Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Composite Fuselage Technology PDF full book. Access full book title Composite Fuselage Technology by National Aeronautics and Space Administration (NASA). Download full books in PDF and EPUB format.
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781720448440 Category : Languages : en Pages : 30
Book Description
Work was conducted over a ten-year period to address the central issue of damage in primary load-bearing aircraft composite structure, specifically fuselage structure. This included the three facets of damage resistance, damage tolerance, and damage arrest. Experimental, analytical, and numerical work was conducted in order to identify and better understand the mechanisms that control the structural behavior of fuselage structures in their response to the three aspects of damage. Furthermore, work was done to develop straightforward design methodologies that can be employed by structural designers in preliminary design stages to make intelligent choices concerning the material, layup, and structural configurations so that a more efficient structure with structural integrity can be designed and built. Considerable progress was made towards achieving these goals via this work. In regard to damage tolerance considerations, the following were identified as important effects: composite layup and associated orthotropy/structural anisotropy, specifics of initial local damage mechanisms, role of longitudinal versus hoop stress, and large deformation and associated geometric nonlinearity. Means were established to account for effects of radius and for the nonlinear response. In particular, nondimensional parameters were identified to characterize the importance of nonlinearity in the response of pressurized cylinders. This led to the establishment of a iso-nonlinear-error plot for reference in structural design. Finally, in the case of damage tolerance, the general approach of the original methodology to predict the failure pressure involving extending basic plate failure data by accounting for the local stress intensification was accomplished for the general case by accounting for the mechanisms noted by utilizing the capability of the STAGS finite element code and numerically calculating the local stress intensification for the particular configuration to be considered. Fo
Author: National Aeronautics and Space Adm Nasa Publisher: Independently Published ISBN: 9781723714511 Category : Science Languages : en Pages : 32
Book Description
Work was conducted over a ten-year period to address the central issue of damage in primary load-bearing aircraft composite structure, specifically fuselage structure. This included the three facets of damage resistance, damage tolerance, and damage arrest. Experimental, analytical, and numerical work was conducted in order to identify and better understand the mechanisms that control the structural behavior of fuselage structures in their response to the three aspects of damage. Furthermore, work was done to develop straightforward design methodologies that can be employed by structural designers in preliminary design stages to make intelligent choices concerning the material, layup, and structural configurations so that a more efficient structure with structural integrity can be designed and built. Considerable progress was made towards achieving these goals via this work. In regard to damage tolerance considerations, the following were identified as important effects: composite layup and associated orthotropy/structural anisotropy, specifics of initial local damage mechanisms, role of longitudinal versus hoop stress, and large deformation and associated geometric nonlinearity. Means were established to account for effects of radius and for the nonlinear response. In particular, nondimensional parameters were identified to characterize the importance of nonlinearity in the response of pressurized cylinders. This led to the establishment of a iso-nonlinear-error plot for reference in structural design. Finally, in the case of damage tolerance, the general approach of the original methodology to predict the failure pressure involving extending basic plate failure data by accounting for the local stress intensification was accomplished for the general case by accounting for the mechanisms noted by utilizing the capability of the STAGS finite element code and numerically calculating the local stress intensification for the particular configuration to be considered. Fo
Author: Ulf Paul Breuer Publisher: Springer ISBN: 3319319183 Category : Technology & Engineering Languages : en Pages : 272
Book Description
This book is based on lectures held at the faculty of mechanical engineering at the Technical University of Kaiserslautern. The focus is on the central theme of societies overall aircraft requirements to specific material requirements and highlights the most important advantages and challenges of carbon fiber reinforced plastics (CFRP) compared to conventional materials. As it is fundamental to decide on the right material at the right place early on the main activities and milestones of the development and certification process and the systematic of defining clear requirements are discussed. The process of material qualification - verifying material requirements is explained in detail. All state-of-the-art composite manufacturing technologies are described, including changes and complemented by examples, and their improvement potential for future applications is discussed. Tangible case studies of high lift and wing structures emphasize the specific advantages and challenges of composite technology. Finally, latest R&D results are discussed, providing possible future solutions for key challenges such as low cost high performance materials, electrical function integration and morphing structures.
