A study of accidental impact scenarios for composite wing damage tolerance evaluation

Дубинский, С. В.; Feygenbaum, Yuri; Сеник, В. Я.; Metelkin, E. V.

doi:10.1017/aer.2018.152

Cited by 15 publications

(3 citation statements)

References 6 publications

(9 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Furthermore, the probability of detection varies with different damage sizes. To elucidate the uncertainty inherent in the detection process, scholars have conducted a plethora of research studies [30,31,34,[37][38][39][40]. The cumulative lognormal distribution is commonly used to describe the damage size a and its probability of detection p D (a).…”

Section: Damage Type and Size Distributionmentioning

confidence: 99%

Dynamic probability modeling-based inspection intervals optimization for civil aircraft composite structures using Bayesian updating

Li,

Zuo,

Yang

2024

Smart Mater. Struct.

View full text Add to dashboard Cite

The evaluation of damage tolerance in composite materials is essential for ensuring the safety of aircraft structures. One of the most challenging aspects of applying probability modeling-based methods to evaluate damage tolerance is determining the actual damage size distributions for in-service aircraft structures. Although existing nondeterministic approaches have been used to optimize inspection intervals of composite structures, few studies have investigated the effects of updates on the actual damage size distribution and its impact on both the probability of structural failure and inspection intervals. This paper proposes a dynamic optimization method for inspection intervals of composite structures based on Bayesian updating. The damage size distribution of the composite structure is characterized by a general stochastic distribution. A Bayesian updating methodology is presented to iteratively update the actual damage size distribution whenever new data becomes available. Based on the constructed probability model, the inspection intervals of composite structures are determined under the objectives of optimal safety and economy for civil aircraft using a Monte Carlo approach. Compared to prior distribution models, the proposed method achieves higher safety for structures during a single inspection, reduces the failure probability of structures throughout their entire service life, and incurs lower maintenance costs. It also enables maintenance personnel to flexibly adjust inspection intervals while facilitating quantitative evaluation of both failure probabilities and maintenance costs associated with these intervals. These findings suggest that the proposed method holds great potential in enabling maintenance personnel to make informed decisions regarding inspection intervals for improved safety and economic performance.

show abstract

Section: Damage Type and Size Distributionmentioning

confidence: 99%

Dynamic probability modeling-based inspection intervals optimization for civil aircraft composite structures using Bayesian updating

Li,

Zuo,

Yang

2024

Smart Mater. Struct.

View full text Add to dashboard Cite

show abstract

“…Nevertheless, composites exhibit modes of damage and failure which are not what typically observed in metals. Physical impacts at low velocity/energy can create defects on the composite materials which may promote the degradation of the integrity of the aircraft's structure and, eventually, have the potential to lead to failures [3]. That includes damage to the lightning protection layer.…”

Section: Introductionmentioning

confidence: 99%

Handling, inspection and repair of aircraft composites: a pilot study on the awareness of maintenance personnel

et al. 2023

View full text Add to dashboard Cite

Composite materials are enjoying an increasing use in aircraft structures. As more fleets transition from metal to more composite aircraft, the practice of maintenance is also adjusting. Handling, inspection and repair of aircraft composites following non-visible or barely visible damage are among the areas of concern, due to associated cost and safety implications. A pilot study was performed to explore the level of awareness and understanding of aviation maintenance practitioners around these issues. In addition, this research project sought to identify factors related to the technical/engineering judgement capacity of the personnel working with composites and to gauge the need for specialised education and training. A questionnaire survey was administered to a group of 40 professionals working for an aircraft maintenance, repair and overhaul (MRO) organisation. Descriptive statistics in conjunction with analysis of variance (ANOVA) were used to analyse the results. The sources of impact and common areas affected on the aircraft have been identified, with situational awareness suggested as the most important mitigator against impact damage. Over 70% of the participants would refer to their engineering manager for instructions on how to handle composite damage. The need for higher standardisation for composites’ maintenance, repair and handling issues emerged as a common theme across different sections of the survey. Almost all respondents agree on the need for specialised knowledge and training for the handling, repair and inspection of composites.

show abstract

“…As delamination is located inside the laminate and not visible on the surface, the tolerance of delamination damage is particularly challenging to achieve a damage tolerant design. A typical cause of delamination damage is the low-velocity impact [4,5], as impact threat usually cannot be completely avoided on aerospace structures [6]. Hence, ways and means to design an airworthy structure with the expected damage have to be established.…”

Section: Introductionmentioning

confidence: 99%

An Experimental Study of the Cyclic Compression after Impact Behavior of CFRP Composites

Bogenfeld

Gorsky

2021

J. Compos. Sci.

View full text Add to dashboard Cite

The behavior of impact damaged composite laminates under cyclic load is crucial to achieve a damage tolerant design of composite structures. A sufficient residual strength has to be ensured throughout the entire structural service life. In this study, a set of 27 impacted coupon specimens is subjected to quasi-static and cyclic compression load. After long intervals without detectable damage growth, the specimens fail through the sudden lateral propagation of delamination and fiber kink bands within few load cycles. Ultrasonic inspections were used to reveal the damage size after certain cycle intervals. Through continuous dent depth measurements during the cyclic tests, the evolution of the dent visibility was monitored. These measurements revealed a relaxation of the indentation of up to 90% before ultimate failure occurs. Due to the distinct relaxation and the short growth interval before ultimate failure, this study confirms the no-growth design approach as the preferred method to account for the damage tolerance of stiffened, compression-loaded composite laminates.

show abstract

A study of accidental impact scenarios for composite wing damage tolerance evaluation

Cited by 15 publications

References 6 publications

Dynamic probability modeling-based inspection intervals optimization for civil aircraft composite structures using Bayesian updating

Dynamic probability modeling-based inspection intervals optimization for civil aircraft composite structures using Bayesian updating

Handling, inspection and repair of aircraft composites: a pilot study on the awareness of maintenance personnel

An Experimental Study of the Cyclic Compression after Impact Behavior of CFRP Composites

Contact Info

Product

Resources

About