Quality characteristic mapping method, computer-readable storage medium and program product

Abstract

Mass characteristic mapping methods, computer-readable storage media, and program products, relating to the field of aircraft overall design, including: dividing a cylindrical section into N sub-sections; and mapping the structural mass m of the i-th sub-section. i_s The mass m of the auxiliary equipment of the i-th sub-section i_a Mapped to the diameter D and length l of the i-th sub-segment respectively. i In a shell element mesh model with the same total number of n meshes, the mass of each element in the initial mass property set of the i-th sub-segment is denoted as m. ij_0 ; for m ij_0 To redistribute, m ij_0 The initial increment is Δm ij_0 , Δm ij_0 The initial set is represented by a function. An intelligent optimization algorithm is employed, with the objective of minimizing the function f(m(i,j)), and the centroid and moment of inertia of the i-th sub-segment as constraints, to optimize the increment Δm. ij_0 The initial set is optimized to obtain the optimized incremental set of the initial incremental set. The above steps are repeated to allocate the mass of each of the N sub-segments of the cylindrical section, resulting in the optimized incremental set of the N sub-segments. This process is highly efficient and meets the iterative requirements for the mechanical calculation of the main structure of the aircraft.

Description

Technical Field

[0001] This invention relates to the field of overall aircraft design, and in particular to a method for mass characteristic mapping of the main structure of an aircraft, a computer-readable storage medium, and a program product. Background Technology

[0002] The mass characteristics of an aircraft are important parameters to be considered in the overall design of an aircraft. In mechanical calculations involving aircraft, the aircraft is generally simplified into a discrete model of elastic-mass components (beams, rods, shells, etc.). However, for aircraft with non-axisymmetric mass distribution, the above simplification method will lead to an imbalance in the aircraft's inertia. In this case, it is usually necessary to establish a detailed three-dimensional model of the aircraft, which requires a precise description of the coordinate positions and mass characteristics of the equipment inside the cabin, forming a detailed three-dimensional model drawing. Although this method can ensure the consistency of mass characteristics, the modeling efficiency is low and cannot meet the rapid iterative requirements of the mechanical calculation of the main structure of the aircraft in the design phase.

[0003] Currently, the finite element method is mainly used to discretize aircraft in three dimensions. The main structure, components, and parts are modeled and assembled according to the 3D model size requirements. The influence of directly assembled components on the mass distribution of the aircraft cannot be ignored. For internal equipment, detailed models of the center of mass and connection methods are established as much as possible. For support structures with significant mass, detailed 3D structural models are required. However, using the above method requires statistical analysis of the dimensions, mass, and installation methods of each level of the aircraft structure and individual equipment, resulting in a huge modeling workload. Often, oversights in the operation of connection units lead to discontinuities in the overall or local stiffness of the aircraft, requiring further correction through simulation methods such as modal analysis.

[0004] In view of the above problems and needs, developing a mass characteristic mapping method for the main structure of aircraft to achieve rapid modeling of the equivalent mass characteristics of aircraft has become a key technical challenge. Summary of the Invention

[0005] The technical problem solved by this application is to overcome the shortcomings of the prior art and provide a mapping method for the mass characteristics of the main structure of an aircraft. This method can effectively avoid the inefficiency of traditional 3D modeling methods, meet the requirements of rapid iteration of mechanical calculations for the main structure of the aircraft, and support the overall scheme demonstration of the aircraft.

[0006] The technical solution provided in this application is as follows:

[0007] A method for mass characteristic mapping of aircraft main structure includes:

[0008] S1: The origin of the coordinate system is located at the geometric center of the bottom surface of the cylindrical compartment. The X-axis points to the axial direction of the compartment, and the Y-axis points to the normal direction of the compartment. The cylindrical compartment with length L, diameter D and total mass M is divided into N sub-segments along the X-axis.

