Aircraft De-Icing/Anti-Icing
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Cranfield University Xue Longxian Actuation
CRANFIELD UNIVERSITY XUE LONGXIAN ACTUATION TECHNOLOGY FOR FLIGHT CONTROL SYSTEM ON CIVIL AIRCRAFT SCHOOL OF ENGINEERING MSc by Research THESIS CRANFIELD UNIVERSITY SCHOOL OF ENGINEERING MSc by Research THESIS Academic Year 2008-2009 XUE LONGXIAN Actuation Technology for Flight Control System on Civil Aircraft Supervisor: Dr. C. P. Lawson Prof. J. P. Fielding January 2009 This thesis is submitted in fulfilment of the requirements for the degree of Master of Science © Cranfield University 2009. All rights reserved. No part of this publication may be reproduced without the written permission of the copyright owner. ABSTRACT This report addresses the author’s Group Design Project (GDP) and Individual Research Project (IRP). The IRP is discussed primarily herein, presenting the actuation technology for the Flight Control System (FCS) on civil aircraft. Actuation technology is one of the key technologies for next generation More Electric Aircraft (MEA) and All Electric Aircraft (AEA); it is also an important input for the preliminary design of the Flying Crane, the aircraft designed in the author’s GDP. Information regarding actuation technologies is investigated firstly. After initial comparison and engineering consideration, Electrohydrostatic Actuation (EHA) and variable area actuation are selected for further research. The tail unit of the Flying Crane is selected as the case study flight control surfaces and is analysed for the requirements. Based on these requirements, an EHA system and a variable area actuation system powered by localised hydraulic systems are designed and sized in terms of power, mass and Thermal Management System (TMS), and thereafter the reliability of each system is estimated and the safety is analysed. -
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. -
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. -
Self-Actuating Flaps on Bird and Aircraft Wings 437
Self-actuating flaps on bird and aircraft wings D.W. Bechert, W. Hage & R. Meyer Department of Turbulence Research, German Aerospace Center (DLR), Berlin, Germany. Abstract Separation control is also an important issue in biology. During the landing approach of birds and in flight through very turbulent air, one observes that the covering feathers on the upper side of bird wings tend to pop up. The raised feathers impede the spreading of the flow separation from the trailing edge to the leading edge of the wing. This mechanism of separation control by bird feathers is described in detail. Self-activated movable flaps (= artificial bird feathers) represent a high-lift system enhancing the maximum lift of airfoils up to 20%. This is achieved without perceivable deleterious effects under cruise conditions. Several data of wind tunnel experiments as well as flight experiments with an aircraft with laminar wing and movable flaps are shown. 1 Movable flaps on wings: artificial bird feathers The issue of artificial feathers on wings, has an almost anecdotal origin. Wolfgang Liebe, the inventor of the boundary layer fence once observed mountain crows in the Alps in the 1930s. He noticed that the covering feathers on the upper side of the wings tend to pop up when the birds were on landing approach or in other situations with high angle of attack, like flight through gusts. Once the attention of the observer is drawn to it, it is comparatively easy to observe this behaviour in almost any bird (see, for example, the feathers on the left-hand wing of a Skua in Fig. -
Auxiliary Power Unit / Environmental Control Unit (APU/ECU) for the Multiple Launch Rocket System
