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

Abstract

The invention discloses a quality characteristic mapping method, a computer readable storage medium and a program product, and relates to the field of overall design of aircrafts. Respectively mapping the structure mass mi of the ith sub-section cabin section and the accessory equipment mass mi of the ith sub-section cabin section to a shell unit grid model which has the same diameter D and length li as the ith sub-section and has the total number n of grids, and recording the mass of each unit in the initial mass characteristic set of the ith sub-section as mij0; the initial increment of the mij0 is deltamij0, an initial set of the deltamij0 is represented by a function # imgabs0 #, an intelligent optimization algorithm is adopted, the minimum value of a function f (m (i, j)) is used as a target, the mass center and the rotational inertia of the ith sub-segment are used as constraint conditions, the initial set of the increment deltamij0 is optimized, an optimized increment set # imgabs1 # of the initial increment set is obtained, the steps are repeated, and the optimal increment set # imgabs1 # is obtained. The mass distribution is carried out on the N sub-segments of the cylindrical cabin segment, the efficiency of obtaining the optimization increment set # imgabs2 # of the N sub-segments is high, and the mechanical calculation iteration requirement of the aircraft main structure is met.

Description

Technical Field

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

[0002] The mass characteristics of an aircraft are important parameters that need to be considered in the overall design of the aircraft. In the mechanical calculations involving the aircraft, the aircraft is generally simplified into a discrete model of elastic-mass parts (beams, rods, shells, etc.). For aircraft with non-axisymmetric mass distribution, the above simplification method will lead to an inertia imbalance of the aircraft. In this case, a detailed three-dimensional model of the aircraft is usually required, and the coordinate position and mass characteristics of the equipment in the cabin need to be accurately described to form a three-dimensional model diagram of the detailed design. Although this processing method can ensure the consistency of mass characteristics, the modeling efficiency is low and cannot meet the rapid iteration requirements for the mechanical calculation of the main structure of the aircraft in the scheme stage.

[0003] At present, the finite element method is mainly used to perform three-dimensional discretization of aircraft. The main structure, components and parts are modeled and assembled according to the size requirements of the three-dimensional model. Generally, the impact of the assembly parts on the mass distribution of the aircraft cannot be ignored. For the equipment in the cabin, a detailed model of the center of mass position and connection method of the equipment in the cabin should be established as much as possible. For the support structure with non-negligible mass, a detailed three-dimensional structural model needs to be established. However, the above method requires statistics on the size, mass, installation method and other information of the aircraft's various levels of structure and single-machine equipment. The modeling workload is huge, and the overall or local stiffness of the aircraft is often discontinuous due to the omission of the connection unit operation, which needs to be further corrected 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 the aircraft and realizing rapid modeling of the equivalent mass characteristics of the 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 existing technology and provide a mapping method for the mass characteristics of the main structure of the aircraft, which can effectively avoid the low efficiency of the traditional three-dimensional modeling method, meet the requirements of rapid iteration of the mechanical calculation of the main structure of the aircraft, and support the overall scheme demonstration of the aircraft.

[0006] The technical solutions provided by this application are as follows:

[0007] A mass characteristic mapping method for a primary structure of an aircraft, comprising:

[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 a length of L, a diameter of D, and a total mass of M is divided into N sub-segments along the X-axis;

[0009] S2: The structural mass m of the i-th sub-segment compartment i_s and the mass of the auxiliary equipment of the i-th sub-section compartment m i_a They are mapped to the diameter D and length l of the i-th sub-segment respectively. i On the same shell element mesh model with a total mesh number of n, the mass of each element in the initial mass property set of the i-th sub-segment is denoted by 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, each unit mass m ij_0 The initial increment is Δm ij_0 , increment Δm ij_0 The initial set of functions Characterization, i = 1, 2, 3...N, using intelligent optimization algorithm, with the minimum value of function f(m(i, j)) as the goal, and the center of mass and moment of inertia of the i-th sub-segment as constraints, for the increment Δm ij_0 The initial set is optimized to obtain the optimized incremental set of the initial incremental set

[0011] S4: Repeat step S3 to distribute the mass of the N sub-segments of the cylindrical compartment to obtain the optimized incremental set of N sub-segments according to Mass is assigned to each cell of each subsegment.

[0012] The length of each sub-segment is l i ,i=1,2,3,...N,satisfying The auxiliary equipment with quality attributes in the i-th sub-section and its connection location are included in the i-th sub-section and meet Where m i is the total mass of the i-th sub-section compartment, i=1,2,3,...N.

[0013] Each of the subsections includes the bulkhead structure mass m of the tank section. i_s and the mass of the auxiliary equipment of the compartment m i_a , m i =m i_s +m i_a .

[0014] The structure of the shell unit grid model is the same as the bulkhead structure of the cabin section.

