Modularized mass distribution design method based on basic configuration items

Abstract

The invention belongs to the field of aircraft overall design, weight design and load strength design, and relates to a modular mass distribution design method based on basic configuration items. By introducing the concept of a basic configuration item mass distribution unit, tedious and time-consuming mass distribution calculation is converted into calculation operations (selection, correction, partitioning and merging) on the mass distribution unit, so that a mass distribution result of a calculation object can be flexibly, quickly, efficiently and accurately obtained, design requirements of other professions are responded in time, and the calculation efficiency is improved. The increasingly rapid aircraft development rhythm is met, and the aircraft development process is promoted.

Description

Technical Field

[0001] This invention belongs to the fields of aircraft overall design, weight design and load strength design, and relates to a modular mass distribution design method based on basic configuration items. Background Technology

[0002] In aircraft development, mass distribution is applied across multiple disciplines, involving frequent and massive calculations and a large number of components. Computer-aided computing (CAD) technology has significantly improved the efficiency and accuracy of mass distribution calculations. Building upon CAD calculations and considering the characteristics of aircraft configuration management (especially the fundamental configuration item, a crucial link in aircraft configuration management, playing a pivotal role; single-aircraft configurations are typically expressed through fundamental configuration items), a modular mass distribution design method based on fundamental configuration items has been invented. With the aid of automated programs, mass distribution units can be flexibly combined to calculate the mass distribution of any sortie or target aircraft, greatly reducing calculation time, improving computational efficiency, and minimizing manpower, thus adapting to the rapid development of modern aircraft. Summary of the Invention

[0003] Purpose of the invention: The invention provides a modular mass distribution design method based on basic configuration terms, which solves the difficulties of cumbersome, time-consuming and labor-intensive calculation of aircraft mass distribution, making it difficult to adapt to the rapid development pace.

[0004] The technical solution of this invention is as follows: a modular mass distribution design method based on basic configuration items. By building a basic configuration item mass distribution unit (MDU) library, and extracting mass distribution units from the mass distribution unit library according to the flight configuration determined by the configuration file, the mass distribution of the corresponding flight or calculation object can be obtained after correction, allocation, and merging.

[0005] The method includes the following steps: First, create a library of basic configuration item mass distribution units.

[0006] Second, the combination of quality distribution units. Quality distribution units of the computational object are selected from the quality distribution unit library in the previous step and combined to form a set of quality distribution units for the computational object.

[0007] Third, the mass distribution unit is corrected. The mass distribution unit determined in the previous step is corrected according to the actual weight.

[0008] Fourth, the allocation of mass distribution units. The mass distribution units corrected in the previous step are allocated to the corresponding components (such as fuselage, wings, horizontal stabilizer, vertical stabilizer, etc.).

[0009] Fifth, the combined calculation of component mass distribution units. All mass distribution units in each component are combined and calculated.

[0010] Sixth, the overall machine mass distribution is generated. The mass distributions of all merged components are integrated to form the overall machine mass distribution.

[0011] Further, step 1 specifically involves creating a mass distribution unit library for basic configuration terms. Mass distribution calculations are performed on each basic configuration term; the calculation results are the mass distribution units. These mass distribution units are then aggregated to form the basic configuration term mass distribution unit library, as shown in the appendix. Figure 2 .

[0012] Further, step 2 specifically involves the combination of mass distribution units. Based on the configuration of the sortie or the object being calculated (generally defined in the configuration list or configuration specification document), corresponding mass distribution units are selected from the aforementioned mass distribution unit library and combined to form a set of mass distribution units for the sortie or the object being calculated. See appendix. Figure 3 .

[0013] Furthermore, step 3 specifically involves the correction of the mass distribution unit. Based on the actual weight of the basic configuration item of the sortie, according to the weight ratio ( k = Actual weight / MDU weight) and the following correction formula: .…………………………………………..………………(1) …………………………………………………………(2) .………………………..…………………………………………(3) .………………………………………….......…………………(4) ………………………………………………………(5) .…….………………………………………………(6) .………..………………………………………………(7) .…….………...……………………………………(8) .…….………………………………………………(9) .…….....……..………………………………………(10) In the above formula, , , , , , , , , , —The center of gravity and moment of inertia of the i-th grid in the mass distribution cell before correction; , , , , , , , , , —The center of gravity and moment of inertia of the i-th grid in the corrected mass distribution element. Each of the selected mass distribution units above is corrected to obtain all corrected mass distribution units for each flight, as shown in the appendix. Figure 4 .

[0014] Further, step 4 specifically involves the allocation of mass distribution units. Following certain rules, such as based on the number of subdivided grids and the location of the mass distribution units, the corrected mass distribution units are allocated to their respective component areas, forming a set of mass distribution units for each component. (See appendix) Figure 5 .

