04 by Providing More Capacity Than Any Other Twin-Engine Freighter, the 777F Brings New Levels of Efficiency to the Long-Haul M
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Stress Analysis of an Aircraft Fuselage with and Without Portholes Using
cs & Aero ti sp au a n c o e r E e Hadjez and Necib, J Aeronaut Aerospace Eng 2015, 4:1 n A g f i o n Journal of Aeronautics & Aerospace l e DOI: 10.4172/2168-9792.1000138 a e r n i r n u g o J Engineering ISSN: 2168-9792 Research Article Open Access Stress Analysis of an Aircraft Fuselage with and without Portholes using CAD/CAE Process Fayssal Hadjez* and Brahim Necib University of Constantine, Faculty of Science and Technology, Department of Mechanical Engineering, Algeria Abstract The airline industry has been marked by numerous incidents. One of the first, who accompanied the start of operation of the first airliners with jet engines, was directly related to the portholes. Indeed, the banal form of the windows was the source of stress concentrations, which combined with the appearance of micro cracks, caused the explosion in flight of the unit. Since that time, all aircraft openings receive special attention in order to control and reduce their impact on the aircraft structure. In this paper we focus on the representation and quantification of stress concentrations at the windows of a regional jet flying at 40000 feet. To do this, we use a numerical method, similar to what is done at major aircraft manufacturers. The Patran/Nastran software will be used the finite element software to complete our goals. Keywords: Aircraft; Bay; Modeling; Portholes; Fuselage; gradually. It is then necessary to pressurize the cabin to the survival Pressurization; Loads and passenger comfort. However this pressurization is not beneficial to the structure as it involves additional structural loads. -
For Improved Airplane Performance
BLENDED WINGLETS FORFOR IMPROVEDIMPROVED AIRPLANEAIRPLANE PERFORMANCEPERFORMANCE New blended winglets on the Boeing Business Jet and the 737-800 commercial airplane offer operational benefits to customers. Besides giving the airplanes a distinctive appear- ance, the winglets create more efficient flight characteristics in cruise and during takeoff and climbout, which translate into additional range with the same fuel and payload. ROBERT FAYE ROBERT LAPRETE MICHAEL WINTER TECHNICAL DIRECTOR ASSOCIATE TECHNICAL FELLOW PRINCIPAL ENGINEER BOEING BUSINESS JETS AERODYNAMICS TECHNOLOGY STATIC AEROELASTIC LOADS BOEING COMMERCIAL AIRPLANES BOEING COMMERCIAL AIRPLANES BOEING COMMERCIAL AIRPLANES TECHNOLOGY/PRODUCT DEVELOPMENT AERO 16 vertical height of the lifting system (i.e., increasing the length of the TE that sheds the vortices). The winglets increase the spread of the vortices along the TE, creating more lift at the wingtips (figs. 2 and 3). The result is a reduction in induced drag (fig. 4). The maximum benefit of the induced drag reduction depends on the spanwise lift distribution on the wing. Theoretically, for a planar wing, induced drag is opti- mized with an elliptical lift distribution that minimizes the change in vorticity along the span. For the same amount of structural material, nonplanar wingtip 737-800 TECHNICAL CHARACTERISTICS devices can achieve a similar induced drag benefit as a planar span increase; however, new Boeing airplane designs Passengers focus on minimizing induced drag with 3-class configuration Not applicable The 737-800 commercial airplane wingspan influenced by additional 2-class configuration 162 is one of four 737s introduced BBJ TECHNICAL CHARACTERISTICS The Boeing Business Jet design benefits. 1-class configuration 189 in the late 1990s for short- to (BBJ) was launched in 1996 On derivative airplanes, performance Cargo 1,555 ft3 (44 m3) medium-range commercial air- Passengers Not applicable as a joint venture between can be improved by using wingtip Boeing and General Electric. -
Aviation Week & Space Technology