Author: Chun Hui Wang Publisher: Academic Press ISBN: 0124171729 Category : Technology & Engineering Languages : en Pages : 307
Book Description
Bonded Joints and Repairs to Composite Airframe Structures is a single-source reference on the state-of-the-art in this rapidly growing area. It provides a thorough analysis of both internal and external joints and repairs, as well as discussions on damage tolerance, non-destructive inspection, self-healing repairs, and other essential information not only on the joints and repairs themselves, but critically, on how they differ from bonds and repairs to metallic aircraft. Authors Wang and Duong bring a valuable combination of academic research and industry expertise to the book, drawing on their cutting-edge composite technology experience, including analytic and computational leadership of damage and repair planning for the Boeing 787. Intended for graduate students, engineers, and scientists working on the subject in aerospace industry, government agencies, research labs, and academia, the book is an important addition to the limited literature in the field. Offers rare coverage of composite joints and repairs to composite structures, focusing on the state of the art in analysis Combines the academic, government, and industry expertise of the authors, providing research findings in the context of current and future applications Covers internal and external joints and repairs, as well as damage tolerance, non-destructive inspection, and self-healing repairs Ideal for graduate students, engineers, and scientists working in the aerospace industry, government agencies, research labs, and academia
Author: Paul A. Lagace Publisher: ISBN: Category : Languages : en Pages : 29
Book Description
Introduction: The aircraft industry continues to pursue the use of advanced composite materials in aircraft structures in order to save weight and produce more efficient, and potentially cost-effective, aircraft. As of the beginning of this work in 1989, advanced composite materials had been applied for over two decades in a number of aerospace structures. Although the list of applications at that time (including aircraft such as the Boeing 757 and 767, the Beech Starship, The Osprey V-22, the F-18, and the AV-8B) represented important engineering achievements, the National Research Council Committee on the Status and Viability of Composite Materials for Aircraft Structures noted in its 1987 report that: "Despite these and other examples, filamentary composites still have significant unfulfilled potential for increasing aircraft productivity [1]." An area identified for application of composite materials, at the time of this work, was primary load-bearing structure in large commercial transports. Although smaller aircraft, such as the Beech Starship, have had primary loadbearing structure, such as wings and fuselages, constructed from composite materials, it is not practical to geometrically scale up a general aviation aircraft into a large transport due to differences such as in the loading indices. There was thus an identified need to pursue further research into the behavior of composite materials and their structures so that increased benefits, such as further reduction in the structural load fraction, can be achieved. Two critical technology areas as related to aircraft are the technologies associated with wings and with fuselages. In considering such applications, an overriding concern is safety. In and of itself, safety is a very wide ranging issues. But, with regard to structure, safety generally deals with the ability of the structure to maintain its integrity while subjected to the loads and environment experienced in operation. A central issue in the case of a primary load-bearing structure is damage. There are three facets to the central issue of damage: damage resistance, which involves the ability of a structure to undergo events without (minimal) damage occurring and which thus addresses the question "how does damage get there"; damage tolerance, which involves the ability of a structure to undergo loading with damage present without failing and which thus addresses the question of "when does damage propagate/cause failure?"; and damage arrest, which involves the ability of a structural configuration to stop propagating damage before such damage causes catastrophic failure and which thus addresses the question "how can the propagating damage be stopped?". Answers to these three questions must be provided in order for a safe structure to be designed. In addressing these issues as they pertain to fuselage configurations made from advanced composite materials, a number of other important technical issues arise. A key issue is that of orthotropy. Due to their inherent orthotropy, composite materials provide the designer the ability to vary the properties of the structure with the structural needs in the various directions of the structure. This "structural tailoring" will affect the damage issues previously enumerated and the designer needs to know how to best tailor the specific fuselage structure to meet the structural needs and to meet the demands placed by the damage issues of resistance, tolerance, and arrest. A further issue deals with the effects of size. Aircraft fuselages are constructed of various dimensions and test articles are often of much smaller size. In order to apply the technology across the entire spectrum of possible sizes, it is necessary to understand the role of scale in the three damage issues. If scaling "laws" or working principles can be established, then the data and lessons learned on one fuselage can be more readily transferred to that of a different geometry and size. A final issue that could be immediately identified was that of configuration and its effects on the three facets of damage. A common structural configuration for aircraft fuselages is that of skin and frame where the underlying frame carries the longitudinal and bending loads while the skin provides the pressure surface and shear capability. In contrast to this typical approach used in metallic airframes, the Beech Starship fuselage has a more monocoque configuration utilizing a sandwich structure with inner and outer graphite/epoxy skins surrounding a Nomex honeycomb core. In this configuration, the sandwich skins provide the bending, longitudinal, pressure, and shear capabilities of the fuselage. In the skin/frame configuration, issues such as the interaction between the skin and the frame and how the skin is attached to the frame must be treated. In the sandwich configuration, issues concerning sandwich construction including debonding of the skins from the honeycomb must be addressed. Again, these need to be addressed in the context of the three facets of damage as to how they affect damage resistance, damage tolerance, and damage arrest. The underlying need is to provide the structural designer with the capability to choose the structural configuration that will most efficiently carry out its mission.
