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Experimental And Numerical Investigation Of Wide Area Blunt Impact Damage To Composite Aircraft Structures
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Book Synopsis Experimental and Numerical Investigation of Wide Area Blunt Impact Damage to Composite Aircraft Structures by : Zhi Ming Chen
Download or read book Experimental and Numerical Investigation of Wide Area Blunt Impact Damage to Composite Aircraft Structures written by Zhi Ming Chen and published by . This book was released on 2015 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt: Due to their high performance and weight efficiency, carbon fiber composites are increasingly being used in aircraft primary structure applications. Exposed composite structures (e.g., fuselage lower body) are susceptible accidental impacts by ground service equipment (GSE). The very high mass (over 10,000 kg) of GSE impact can involve high energy (over 1000 J) and thus can induce significant internal damage. Furthermore, the large contact area potentially involved with GSE impact can create significant internal delamination and fiber failure without leaving exterior-visible signs that any damage has occurred. The objectives of the research described herein are to : (1) conduct experimental investigation into the composite aircraft damage caused by GSE impact, (2) examine the small-scale failure modes in focused, element-level studies, (3) establish a finite element modeling methodology involving detailed simulation capability that is validated via small-scale tests, and (4) apply these modeling capabilities to accurately predict full-scale structural behavior without adjustment (e.g., tuning) of modeling input parameters.
Book Synopsis High Energy Wide Area Blunt Impact Damage to Internal Structural Components of Composite Aircraft Fuselage Structures by : Moonhee Nam
Download or read book High Energy Wide Area Blunt Impact Damage to Internal Structural Components of Composite Aircraft Fuselage Structures written by Moonhee Nam and published by . This book was released on 2021 with total page 331 pages. Available in PDF, EPUB and Kindle. Book excerpt: Since 2009, research focused on damage formation of composite aircraft fuselage by High Energy Wide Area Blunt Impact (HEWABI) has been conducted at UCSD. As a major damage source to composite aircraft fuselage structures, HEWABI, caused by accidental contact by heavy ground service equipment (GSE), potentially leaves significant internal damage in multiple structural components with barely visible damage signs on the outside skin surface. Accounting for key structural components existing in real fuselage structures, specifically floor structures and continuous shear tie, a series of new 2nd generation large scale specimens were designed, fabricated, and tested. The objectives of the research described herein are to: (1) use of large-scale experiments to understand damage formation from HEWABI events near the floor structure location using the 2nd generation composite fuselage panel; of interest is examining how damage development is affected by the major changes from the 1st to 2nd generation panel design and boundary conditions, (2) investigation of C-frame failure both experimentally and analytically, and (3) evaluation of current FE modeling capability correlated with the 2nd generation HEWABI test results.
Book Synopsis High Energy Wide Area Blunt Impact on Composite Aircraft Structures by : Gabriela K. DeFrancisci
Download or read book High Energy Wide Area Blunt Impact on Composite Aircraft Structures written by Gabriela K. DeFrancisci and published by . This book was released on 2013 with total page 257 pages. Available in PDF, EPUB and Kindle. Book excerpt: The largest source of damage to commercial aircraft is caused by accidental contact with ground service equipment (GSE). The cylindrical bumper typically found on GSE distributes the impact load over a large contact area, possibly spanning multiple internal structural elements (frame bays) of a stiffened-skin fuselage. This type of impact can lead to damage that is widespread and difficult to detect visually. To address this problem, monolithic composite panels of various size and complexity have been modeled and tested quasi-statically and dynamically. The experimental observations have established that detectability is dependent on the impact location and immediately-adjacent internal structure of the panel, as well as the impactor geometry and total deformation of the panel. A methodology to model and predict damage caused by wide area blunt impact events was established, which was then applied to more general cases that were not tested in order to better understand the nature of this type of impact event and how it relates to the final damage state and visual detectability.
Book Synopsis Damage Initiation, Progression and Modeling of High Energy Wide Area Blunt Impacts to Aircraft Structures by : Chaiane Wiggers de Souza
Download or read book Damage Initiation, Progression and Modeling of High Energy Wide Area Blunt Impacts to Aircraft Structures written by Chaiane Wiggers de Souza and published by . This book was released on 2022 with total page 476 pages. Available in PDF, EPUB and Kindle. Book excerpt: Composite structures have been increasingly employed in the aerospace industry, particularly in commercial aircraft due to their high stiffness and strength and low density. Carbon Fiber Reinforced Polymers (CFRPs) are brittle materials, and are hence prone to leaving little residual deformation due to lack of plasticity and may fail catastrophically. This is a concerning characteristic especially for High Energy Wide Area Blunt Impact (HEWABI), which can cause significant internal damage without external visibility. Experiments were performed on a 6-stringer curved panel with co-cured skin, bolted shear tie and C-frame representative of commercial composite aircraft, with loading next to passenger floor beam. The first damage observed was on the shear tie radius, and other damage modes include skin-stringer delamination, fractured C-frame, cut stringer cap and more shear tie cracks. The experimental data were compared to Finite Element Analyses (FEA), which were able to predict the first shear tie crack, stringers contact to shear tie/C-frame and damage to stringer cap. However, the exact timing of the damages was not captured. Additional fastener modeling, which affects the stiffness of the FEA, was introduced. Following the experiments, Non-Destructive Evaluation (NDE) of 2-stringer with co-cured skin curved panel using Mahalanobis Square Distance for outlier analysis was able to detect damage on stringer heel.