[0015] Furthermore, step 5 specifically involves the merging calculation of the component's mass distribution elements. Assuming the mass characteristics of a specific mesh of the component are being merged, the merging formula is as follows: ...............……………………………………………(11) …….............……………………………………(12) ……...............……………………………………(13) ……………………………………………………(14) .………………………………(15) .…..…………………………(16) .………………………………(17) ...……………………………………(18) ………………………………………(19) .……………………………………(20) In the above formula, , , , , , , , , , —The weight, center of gravity, and moment of inertia of a specific grid cell within the mass distribution unit to which the component belongs; W , X , Y , Z , , , , , , —Weight, center of gravity, and moment of inertia of a specific grid in the merged component The mass distribution units of each of the above components are merged and calculated to form the mass distribution of each component, as shown in the appendix. Figure 6 .

[0016] Furthermore, step 6 specifically involves generating the overall aircraft mass distribution. The mass distribution results of all components are integrated to form the overall aircraft (flight) mass distribution.

[0017] Technical effects: By introducing the concept of "basic configuration item mass distribution unit," the tedious and time-consuming mass distribution calculation is transformed into calculation operations on mass distribution units (selection, modification, partitioning, and merging). This allows for flexible, rapid, efficient, and accurate acquisition of the mass distribution results of the calculated object, enabling timely responses to the design needs of other disciplines, meeting the increasingly rapid pace of aircraft development, and accelerating the aircraft development process. The specific effects are mainly reflected in: 1) Flexible and diverse calculation objects. Calculation objects can be flexibly combined according to configuration; objects can be components, parts, or the entire aircraft. 2) Strong development adaptability. As aircraft development progresses and configurations are continuously adjusted, the mass unit library can be expanded in a timely manner to prepare data for new calculation objects, adapting to new stages of aircraft development. 3) Significantly improved calculation efficiency. Using the created mass distribution unit library, the mass distribution calculation results of the calculated object can be obtained quickly and efficiently through combination, modification, partitioning, merging operations, and calculation. 4) Convenient calculation checking and improved result accuracy. The entire calculation process is verifiable, data is traceable, and the checking of calculation results and the investigation of problems are convenient and clear, greatly improving the accuracy of the calculation results. 5) Reduced calculation costs. Compared to existing calculation methods, this method requires significantly less manpower and resources, thus reducing the overall calculation cost. 6) It can be automated. Automated programs can be developed at each stage of the calculation to improve operational capabilities. 7) Expanded applications in technical fields. This method can be applied to aircraft overall design and weight design, and can also be extended to load design, strength design, and other related fields. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the entire process of the present invention.

[0019] Figure 2 This is a schematic diagram illustrating the creation of a mass distribution unit library based on basic configuration terms according to the present invention.

[0020] Figure 3 This is a schematic diagram of the mass distribution unit combination of the flights in this invention.

[0021] Figure 4 This is a schematic diagram of the weight correction of the mass distribution unit in this invention.

[0022] Figure 5 This is a schematic diagram of the mass distribution unit being allocated to the components in this invention.

[0023] Figure 6 This is a schematic diagram showing the combined mass distribution of the components in this invention. Detailed Implementation

[0024] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific design details are set forth in the following detailed description to provide a more complete understanding of the invention. However, it will be apparent to those skilled in the art that the invention can be practiced without some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setup and method set forth below, but covers any improvements, substitutions, and modifications to the structures, methods, and devices without departing from the spirit of the invention. In the drawings and the following description, any parts not exhaustively described are considered to be common knowledge or conventional practices in the art.

[0025] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0026] Example 1: The following is combined Figure 1 The specific implementation of the present invention (a modular mass distribution design method based on basic configuration terms) is further illustrated below.

[0027] First, the mass distribution of each basic configuration item is calculated, and the calculation results form a mass distribution unit library, which contains all basic configuration item units for all flights.

[0028] Second, based on the configuration list of the computational object, corresponding mass distribution units are selected from the aforementioned mass distribution unit library and combined to form a mass distribution unit set for the computational object. For example, if a computational object has 50 basic configuration items according to the configuration list, then the corresponding 50 basic configuration item mass distribution units are selected from the mass distribution unit library to form a mass distribution unit set for that computational object.

[0029] Third, based on the actual weight of the basic configuration item (data from the weight database) and the weight of the mass distribution unit (MDU), the weight correction factor is obtained. k ( k =Actual weight / MDU weight), adjusted by a factor k The mass distribution unit is corrected using the correction formula described in step 3 above. For example, if the weight of a mass distribution unit is 2 kg, but its actual weight is 10 kg, then the correction factor is... k =5, the weight W of the i-th item in the mass distribution unit. i Moment of inertia (I) X(i) I Y(i) I Z(i) I XY(i) IYZ(i) I XZ(i) All need to be magnified to 5 times, center of gravity (X) i Y i Z i )constant.

