DOCSLIB.ORG

Alternative Air Brake Concepts for Transport Aircraft Steep Approach

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Alternative Air Brake Concepts for Transport Aircraft Steep Approach Technische Universität München Lehrstuhl für Aerodynamik und Strömungsmechanik Alternative Air Brake Concepts for Transport Aircraft Steep Approach Ulrich Sebastian Jung Vollständiger Abdruck der von der Fakultät für Maschinenwesen der Technischen Universität München zur Erlangung des akademischen Grades eines Doktor-Ingenieurs genehmigten Dissertation. Vorsitzender: Univ.-Prof. Dr.-Ing. Manfred Hajek Prüfer der Dissertation: 1. apl. Prof. Dr.-Ing. Christian Breitsamter 2. Univ.-Prof. Dr.-Ing. Mirko Hornung Die Dissertation wurde am 20.10.2011 bei der Technischen Universität München eingereicht und durch die Fakultät für Maschinenwesen am 06.02.2012 angenommen. VORWORT Die vorliegende Arbeit entstand während meiner Tätigkeit als wissenschaftlicher Mitarbeiter am Lehrstuhl für Aerodynamik und Strömungsmechanik der Technischen Universität München. All denen, die mich auf diesem Weg bis hierher unterstützt haben, möchte ich herzlich danken. Besonders möchte ich mich bei meinem Doktorvater Herrn apl. Prof. Dr.-Ing. Christian Breitsamter für die ausgezeichnete Betreuung und die vielen wertvollen Ratschläge bedanken. Ebenfalls bedanke ich mich bei Herrn Univ.-Prof. Dr.-Ing. Mirko Hornung, der die Aufgabe des Zweitprüfers übernommen hat, und Herrn Univ.-Prof. Dr.-Ing. Manfred Hajek für die Übernahme des Prüfungsvorsitzes. Ein großer Dank geht an meine Kollegen, die meine Zeit am Lehrstuhl durch die großartige Atmosphäre sehr angenehm machten und mich mittels ausgiebiger Diskussionen fachlich voranbrachten. Der Lehrstuhlwerkstatt gebührt ebenfalls Dank, insbesondere für die Hilfe bei den anspruchsvollen CNC-Fertigungsarbeiten und für die Wartung der Messtechnik. Des Weiteren möchte ich mich herzlichst bei meiner Familie für all das bedanken, was sie mir auf den Weg gegeben hat. Widmen möchte ich diese Arbeit meiner Frau Michaela Jung, die durch Ihre umfangreiche menschliche Unterstützung ganz maßgeblich zum Gelingen der Arbeit beigetragen hat. Eching, März 2012 Ulrich Sebastian Jung ABSTRACT With the exponential increase of commercial air traffic, methods for reducing perceived noise in airport vicinities are urgently required. Steep approaches have been identified as one feasible means of achieving the desired magnitude of noise reduction. In addition to this, steep approaches can help to increase airport capacities and enable operation into airports surrounded by large buildings or mountains. This thesis makes its contribution to the field by evaluating the applicability of four novel aerodynamic devices for use in steep approaches of commercial transport aircraft. It begins by unpacking the legislatory and political conditions surrounding air traffic noise reduction and steep approach, surveying the leading edge research and outlining the thesis’s specific contribution to the field. The necessary theoretical background knowledge is then gathered. Subsequently, experimental and numerical methods are introduced. The investigations conducted on the basis of these methods and the findings drawn from them are then reported on. The devices under investigation can all be seamlessly integrated into the wing of a commercial transport aircraft through a straight-forward modification of their existing aileron system and spoiler system, respectively. In order to evaluate the relevant steep approach parameters, they are compared with a Baseline configuration - the Baseline being defined as the approach configuration without deployed air brakes. Analogously, conventional spoilers are investigated to provide an additional basis for comparison. The steep approach effectiveness of the devices is evaluated through force measurements. To visualize the flow topology and thereby understand the flow physics underlying the achieved steep approach parameters, flow visualization methods and computational fluid dynamic simulations are utilized. The flow visualization methods utilized comprise tuft flow visualization, stereoscopic particle image velocimetry, and hot wire anemometry. All results gathered are evaluated in a synthesis section per results chapter. Taking these syntheses together, it is concluded that none of the investigated aerodynamic devices alone is best suited for conducting steep approaches. Instead, suitability depends on the desired additional descent angle and the acceptable penalty in approach velocity. For low values of both parameters, one of either novel aileron device is feasible. While for the higher values, one of the two spoiler devices under investigation, as well as the conventional spoiler are superior. To address the feasibility of using these devices with regard to possible horizontal tail plane buffet issues, a thorough investigation of the wing