Development of a Probabilistic Linear Damage Methodology for Small Aircraft

Ocampo, Juan; Millwater, Harry; Singh, Gurkirat; Smith, Herb; Abali, Felix; Nuss, Marvin; Reyer, Michael; Shiao, Michael

doi:10.2514/1.c031463

Cited by 10 publications

(8 citation statements)

References 6 publications

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“…In the viewpoint of DT design, parts (e.g., a portion of the spar cap shown in Fig. 3) are sized such that a particular design life goal is achieved (e.g., 24,000 flight hours for a typical business jet spar cap [20][21][22]). The FCG design life is predicted by executing an analytical crack growth analysis for the given load conditions (e.g., using inputs given in Table 2).…”

Section: Design Of Lower Wing Spar Caps Using Fatigue Crack Growmentioning

confidence: 99%

“…properties (e.g., yield strength, crack growth rate) needed for designing safe and low-weight aircraft structures [1]. In general, material properties are random and can be modeled with statistical distributions [2]. For static strength design, the Federal Aviation Administration (FAA) requires the use of A-basis or B-basis material allowable to compensate for material variability and sampling uncertainty arising from limited number of coupon tests [3].…”

mentioning

confidence: 99%

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Deciding Optimal Number of Fatigue Crack Growth Tests for Damage-Tolerant Design

Bhachu

Haftka

Kim

2016

Journal of Aircraft

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Section: Design Of Lower Wing Spar Caps Using Fatigue Crack Growmentioning

confidence: 99%

mentioning

confidence: 99%

Deciding Optimal Number of Fatigue Crack Growth Tests for Damage-Tolerant Design

Bhachu

Haftka

Kim

2016

Journal of Aircraft

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“…Normal, Weibull, etc.) (Ocampo, 2011). The statistical characterisation of design parameters permits the variability to be propagated through the safe-life analysis process to produce an output probability distribution of the accumulated fatigue damage or the component safe-life.…”

Section: Introductionmentioning

confidence: 99%

A Framework to Implement Probabilistic Fatigue Design of Safe-Life Components

Hoole

Sartor

Booker

et al. 2019

ICAF 2019 – Structural Integrity in the Age of Additive Manufacturing

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Safety-critical components, such as aircraft landing gear, are designed using the 'safelife' fatigue analysis process. Variability exists within materials data, loads data and component dimensions and is currently mitigated using safety factors. Probabilistic approaches to safe-life fatigue design have been proposed to better represent this variability. However, challenges currently exist that prevent the wider utilisation of a probabilistic approach. This paper presents a framework that aims to overcome these challenges. The statistical characterisation, probabilistic, surrogate modelling and sensitivity analysis methods required to implement the framework are introduced. Finally, a discussion of how recent advances within aerospace fatigue design, such as 'big-data', can be used to support a probabilistic framework is presented.

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“…Some researchers have developed computer codes for the probabilistic life assessment of aerospace components with MSD, such as PROF, SMART/LD and PISA (Probabilistic Investigation for Safe Aircrafts) …”

Section: Introductionmentioning

confidence: 99%

Experiments and model predictions for fatigue crack propagation in riveted lap‐joints with multiple site damage

Galatolo

Lazzeri

2015

Fatigue Fract Eng Mat Struct

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In this paper, the growth of long fatigue cracks up to failure in aircraft components is studied. A deterministic model is presented, able to simulate the growth of fatigue through cracks located at rivet holes in lap-joint panels. It also includes criteria to assess the link-up of collinear adjacent cracks in a MSD scenario. To validate the model, a fatigue test campaign was carried out on riveted lap-joint specimens in order to produce experimental crack growth and link-up data. Accurate measurements of naturally occurred surface cracks were automatically performed by the Image Analysis technique, thus allowing the tests to run 24 h a day. The comparison between experimental tests and numerical simulations is good, thus confirming the model as a useful tool for the assessment of fatigue life of aircraft riveted joints

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Development of a Probabilistic Linear Damage Methodology for Small Aircraft

Cited by 10 publications

References 6 publications

Deciding Optimal Number of Fatigue Crack Growth Tests for Damage-Tolerant Design

Deciding Optimal Number of Fatigue Crack Growth Tests for Damage-Tolerant Design

A Framework to Implement Probabilistic Fatigue Design of Safe-Life Components

Experiments and model predictions for fatigue crack propagation in riveted lap‐joints with multiple site damage

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