[0030] Fourth, according to certain rules, such as the number of grid cells and the position of the mass distribution units, the corrected mass distribution units are assigned to their respective component areas, forming a set of mass distribution units for each component. For example 1: The fuselage has 7 grid cells, the wing has 12, the horizontal stabilizer has 8, and the vertical stabilizer has 5. Therefore, the corresponding component can be determined based on the number of grid cells in the mass distribution unit. For example 2: The fuselage and horizontal stabilizer both have 7 grid cells, but their vertical Z-axis data are not in the same range. Therefore, by combining the number of grid cells and the vertical Z-axis data, the corresponding component to which the mass distribution unit belongs can be determined.

[0031] Fifth, all mass distribution units in each component are combined and calculated according to the formula in step 5 above to obtain the mass distribution results of each component. For example, if there are 20 mass distribution units in the fuselage component and the fuselage grid number is 7, then these 20 mass distribution units are combined and calculated to obtain the mass characteristics of the 7 grids of the fuselage component, that is, the mass distribution results of the fuselage.

[0032] Sixth, summarize the mass distribution results of each component to form the mass distribution of the entire aircraft. For example, if the calculation object includes the fuselage, wings, horizontal stabilizer, and vertical stabilizer, then the merged results of these four components are sorted into a sequential list and summarized into the mass distribution file of the entire aircraft, forming a complete mass distribution file for the calculation object.

[0033] The above description is only a preferred embodiment of the present invention. It should be noted that those skilled in the art can make several improvements without departing from the principle of the present invention, and these improvements should also be considered within the scope of protection of the present invention.

Claims

1. A modular mass distribution design method based on basic configuration terms, characterized in that, By building a basic configuration item mass distribution unit library, and extracting the mass distribution units from the mass distribution unit library according to the flight configuration determined by the configuration file, the mass distribution of the corresponding flight or calculation object can be obtained after correction, allocation and merging.

2. The method as described in claim 1, characterized in that, The method includes the following steps: First, create a library of basic configuration item mass distribution units; Second, the combination of quality distribution units; select the quality distribution units of the computational object from the quality distribution unit library in the previous step, and combine them to form a set of quality distribution units of the computational object; Third, the mass distribution unit is corrected; the mass distribution unit determined in the previous step is corrected according to the actual weight. Fourth, the allocation of mass distribution units; the corrected mass distribution units from the previous step are allocated to the corresponding components; Fifth, the combined calculation of component mass distribution units; the combined calculation of all mass distribution units in each component; Sixth, the overall machine mass distribution is generated; the mass distributions of all merged components are integrated to form the overall machine mass distribution.

3. The method as described in claim 2, characterized in that, Step 1 specifically involves creating a mass distribution unit library for basic configuration items; calculating the mass distribution for each basic configuration item, with the calculation result being the mass distribution unit; and combining each mass distribution unit to form the mass distribution unit library for basic configuration items.

4. The method as described in claim 2, characterized in that, Step 2 specifically involves the combination of quality distribution units; based on the configuration of the flight or the object being calculated, the corresponding quality distribution units are selected from the aforementioned quality distribution unit library and combined to form a set of quality distribution units for the flight or the object being calculated.

5. The method as described in claim 2, characterized in that, Step 3 specifically involves the correction of the mass distribution unit; based on the actual weight of the basic configuration item of the sortie, and according to the weight ratio and the following correction formula: .…………………………………………..………………(1) .…………………………………………………...……………(2) .………………………..……………………......………………(3) .………………………………………….......…………………(4) ………………………………………………………(5) .…….…………………………………………………(6) .………..………………………………………………(7) .…….………...………………………………………(8) .…….…………………………………………………(9) .…….....……..………………………………………(10) In the above formula, , , , , , , , , , —The center of gravity and moment of inertia of the i-th grid in the mass distribution cell before correction; , , , , , , , , , —The center of gravity and moment of inertia of the i-th grid in the corrected mass distribution element. Each of the selected quality distribution units is modified to obtain all the modified quality distribution units for each flight.

6. The method as described in claim 2, characterized in that, Step 4 specifically involves the allocation of mass distribution units. According to the rules, based on the number of grid segments and the location of the mass distribution units, the corrected mass distribution units are allocated to their respective component areas, forming a set of mass distribution units for each component.

7. The method as described in claim 2, characterized in that, Step 5 specifically involves the merging calculation of the component mass distribution elements; assuming the mass characteristics of a certain mesh of the component are being merged, the merging formula is as follows: ...............……………………………………………(11) …….............……………………………………(12) ……...............……………………………………(13) …………............………………………………(14) .………………………………(15) .…..…………………………(16) .………………………………(17) ...……………………………………(18) ………………………………………(19) .……………………………………(20) In the above formula, , , , , , , , , , —The weight, center of gravity, and moment of inertia of a specific grid cell within the mass distribution unit to which the component belongs; W , X , Y , Z , , , , , , —Weight, center of gravity, and moment of inertia of a specific grid in the merged component The mass distribution units of each component are merged and calculated to form the mass distribution of each component.

8. The method as described in claim 2, characterized in that, Step 6 specifically involves generating the overall machine mass distribution and integrating the mass distribution results of all components to form the overall machine mass distribution.

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