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781723506246 Category : Languages : en Pages : 250
Book Description
The goal of Boeing's Advanced Technology Composite Aircraft Structures (ATCAS) program was to develop the technology required for cost and weight efficient use of composite materials in transport fuselage structure. This contractor report describes results of material and process selection, development, and characterization activities. Carbon fiber reinforced epoxy was chosen for fuselage skins and stiffening elements and for passenger and cargo floor structures. The automated fiber placement (AFP) process was selected for fabrication of monolithic and sandwich skin panels. Circumferential frames and window frames were braided and resin transfer molded (RTM'd). Pultrusion was selected for fabrication of floor beams and constant section stiffening elements. Drape forming was chosen for stringers and other stiffening elements. Significant development efforts were expended on the AFP, braiding, and RTM processes. Sandwich core materials and core edge close-out design concepts were evaluated. Autoclave cure processes were developed for stiffened skin and sandwich structures. The stiffness, strength, notch sensitivity, and bearing/bypass properties of fiber-placed skin materials and braided/RTM'd circumferential frame materials were characterized. The strength and durability of cocured and cobonded joints were evaluated. Impact damage resistance of stiffened skin and sandwich structures typical of fuselage panels was investigated. Fluid penetration and migration mechanisms for sandwich panels were studied. Scholz, D. B. and Dost, E. F. and Flynn, B. W. and Ilcewicz, L. B. and Nelson, K. M. and Sawicki, A. J. and Walker, T. H. and Lakes, R. S. Langley Research Center NASA-CR-4731, NAS 1.26:4731 NAS1-18889; NAS1-20013; RTOP 510-02-13-01...
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722924478 Category : Languages : en Pages : 190
Book Description
The goal of Boeing's Advanced Technology Composite Aircraft Structures (ATCAS) program is to develop the technology required for cost-and weight-efficient use of composite materials in transport fuselage structure. Carbon fiber reinforced epoxy was chosen for fuselage skins and stiffening elements, and for passenger and cargo floor structures. The automated fiber placement (AFP) process was selected for fabrication of stringer-stiffened and sandwich skin panels. Circumferential and window frames were braided and resin transfer molded (RTM'd). Pultrusion was selected for fabrication of floor beams and constant-section stiffening elements. Drape forming was chosen for stringers and other stiffening elements cocured to skin structures. Significant process development efforts included AFP, braiding, RTM, autoclave cure, and core blanket fabrication for both sandwich and stiffened-skin structure. Outer-mold-line and inner-mold-line tooling was developed for sandwich structures and stiffened-skin structure. The effect of design details, process control and tool design on repeatable, dimensionally stable, structure for low cost barrel assembly was assessed. Subcomponent panels representative of crown, keel, and side quadrant panels were fabricated to assess scale-up effects and manufacturing anomalies for full-scale structures. Manufacturing database including time studies, part quality, and manufacturing plans were generated to support the development of designs and analytical models to access cost, structural performance, and dimensional tolerance. Wilden, K. S. and Harris, C. G. and Flynn, B. W. and Gessel, M. G. and Scholz, D. B. and Stawski, S. and Winston, V. Langley Research Center COMPOSITE STRUCTURES; MANUFACTURING; FUSELAGES; TRANSPORT AIRCRAFT; SANDWICH STRUCTURES; RESIN TRANSFER MOLDING; DATA BASES; FABRICATION; EPOXY MATRIX COMPOSITES; CARBON FIBERS; STIFFENING; STRINGERS; TOOLING; PULTRUSION; PANELS; DIMENSIONAL STABILITY; SKIN (STRUCTURAL MEMBER); BRAIDED CO...