STARTS AFTER PAGE 34 How Air Trvel New Momentum for My Return Smll Nrrowbodies? ™ $14.95 APRIL 20-MAY 3, 2020 SUSTAINABLY Digital Edition Copyright Notice The content contained in this digital edition (“Digital Material”), as well as its selection and arrangement, is owned by Informa. and its affiliated companies, licensors, and suppliers, and is protected by their respective copyright, trademark and other proprietary rights. Upon payment of the subscription price, if applicable, you are hereby authorized to view, download, copy, and print Digital Material solely for your own personal, non-commercial use, provided that by doing any of the foregoing, you acknowledge that (i) you do not and will not acquire any ownership rights of any kind in the Digital Material or any portion thereof, (ii) you must preserve all copyright and other proprietary notices included in any downloaded Digital Material, and (iii) you must comply in all respects with the use restrictions set forth below and in the Informa Privacy Policy and the Informa Terms of Use (the “Use Restrictions”), each of which is hereby incorporated by reference. Any use not in accordance with, and any failure to comply fully with, the Use Restrictions is expressly prohibited by law, and may result in severe civil and criminal penalties. Violators will be prosecuted to the maximum possible extent. You may not modify, publish, license, transmit (including by way of email, facsimile or other electronic means), transfer, sell, reproduce (including by copying or posting on any network computer), create derivative works from, display, store, or in any way exploit, broadcast, disseminate or distribute, in any format or media of any kind, any of the Digital Material, in whole or in part, without the express prior written consent of Informa. -
Sizing and Layout Design of an Aeroelastic Wingbox Through Nested Optimization
Sizing and Layout Design of an Aeroelastic Wingbox through Nested Optimization Bret K. Stanford∗ NASA Langley Research Center, Hampton, VA, 23681 Christine V. Juttey Craig Technologies, Inc., Cape Canaveral, FL, 32920 Christian A. Coker z Mississippi State University, Starkville, MS, 39759 The goals of this work are to 1) develop an optimization algorithm that can simulta- neously handle a large number of sizing variables and topological layout variables for an aeroelastic wingbox optimization problem and 2) utilize this algorithm to ascertain the ben- efits of curvilinear wingbox components. The algorithm used here is a nested optimization, where the outer level optimizes the rib and skin stiffener layouts with a surrogate-based optimizer, and the inner level sizes all of the components via gradient-based optimization. Two optimizations are performed: one restricted to straight rib and stiffener components only, the other allowing curved members. A moderate 1.18% structural mass reduction is obtained through the use of curvilinear members. I. Introduction Layout optimization of a wingbox structure, a form of topology optimization, involves deciding upon the best placement of ribs, spars, and stiffeners within a semimonocoque structure. There are numerous examples of layout design in the literature, including Refs.1-6. Some of these papers adhere to conventional orthogonal layouts of ribs, spars, and stiffeners,3 others blend the roles of these components through angled and/or curved members,2,5,6 and others abandon this convention entirely with a complex network of full- and partial-depth members.1,4 Regardless of how the layout design is conducted, sizing design must be included as well, by optimizing the thickness distribution of the various shell components: ribs, spars, stiffeners, and skins (cover panels). -
Structural Analysis of a Wing Box
L Ferroni Soares et al. Int. Journal of Engineering Research and Applications www.ijera.com ISSN : 2248-9622, Vol. 5, Issue 5, ( Part -4) May 2015, pp.23-31 RESEARCH ARTICLE OPEN ACCESS Structural Analysis of a wing box Structural behavior of aircraft IPUC001-CARCARÁwing Layston Ferroni Soares, Estêvão Guimarães Lapa, Pedro Américo Almeida Magalhães Junior, Bruno Daniel Pignolati Abstract The structural analysis is an important tool that allows the research for weight reduction, the choose of the best materials and to satisfy specifications and requirements. In an aircraft’s design, several analyzes are made to prove that this aircraft will stand the set of maneuvers that it was designed to accomplish. This work will consider the preliminar project of an aircraft seeking to check the behavior of the wing under certain loading conditions in the flight envelope.To get to this load set, it has been done all the process of specification of an aircraft, such as mission definition, calculation of weight and c.g. envelope, definition of the geometric characteristics of the aircraft, the