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Book Synopsis Experimental and Numerical Investigation of Soft Impact Loading on Aircraft Materials by : Jie Zhou
Download or read book Experimental and Numerical Investigation of Soft Impact Loading on Aircraft Materials written by Jie Zhou and published by . This book was released on 2017 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Ultrasonic Guided Waves Test Method for Blunt Impact Damage Assessment on Composite Aircraft Structures by : Hyung Suk Kim
Download or read book Ultrasonic Guided Waves Test Method for Blunt Impact Damage Assessment on Composite Aircraft Structures written by Hyung Suk Kim and published by . This book was released on 2020 with total page 159 pages. Available in PDF, EPUB and Kindle. Book excerpt: Blunt impact damage (BID) is known to potentially cause significant strength reduction on composite structures even when the damage is barely noticeable. Therefore, non-destructive evaluation (NDE) to assess blunt-impacted composite aircraft structures is a crucial procedure to determine existence and severity of the damage to examine airworthiness. Ultrasonic guided waves (UGWs) test method has been studied herein as an NDE technique to evaluate large composite structures, because the typically thin-walled aircraft structures effectively act as has guided waves propagation paths. UGW scanning methods were performed only from the external skin-side using pitch-catch method: an actuator and a receiver located at a distance apart to scan the structure within. The actuator and the receiver transducers were placed on the adjacent skin-to-shear tie bolted joint regions for scanning of internal shear tie and C-frame components, and placed at opposite sides of the hat stringer on the skin bay for investigation of co-cured stringer components. UGWs transmission through bolted joint structure was examined to determine the test frequency that allowed wave transmission through bolted joints at low attenuation. And UGW tests from the skin-to-shear tie joint regions identified significant wave energy drop at the test frequency from the comparison of the pristine and the damaged (HEWABI) shear ties. Furthermore, damage characteristics were analyzed from the UGW measurements of the stringer scan followed by successful blunt impacted stringer delamination damage detection. Features extracted from the UGW test results showed exceptional match to the damage location, severity, and modes determined from the conventional NDE methods. Finally, UGW measurements-based residual strength estimation was studied from simple notched coupon tests and is an on-going study for more complex structures with realistic damage modes.
Book Synopsis Scientific and Technical Aerospace Reports by :
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Book Synopsis A Computational and Experimental Analysis of Impact to Aircraft Structures by : Pierce Kennedy
Download or read book A Computational and Experimental Analysis of Impact to Aircraft Structures written by Pierce Kennedy and published by . This book was released on 2005 with total page 195 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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Book Synopsis Experimental and Numerical Investigation Into the Effects of Panel Curvature on the High Velocity Ballistic Impact Response of Aluminum and Composite Panels by :
Download or read book Experimental and Numerical Investigation Into the Effects of Panel Curvature on the High Velocity Ballistic Impact Response of Aluminum and Composite Panels written by and published by . This book was released on 2005 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Impact Behaviour of Fibre-Reinforced Composite Materials and Structures by : S. R. Reid
Download or read book Impact Behaviour of Fibre-Reinforced Composite Materials and Structures written by S. R. Reid and published by Elsevier. This book was released on 2000-10-12 with total page 318 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study covers impact response, damage tolerance and failure of fibre-reinforced composite materials and structures. Materials development, analysis and prediction of structural behaviour and cost-effective design all have a bearing on the impact response of composites and this book brings together for the first time the most comprehensive and up-to-date research work from leading international experts. State of the art analysis of impact response, damage tolerance and failure of FRC materials Distinguished contributors provide expert analysis of the most recent materials and structures Valuable tool for R&D engineers, materials scientists and designers
Author :Great Britain. Department of Transport. Air Accidents Investigation Branch Publisher : ISBN 13 : Total Pages :184 pages Book Rating :4.F/5 ( download)
Book Synopsis Report on the Accident to Boeing 747-121, N739PA at Lockerbie, Dumfriesshire, Scotland on 21 December 1988 by : Great Britain. Department of Transport. Air Accidents Investigation Branch
Download or read book Report on the Accident to Boeing 747-121, N739PA at Lockerbie, Dumfriesshire, Scotland on 21 December 1988 written by Great Britain. Department of Transport. Air Accidents Investigation Branch and published by . This book was released on 1990 with total page 184 pages. Available in PDF, EPUB and Kindle. Book excerpt: Dated 6 August 1990. Includes 3 folded diagrams
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Book Synopsis Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 235) by :
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