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An aircraft load calculation method based on a discretized load model

A technology of aircraft load and calculation method, applied in calculation, special data processing applications, instruments, etc., can solve problems such as load calculation result error, internal force imbalance and inconsistency of the whole aircraft, reduce calculation error, ensure internal force, and facilitate implementation Effect

Pending Publication Date: 2019-06-21
中航通飞华南飞机工业有限公司
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Problems solved by technology

In the above method, since the aerodynamic data and aerodynamic pressure distribution data are usually obtained through different experiments or theoretical calculation methods, there is a problem of inconsistency between the two, and the nodes corresponding to the aerodynamic pressure distribution data and the nodes corresponding to the mass distribution data are often Inconsistency, combined will lead to errors in load calculation results, and the phenomenon of internal force imbalance of the whole machine will appear

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  • An aircraft load calculation method based on a discretized load model
  • An aircraft load calculation method based on a discretized load model
  • An aircraft load calculation method based on a discretized load model

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Embodiment Construction

[0021] The present invention will be described in further detail below.

[0022] An aircraft load calculation method based on a discretized load model of the present invention discretizes the aircraft structure, establishes a discretized load model, and establishes a mapping relationship between aircraft load calculation input data and the load model to form an aircraft load calculation database, Carry out aircraft load calculation based on the load calculation database, and convert the load calculation structure into the node load of the aircraft strength finite element model, so that the aircraft load results can be obtained quickly and accurately. The specific steps are as follows:

[0023] (1) Discretize the aircraft structure according to the geometric shape and structural layout characteristics of the aircraft, establish a set of discrete nodes, and form a load model that can describe the aircraft and its components;

[0024] (2) Map the aircraft aerodynamic distribution...

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Abstract

The invention belongs to the technical field of aircraft load calculation, and relates to an aircraft load calculation method based on a discrete load model. The method comprises the following steps:firstly, discretizing an aircraft structure to form an aircraft discretized load model; Establishing a pneumatic and mass database based on a load model; calculating the load; Screening the severely loaded condition; and converting finite element node loads for structural strength design analysis. According to the aircraft load calculation method based on the discretized load model, a coordinatedand consistent load result is obtained, calculation errors are reduced, screening of serious load conditions and conversion of finite element node loads are facilitated, implementation is convenient,and the applicability is wide.

Description

technical field [0001] The invention belongs to the field of aircraft load calculation, and relates to an aircraft load calculation method based on a discrete load model. Background technique [0002] From taxiing, take-off, climbing, cruising, to sliding, landing or water landing, the aircraft is under load all the time. Aircraft designers must calculate these loading conditions to find out the maximum load occurrence of each component of the aircraft and the magnitude and distribution of the load, and use this as the basis for design and analysis of the structural strength of the aircraft. General aircraft load calculations mostly use mathematical modeling based on the requirements of applicable design specifications for the aircraft, use aerodynamic force and weight data as input to solve the total load of the aircraft, and use the aerodynamic pressure distribution and mass distribution database to calculate the total load of the aircraft. The component distributed load ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 周立胜温庆
Owner 中航通飞华南飞机工业有限公司
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