Auxiliary Power Unit / Environmental Control Unit (APU/ECU) for the Multiple Launch Rocket System Multiple Launch Rocket System (MLRS) APU KEY FEATURES: − 8.5 kW 28 VDC Power Output − 18,500 BTU Net Cooling Capacity ECU Condenser GENERAL PRODUCT DESCRIPTION: The MLS Auxiliary Power Unit brushless, permanent magnet conditions. /Environmental Control Unit generator. The generator system (APU/ECU) has been designed to output and Engine power is The APU gross weight is under provide electrical power and controlled by a variable speed 330 pounds with the ECU cooling to the MLRS tracked governor which, depending on weighing 150 lbs. The System vehicle. Both systems can operate system load, optimizes the engine provides 18,500 Btu/hr cooling independently of one another. The operating speed. The vapor cycle capacity and 8.5 kW at 28-vDC ECU is completely electrically air conditioning system is power output (with voltage ripple driven and can be operated from designed to be in compliance with independent of the engine speed the main engine alternators or the the current environmental or load at less than 100 mV APU. regulations using R-134a RMS). refrigerant and is capable of The power plant is a Hatz 2G-40 operating in severe desert air-cooled diesel engine with a conditions. Its power draw is 150 shaft mounted three-phase amps at 28-vDC at full load APU/ECU FOR MILITARY APPLICATIONS Auxiliary Power Unit / Environmental Control Unit (APU/ECU) for the Multiple Launch Rocket System Condenser Assembly APU Evaporator Assembly Overall APU/ECU Specifications: Exterior Dimensions (L x W x H)........................................…........... -
Design of a Flight Stabilizer System and Automatic Control Using HIL Test Platform
International Journal of Mechanical Engineering and Robotics Research Vol. 5, No. 1, January 2016 Design of a Flight Stabilizer System and Automatic Control Using HIL Test Platform Şeyma Akyürek, Gizem Sezin Özden, Emre Atlas, and Coşku Kasnakoğlu Electrical & Electronics Engineering, TOBB University of Economics & Technology, Ankara, Turkey Email: {seymaakyurek , sezin.ozden, emreatlas90, kasnakoglu}@gmail.com Ünver Kaynak Mechanical Engineering, TOBB University of Economics & Technology, Ankara, Turkey Email: [email protected] Abstract—In this paper a Hardware-In-the-Loop (HIL) test Both manual calibration and MATLAB’s automated platform is used to design a flight stabilization system for design tools are used to determine the PID coefficients. Unmanned Aerial Vehicles (UAV). Controllers are first designed and tested separately for lateral and longitudinal II. DESIGN STAGES axes using numerical simulations, and later these controllers are merged on the HIL platform. It is observed that the A. Controller Design resulting controller successfully stabilizes the aircraft to A general treatment of the stability and control of achieve straight and level flight. airplanes requires a study of the dynamics of flight [4]. Much useful information can be obtained, however, from Index Terms—UAV, autopilot, PID controller, Hardware-In- a more limited view, in which we consider not the motion the-Loop, flight control, SISO, MIMO of the airplane, but only its equilibrium states. This is the approach in what is commonly known as static stability and control analysis [4]. I. INTRODUCTION Elevators and ailerons are flight control surfaces. Elevators are surfaces on the tailplane (the horizontal part Aeronautics has recently gained great importance in of the tail assembly). -
Flexfloil Shape Adaptive Control Surfaces—Flight Test and Numerical Results
FLEXFLOIL SHAPE ADAPTIVE CONTROL SURFACES—FLIGHT TEST AND NUMERICAL RESULTS Sridhar Kota∗ , Joaquim R. R. A. Martins∗∗ ∗FlexSys Inc. , ∗∗University of Michigan Keywords: FlexFoil, adaptive compliant trailing edge, flight testing, aerostructural optimization Abstract shape-changing control surface technologies has been realized by the ACTE program in which the The U.S Air Force and NASA recently concluded high-lift flaps of the Gulfstream III test aircraft a series of flight tests, including high speed were replaced by a 19-foot spanwise FlexFoilTM (M = 0:85) and acoustic tests of a Gulfstream III variable-geometry control surfaces on each wing, business jet retrofitted with shape adaptive trail- including a 2 ft wide compliant fairings at each ing edge control surfaces under the Adaptive end, developed by FlexSys Inc. The flight tests Compliant Trailing Edge (ACTE) program. The successfully demonstrated the flight-worthiness long-sought goal of practical, seamless, shape- of the variable geometry control surfaces. changing control surface technologies has been Modern aircraft wings and engines have realized by the ACTE program in which the high- reached near-peak levels of efficiency, making lift flaps of the Gulfstream III test aircraft were further improvements