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A method for determining an equivalent damage model

A technology of equivalent damage and determination method, which is applied in the field of aviation fatigue, can solve the problems of poor applicability and poor damage model accuracy, and achieve the effect of facilitating automatic calculation

Active Publication Date: 2019-04-26
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to provide a method for determining the equivalent damage model based on the full-scale fatigue test load spectrum, so as to solve the technical problems of poor accuracy and poor applicability of the damage model in the process of determining the equivalent damage in the life monitoring of a single machine

Method used

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  • A method for determining an equivalent damage model
  • A method for determining an equivalent damage model
  • A method for determining an equivalent damage model

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Embodiment Construction

[0044] Below in conjunction with accompanying drawing and embodiment the present invention will be further described:

[0045] Such as figure 1 Shown is the flowchart for determining the equivalent damage model. Parameters used in the examples are given.

[0046] Such as figure 2 Shown is a schematic diagram of the relationship between damage-equivalent pulsating overload and damage index. Parameters used in the examples are given.

[0047] Such as image 3 shown, for N fh Schematic diagram of the relationship with the damage index m considering multiple key parts. Parameters used in the examples are given.

[0048] The specific steps of the method for comprehensively determining the equivalent damage model in the stand-alone life monitoring proposed by the present invention are as follows:

[0049] Step 1. Taking the load spectrum of the whole aircraft fatigue test when the service life is known for fatigue life determination as the reference spectrum, the data of a ...

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Abstract

The invention belongs to the field of aviation structure single machine service life monitoring, and particularly relates to a method for determining an equivalent damage model. According to the method, the structural characteristics of fatigue key parts of a certain type of aircrafts are combined; the characteristics of the used material and the load / environmental spectrum condition endured by the material are improved; The method comprises the following steps: taking a full-aircraft fatigue test load spectrum as a reference, based on a relative linear damage accumulation theory, on the basisof analyzing and comparing a plurality of equivalent damage calculation methods, researching and determining an equivalent damage model suitable for monitoring the service life of a single aircraft of the type, and proposing an equivalent damage model based on a Gerber formula; According to the method provided by the invention, on the basis that the reference spectrum damage reality is met, the result obtained by each equivalent damage calculation method and the reference spectrum error are minimum, and the method can be widely applied to the comprehensive determination of the equivalent damage model in the life monitoring of various aircraft single machines.

Description

technical field [0001] The invention belongs to the field of aviation fatigue, and in particular relates to a method for determining an equivalent damage model. Background technique [0002] Domestic aircraft life is basically based on "fleet life management", that is, all aircraft are controlled and used according to predetermined life indicators. The work of "stand-alone life management" has just started, but the current method is relatively single, and the monitoring software means are relatively backward. The existing means can no longer meet the needs of the current aircraft structure health monitoring technology. In the life monitoring work of a single machine, the most important thing is to determine the equivalent damage model. The determination of the damage model must be comprehensively determined in combination with the actual structural form, material, and use of the aircraft, so that a more accurate life consumption can be given, and reliable data support can b...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F2119/06G06F30/20Y02T90/00
Inventor 张彦军闵强陈全礼纪露明
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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