[0009] S2: The structural mass m of the i-th sub-segment i_s The mass m of the auxiliary equipment of the i-th sub-section i_a Mapped to the diameter D and length l of the i-th sub-segment respectively. i In a shell element mesh model with the same total number of n meshes, the mass of each element in the initial mass property set of the i-th sub-segment is denoted as m. ij_0 , i=1,2,3...N, j=1,2,3...n;

[0010] S3: For each unit mass m in the initial mass characteristic set of the i-th sub-segment ij_0 Redistribute the mass m of each unit. ij_0 The initial increment is Δm ij_0 Increment Δm ij_0 The initial set is set using a function Characterized by i = 1, 2, 3... N, an intelligent optimization algorithm is employed, aiming to minimize the function f(m(i,j)), with the centroid and moment of inertia of the i-th sub-segment as constraints, and adjusting the increment Δm. ij_0 The initial set is optimized to obtain the optimized increment set of the initial increment set.

[0011] S4: Repeat step S3 to allocate mass to each of the N sub-segments of the cylindrical compartment, obtaining the optimized incremental set of the N sub-segments. according to Mass allocation is performed on each unit of each sub-segment.

[0012] Each of the sub-segments has a length of l. i i = 1, 2, 3, ..., N, satisfying The auxiliary devices with quality attributes and their connection locations within the i-th sub-segment are included within the i-th sub-segment, and satisfy the following conditions: Where m i Let be the total mass of the i-th sub-segment, where i = 1, 2, 3, ... N.

[0013] Each of the sub-segments includes the bulkhead structural mass m of the segment. i_s Mass of auxiliary equipment of the compartment m i_a m i =m i_s +m i_a .

[0014] The structure of the shell unit mesh model is the same as the bulkhead structure of the compartment.

[0015] In S2, the structural mass m of the i-th sub-segment is... i_s The mass m of the auxiliary equipment of the i-th sub-section i_a Mapped to the diameter D and length l of the i-th sub-segment respectively. i On a shell-element mesh model with the same total number of n meshes, including a segment structure mass of m allocated to each shell-element mesh. i_s / n, the projection is based on the closest distance between the auxiliary equipment and the compartment wall, and the number of cell grids within the projected area is n. list The mass of the auxiliary equipment assigned to each cell grid within the projected area is m. i_a / n list The mass assigned to each cell within the projected area is m. i_s / n+m i_a / n list The total mass of the unit within the projected area is m project_in =m i_s n list / n+m i_a The total mass of the unit outside the projected area is m. project_out =(nn list )m i_s / n, satisfying m i =m project_in +m project_out This constitutes the initial set of quality characteristics for the i-th sub-segment.

[0016] In S3, the constraints are the center of mass and moment of inertia of the i-th sub-segment, including: |J x_mi -J' x_mi | / J x_mi ≤5%|J y_mi -J' y_mi | / J y_mi ≤5%|J z_mi -J' z_mi | / J z_mi ≤5%|X c_mi -X' c_mi | / X c_mi ≤5%|Y c_mi -Y' c_mi | / Y c_mi ≤5%

[0017] Where the centroid of the i-th sub-segment is X c_mi Y c_mi , Z c_mi The moment of inertia of the i-th sub-segment is J. x_mi J y_mi J z_mi J' x_mi 、J'y_mi 、J' z_mi Let X' be the moment of inertia of the i-th sub-segment after redistribution. c_mi Y' c_mi Z' c_mi Let be the centroid of the i-th sub-segment after redistribution.

[0018] In S4, if the following conditions are met The quality characteristic mapping method oriented towards the main structure is considered effective.

[0019] A computer-readable storage medium having a computer program / instructions stored thereon, which, when executed by a processor, implement the steps of any of the methods described above.

[0020] A computer program product includes a computer program / instructions that, when executed by a processor, implement the steps of any of the methods described above.