exceedingly difficult. The replaced with 23 ft spanwise FlexFoilTM variable next frontier in improving aircraft efficiency is to geometry control surfaces on each wing. The change the shape of the aircraft wing in-flight to flight tests successfully demonstrated the flight- maximize performance under all operating con- worthiness of the variable geometry control sur- ditions. Modern aircraft wing design is a com- faces. We provide an overview of structural and promise between several constraints and flight systems design requirements, test flight envelope conditions with best performance occurring very (including critical design and test points), re- rarely or purely by chance. -
Lockheed Martin F-35 Lightning II Incorporates Many Significant Technological Enhancements Derived from Predecessor Development Programs
AIAA AVIATION Forum 10.2514/6.2018-3368 June 25-29, 2018, Atlanta, Georgia 2018 Aviation Technology, Integration, and Operations Conference F-35 Air Vehicle Technology Overview Chris Wiegand,1 Bruce A. Bullick,2 Jeffrey A. Catt,3 Jeffrey W. Hamstra,4 Greg P. Walker,5 and Steve Wurth6 Lockheed Martin Aeronautics Company, Fort Worth, TX, 76109, United States of America The Lockheed Martin F-35 Lightning II incorporates many significant technological enhancements derived from predecessor development programs. The X-35 concept demonstrator program incorporated some that were deemed critical to establish the technical credibility and readiness to enter the System Development and Demonstration (SDD) program. Key among them were the elements of the F-35B short takeoff and vertical landing propulsion system using the revolutionary shaft-driven LiftFan® system. However, due to X- 35 schedule constraints and technical risks, the incorporation of some technologies was deferred to the SDD program. This paper provides insight into several of the key air vehicle and propulsion systems technologies selected for incorporation into the F-35. It describes the transition from several highly successful technology development projects to their incorporation into the production aircraft. I. Introduction HE F-35 Lightning II is a true 5th Generation trivariant, multiservice air system. It provides outstanding fighter T class aerodynamic performance, supersonic speed, all-aspect stealth with weapons, and highly integrated and networked avionics. The F-35 aircraft -
Feb. 14, 1939. E
Feb. 14, 1939. E. F. ZA PARKA 2,147,360 AIRPLANE CONTROL APPARATUS Original Filed Feb. 16, 1933 7 Sheets-Sheet Feb. 14, 1939. E. F. ZA PARKA 2,147,360 AIRPLANE CONTROL APPARATUS Original Filed Feb. 16, 1933 7 Sheets-Sheet 2 &tkowys Feb. 14, 1939. E. F. zAPARKA 2,147,360 ARP ANE CONTROL APPARATUS Original Filed Feb. 16, 1933 7 Sheets-Sheet 3 Wr a NSeta ?????? ?????????????? "??" ?????? ??????? 8tkowcA" Feb. 14, 1939. E. F. ZA PARKA 2,147,360 AIRPLANE CONTROL APPARATUS Original Filled Feb. 16, 1933 7 Sheets-Sheet 4 Feb. 14, 1939. E. F. ZA PARKA 2,147,360 AIRPLANE CONTROL APPARATUS Original Filed. Feb. l6, l933 7 Sheets-Sheet 5 3. 8. 2. 3 Feb. 14, 1939. E. F. ZA PARKA 2,147,360 AIRPANE CONTROL APPARATUS Original Filled Feb. 16, 1933 7 Sheets-Sheet 6 M76, az 42a2/22/22a/7 ?tows Feb. 14, 1939. E. F. ZAPARKA 2,147,360 AIRPANE CONTROL APPARATUS Original Filled Feb. l6, l933 7 Sheets-Sheet 7 Jway/7 -ZWAZZ/JAZZA/ Juventor. Zff60 / Ze/7 384 ?r re? Patented Feb. 14, 1939 2,147,360 UNITED STATES PATENT OFFICE AIRPLANE CONTRO APPARATUS Edward F. Zaparka, Baltimore, Md., assignor to Zap Development Corporation, Baltimore, Md., a corporation of Delaware Application February 16, 1933, serial No. 657,133 Renewed February 1, 1937 4. Claims. (CI. 244—42) My invention relates to aircraft construction, parting from the spirit and scope of the appended and in particular relates to the control of aircraft claims, equipped with Wing flaps which Operate in the In order to make my invention more clearly Zone of optimum efficency. -
Amateur-Built Fabrication and Assembly Checklist (2009) (Fixed Wing)
