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Method for load calculation of high lift system of aircraft

A technology of load calculation and lift, applied in calculation, special data processing applications, instruments, etc., can solve problems such as inability to meet design requirements and low efficiency

Active Publication Date: 2015-09-23
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

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  • Method for load calculation of high lift system of aircraft
  • Method for load calculation of high lift system of aircraft
  • Method for load calculation of high lift system of aircraft

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Embodiment

[0067] Design load calculation of an aircraft high-lift system.

[0068] 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.

[0069] After in-depth research, this patent provides a high-lift system load calculation method based on variational method and quadratic programming. The calculation speed is fast, and the complicated and lengthy process required by finite elemen...

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Abstract

The invention relates to the field of design of aviation systems, in particular to a method for load calculation of a high lift system of an aircraft, to solve the problem of incapability of meeting the design requirements due to the low efficiency of the existing computing method. A high lift device in the high lift system is connected to a plurality of connecting points of a suspension mechanism; the suspension mechanism is in point contact with a plurality of movement mechanisms in the high lift system; according to the stress and constraint condition of each link on a force transfer path, the force transfer path can be decomposed into two sub-systems, namely high lift device-suspension mechanism and suspension mechanism-movement mechanisms, which are organically related, and then the force transfer computing problem of a complex system is solved step by step based on the design philosophy and the mechanical characteristics of each sub-system. The method has the advantages of quick computing speed and accurate and reliable computing result, and is capable of completely avoiding a complicated and tedious process needed 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 Applications(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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