[0015] In S2, the structural mass m of the i-th sub-segment compartment is i_s and the mass of the auxiliary equipment of the i-th sub-section compartment m i_a They are mapped to the diameter D and length l of the i-th sub-segment respectively. i On the same shell unit grid model with a total grid number of n, including: the cabin structure mass assigned to each shell unit grid is m i_s / n, projection is performed according to the shortest distance between the auxiliary equipment and the cabin wall, and the number of unit grids within the projection area is n list , the mass of the auxiliary equipment assigned to each unit grid within the projected area is m i_a / n list , the mass assigned to each unit 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, satisfy m i =m project_in +m project_out , constituting the initial set of quality characteristics of the i-th sub-segment.

[0016] In S3, the center of mass and moment of inertia of the i-th sub-segment are used as constraints, including: 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] Among them, 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 is the moment of inertia of the ith sub-segment after redistribution, X' c_mi , Y' c_mi , Z' c_mi is the centroid of the i-th subsegment after redistribution.

[0018] In S4, if The main structure-oriented quality characteristic mapping method is considered effective.

[0019] A computer-readable storage medium stores a computer program / instruction, which implements the steps of any of the above methods when executed by a processor.

[0020] A computer program product comprises a computer program / instruction, which implements the steps of any of the above methods when executed by a processor.

[0021] The main content of the present invention is to map the overall mass characteristics of the aircraft cabin section to a shell unit grid model with greater rigidity of the same size as the main structure to simulate the mass characteristic distribution of the aircraft cabin section. First, determine the reference coordinate system of the cabin section mass characteristics, and divide the cabin section into multiple sub-segments along its axis. The division principle is that the auxiliary equipment with mass attributes in the sub-segment and its connection position should be included in the same sub-segment. Secondly, count the mass, center of mass and moment of inertia of each sub-segment as a whole, and then count the mass of each sub-segment according to the cabin structure and the auxiliary equipment with mass attributes, and distribute its mass to the shell unit grid model of the same size as the main structure. By adjusting the mass distribution of the shell unit grid model, the effect consistent with the mass, center of mass and moment of inertia of the divided sub-segment is achieved, and the main structure shell unit grid mass mapping model of the sub-segment is obtained. Finally, the main structure shell unit grid mass mapping models of each sub-segment are assembled to obtain a shell unit grid mass mapping model with the same size as the original aircraft cabin section main structure.

[0022] The main content of the present invention is to map the overall mass characteristics of the aircraft cabin section to a shell unit grid model with greater rigidity of the same size as the main structure to simulate the mass characteristic distribution of the aircraft cabin section. First, determine the reference coordinate system of the cabin section mass characteristics, and divide the cabin section into multiple sub-segments along its axis. The division principle is that the auxiliary equipment with mass attributes in the sub-segment and its connection position should be included in the same sub-segment. Secondly, count the mass, center of mass and moment of inertia of each sub-segment as a whole, and then count the mass of each sub-segment according to the cabin structure and the auxiliary equipment with mass attributes, and distribute its mass to the shell unit grid model of the same size as the main structure. By adjusting the mass distribution of the shell unit grid model, the effect consistent with the mass, center of mass and moment of inertia of the divided sub-segment is achieved, and the main structure shell unit grid mass mapping model of the sub-segment is obtained. Finally, the main structure shell unit grid mass mapping models of each sub-segment are assembled to obtain a shell unit grid mass mapping model with the same size as the original aircraft cabin section main structure.

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

[0024] Ability to quickly build a primary structure mass property mapping model equivalent to a detailed 3D model of the aircraft.

[0025] Able to support the rapid iteration requirements of aircraft main structure mechanics calculations. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 Schematic diagram of initial mass distribution of cabin units.

[0027] Figure 2 Schematic diagram of optimized distribution of cabin unit mass.

[0028] Figure 3 Schematic diagram of the combination after optimization of mass distribution of each compartment. DETAILED DESCRIPTION

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

[0030] The present application embodiment discloses a method for mapping the quality characteristics of the main structure of an aircraft, such as Figure 1 As shown, a cylindrical compartment with a length of L, a diameter of D, and a total mass of M is divided into N sections. The origin of the coordinate system is located at the geometric center of the bottom surface of the compartment, the X axis points to the axial direction of the compartment, and the Y axis points to the normal direction of the compartment, satisfying the right-hand rule. The length of each sub-segment is l i(i＝1,2,3,...N) ,satisfy And the auxiliary equipment with quality attributes in the i-th sub-segment and its connection location are included in the i-th sub-segment and meet Where mi is the total mass of the i-th sub-section compartment. The structural mass of the i-th sub-section compartment is m i_s , the mass of the auxiliary equipment of the i-th sub-section compartment 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 compartment is i_s , the mass of the auxiliary equipment of the i-th sub-section compartment is m i_a They are mapped to the diameter D and length l of the i-th sub-segment respectively. i On the same shell unit grid model with a total grid number of n, the cabin structure mass assigned to each shell unit grid is m i_s / n. Projection is performed based on the closest distance between the auxiliary equipment and the cabin wall, and the number of unit grids within the projection area is n list , the mass of the auxiliary equipment allocated to each unit grid in the projection area is m i_a / n list , then the mass assigned to each unit grid within the projected area is m i_s / n+m i_a / n list , the total mass of the unit in 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, satisfy m i =m project_in +m project_out , which constitutes the initial quality characteristic set of the i-th sub-segment, denoted as m i0 ,like Figure 1 As shown. The mass of each unit of 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 mass characteristic set of the i-th sub-segment ij_0 To redistribute, the unit mass m 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 of functions Characterization, using intelligent optimization algorithm, with the minimum value of the function f(m(i,j)) as the goal, and the center of mass and moment of inertia of the i-th sub-segment as constraints, the mathematical model of the problem can be expressed as (as shown in formula 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 shown.