wake is also reported on. The main outcome from this wake investigation is that none of the investigated spoiler-devices pose a higher risk for horizontal tail plain buffet than the standard equivalents tested. ÜBERSICHT Da der kommerzielle Luftverkehr exponentiell wächst, sind Maßnahmen zur Reduktion des dadurch verursachten Lärms in der Umgebung von Flughäfen dringend erforderlich. Als eine Maßnahme, die die erforderliche Größenordnung an Lärmreduktion bewirken kann, wird das Steilanflugverfahren betrachtet. Außerdem kann mit dem Steilanflugverfahren zusätzlich die Flughafenkapazität vergrößert werden und es ermöglicht Operationen an Flughäfen, die von hohen Gebäuden und Bergen umgeben sind. Zu Beginn dieser Arbeit werden die Gründe für Steilanflüge weiter herausgearbeitet und der Stand der Technik zusammengefasst. Anschließend wird der Beitrag dieser Arbeit zum Forschungsgebiet erläutert und die zugehörigen theoretischen Hintergrundinformationen erarbeitet. Die in der Arbeit angewandten experimentellen und numerischen Methoden werden erläutert. Auf Basis dieser Methoden wurden sowohl experimentelle, als auch numerische Untersuchungen durchgeführt, um die Eignung von neuartigen aerodynamischen Steuerflächen zur Durchführung von Steilanflügen durch Verkehrsflugzeuge zu bewerten. Alle untersuchten neuartigen Steuerflächen haben gemein, dass sie direkt in den Flügel einer bestehenden Verkehrsflugzeugkonfiguration integriert werden können. Dabei ersetzen sie vorhandene Spoiler und das Querruder. Um die Effektivität zur Durchführung von Steilanflügen zu bewerten, dienen Kraftmessungen im Windkanal. Auch die unveränderte Verkehrsflugzeugkonfiguration wurde vermessen und dient als Grundlage dieser Bewertung. Zusätzlich wurden konventionelle Spoiler als Vergleichsbasis untersucht. Um die durch die verschiedenen Steuerflächen verursachte Strömungstopologie zu untersuchen, wurde die Strömung mittels Fadensonden, stereoskopischer Particle Image Velocimetry und Hitzdrahtanemometrie vermessen. Außerdem dienten dazu die Untersuchungen mittels numerischer Strömungssimulation. Um beim Einsatz der untersuchten Steuerflächen auch das Risiko des Auftretens von Höhenleitwerks-Buffeting zu bewerten, wurde der Nachlauf im Windkanal untersucht. Alle ermittelten Ergebnisse sind pro Kapitel jeweils in einer Synthese zusammengefasst. In Summe kann gefolgert werden, dass keine der untersuchten Steuerflächentypen in jedem Fall am besten abschneidet. Viel mehr kommt es darauf an, welche Größenordnung die wichtigsten Steilanflugparameter – Vergrößerung des Anflugwinkels und der Anfluggeschwindigkeit – erreichen sollen. Für jeweils niedrige Werte der beiden Parameter eignen sich die neuartigen Querruder am besten, bei höheren Werten schneiden die konventionellen Spoiler sowie einer der beiden unkonventionellen Spoilertypen am besten ab. Des Weiteren zeigen die Nachlaufuntersuchungen, dass keines der untersuchten Spoilersysteme ein erhöhtes Risiko für Höhenleitwerks-Buffeting birgt. CONTENTS LIST OF FIGURES .........................................................................................................VII LIST OF TABLES ........................................................................................................... XV NOMENCLATURE ...................................................................................................... XVII 1. INTRODUCTION ........................................................................................................ 1 1.1 Motivation and Purpose of the Study .......................................................................... 1 1.2 Current Research into the Field .................................................................................. 2 1.3 Contribution of This Work and Thesis Overview ....................................................... 5 2. THEORETICAL BACKGROUND ............................................................................ 7 2.1 Steep Approach Operations ........................................................................................ 7 2.1.1 Approach Operations in General ....................................................................................... 8 2.1.2 Necessity to Conduct Steep Approaches ........................................................................... 9 2.1.3 Requirements for Steep Approach Operations ................................................................ 10 2.1.4 Measures to Achieve Steep Approach Capabilities ......................................................... 11 2.1.5 Steep Approach Capable Aircraft .................................................................................... 12 2.2 Transport Aircraft Wing ............................................................................................ 12 2.2.1 Cruise Flight Wing ..........................................................................................................
