Application of a design-build-team approach to low cost and weight composite fuselage structure Download PDF EPUB FB2
Get this from a library. Application of a design-build-team approach to low cost and weight composite fuselage structure. [L B Ilcewicz; United States. National Aeronautics and Space Administration. Scientific and Technical Information Program.;]. Composite materials technology, together with improvements in propulsion, avionics, and other technologies, will provide the total aircraft performance required to make V/STOL capability cost-effective.
Vought is conducting research into the application of composite materials to lightly loaded fuselage shell by: 2. A team approach, integrating the disciplines responsible for aircraft structural design and manufacturing, was developed to perform cost and weight trade studies for a twenty-foot diameter aft fuselage section.
Baseline composite design and manufacturing concepts were selected for large quadrant panels in crown, side, and keel areas of the. As part of an approach to design fuselage frames for minimum weight, minimum cost, or a combination of the two, the design constraints and the effects of manufacturing process are discussed.
Four different fabrication processes are considered: Conventional sheet metal, high speed machined metal, hand laid-up composite, and resin transfer molded Cited by: Detailed design of a lattice composite fuselage structure by a mixed optimization method and confident composite structure weight estimation on the basis of multilevel approach was described.
The effects of design details on cost and weight of fuselage structures Article (PDF Available) January with Reads How we measure 'reads'. fuselage and a composite fuselage is also presented showing the less weight advantage of the composite fuselage.
This paper presents, as an example, the solutions of the structures design of a fuselage for a 30 seats commercial aircraft. Among the solutions are the interior layout and cross section definition, initial geometric and weight. Similarly, the new Boeing Dreamliner structure, including the fuselage, wings, tail, doors, and the interior is made of over 50% by weight composite materials (80% by volume).
The all-composite fuselage made it the first composite airliner in. An illustration of a computer application window Wayback Machine. An illustration of an open book.
Books. An illustration of two cells of a film strip. Video. An illustration of an audio speaker. Full text of "Advanced Technology Composite Fuselage - Manufacturing". An illustration of a computer application window Wayback Machine.
An illustration of an open book. Books. An illustration of two cells of a film strip. Video. An illustration of an audio speaker. Audio.
An illustration of a " floppy disk. Full text of "Advanced Technology Composite Fuselage. transverse stiffening is provided (e.g, orbital frames for a fuselage structure).
Centre wing box or section 21 Upper panel Panel bay or super-stiffener = stiffener + skin Pitch Fig Airframe structure decomposition The advantage of such an approach is that the. less weight and stronger structures. An efficient 0structural component must have three primary attributes namely, the capability to perform its 0intended function, sufficient service life and with the ability of being produced at 0reasonable cost.
To begin with the fuselage in the aircraft, it is a major structure. The last few decades have seen a steady rise in the amount of ‘composite’ materials used in the airframe of aircraft.
These have added strength but lowered the overall weight of the aircraft. The use of composites in one new aircraft has generated a weight saving. perspective aircraft wing and fuselage structures based on frame/lattice pro-composite concepts. 1 Pro-composite aircraft structures The problem of weight and cost saving for the airframe structure is remaining relevant through all the history of aviation and it is substantially one of the most important factors in providing the development of.
Typical Cost Modeling 1. Take empirical data from past programs. Perform regression to get variation with selected parameters, e.g. cost vs. weight. Apply “judgment factors” for your case. e.g. configuration factors, complexity factors, composite factors.
There is widespread belief that aircraft manufacturers do not know what it actually. cross-section of this central fuselage section. In order to accommodate a specific number of passengers, the fuselage can be long and narrow or, conversely, short and wide.
As the fuselage contributes approximately 25% to 50 % of an aircraft's total drag, it is especially important to ensure that it has a low-drag shape. A fuselage. business jet that utilizes an all-composite fuselage. Fig. 1, shows the stringers and frame cross-section of this concept.