[0021] The main content of this invention is to map the overall mass characteristics of an aircraft segment onto a shell-element mesh model with high stiffness and the same dimensions as the main structure, in order to simulate the mass characteristic distribution of the aircraft segment. First, a reference coordinate system for the mass characteristics of the segment is determined, and the segment is divided into multiple sub-segments along its axis. The division principle is that auxiliary equipment with mass attributes and their connection positions within a sub-segment should be included in the same sub-segment. Second, the overall mass, center of mass, and moment of inertia of each sub-segment are statistically analyzed. Then, the mass of each sub-segment is statistically analyzed according to the cabin structure and auxiliary equipment with mass attributes, and its mass is allocated to a shell-element mesh model with the same dimensions as the main structure. By adjusting the mass distribution of the shell-element mesh model, the effect of consistent mass, center of mass, and moment of inertia with the divided sub-segments is achieved, resulting in a main structure shell-element mesh mass mapping model for each sub-segment. Finally, the main structure shell-element mesh mass mapping models of each sub-segment are assembled to obtain a shell-element mesh mass mapping model with the same dimensions as the original aircraft segment's main structure.

[0022] The main content of this invention is to map the overall mass characteristics of an aircraft segment onto a shell-element mesh model with high stiffness and the same dimensions as the main structure, in order to simulate the mass characteristic distribution of the aircraft segment. First, a reference coordinate system for the mass characteristics of the segment is determined, and the segment is divided into multiple sub-segments along its axis. The division principle is that auxiliary equipment with mass attributes and their connection positions within a sub-segment should be included in the same sub-segment. Second, the overall mass, center of mass, and moment of inertia of each sub-segment are statistically analyzed. Then, the mass of each sub-segment is statistically analyzed according to the cabin structure and auxiliary equipment with mass attributes, and its mass is allocated to a shell-element mesh model with the same dimensions as the main structure. By adjusting the mass distribution of the shell-element mesh model, the effect of consistent mass, center of mass, and moment of inertia with the divided sub-segments is achieved, resulting in a main structure shell-element mesh mass mapping model for each sub-segment. Finally, the main structure shell-element mesh mass mapping models of each sub-segment are assembled to obtain a shell-element mesh mass mapping model with the same dimensions as the original aircraft segment's main structure.

[0023] In summary, this application includes at least the following beneficial technical effects:

[0024] It can quickly construct a main structure mass characteristic mapping model that is equivalent to a detailed 3D model of an aircraft.

[0025] It can support the rapid iterative requirements of mechanical calculations for the main structure of aircraft. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the initial mass allocation of the compartment units.

[0027] Figure 2 A schematic diagram for optimizing the allocation of mass in the compartment units.

[0028] Figure 3 A schematic diagram of the optimized mass distribution of each compartment. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments disclosed in the present invention will be described in further detail below with reference to the accompanying drawings.