airfoil choice, preliminary performance equations, aerodynamic coefficients and the aircraft’s balancing for the equilibrium condition, but such things will not be considered in this article. For the structural analysis of the wing will be considered an arbitrary flight condition, disregarding the effect of gusts loads. With the acquisition of the items mentioned, the main forces acting on the wing structure and their equations will be calculated. The use of finite element method will enable the application of loads obtained just as the development of a method of calculation, along with the construction of a three-dimensional model that represents a chosen condition. -
Tailored Wingbox Structures Through Additive Manufacturing: a Summary of Ongoing Research at NASA Larc
Tailored Wingbox Structures through Additive Manufacturing: a Summary of Ongoing Research at NASA LaRC Bret. K. Stanford and Karen M. B. Taminger NASA Langley Research Center, Hampton, VA USA [email protected], [email protected] ABSTRACT The use of wingbox structural design for improved performance (i.e., fuel burn reduction) of subsonic transports is driven by two trends: reduced structural weight and increased wingspan. These two trends are in direct competition, as the increased span will exacerbate the structural reaction to aerodynamic loading, and the reduced structural weight will nominally weaken the aircraft’s ability to handle this response. Novel structural configurations, enabled by recent improvements in manufacturing, may be critical toward bridging this gap. This paper summarizes pertinent activities at the NASA Langley Research Center in terms of additive manufacturing of metallic wing structures and substructures. Numerical design optimization activities are summarized as well, in order to understand where on a wingbox an additively-manufactured part may be useful and the way in which that part beneficially impacts the flight physics. The paper concludes with a discussion of how these two research paths may be better married in order to fully integrate both the benefits and realistic limitations of additive manufacturing and numerical structural design. 1.0 INTRODUCTION A common goal across the aviation industry and aeronautics-centric government laboratories is for the next generations of subsonic transport aircraft to attain significant reductions in fuel burn, emissions, and noise pollution, relative to the current fleet of aircraft. These ambitious goals will likely only be realized with a sustained focus and investment in new numerical design tools, experimental testing procedures, and manufacturing processes, as applied to all components of the aircraft: fuselage, wing, engine, etc. -
Department of the Air Force
NOT FOR PUBLICATION UNTIL RELEASED BY THE COMMITTEE ON ARMED SERVICES SUBCOMMITTEE ON AIR AND LAND FORCES UNITED STATES HOUSE OF REPRESENTATIVES DEPARTMENT OF THE AIR FORCE PRESENTATION TO THE HOUSE ARMED SERVICES COMMITTEE SUBCOMMITTEE ON AIR AND LAND FORCES UNITED STATES HOUSE OF REPRESENTATIVES SUBJECT: UNITED STATES TRANSPORTATION COMMAND POSTURE AND AIR FORCE MOBILITY AIRCRAFT PROGRAMS STATEMENT OF: GENERAL ARTHUR J. LICHTE COMMANDER, AIR MOBILITY COMMAND APRIL 1, 2008 NOT FOR PUBLICATION UNTIL RELEASED BY THE COMMITTEE ON ARMED SERVICES SUBCOMMITTEE ON AIR AND LAND FORCES UNITED STATES HOUSE OF REPRESENTATIVES 2 INTRODUCTION Mr. Chairman and distinguished committee members, thank you for the invitation to testify today in support of the “United States Transportation Command Posture and Air Force Mobility Aircraft Programs” hearing. It is my honor to represent the 133,000 Active Duty, Air National Guard and Air Reserve mobility Airmen who make up Air Mobility Command (AMC). Appearing before you today with the commander of United States Transportation Command (USTRANSCOM), General Norton Schwartz, and the Assistant Secretary of the Air Force for Acquisition, Ms. Sue Payton, presents an incredible opportunity to discuss a myriad of important issues critical to our national security. My testimony will focus on topics critical to AMC. Primarily, I will discuss the Air Force’s versatile new air refueling tanker, the KC-45A. Secondly, I will explain how our intertheater and intratheater airlift fleets are impacted by ever- changing requirements. Finally, I will outline several other issues on the forefront of this subcommittee’s legislative agenda. THE KC-45A I look forward to receiving KC-45As as soon as possible. -
