly extended along the runway centerline at an extension rate E_takeoff until it reaches the total length L_takeoff. At the same time, the surface is continuously climbed along the runway centerline at a slope S_takeoff to obtain the end point of the takeoff climb surface. The half-width W_end and elevation Z of the section at a distance x from the runway finish line are obtained using the following formula: W_end = W0 + 2 L_takeoff E_takeoff; Z= x tan(S_takeoff) The three-dimensional coordinates of the boundary control point of the takeoff and climb surface in the local coordinate system are obtained based on the half-width W_end and the elevation Z.

8. The method for creating fourteen annexes to a civil airport based on an autonomous programming platform as described in claim 4, characterized in that, The acquisition of the three-dimensional coordinates of the boundary control points of the re-flight surface in the local coordinate system includes: The starting distance D_takeoff, starting width W_takeoff, expansion rate E_goaround, and total length L_goaround of the overflight are obtained based on the geometric dimensions and slope parameters of the overflight. Taking the distance D_takeoff from the runway entrance as the starting point of the go-around surface, extend it in the opposite direction along the runway centerline to the total length L_goaround to obtain the ending point of the go-around surface. Along the extension direction of the overflight surface, the initial width W_takeoff is linearly extended to the final width according to the expansion rate E_goaround; at the same time, the overflight surface is segmented and climbed along the extension direction according to the specified slope of each segment, and the elevation is determined by segmented linear interpolation. Within the extended range of the overflight surface, cross sections are sampled at equal intervals according to a preset sampling number to generate control points on the left and right sides of each cross section. The width and elevation of the control points on the left and right sides are obtained to obtain the three-dimensional coordinates of the boundary control points of the overflight surface in the local coordinate system.

9. A device for creating fourteen side panels of a civil airport based on an autonomous programming platform, characterized in that: The device includes: Runway Model Building Module: Used to build the planar alignment model and corresponding longitudinal profile model of the runway in Civil3D software, and extract the planar coordinate information and elevation information of the runway centerline; Parameter configuration module: Used to configure the parameter panel in the Dynamo platform, input runway category and airspace level indicators, and obtain the geometric dimensions and slope parameters of each obstacle restriction surface; Local coordinate acquisition module: used to establish a local coordinate system with the runway entrance as the origin, the runway centerline direction as the positive X-axis, the Y-axis perpendicular to the X-axis in the horizontal plane, and the Z-axis perpendicular to the XY-axis; based on the elevation information of the runway centerline and the geometric dimensions and slope parameters of each obstacle restriction surface, to acquire the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the local coordinate system; Coordinate transformation module: used to obtain the direction unit vector of the runway centerline based on the planar coordinate information of the runway centerline, and transform the three-dimensional coordinates of the boundary control points of each obstacle restriction surface from the local coordinate system to the Civil3D world coordinate system according to the direction unit vector, so as to obtain the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the world coordinate system. Surface generation module: This module is used to group the three-dimensional coordinates of the boundary control points of each obstacle restriction surface in the world coordinate system according to the surface region of the obstacle restriction surface to obtain the three-dimensional coordinate group of the boundary control points of each obstacle restriction surface; based on the Dynamo surface generation node, it constructs the triangular mesh surface of each obstacle restriction surface according to the three-dimensional coordinate group of the boundary control points of each obstacle restriction surface to obtain the three-dimensional model of each obstacle restriction surface.

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