Application of a design-build-team approach to low cost and weight composite fuselage structure



Publisher: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, Publisher: National Technical Information Service, distributor] in [Washington, D.C.], [Springfield, Va

Written in English
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Edition Notes

StatementL.B. Ilcewicz ... [et al.].
SeriesNASA contractor report -- 4418., NASA contractor report -- NASA CR-4418.
ContributionsIlcewicz, L. B., United States. National Aeronautics and Space Administration. Scientific and Technical Information Program.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL17002464M
OCLC/WorldCa32368704

  In the early s, I had the pleasure of working on one of the largest aerospace composites research and development (R&D) projects that has ever been conducted. The program focused on composite fuselage and wing structure for large aircraft. Designs were developed and manufacturing processes were demonstrated at. Composite materials are used more and more for primary structures in commercial, industrial, aerospace, marine and recreational structures. Advanced composites do not corrode like metals – the combination of corrosion and fatigue cracking is a significant problem for aluminium commercial fuselage structure. Panels usually refer to a composite structure consisting of both skins and stiffeners (stringers). Sketches of panels were shown in the first couple of pages of this section. When it comes to sizing the skin and stringers, Bruhn in Analysis and Design of Missile Structures and Shanley both state or imply that it is difficult to treat the.   practical for strength and weight savings. Tensile strength is one starting point to calculate the cross sectional area of a load path but often buckling of a section determines the cross sectional areas. Then you choose a type of structure such as tube and fabric, or aluminum sheet metal or , or the wood with many gussets approach.

  After working in avaiation industry more than 15 years, most of time to be a structure engineer, this is a really excellent book that 1. provide the every aspect structure engineer should be aware of. 2. no complicate math but just simple and direct approach to understand the structure Reviews: solution. With an aircraft based in steel alloys, the weight was 29 ton. High specific weight of the steels prevented from wide use in aircraft construction. But steel is used for highly stressed components such as undercarriage, control surface tracks, fasteners (bolts), wing and tail to fuselage attachments. Airframe structure and weight The airframe structural and weight models used by TASOPT treat the primary structure elements as simple geometric shapes, with appropriate load distributions imposed at critical loading cases. The fuselage is assumed to be a pressure vessel with one or more “bubbles”. The design of the monocoque fuselage is called stressed skin and this is because the skin carries the primary loads. There are two types of monocoque: true monocoque and semi-monocoque. The true monocoque structure uses frames, formers and bulkheads to give shape to the fuselage and the skin is used to carry the primary stresses.

Composite structures can lower the weight of an airliner signi cantly. The increased production cost, however, requires the application of cost-e ective design strategies. Hence, a comparative value is required which is used for the evaluation of a design solution in terms of cost and weight. The direct operating cost (DOC) can be used as this. and has a very strong structure. Theairframeofafixed-wingaircraftconsistsofthe following five major units: 1. Fuselage 2. Wings 3. Stabilizers 4. Flight controls surfaces 5. Landing gear A rotary-wing aircraft consists of the following four major units: 1. Fuselage 2. Landing gear 3. . Cost analysis Table Weight savings from thermoplastic composite material systemsComposite solution CF/PA12 GF/PET GF/PPStamped sheet thickness (mm) Average over-moulded polymer thickness (mm)Composite part weight (kg) Weight saved (%) 60 35 30Raw material cost (7) 58 44require longer in-mould cycle.   Composite materials provide design and structural advantages over aluminum and steel, Collier argues, saying they are light, stiff, and strong. The HyperSizer software automatically performs design, stress analysis, and sizing optimization, typically reducing the weight .

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