Transatlantic Airline Fuel Efficiency Ranking, 2017
WHITE PAPER SEPTEMBER 2018 TRANSATLANTIC AIRLINE FUEL EFFICIENCY RANKING, 2017 Brandon Graver, Ph.D., and Daniel Rutherford, Ph.D. www.theicct.org [email protected] BEIJING | BERLIN | BRUSSELS | SAN FRANCISCO | WASHINGTON ACKNOWLEDGMENTS The authors thank Tim Johnson, Andrew Murphy, Anastasia Kharina, and Amy Smorodin for their review and support. We also acknowledge Airline Data Inc. for providing processed BTS data, and FlightGlobal for Ascend Fleet data. International Council on Clean Transportation 1225 I Street NW Suite 900 Washington, DC 20005 USA [email protected] | www.theicct.org | @TheICCT © 2018 International Council on Clean Transportation TRANSATLANTIC AIRLINE FUEL EFFICIENCY RANKING, 2017 TABLE OF CONTENTS EXECUTIVE SUMMARY ............................................................................................................ iii 1. INTRODUCTION .................................................................................................................... 2 2. METHODOLOGY ................................................................................................................... 3 2.1 Airline selection .................................................................................................................................3 2.2 Fuel burn modeling..........................................................................................................................5 2.3 Fuel efficiency calculation ............................................................................................................6 -
Qtr 02 09 a Quarterly Publication Boeing.Com/Commercial/ Aeromagazine
Qtr_02 09 A QUarterlY PUBLIcatION BOEING.COM/COMMERCIAL/ AEROMAGAZINE Material Management: Providing Customer Solutions 777 Freighter: Greater Efficiency for Long-Haul Operators Landing Gear Program Provides Overhaul Alternative Exceeding Tire Speed Rating During Takeoff Contribution of Flight Systems to Performance-Based Navigation AERO Cover photo: 777 in factory AERO Contents 03 Material Management: Providing Customer Solutions Our services are designed to help airlines operate more efficiently while reducing costs. 05 777 Freighter: Greater Efficiency for Long-Haul Operators The Boeing 777 Freighter is an efficient, long-range, high-capacity freighter offering the advanced features of the 05 777 family. 11 Landing Gear Program Provides Overhaul Alternative Boeing’s overhaul and exchange program offers operators additional options for 11 servicing landing gear. 15 Exceeding Tire Speed Rating During Takeoff Boeing offers guidance to help prevent 15 tire overspeed events during takeoff. 21 Contribution of Flight Systems to Performance-Based Navigation The evolution of flight management systems has led the way for performance- based navigation and the Next Generation 21 Air Transportation System. 01 WWW.boeIng.com/commercIal/aeromagaZIne Issue 34_Quarter 02 | 2009 AERO Publisher Design Cover photography Editorial Board Shannon Frew Methodologie Jeff Corwin Gary Bartz, Frank Billand, Richard Breuhaus, Darrell Hokuf, Al John, Doug Lane, Jill Langer, Mick Pegg, Wade Price, Bob Rakestraw, Editorial director Writer Printer Frank Santoni, Jerome -
Systems Study for an Integrated Digital/Electric Aircraft (IDEA)
NASA-CR-3840 19850007405 NASA Contractor Report 3840 t i Systems Study for an Integrated Digital/Electric Aircraft (IDEA) G. E. Tagge, L. A. Irish, and A. R.Bailey CONTRACT NAS1-17528 JANUARY 1985 R [_.._ _ _ _'l _ €__!7 . ','7:2! ' ;: ;; 11) LANGLEY RESEJtRCHCEI",I_ER LIBRARY, NASA H;_4MPTO_JVIRG_N!A, NASA Contractor Report 3840 Systems Study for an Integrated Digital/Electric Aircraft (IDEA) G. E. Tagge, L. A. Irish, and A. R. Bailey Boeing Commercial Airplane Company Seattle, Washington Prepared for Langley Research Center under Contract NAS1-17528 N/ A NationalAeronautics and SpaceAdministration Scientific and Technical IntormatlonBranch 1985 FOREWORD This document constitutes the final report of the Integrated Digital/Electric Aircraft (IDEA)Program,ContractNASI-17528. The major studyobjectiveweres to definethe configurationof an IDEA aircraftd,efine technicalrisksassociatedwith the IDEA systemsconcepts,and identifytheresearchand developmentrequiredto reducetheserisksforpotentialapplicationto transporatircraft