Load more

Recommended publications
  • Evaluation and Flight Assessment of a Scale Glider
    Dissertations and Theses 8-2014 Evaluation and Flight Assessment of a Scale Glider Alvydas Anthony Civinskas Embry-Riddle Aeronautical University - Daytona Beach Follow this and additional works at: https://commons.erau.edu/edt Part of the Aerospace Engineering Commons Scholarly Commons Citation Civinskas, Alvydas Anthony, "Evaluation and Flight Assessment of a Scale Glider" (2014). Dissertations and Theses. 41. https://commons.erau.edu/edt/41 This Thesis - Open Access is brought to you for free and open access by Scholarly Commons. It has been accepted for inclusion in Dissertations and Theses by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. Evaluation and Flight Assessment of a Scale Glider by Alvydas Anthony Civinskas A Thesis Submitted to the College of Engineering Department of Aerospace Engineering in Partial Fulfillment of the Requirements for the Degree of Master of Science in Aerospace Engineering Embry-Riddle Aeronautical University Daytona Beach, Florida August 2014 Acknowledgements The first person I would like to thank is my committee chair Dr. William Engblom for all the help, guidance, energy, and time he put into helping me. I would also like to thank Dr. Hever Moncayo for giving up his time, patience, and knowledge about flight dynamics and testing. Without them, this project would not have materialized nor survived the many bumps in the road. Secondly, I would like to thank the RC pilot Daniel Harrison for his time and effort in taking up the risky and stressful work of piloting. Individuals like Jordan Beckwith and Travis Billette cannot be forgotten for their numerous contributions in getting the motor test stand made and helping in creating the air data boom pod so that test data.
    [Show full text]
  • The Difference Between Higher and Lower Flap Setting Configurations May Seem Small, but at Today's Fuel Prices the Savings Can Be Substantial
    THE DIFFERENCE BETWEEN HIGHER AND LOWER FLAP SETTING CONFIGURATIONS MAY SEEM SMALL, BUT AT TODAY'S FUEL PRICES THE SAVINGS CAN BE SUBSTANTIAL. 24 AERO QUARTERLY QTR_04 | 08 Fuel Conservation Strategies: Takeoff and Climb By William Roberson, Senior Safety Pilot, Flight Operations; and James A. Johns, Flight Operations Engineer, Flight Operations Engineering This article is the third in a series exploring fuel conservation strategies. Every takeoff is an opportunity to save fuel. If each takeoff and climb is performed efficiently, an airline can realize significant savings over time. But what constitutes an efficient takeoff? How should a climb be executed for maximum fuel savings? The most efficient flights actually begin long before the airplane is cleared for takeoff. This article discusses strategies for fuel savings But times have clearly changed. Jet fuel prices fuel burn from brake release to a pressure altitude during the takeoff and climb phases of flight. have increased over five times from 1990 to 2008. of 10,000 feet (3,048 meters), assuming an accel­ Subse quent articles in this series will deal with At this time, fuel is about 40 percent of a typical eration altitude of 3,000 feet (914 meters) above the descent, approach, and landing phases of airline’s total operating cost. As a result, airlines ground level (AGL). In all cases, however, the flap flight, as well as auxiliary­power­unit usage are reviewing all phases of flight to determine how setting must be appropriate for the situation to strategies. The first article in this series, “Cost fuel burn savings can be gained in each phase ensure airplane safety.