Amateur-Built Fabrication and Assembly Checklist (2009) (Fixed Wing) NOTE: This checklist is only applicable to Name(s) Team Tango fixed wing aircraft. Evaluation of other types of aircraft (i.e., rotorcraft, balloons, Address: 1990 SW 19th Ave. Williston, FL 32696 lighter than air) will not be accomplished Aircraft Model: Foxtrot / Foxtrot ER with this form. Date: 6/23/2010 National Kit Evaluation Team: Tony Peplowski, Steve Remarks: Buczynski, Mike Sloat, Joe Palmisano NOTE: This checklist is invalid for and will This evaluation contains two variants of the Foxtrot aircraft, the base not be used to evaluate an altered or Foxtrot and the extended range (ER) aircraft. The two aircraft are modified type certificated aircraft with the contained in the same parts list and builder's instructions. The ER intent to issue an Experimental Amateur- differences are covered in Appendix 5 of the document. The Foxtrot kit is built Airworthiness Certificate. Such action defined by the Foxtrot 4 Builder’s Manual, “Version 1.1 Dated 5/2010”, violates FAA policy and DOES NOT meet and the Foxtrot Parts List “Version 1.1. dated 5/25/2010.” the intent of § 21.191(g). NOTE: Enter “N/A” in any box where a listed task is not applicable to the particular aircraft being evaluated. Use the “Add item” boxes at the end of each section to add applicable unlisted tasks and award credit. ABCD FABRICATION AND ASSEMBLY TASKS Mfr Kit/Part/ Commercial Am-Builder Am-Builder Component Assistance Assembly Fabrication Task Fuselage – 24 Listed Tasks # F1 Fabricate Longitudinal -
On Aircraft Trailing Edge Noise
NEAT Consulting On Aircraft Trailing Edge Noise Yueping Guo NEAT Consulting, Seal Beach, CA 90740 USA and Russell H. Thomas NASA Langley Research Center, Hampton, VA 23681 USA Future Aircraft Design and Noise Impact 22nd Workshop of the Aeroacoustics Specialists Committee of the CEAS 6 – 7 September 2018 Netherlands Aerospace Centre – Amsterdam Acknowledgments NEAT Consulting • Aircraft Noise Reduction (ANR) Subproject of the Advanced Air Transport Technology (AATT) Project for funding this research 2 Outline NEAT Consulting • Introduction • Trailing edge noise data • Prediction methods • Estimate of HWB trailing edge noise • Summary 3 Introduction NEAT Consulting • Significant noise reduction opportunities for future aircraft have been investigated for the major airframe noise sources • Is trailing edge noise the noise floor? – Need reliable data and/or prediction tool to assess its relative importance • Objectives of this presentation – Review currently available data and prediction methods – Illustrate importance of trailing edge noise for future aircraft by preliminary estimate for the Hybrid-Wing- Body (HWB) aircraft 4 Airframe Noise Reduction NEAT Consulting • Thomas R. H., Burley C.L. and Guo Y. P., “Potential for Landing Gear Noise Reduction on Advanced Aircraft Configurations,” AIAA 2016-3039 • Thomas R. H., Guo Y. P., Berton J. J. and Fernandez H., “Aircraft Noise Reduction Technology Roadmap Toward Achieving the NASA 2035 Noise Goal,” AIAA 2017-3193 • Guo Y. P., Thomas R. H., Clark I.A. and June J.C., “Far Term Noise Reduction -
Ultrasonic Ice Protection Systems
Ultrasonic Ice Protection Systems: Analytical and Numerical Models for Architecture Tradeoff Marc Budinger, Valérie Pommier-Budinger, Gael Napias, Arthur Costa da Silva To cite this version: Marc Budinger, Valérie Pommier-Budinger, Gael Napias, Arthur Costa da Silva. Ultrasonic Ice Pro- tection Systems: Analytical and Numerical Models for Architecture Tradeoff. Journal of Aircraft, American Institute of Aeronautics and Astronautics, 2016, 53 (3), pp.680 - 690. 10.2514/1.C033625. hal-01861799 HAL Id: hal-01861799 https://hal.archives-ouvertes.fr/hal-01861799 Submitted on 25 Aug 2018 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. Ultrasonic ice protection systems: analytical and numerical models for architecture trade-off Marc Budinger(1), Valérie Pommier-Budinger(2), Gael Napias(2), Arthur Costa Da Silva(2) (1) INSA Toulouse, Institut Clément Ader, Toulouse, 31077, France (2) ISAE SUPAERO, Institut Supérieur de l'Aéronautique et de l'Espace, 31055, France ABSTRACT Protection systems against ice conventionally use thermal, pneumatic or electro-thermal solutions. However, they are characterized by high energy consumption. This article focuses on low-consumption electromechanical deicing solutions based on piezoelectric transducers. After a review of the state of the art to identify the main features of electromechanical de-icing devices, piezoelectric transducer-based architectures are studied.