intheearly1990s. The NASA TechnicalRepresentativeforthistaskwas Cary R. SF1tzer;the Contracting Officerwas James Y. Taylor,of theLangleyResearchCenter. The work was accompUshed withinthe PreUmlnaryDesign Department of the Boeing Commercial AirplaneCompany. Key personnelwho contrlbutewdere: G. E.Tagge ProgramManager L.A. Irish StudyManager J.D.Vachal AerodynamicsTechnology L.A. Ostrom AerodynamicsTechnology R. H. Johnson PropulslonTeclmology G. G. Redfield PropulsionTechnology A. R. Bailey WeightsTechnology K. E. Siedentopf We_,_htsTechnology D. L.Grande StructuresTechnology C. B. Crumb Electronic FlightControlDesign F.Byford Mechanical FlightControlDesign W. F. Shivttz Flight Systems Technology C. W. Lee Flight Systems Technology P.J.Campbell FUght Systems Technology J. W. Harper Airframe Systems Technology-Electrlcal K. T. Tanemura AirframeSystemsTechnology-ECS E. C. Lim AirframeSystemsTechnology-ECS R. A. Johnson AirframeSystemsTechnology-ECS D. E. Cozby AirframeSystemsTechnology-lcing J.R. -
Design and Development of a Multi- Mission UAS Through Modular Component Integration and Additive Manufacturing
Design and Development of a Multi- Mission UAS through Modular Component Integration and Additive Manufacturing A project present to The Faculty of the Department of Aerospace Engineering San Jose State University in partial fulfillment of the requirements for the degree Master of Science in Aerospace Engineering By Kim Lau August, 2018 approved by Dr. Nikos Mourtos Faculty Advisor 2 Table of Contents 1. Introduction ........................................................................................................................5 1.1. Motivation .................................................................................................................5 1.2. Literature Review .....................................................................................................5 1.2.1. UAV Design and Development Trends ...........................................................5 1.2.2. Push for Modularity .........................................................................................7 1.2.3. Additive Manufacturing ...................................................................................8 1.3. Project Proposal ........................................................................................................11 1.4. Methodology .............................................................................................................11 2. Design Process ...................................................................................................................12 2.1. Mission Specification and -
Taxiway TAC Meeting #1 Agenda and Meeting Packet
MEETING AGENDA RE: Taxiway and Apron Network Date of Meeting: December 3, 2019 Technical Advisory Committee Meeting #1 Project Manager: Kaci Nowicki Time of Meeting: 8:00 a.m. SEH No.: 150733 16.00 Location of Meeting: Duluth International Airport, Amatuzio Room Attendees: Duluth Airport Authority SEH City of Duluth Minnesota Air National Guard 148th Fighter Wing Duluth International Airport Tenant Association (DIATA) Cirrus Aircraft Military Affairs Committee – Duluth Chamber of Commerce Hermantown Chamber of Commerce Federal Aviation Administration (FAA) Minnesota Department of Transportation (MnDOT) Citizens Committee for Environmental Concern Airport commercial operators (airlines and cargo carriers) Lake Superior College General aviation tenants Lake Superior Helicopters I. Existing taxiway network and aprons – current conditions and use A. Introduction to the DLH taxiway and apron system B. How do users use the taxiway system? 1. What segments are heavily used? 2. Which segments are used by large aircraft? 3. For aircraft exiting the runway, which connectors are most frequently used (when landing on each end, considering various aircraft types)? C. How do you use the apron system? 1. How is each ramp used? By who, what types of aircraft? 2. Where do large aircraft park? D. Vehicle operations on the airport II. Stakeholder feedback on taxiway and apron system A. What wouldn’t you change? B. Are there areas where stakeholder needs are not being met? C. Are there areas of congestion? D. What areas, if any, are confusing to aircraft or vehicles? E. Could any taxiway connectors be better utilized if relocated? Or are there additional connectors that are needed? F.