    [Show full text]
  • Electrically Heated Composite Leading Edges for Aircraft Anti-Icing Applications”
    UNIVERSITY OF NAPLES “FEDERICO II” PhD course in Aerospace, Naval and Quality Engineering PhD Thesis in Aerospace Engineering “ELECTRICALLY HEATED COMPOSITE LEADING EDGES FOR AIRCRAFT ANTI-ICING APPLICATIONS” by Francesco De Rosa 2010 To my girlfriend Tiziana for her patience and understanding precious and rare human virtues University of Naples Federico II Department of Aerospace Engineering DIAS PhD Thesis in Aerospace Engineering Author: F. De Rosa Tutor: Prof. G.P. Russo PhD course in Aerospace, Naval and Quality Engineering XXIII PhD course in Aerospace Engineering, 2008-2010 PhD course coordinator: Prof. A. Moccia ___________________________________________________________________________ Francesco De Rosa - Electrically Heated Composite Leading Edges for Aircraft Anti-Icing Applications 2 Abstract An investigation was conducted in the Aerospace Engineering Department (DIAS) at Federico II University of Naples aiming to evaluate the feasibility and the performance of an electrically heated composite leading edge for anti-icing and de-icing applications. A 283 [mm] chord NACA0012 airfoil prototype was designed, manufactured and equipped with an High Temperature composite leading edge with embedded Ni-Cr heating element. The heating element was fed by a DC power supply unit and the average power densities supplied to the leading edge were ranging 1.0 to 30.0 [kW m-2]. The present investigation focused on thermal tests experimentally performed under fixed icing conditions with zero AOA, Mach=0.2, total temperature of -20 [°C], liquid water content LWC=0.6 [g m-3] and average mean volume droplet diameter MVD=35 [µm]. These fixed conditions represented the top icing performance of the Icing Flow Facility (IFF) available at DIAS and therefore it has represented the “sizing design case” for the tested prototype.
    [Show full text]
  • Ai2019-2 Aircraft Serious Incident Investigation Report
    AI2019-2 AIRCRAFT SERIOUS INCIDENT INVESTIGATION REPORT ACADEMIC CORPORATE BODY JAPAN AVIATION ACADEMY J A 2 4 5 1 March 28, 2019 The objective of the investigation conducted by the Japan Transport Safety Board in accordance with the Act for Establishment of the Japan Transport Safety Board and with Annex 13 to the Convention on International Civil Aviation is to prevent future accidents and incidents. It is not the purpose of the investigation to apportion blame or liability. Kazuhiro Nakahashi Chairman Japan Transport Safety Board Note: This report is a translation of the Japanese original investigation report. The text in Japanese shall prevail in the interpretation of the report. AIRCRAFT SERIOUS INCIDENT INVESTIGATION REPORT INABILITY TO OPERATE DUE TO DAMAGE TO LANDING GEAR DURING FORCED LANDING ON A GRASSY FIELD ABOUT 3 KM SOUTHWEST OF NOTO AIRPORT, JAPAN AT ABOUT 15:00 JST, SEPTEMBER 26, 2018 ACADEMIC CORPORATE BODY JAPAN AVIATION ACADEMY VALENTIN TAIFUN 17EII (MOTOR GLIDER: TWO SEATER), JA2451 February 22, 2019 Adopted by the Japan Transport Safety Board Chairman Kazuhiro Nakahashi Member Toru Miyashita Member Toshiyuki Ishikawa Member Yuichi Marui Member Keiji Tanaka Member Miwa Nakanishi 1. PROCESS AND PROGRESS OF THE INVESTIGATION 1.1 Summary of On Wednesday, September 26, 2018, a Valentin Taifun 17EII (motor the Serious glider), registered JA2451, owned by Japan Aviation Academy, took off from Incident Noto Airport in order to make a test flight before the airworthiness inspection. During the flight, as causing trouble in its electric system, the aircraft tried to return to Noto Airport by gliding, but made a forced landing on a grassy field about 3 km short of Noto Airport, and sustained damage to the landing gear, therefore, the operation of the aircraft could not be continued.
