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Fatigue design method for test-oriented helicopter rotor metal part

A helicopter rotor and design method technology, applied in computer-aided design, design optimization/simulation, calculation, etc., can solve problems such as test cost and development cycle waste, failure mode life asynchrony, and acceleration difference, and avoid premature failure. , The effect of saving development cycle and test cost

Active Publication Date: 2021-01-05
CHINA HELICOPTER RES & DEV INST
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AI Technical Summary

Problems solved by technology

Helicopter rotor system components basically adopt fatigue characteristic test to assess the structural life, but the fatigue characteristic test has the problem that the life of each failure mode is not synchronized and the acceleration varies greatly, which leads to the failure of the structural fatigue test
Such test results do not match the expected failure mode, resulting in waste of test costs and development cycles

Method used

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  • Fatigue design method for test-oriented helicopter rotor metal part
  • Fatigue design method for test-oriented helicopter rotor metal part
  • Fatigue design method for test-oriented helicopter rotor metal part

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Embodiment Construction

[0034] see figure 1 , the present invention proposes a kind of test-oriented helicopter rotor metal parts fatigue design method, realizes metal parts fatigue life evaluation and structural design, and this method comprises the following steps:

[0035] Step 1, fatigue test load analysis under different metal parts materials and erosion states

[0036] Based on the cumulative damage theory, the fatigue performance characterization model of helicopter rotor components is established:

[0037]

[0038] In the formula, C and m are the slope and intercept parameters of the metal fatigue curve, which are determined according to the test data; T a,i (i=1,2,...,p) is a set of dynamic loads of the characteristic load T in each flight state; n i (i=1,2,...,p) is the frequency of each flight state per hour; L is the high-cycle fatigue life of the helicopter structure; T ∞ is the high cycle fatigue limit of the characteristic load T corresponding to the life L. Equation (1) establi...

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Abstract

The invention discloses a fatigue design method for a test-oriented helicopter rotor metal part. The method comprises the following steps: determining a proofing fatigue limit corresponding to a target life test, calculating the maximum loading load of a rotor metal part for carrying out a fatigue test under different materials and abrasion corrosion modes, and analyzing the same under the test load; according to the test proofing fatigue limit of each material of the rotor moving part in the back calculation fatigue test under the rubbing corrosion mode state, carrying out static load correction by considering the stress ratio effect, calculating equivalent dynamic load of each characteristic load proofing, and evaluating the fatigue life of the structure; determining the optimized size of the dangerous part of the rotor moving part and guiding the design to meet the fatigue test assessment target requirement. According to the method, whether the strength, rigidity and boundary constraints of the test piece and the matching piece under the characteristic test acceleration load can meet the requirements or not is pre-judged in advance, and early failure caused by unreasonable design of a test scheme is prevented.

Description

technical field [0001] The invention belongs to the field of helicopter rotor strength design, and relates to a test-oriented method for evaluating the fatigue life of metal parts of a helicopter rotor and designing a structural key dimension. Background technique [0002] The strength design of the traditional rotor system is based on the premise that the various failure modes meet the service life, and the dimension definition is carried out by taking the strength margin according to the engineering experience. Helicopter rotor system components basically adopt fatigue characteristic test to assess the structural life, but there are problems in the fatigue characteristic test that the life of each failure mode is not synchronized and the acceleration varies greatly, which leads to the failure of the structural fatigue test. Such test results do not match the expected failure mode, resulting in waste of test costs and development cycles. Contents of the invention [0003...

Claims

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Application Information

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IPC IPC(8): G06F30/20G06F30/15G06F119/04G06F119/14
CPCG06F30/20G06F30/15G06F2119/04G06F2119/14Y02T90/00
Inventor 熊欣刘牧东赵凤帅喻溅鉴崔韦
Owner CHINA HELICOPTER RES & DEV INST
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