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A load calculation method for aircraft high-lift system

A load calculation and lift technology, applied in calculation, special data processing applications, instruments, etc., can solve problems such as failure to meet design requirements and low efficiency, and achieve accurate and reliable calculation results, avoid complex and lengthy calculations, and fast calculation speed Effect

Active Publication Date: 2018-04-13
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0003] The purpose of the present invention is to provide a method for calculating the load of an aircraft high-lift system, to solve the problem that the existing calculation method has low efficiency and cannot meet the design requirements

Method used

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  • A load calculation method for aircraft high-lift system
  • A load calculation method for aircraft high-lift system
  • A load calculation method for aircraft high-lift system

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Embodiment

[0068] Design load calculation of an aircraft high-lift system.

[0069] When the commercial finite element software MSC / nastran is used to calculate the design load of the Dayun aircraft high-lift system, there are problems such as slow calculation speed and strange results, which cannot meet the design requirements. These problems are caused by the defects of the nonlinear module of nastran software. Other nonlinear commercial finite element software can be completed through finite element modeling, load distribution, nonlinear analysis and other processes. These processes are too complicated and lengthy for aircraft design with multiple loads, complex system configurations, multiple slots, and multiple rudder surface structures.

[0070] After in-depth research, this patent provides a high-lift system load calculation method based on the variational method and quadratic programming. The calculation speed is fast, and the complex and lengthy process required by the finite el...

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Abstract

The invention relates to the field of aviation system design, in particular to a method for calculating the load of an aircraft high-lift system to solve the problem that the existing calculation method has low efficiency and cannot meet design requirements. The lifting device in the high-lift system is connected to the suspension mechanism at multiple connection points, and the suspension mechanism is in contact with multiple moving mechanisms in the high-lift system. According to the force and constraints of each link on the force transmission route, the force transmission route can be It is decomposed into organically linked booster-suspension mechanism, suspension mechanism-kinematic mechanism subsystems, and then based on the design concept and mechanical characteristics of each subsystem, it solves the force transmission calculation problem of the complex system step by step, with fast calculation speed and accurate and reliable calculation results , can completely avoid the complex and lengthy process required by finite element software.

Description

technical field [0001] The invention relates to the field of aviation system design, in particular to a load calculation method for an aircraft high-lift system. Background technique [0002] In the prior art, the commercial finite element software NASTRAN or MARC is used to calculate the load of the aircraft high-lift system. However, for the high-lift system with many and complex design loads, the calculation efficiency of the previous method is low, and even the load of the high-lift system cannot be completed. Computing work restricts the design of aircraft systems in our country. Contents of the invention [0003] The purpose of the present invention is to provide a method for calculating the load of an aircraft high-lift system to solve the problem that the existing calculation method has low efficiency and cannot meet the design requirements. [0004] Technical scheme of the present invention is: [0005] A method for calculating the load of an aircraft high-lift ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 左朋杰张建刚
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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