    [Show full text]
  • Hoffmann Aircraft
    HOFFMANN AIRCRAFT HOFFMANN AIRCRAFT CORP P.0: Box No. 100 A-1214 Vienna Austria Phone (0 22 2/39 88 18 or 39 89 05 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS H36 DIMONA This Service and Maintenance Manual is for U.S. registered gliders. (Type Certificate Data Sheet No.: ………………….EU) Reg. No.:……………………… Ser. No.. ……………………………. Owner: …………………………………………………………………. ………………………………………………………………….. ………………………………………………………………….. Published 15 Nov 1985 Approval of translation has been done by best knowledge and judgment. In any case the original text in German language is authoritative. —1— Hoffmann General H 36 DIMONA 1. GENERAL: Table of contents Page 1. General ------------------------------------ 1 2. List of Revisions --------------------------- 2 3. System Description -------------------------- 3 4. Maintenance and Inspections --------- 23 5. Rigging ------------------------------------ 35 6. Weight and Balance --------------------------- 39 7 . Servicing ------------------------------------ 42 8. Repair ------------------------------------ 45 9. Table of consumables ------------------ 57 10. Airworthiness Limitations ------------------ 60 -2- Hoffmann Revisions H 36 Dimona 2. REVISIONS: 2. Revisions . Revision No Affected Pages Source Date Signature -3- Hoffmann Systems H 36 Dimona Description 3. SYSTEMS DESCRIPTION: Table of Contents Paragraph page 3.1 FLIGHT CONTROLS ------------------ 4 3.2 AIRBRAKES & WHEEL-BRAKES --- 5 3.3 TRIM UNIT ------------------------------- 5 3.4 FUEL SYSTEM ---------------------- 10 3.5 POWER PLANT ----------------------
    [Show full text]
  • A Flight Simulation Study of the Simultaneous Non-Interfering
    A FLIGHT SIMULATION STUDY OF THE SIMULTANEOUS NON-INTERFERING AIRCRAFT APPROACH A Thesis presented to the Faculty of California Polytechnic State University, San Luis Obispo In Partial Fulfillment of the Requirements for the Degree Master of Science in Aerospace Engineering by Brian Reel May 2009 © 2009 Brian Hogan Reel ALL RIGHTS RESERVED ii COMMITTEE MEMBERSHIP TITLE: A Flight Simulation Study of the Simultaneous Non-Interfering Aircraft Approach AUTHOR: Brian Hogan Reel DATE SUBMITTED: May 2009 COMMITTEE CHAIR: Dr. Daniel Biezad, Cal Poly Aerospace Engineering COMMITTEE MEMBER: Craig Hange, NASA AMES COMMITTEE MEMBER: Dr. Eric Mehiel, Cal Poly Aerospace Engineering COMMITTEE MEMBER: Dr. Frank Owen, Cal Poly Mechanical Engineering COMMITTEE MEMBER: Dr. Kurt Colvin, Cal Poly Industrial/Manufacturing Engineering iii ABSTRACT A Flight Simulation Study of the Simultaneous Non-Interfering Aircraft Approach Brian Hogan Reel Using a new implementation of a NASA flight simulation of the Quiet Short-Haul Research Aircraft, autopilots were designed to be capable of flying both straight in (ILS) approaches, and circling (SNI) approaches. A standard glideslope coupler was sufficient for most conditions, but a standard Proportional-Integral-Derivative (PID) based localizer tracker was not sufficient for maintaining a lateral track on the SNI course. To track the SNI course, a feed-forward system, using GPS steering provided much better results. NASA and the FAA embrace the concept of a Simultaneous, Non-Interfering (SNI) approach as a way to increase airport throughput while reducing the noise footprints of aircraft on approach. The NASA concept for the SNI approach for Short Takeoff and Landing (STOL) aircraft involves a straight in segment flown above the flight path of a normal approach, followed by a spiraling descent to the runway.
    [Show full text]
  • Fly-By-Wire - Wikipedia, the Free Encyclopedia 11-8-20 下午5:33 Fly-By-Wire from Wikipedia, the Free Encyclopedia
    Fly-by-wire - Wikipedia, the free encyclopedia 11-8-20 下午5:33 Fly-by-wire From Wikipedia, the free encyclopedia Fly-by-wire (FBW) is a system that replaces the Fly-by-wire conventional manual flight controls of an aircraft with an electronic interface. The movements of flight controls are converted to electronic signals transmitted by wires (hence the fly-by-wire term), and flight control computers determine how to move the actuators at each control surface to provide the ordered response. The fly-by-wire system also allows automatic signals sent by the aircraft's computers to perform functions without the pilot's input, as in systems that automatically help stabilize the aircraft.[1] Contents Green colored flight control wiring of a test aircraft 1 Development 1.1 Basic operation 1.1.1 Command 1.1.2 Automatic Stability Systems 1.2 Safety and redundancy 1.3 Weight saving 1.4 History 2 Analog systems 3 Digital systems 3.1 Applications 3.2 Legislation 3.3 Redundancy 3.4 Airbus/Boeing 4 Engine digital control 5 Further developments 5.1 Fly-by-optics 5.2 Power-by-wire 5.3 Fly-by-wireless 5.4 Intelligent Flight Control System 6 See also 7 References 8 External links Development http://en.wikipedia.org/wiki/Fly-by-wire Page 1 of 9 Fly-by-wire - Wikipedia, the free encyclopedia 11-8-20 下午5:33 Mechanical and hydro-mechanical flight control systems are relatively heavy and require careful routing of flight control cables through the aircraft by systems of pulleys, cranks, tension cables and hydraulic pipes.