[0031]

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

[0033] By using the above mass allocation method to allocate the masses of the N sub-segments of the cylindrical compartment, the optimized incremental set of the N sub-segments can be obtained. like Figure 3 As shown, if it satisfies It can be considered that the main structure-oriented quality characteristic mapping method is effective.

[0034] The present invention distributes the mass of the cabin structure and the mass of the auxiliary equipment to the shell unit grid model of the same size, takes the minimum value of the optimized incremental set of each sub-segment as the goal, takes the center of mass and moment of inertia of each sub-segment as constraints, and uses an intelligent optimization algorithm to optimize the optimized incremental set to establish a mass characteristic mapping method for the main structure.

[0035] Through the above method, the overall characteristics of the aircraft cabin can be mapped to a shell unit grid model with the same size as the main structure of the cabin.

[0036] This embodiment also discloses a computer-readable storage medium, on which a computer program / instruction is stored. When the computer program / instruction is executed by a processor, the steps of any of the above methods are implemented.

[0037] This embodiment also discloses a computer program product, including a computer program / instruction, which implements the steps of any of the above methods when executed by a processor.

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

[0039] The present application is described in detail above in conjunction with specific implementation methods and exemplary examples, but these descriptions cannot be understood as limiting the present application. Those skilled in the art understand that, without departing from the spirit and scope of the present application, a variety of equivalent replacements, modifications or improvements can be made to the technical solution of the present application and its implementation methods, all of which fall within the scope of the present application. The scope of protection of the present application shall be subject to the attached 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 a length of L, a diameter of D, and a total mass of M is divided into N sub-segments along the X-axis; S2: The structural mass m of the i-th sub-segment compartment i_s and the mass of the auxiliary equipment of the i-th sub-section compartment m i_a They are mapped to the diameter D and length l of the i-th sub-segment respectively. i On the same shell element mesh model with a total mesh number of n, the mass of each element in the initial mass property set of the i-th sub-segment is denoted by 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, each unit mass m ij_0 The initial increment is Δm ij_0 , increment Δm ij_0 The initial set of functions Characterization, i = 1, 2, 3...N, using intelligent optimization algorithm, with the minimum value of function f(m(i, j)) as the goal, and the center of mass and moment of inertia of the i-th sub-segment as constraints, for the increment Δm ij_0 The initial set is optimized to obtain the optimized incremental set of the initial incremental set S4: Repeat step S3 to distribute the mass of the N sub-segments of the cylindrical compartment to obtain the optimized incremental set of N sub-segments according to Mass is assigned to each cell of each subsegment.

2. A quality characteristic mapping method according to claim 1, characterized in that: The length of each sub-segment is l i ,i=1,2,3,...N,satisfying The auxiliary equipment with quality attributes in the i-th sub-section and its connection location are included in the i-th sub-section and meet Where m i is the total mass of the i-th sub-section compartment, i=1,2,3,...N.

3. A quality characteristic mapping method according to claim 2, characterized in that: Each of the subsections includes the bulkhead structure mass m of the tank section. i_s The mass of the auxiliary equipment of the compartment m i_a , m i =m i_s +m i_a .

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

5. A quality characteristic mapping method according to claim 1, characterized in that: In S2, the structural mass m of the i-th sub-segment compartment is i_s and the mass of the auxiliary equipment of the i-th sub-section compartment m i_a They are mapped to the diameter D and length l of the i-th sub-segment respectively. i On the same shell unit grid model with a total grid number of n, including: the cabin structure mass assigned to each shell unit grid is m i_s / n, projection is performed according to the shortest distance between the auxiliary equipment and the cabin wall, and the number of unit grids within the projection area is n list , the mass of the auxiliary equipment assigned to each unit grid within the projected area is m i_a / n list , the mass assigned to each unit 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, satisfy m i =m project_in +m project_out , constituting the initial set of quality characteristics of the i-th sub-segment.

6. A quality characteristic mapping method according to claim 1, characterized in that: In S3, the center of mass and moment of inertia of the ith sub-segment are used as constraints, 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% Among them, 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 is the moment of inertia of the ith sub-segment after redistribution, X' c_mi , Y' c_mi , Z' c_mi is the centroid of the i-th subsegment after redistribution.

7. A quality characteristic mapping method according to claim 1, characterized in that: In S4, if The main structure-oriented quality characteristic mapping method is considered effective.

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

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

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