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722925130 Category : Languages : en Pages : 102
Book Description
Boeing is studying the technologies associated with the application of composite materials to commercial transport fuselage structure under the NASA-sponsored contracts for Advanced Technology Composite Aircraft Structures (ATCAS) and Materials Development Omnibus Contract (MDOC). This report addresses the program activities related to structural performance of the selected concepts, including both the design development and subsequent detailed evaluation. Design criteria were developed to ensure compliance with regulatory requirements and typical company objectives. Accurate analysis methods were selected and/or developed where practical, and conservative approaches were used where significant approximations were necessary. Design sizing activities supported subsequent development by providing representative design configurations for structural evaluation and by identifying the critical performance issues. Significant program efforts were directed towards assessing structural performance predictive capability. The structural database collected to perform this assessment was intimately linked to the manufacturing scale-up activities to ensure inclusion of manufacturing-induced performance traits. Mechanical tests were conducted to support the development and critical evaluation of analysis methods addressing internal loads, stability, ultimate strength, attachment and splice strength, and damage tolerance. Unresolved aspects of these performance issues were identified as part of the assessments, providing direction for future development. Walker, T. H. and Minguet, P. J. and Flynn, B. W. and Carbery, D. J. and Swanson, G. D. and Ilcewicz, L. B. Langley Research Center COMPOSITE STRUCTURES; FUSELAGES; TRANSPORT AIRCRAFT; STRUCTURAL DESIGN; PERFORMANCE PREDICTION; COMPOSITE MATERIALS; MANUFACTURING; DATA BASES; STRUCTURAL FAILURE; DAMAGE ASSESSMENT; LOADS (FORCES); AEROELASTICITY; TOLERANCES (MECHANICS); DESIGN ANALYSIS; PREDICTION ANALYSIS TECHNIQUES; STABILITY...
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781722924836 Category : Languages : en Pages : 140
Book Description
The Advanced Technology Composite Aircraft Structures (ATCAS) program has studied transport fuselage structure with a large potential reduction in the total direct operating costs for wide-body commercial transports. The baseline fuselage section was divided into four 'quadrants', crown, keel, and sides, gaining the manufacturing cost advantage possible with larger panels. Key processes found to have savings potential include (1) skins laminated by automatic fiber placement, (2) braided frames using resin transfer molding, and (3) panel bond technology that minimized mechanical fastening. The cost and weight of the baseline fuselage barrel was updated to complete Phase B of the program. An assessment of the former, which included labor, material, and tooling costs, was performed with the help of design cost models. Crown, keel, and side quadrant cost distributions illustrate the importance of panel design configuration, area, and other structural details. Composite sandwich panel designs were found to have the greatest cost savings potential for most quadrants. Key technical findings are summarized as an introduction to the other contractor reports documenting Phase A and B work completed in functional areas. The current program status in resolving critical technical issues is also highlighted. Ilcewicz, L. B. and Smith, P. J. and Hanson, C. T. and Walker, T. H. and Metschan, S. L. and Mabson, G. E. and Wilden, K. S. and Flynn, B. W. and Scholz, D. B. and Polland, D. R. and Fredrikson, H. G. and Olson, J. T. and Backman, B. F. Langley Research Center COMPOSITE STRUCTURES; FUSELAGES; TRANSPORT AIRCRAFT; COST REDUCTION; SANDWICH STRUCTURES; OPERATING COSTS; COMPOSITE MATERIALS; RESIN TRANSFER MOLDING; WEIGHT REDUCTION; MANUFACTURING; STRUCTURAL DESIGN; TOOLING; DESIGN TO COST; MAINTENANCE; SKIN (STRUCTURAL MEMBER)...
Author: National Aeronautics and Space Administration (NASA)
Author: National Aeronautics and Space Adm Nasa
Author: Ulf Paul Breuer
Author: Chun Hui Wang
Author: Paul A. Lagace
Author: National Aeronautics and Space Administration (NASA)
Author: 
Author: National Aeronautics and Space Administration (NASA)
Author: National Aeronautics and Space Administration (NASA)
Author: National Aeronautics and Space Administration (NASA)
Author: Langley Research Center