    [Show full text]
  • Effects of Aircraft Integration on Compact Nacelle Aerodynamics
    Eects of Aircraft Integration on Compact Nacelle Aerodynamics Fernando Tejeroa,∗, Ioannis Goulosa, David G MacManusa, Christopher Sheafb aCentre for Propulsion Engineering, School of Aerospace, Transport and Manufacturing, Craneld University, Bedfordshire, MK43 0AL bRolls-Royce plc., P.O. box 31, Derby, United Kingdom, DE24 8BJ Abstract To reduce specic fuel consumption, it is expected that the next generation of aero-engines will operate with higher bypass-ratios, and therefore fan diame- ters, than current in-service architectures. These new propulsion systems will increase the nacelle size and incur in an additional overall weight and drag con- tribution to the aircraft. In addition, they will be installed more closely-coupled with the airframe, which may lead to an increase in adverse installation eects. As such, it is required to develop compact nacelles which will not counteract the benets obtained from the new engine cycles. A comprehensive investigation of the eects of nacelle design on the overall aircraft aerodynamic performance is required for a better understanding on the eects of aero-engine integration. This paper presents a method for the multi-objective optimisation of drooped and scarfed non-axisymmetric nacelle aero-engines. It uses intuitive Class Shape Tranformations (iCSTs) for the aero-engine geometry denition, multi-point aerodynamic simulation, a near-eld nacelle drag extraction method and the NSGA-II genetic algorithm. The process has been employed for the aerody- namic optimisation of a compact nacelle aero-engine as well as a conventional nacelle conguration. Subsequently, the designed architectures were installed on a conventional commercial transport aircraft and evaluated at dierent in- stallation positions.
    [Show full text]
  • Glider Handbook, Chapter 2: Components and Systems
    Chapter 2 Components and Systems Introduction Although gliders come in an array of shapes and sizes, the basic design features of most gliders are fundamentally the same. All gliders conform to the aerodynamic principles that make flight possible. When air flows over the wings of a glider, the wings produce a force called lift that allows the aircraft to stay aloft. Glider wings are designed to produce maximum lift with minimum drag. 2-1 Glider Design With each generation of new materials and development and improvements in aerodynamics, the performance of gliders The earlier gliders were made mainly of wood with metal has increased. One measure of performance is glide ratio. A fastenings, stays, and control cables. Subsequent designs glide ratio of 30:1 means that in smooth air a glider can travel led to a fuselage made of fabric-covered steel tubing forward 30 feet while only losing 1 foot of altitude. Glide glued to wood and fabric wings for lightness and strength. ratio is discussed further in Chapter 5, Glider Performance. New materials, such as carbon fiber, fiberglass, glass reinforced plastic (GRP), and Kevlar® are now being used Due to the critical role that aerodynamic efficiency plays in to developed stronger and lighter gliders. Modern gliders the performance of a glider, gliders often have aerodynamic are usually designed by computer-aided software to increase features seldom found in other aircraft. The wings of a modern performance. The first glider to use fiberglass extensively racing glider have a specially designed low-drag laminar flow was the Akaflieg Stuttgart FS-24 Phönix, which first flew airfoil.
    [Show full text]
  • Using an Autothrottle to Compare Techniques for Saving Fuel on A
    Iowa State University Capstones, Theses and Graduate Theses and Dissertations Dissertations 2010 Using an autothrottle ot compare techniques for saving fuel on a regional jet aircraft Rebecca Marie Johnson Iowa State University Follow this and additional works at: https://lib.dr.iastate.edu/etd Part of the Electrical and Computer Engineering Commons Recommended Citation Johnson, Rebecca Marie, "Using an autothrottle ot compare techniques for saving fuel on a regional jet aircraft" (2010). Graduate Theses and Dissertations. 11358. https://lib.dr.iastate.edu/etd/11358 This Thesis is brought to you for free and open access by the Iowa State University Capstones, Theses and Dissertations at Iowa State University Digital Repository. It has been accepted for inclusion in Graduate Theses and Dissertations by an authorized administrator of Iowa State University Digital Repository. For more information, please contact [email protected]. Using an autothrottle to compare techniques for saving fuel on A regional jet aircraft by Rebecca Marie Johnson A thesis submitted to the graduate faculty in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE Major: Electrical Engineering Program of Study Committee: Umesh Vaidya, Major Professor Qingze Zou Baskar Ganapathayasubramanian Iowa State University Ames, Iowa 2010 Copyright c Rebecca Marie Johnson, 2010. All rights reserved. ii DEDICATION I gratefully acknowledge everyone who contributed to the successful completion of this research. Bill Piche, my supervisor at Rockwell Collins, was supportive from day one, as were many of my colleagues. I also appreciate the efforts of my thesis committee, Drs. Umesh Vaidya, Qingze Zou, and Baskar Ganapathayasubramanian. I would also like to thank Dr.
