Study on Utilization of Advanced Composites in Fuselage Structures of Large Transports PDF Download

Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 154

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Author: A. C. Jackson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 112

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Author: D. J. Watts
Publisher: BiblioGov
ISBN: 9781289144708
Category :
Languages : en
Pages : 186

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A study was conducted to define the technology and data needed to support the introduction of advanced composites in the future production of fuselage structure in large transport aircraft. Fuselage structures of six candidate airplanes were evaluated for the baseline component. The MD-100 was selected on the basis of its representation of 1990s fuselage structure, an available data base, its impact on the schedule and cost of the development program, and its availability and suitability for flight service evaluation. Acceptance criteria were defined, technology issues were identified, and a composite fuselage technology development plan, including full-scale tests, was identified. The plan was based on composite materials to be available in the mid to late 1980s. Program resources required to develop composite fuselage technology are estimated at a rough order of magnitude to be 877 man-years exclusive of the bird strike and impact dynamic test components. A conceptual composite fuselage was designed, retaining the basic MD-100 structural arrangement for doors, windows, wing, wheel wells, cockpit enclosure, major bulkheads, etc., resulting in a 32 percent weight savings.

Author: National Research Council
Publisher: National Academies Press
ISBN: 030917595X
Category : Technology & Engineering
Languages : en
Pages : 98

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The major objective of this book was to identify issues related to the introduction of new materials and the effects that advanced materials will have on the durability and technical risk of future civil aircraft throughout their service life. The committee investigated the new materials and structural concepts that are likely to be incorporated into next generation commercial aircraft and the factors influencing application decisions. Based on these predictions, the committee attempted to identify the design, characterization, monitoring, and maintenance issues that are critical for the introduction of advanced materials and structural concepts into future aircraft.

Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 538

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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 456

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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Author:
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Category :
Languages : en
Pages : 28

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The effort required by commercial transport manufacturers to accomplish the transition from current construction materials and practices to extensive use of composites in aircraft wings was investigated. The engineering and manufacturing disciplines which normally participate in the design, development, and production of an aircraft were employed to ensure that all of the factors that would enter a decision to commit to production of a composite wing structure were addressed. A conceptual design of an advanced technology reduced energy aircraft provided the framework for identifying and investigating unique design aspects. A plan development effort defined the essential technology needs and formulated approaches for effecting the required wing development. The wing development program plans, resource needs, and recommendations are summarized.

Author: Langley Research Center
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 196

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Author:
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ISBN:
Category :
Languages : en
Pages : 196

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Author: Paul A. Lagace
Publisher:
ISBN:
Category :
Languages : en
Pages : 29

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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.