Also, the main feature of this fuselage structure was to reduce both weight and cost. Another key feature mentioned is that a buckling tolerance design was adopted for the skin. Application of a Design-Build Team Approach to Low Cost and Weight Composite Fuselage Structure.
Ilcewicz, L.B., Walker, T.H., Willden, K.S., Swanson, G.D., Truslove. 2 American Institute of Aeronautics and Astronautics bubble fuselage section models for structural analysis12 and weight reduction study.
A finite element model (FEM) of a notional % scaled up version of the double-bubble D8 aircraft concept is also developed for preliminary structural analysis and weight estimation. wing, tail and fuselage internal structure.
The fuselage will have detachable high wing, allows easy access to the payload. This payload-focused con guration minimizes the key parameters of system weight through its structural e ciency and access to payloads, while providing su cient aerodynamic performance and propulsive power density.
Structural research aimed at low-cost, low-weight composite fuselage structures will benefit the rotorcraft industry greatly.
However, unlike commuter aircraft, rotorcraft involve a number of unique structural issues that impede development and successful application to commercial operations. Investigation of Stiffening and Curvature Effects on the Residual Strength of Composite Stiffened Panels with Large Transverse Notches.
Enjuto, P., Walker, T.H., Lobo. By far, the largest composite applications are sandwich panels made with honeycomb core and thermoset resins, used for flooring, ceilings, galley walls, lavatories and cargo hold liners. Low-density, lightweight core between thin facesheets dramatically increases a panel's stiffness with little added weight.
Additional strategic defence benefits have led to more military applications such as wing and fuselage, than commercial. Relatively high fuel costs helped to justify the initial commercial applications based on composite weight savings.
In the s and s, fuel costs dropped relative to other airline costs, such as ownership. application of affordable composite technology to pressurized fuselage structure of future aircraft. As part of this effort, a design study was conducted on the keel section of the aft fuselage. A design build team (DBT) approach was used to identify and evaluate several design concepts which incorporated different material.
Wing and Fuselage Structural Optimization Considering Alternative Material Systems By Jonathan Lusk B.S.A.E., University of Kansas, Submitted to the Department of Aerospace Engineering and. matrix. the main advantages of composite ma-terials are their high strength and stiffness, com-bined with low density, when compared with bulk materials, allowing for a weight reduction in the finished part.
the reinforcing phase provides the strength and stiffness. In most cases, the reinforcement is. the strength involved. They represent the basic structure of the floor. Fuselage loads The fuselage will experience a wide range of loads from the number of sources.
The weight of the fuselage structure and payload will cause the fuselage to bend downwards from its support at the wing, putting the top portion in tension and the.
The preliminary design study was conducted to identify, evaluate, and select advanced concepts for cargo aircraft fuselage structure. The goals were to reduce the structural weight, maintain the baseline fatigue life (60, flight-hours flights), and reduce the acquisition cost.
All three selected fuselage shell concepts provide a reduction in both total unit cost (2% to 7%) and. Concorde Wing Structure. Wing Wing Structure. 1 Introduction Flight simulation of a morphing aircraft is a key - Selection from Morphing Aerospace Vehicles and Structures [Book].
Aircraft Wing Structure. mm-thick Aluminum, lasercut with CO 2 laser. the struts to the main fuselage structure. Since the wing struts are usually attached approximately halfway out on the wing, this type of wing structure is called semi-cantilever. A few high-wing and most low-wing airplanes have a full cantilever wing designed to carry the loads without external struts.USB2 US10/, USA USB2 US B2 US B2 US B2 US A US A US A US B2 US B2 US B2 Authority US United States Prior art keywords container fuselage aircraft shell compartment Prior art date Legal status (The legal status is an assumption and is not a legal conclusion.Although many cost drivers affect the entire fuselage section, each area of the fuselage (crown, side, and keel) has unique challenges that must be overcome to achieve low costs.
Important composite structural design issues are also unique to each of the fuselage areas as shown in figure