    [Show full text]
  • Kaman Corporation · Annual Report 2016 Powering the Future Corporate and Shareholder Information Kaman Corporation and Subsidiaries
    PEOPLE POWERING THE FUTURE KAMAN CORPORATION · ANNUAL REPORT 2016 POWERING THE FUTURE CORPORATE AND SHAREHOLDER INFORMATION KAMAN CORPORATION AND SUBSIDIARIES CORPORATE HEADQUARTERS Kaman Corporation 1332 Blue Hills Avenue Bloomfield, Connecticut 06002 (860) 243-7100 STOCK LISTING Kaman Corporation’s common stock is traded on the New York Stock Exchange under the symbol KAMN. INVESTOR, MEDIA, AND PUBLIC RELATIONS CONTACT Eric B. Remington Vice President, Investor Relations (860) 243-6334 [email protected] ANNUAL MEETING The Annual Meeting of Shareholders is scheduled to be held on Wednesday, April 19, 2017 at 9:00 am local time at the offices of the Company, 1332 Blue Hills Avenue, Bloomfield, Connecticut, 06002. TRANSFER AGENT Computershare P.O. Box 30170 College Station, Texas 77842-3170 (866) 339-2742 www.computershare.com/investor Overnight correspondence should be sent to: Computershare 211 Quality Circle, Suite 210 College Station, Texas 77845 PEOPLE POWERING INNOVATION PEOPLE POWERING VALUE-ADDED SOLUTIONS PEOPLE POWERING GLOBAL SUCCESS PEOPLE POWERING NEW RELATIONSHIPS PEOPLE POWERING KAMAN KAMAN ANNUAL REPORT 2016 1 “ When I consider the future of Kaman, it’s the people who inspire the most confi dence in our continued success. We have an exceptional team across all of our businesses. They are truly the future of this company.” Neal J. Keating Chairman, President and Chief Executive Offi cer DEAR SHAREHOLDERS, When thinking about Kaman’s future, what excites me delivering outstanding experiences to our customers, most is not our products, solutions, technologies, and resulting in record satisfaction scores. In Aerospace, infrastructure, important as these are to our continued strong growth put pressure on our people to step up success.
    [Show full text]
  • Propulsion and Flight Controls Integration for the Blended Wing Body Aircraft
    Cranfield University Naveed ur Rahman Propulsion and Flight Controls Integration for the Blended Wing Body Aircraft School of Engineering PhD Thesis Cranfield University Department of Aerospace Sciences School of Engineering PhD Thesis Academic Year 2008-09 Naveed ur Rahman Propulsion and Flight Controls Integration for the Blended Wing Body Aircraft Supervisor: Dr James F. Whidborne May 2009 c Cranfield University 2009. All rights reserved. No part of this publication may be reproduced without the written permission of the copyright owner. Abstract The Blended Wing Body (BWB) aircraft offers a number of aerodynamic perfor- mance advantages when compared with conventional configurations. However, while operating at low airspeeds with nominal static margins, the controls on the BWB aircraft begin to saturate and the dynamic performance gets sluggish. Augmenta- tion of aerodynamic controls with the propulsion system is therefore considered in this research. Two aspects were of interest, namely thrust vectoring (TVC) and flap blowing. An aerodynamic model for the BWB aircraft with blown flap effects was formulated using empirical and vortex lattice methods and then integrated with a three spool Trent 500 turbofan engine model. The objectives were to estimate the effect of vectored thrust and engine bleed on its performance and to ascertain the corresponding gains in aerodynamic control effectiveness. To enhance control effectiveness, both internally and external blown flaps were sim- ulated. For a full span internally blown flap (IBF) arrangement using IPC flow, the amount of bleed mass flow and consequently the achievable blowing coefficients are limited. For IBF, the pitch control effectiveness was shown to increase by 18% at low airspeeds.
    [Show full text]