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Rationality determination method for structural parameter matching of integral reinforced wallboard of aircraft

A technology of reinforced wall panels and structural parameters, applied in the direction of electrical digital data processing, special data processing applications, instruments, etc., to achieve the effects of correct theoretical analysis methods, clear engineering concepts, and clear implementation steps

Active Publication Date: 2021-04-23
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

At present, the overall stiffened panel of the newly developed aircraft is designed with reference to the existing aircraft models. However, after the structural parameters of the overall Whether the structural parameters of the reinforced wall plate meet the design requirements of the new structural model has always been a difficult problem

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  • Rationality determination method for structural parameter matching of integral reinforced wallboard of aircraft
  • Rationality determination method for structural parameter matching of integral reinforced wallboard of aircraft

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specific Embodiment

[0055] The implementation of the method for determining the rationality of the parameter matching of the overall stiffened panel structure of the aircraft provided by the embodiment of the present invention will be further described in detail below through a specific example.

[0056] This specific embodiment provides a method for determining the rationality of structural parameter matching of an overall stiffened panel of an aircraft, and its implementation is as follows:

[0057] It is known that the overall stiffened panel structure of the aircraft includes 7 ribs (such as figure 2 rod unit in the longitudinal direction), 6 wall panels (such as figure 2 rod unit in the middle and transverse direction), the rib and the wall plate are integrated as a whole. In the finite element model, the wall plate and rib are simplified as plate unit and bar unit respectively. Disconnect the 2nd rod unit at the same time, disconnect the 1st and 2nd plate units. Here, Z=7.

[0058] Th...

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Abstract

The invention discloses a rationality determination method for structural parameter matching of an integral reinforced wallboard of an aircraft. The rationality determination method comprises the following steps: establishing a full-aircraft static strength finite element model; selecting an assessment section of the integral reinforced wallboard structure of the airplane, and determining a rod unit and a board unit on the assessment section; calculating the residual structure stress level after the structure between the two adjacent wall plates is completely invalid, calculating the residual structure stress level after the structure of the first rod unit or the last rod unit is completely invalid, and judging whether all the residual structure stress levels meet the static strength limit load requirement or not; and determining that the structural parameter matching of the integral stiffened wall plate of the airplane is reasonable. From the technical perspective of judging whether the residual structure after the adjacent wall plates are disconnected meets the static strength limit load requirement or not, the rationality evaluation method for the structural parameter matching of the airplane integral reinforced wall plate is provided, and the blank of rationality evaluation and judgment of parameter matching in the design process of the structural parameters of the existing airplane integral reinforced wall plate is filled up.

Description

technical field [0001] The invention relates to but not limited to the field of aeronautical structure design, in particular to a method for determining the rationality of structural parameter matching of an overall stiffened panel of an aircraft. Background technique [0002] Aircraft integrally stiffened panels are very common in aircraft wings and fuselages, and serve as the main load-bearing structure of aircraft wings and fuselages. [0003] The rationality of the structural parameter design of the overall stiffened panel of the aircraft can improve the fatigue resistance of the aircraft wing and fuselage structure. At present, the overall stiffened panel of the newly developed aircraft is designed with reference to the existing aircraft models. However, after the structural parameters of the overall Whether the structural parameters of the reinforced wall plate meet the design requirements of the new structural model has always been a difficult problem. Contents of ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/23G06F119/14
CPCG06F30/15G06F30/23G06F2119/14Y02T90/00
Inventor 翟新康田小幸
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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