[0030] This application discloses a method for mass characteristic mapping of the main structure of an aircraft, such as... Figure 1 As shown, a cylindrical section of length L, diameter D, and total mass M is divided into N segments. The origin of the coordinate system is located at the geometric center of the bottom surface of each segment, the X-axis points along the axial direction of the segment, and the Y-axis points along the normal direction of the segment, satisfying the right-hand rule. Each sub-segment has a length of l. i(i＝1,2,3,...N) ,satisfy Furthermore, the auxiliary devices with quality attributes and their connection locations within the i-th sub-segment are included within the i-th sub-segment, and satisfy the following condition: Where mi Let m be the total mass of the i-th sub-segment. The structural mass of the i-th sub-segment is m. i_s The mass of the auxiliary equipment of the i-th sub-section is m. i_a , satisfying m i =m i_s +m i_a The centroid of the i-th sub-segment is X. c_mi Y c_mi , Z c_mi The moment of inertia of the i-th sub-segment is J. x_mi J y_mi J z_mi The structural mass m of the i-th sub-segment is... i_s The mass m of the auxiliary equipment of the i-th sub-section i_a Mapped to the diameter D and length l of the i-th sub-segment respectively. i On a shell element mesh model with the same total number of n meshes, the structural mass of the compartment allocated to each shell element mesh is m. i_s / n. Projecting the auxiliary equipment according to the closest distance to the compartment wall, the number of cell grids within the projected area is n. list The mass of the auxiliary equipment allocated to each cell grid within the projected area is m. i_a / n list Then the mass assigned to each cell grid within the projected area is m. i_s / n+m i_a / n list The total mass of the unit within the projected area is m. project_in =m i_s n list / n+m i_a The total mass of the unit outside the projected area is m. project_out =(nn list )m i_s / n, satisfying m i =m project_in +m project_out This constitutes the initial set of quality characteristics for the i-th sub-segment, denoted as m. i0 ,like Figure 1 As shown. The mass of each unit in the initial mass characteristic set of the i-th sub-segment is denoted as m. ij_0 (j = 1, 2, 3... n). For each unit mass m in the initial set of mass characteristics of the i-th sub-segment. ij_0 The unit mass m is redistributed. ij_0 The initial increment is Δm ij_0 The initial mass of the redistributed unit is m. ij_1 , satisfying m ij_1 =m ij_0 +Δmij_0 The increment Δm ij_0 The initial set is set using a function Characterization, employing an intelligent optimization algorithm, with the objective of minimizing the function f(m(i,j)), and constrained by the centroid and moment of inertia of the i-th sub-segment, the mathematical model of this problem can be expressed as (as shown in Equation 1), for the increment Δm ij_0 The initial set is optimized to obtain the optimized incremental set of the initial incremental set. like Figure 2 As shown.

[0031]

[0032] Among them, J' x_mi 、J' y_mi 、J' z_mi Let X' be the moment of inertia of the i-th sub-segment after redistribution. c_mi Y' c_mi Z' c_mi Let be the centroid of the i-th sub-segment after redistribution.

[0033] By applying the above-described mass allocation method to the N sub-segments of the cylindrical section, an optimized incremental set of the N sub-segments can be obtained. like Figure 3 As shown, if the following conditions are met Therefore, the quality characteristic mapping method oriented towards the main structure can be considered effective.

[0034] This invention establishes a mass characteristic mapping method for the main structure by allocating the structural mass and auxiliary equipment mass of the compartments to a shell element mesh model of the same size, aiming at minimizing the optimized incremental set of each sub-segment, using the centroid and moment of inertia of each sub-segment as constraints, and employing an intelligent optimization algorithm to optimize the optimized incremental set.

[0035] Using the above method, the overall characteristics of an aircraft segment can be mapped onto a shell element mesh model with the same dimensions as the main structure of the segment.

[0036] This embodiment also discloses a computer-readable storage medium storing a computer program / instructions thereon, which, when executed by a processor, implements the steps of any of the methods described above.

[0037] This embodiment also discloses a computer program product, including a computer program / instructions that, when executed by a processor, implement the steps of any of the methods described above.

[0038] The contents not described in detail in this application specification are common knowledge to those skilled in the art.

[0039] The present application has been described in detail above with reference to specific embodiments and exemplary examples; however, these descriptions should not be construed as limiting the present application. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and implementation methods of the present application without departing from the spirit and scope of the present application, and all such modifications and improvements fall within the scope of the present application. The scope of protection of the present application is determined by the appended claims.

Claims

1. A quality characteristic mapping method, characterized in that, include: S1: The origin of the coordinate system is located at the geometric center of the bottom surface of the cylindrical compartment. The X-axis points to the axial direction of the compartment, and the Y-axis points to the normal direction of the compartment. The cylindrical compartment with length L, diameter D and total mass M is divided into N sub-segments along the X-axis. S2: The structural mass m of the i-th sub-segment i_s The mass m of the auxiliary equipment of the i-th sub-section i_a Mapped to the diameter D and length l of the i-th sub-segment respectively. i In a shell element mesh model with the same total number of n meshes, the mass of each element in the initial mass property set of the i-th sub-segment is denoted as m. ij_0 , i=1,2,3…N, j=1,2,3…n; S3: For each unit mass m in the initial mass characteristic set of the i-th sub-segment ij_0 Redistribute the mass m of each unit. ij_0 The initial increment is Δm ij_0 Increment Δm ij_0 The initial set is set using a function Characterized by i = 1, 2, 3... N, an intelligent optimization algorithm is employed, aiming to minimize the function f(m(i,j)), with the centroid and moment of inertia of the i-th sub-segment as constraints, and adjusting the increment Δm. ij_0 The initial set is optimized to obtain the optimized increment set of the initial increment set. S4: Repeat step S3 to allocate mass to each of the N sub-segments of the cylindrical compartment, obtaining the optimized incremental set of the N sub-segments. according to Mass allocation is performed on each unit of each sub-segment.

2. The quality characteristic mapping method according to claim 1, characterized in that: The length of each sub-segment is li,i＝1,2,3,..N ,satisfy The auxiliary devices with quality attributes and their connection locations within the i-th sub-segment are included within the i-th sub-segment, and satisfy the following conditions: Where m i Let be the total mass of the i-th sub-segment, where i = 1, 2, 3, ... N.

3. The quality characteristic mapping method according to claim 2, characterized in that: Each of the sub-segments includes the bulkhead structural mass m of the segment. i_s Mass of auxiliary equipment of the compartment m i_a m i =m i_s +m i_a .

4. The quality characteristic mapping method according to claim 3, characterized in that: The structure of the shell unit mesh model is the same as the bulkhead structure of the compartment.

5. The quality characteristic mapping method according to claim 1, characterized in that, In S2, the structural mass m of the i-th sub-segment is... i_s The mass m of the auxiliary equipment of the i-th sub-section i_a Mapped to the diameter D and length l of the i-th sub-segment respectively. i On a shell-element mesh model with the same total number of n meshes, including a segment structure mass of m allocated to each shell-element mesh. i_s / n, the projection is based on the closest distance between the auxiliary equipment and the compartment wall, and the number of cell grids within the projected area is n. list The mass of the auxiliary equipment assigned to each cell grid within the projected area is m. i_a / n list The mass assigned to each cell within the projected area is m. i_s / n+m i_a / n list The total mass of the unit within the projected area is m project_in =m i_s n list / n+m i_a The total mass of the unit outside the projected area is m. project_out =(nn list )m i_s / n, satisfying m i =m project_in +m project_out This constitutes the initial set of quality characteristics for the i-th sub-segment; where m i Let be the total mass of the i-th sub-segment, where i = 1, 2, 3, ... N.

6. The quality characteristic mapping method according to claim 1, characterized in that, In S3, the constraints are the center of mass and moment of inertia of the i-th sub-segment, including: |J x_mi -I x_mi | / J x_mi ≤5% |J y_mi -I y_mi | / J y_mi ≤5% |J z_mi -I z_mi | / J z_mi ≤5% |X c_mi -X' c_mi | / X c_mi ≤5% |And c_mi -AND' c_mi | / And c_mi ≤5% Where the centroid of the i-th sub-segment is X c_mi Y c_mi , Z c_mi The moment of inertia of the i-th sub-segment is J. x_mi J y_mi J z_mi J' x_mi J' y_mi 、J' z_mi Let X' be the moment of inertia of the i-th sub-segment after redistribution. c_mi Y' c_mi Z' c_mi Let be the centroid of the i-th sub-segment after redistribution.

7. The quality characteristic mapping method according to claim 1, characterized in that: In S4, if the following conditions are met The quality characteristic mapping method oriented towards the main structure is considered effective; among which... m i Let be the total mass of the i-th sub-segment, where i = 1, 2, 3, ... N.

8. A computer-readable storage medium having a computer program / instructions stored thereon, characterized in that, When the computer program / instructions are executed by the processor, they implement the steps of the method described in any one of claims 1-7.

9. A computer program product comprising a computer program / instructions, characterized in that, When the computer program / instructions are executed by the processor, they implement the steps of the method described in any one of claims 1-7.

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