Review Paper on Wing Folding Mechanism
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Design, Analysis and Optimization of Folding Wing Mechanism for Effective Utilization of Air Side Area
ISSN (O): 2393-8609 International Journal of Aerospace and Mechanical Engineering Volume 3 – No.5, September 2016 DESIGN, ANALYSIS AND OPTIMIZATION OF FOLDING WING MECHANISM FOR EFFECTIVE UTILIZATION OF AIR SIDE AREA Dishant Kothia Japneet Singh Akanksha Dadhich University of Petroleum and University of Petroleum and University of Petroleum and Energy Studies, Dehradun Energy Studies, Dehradun Energy Studies, Dehradun [email protected] [email protected] akankshadadhich4@gmai om l.com ABSTRACT ground operations altogether, a folding wing design has been This paper aims to suggest a solution for the problem of employed to Boeing 787. disproportionately lesser growth of airside space with respect to growth of passengers/air traffic by using wing folding 2. LITERARY REVIEW mechanism in aircrafts while on ground. A study of air traffic A study was done for past World War-2 era mechanisms, growth was followed by selecting STO-wing mechanism currently used mechanisms in small private aircrafts and also which met with desired requirements. spring loaded mechanisms used in some modern cruise missiles. The naval helicopters and the ship-borne aircraft- Boeing 787-8 Dreamliner was selected as base aircraft as it carriers have been the pioneer, in the sphere of foldable main- met certain criterion and analysis for mechanism was started. planes and tail-planes. Many patents have been created by the Different mechanisms of implementing STO-wing are leading designers and manufacturers. The merits and demand discussed, and calculation for rod-lug mechanism which was of a folding wing mechanism to potentially cease the ill- finally chosen is shown. Its FEM analysis was carried out in effects of traffic growth in aviation industry have paved the ANSYS 14.5 along with mesh sensitivity study. -
Conceptual Design of Self-Expanding/Folding Extremely Large Aspect Ratio Wing Airplane
DOI: 10.13009/EUCASS2017-209 7TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) Conceptual Design of Self-Expanding/Folding Extremely Large Aspect Ratio Wing Airplane Zhou Xiaopeng* and Chen Haixin* * School of Aerospace Engineering, Tsinghua University Beijing, China Abstract This paper puts forward the idea of self-expanding/folding wing and makes a preliminary conceptual design of extremely large aspect ratio airplane based on this idea. The expanding and folding process in flight is carried out by the movement of the rudder surfaces, the adjustment of distributed propulsion system and the active flight control technology. The preliminary conceptual design and performance analysis indicates that the extremely large aspect ratio airplane based on self-expanding/folding wing can obviously improve the airplane’s airport runway adaptability, take-off and landing performance, keeping a high cruise lift-drag ratio, with acceptable increasing of take-off weight. 1. Introduction 1.1 Requirement for extremely large aspect ratio wing Reducing drag has always been one of the first considerations in aircraft design process. The extremely large aspect ratio wing has great advantages in cutting down induced drag, which leading to widely applications in glider, long- endurance UAV, high-altitude launch aircraft and other aircrafts. Finding out a suitable configuration to carry out the extremely large aspect ratio wing, keeping the advantages and overcoming the shortcomings, is the focus of high- altitude long-endurance aircraft and other similar aircrafts design. 1.2 Implement methods of extremely large aspect ratio wing airplane The increasing wingspan of conventional cantilever wings is limited by the conditions for take-off and landing of airport runways, poor flight conditions of lower atmosphere owing to unstable airflow, structural strength and rigidity of aircraft, and flight handling qualities. -
Aircraft Technology Roadmap to 2050 | IATA
Aircraft Technology Roadmap to 2050 NOTICE DISCLAIMER. The information contained in this publication is subject to constant review in the light of changing government requirements and regulations. No subscriber or other reader should act on the basis of any such information without referring to applicable laws and regulations and/or without taking appropriate professional advice. Although every effort has been made to ensure accuracy, the International Air Transport Association shall not be held responsible for any loss or damage caused by errors, omissions, misprints or misinterpretation of the contents hereof. Furthermore, the International Air Transport Association expressly disclaims any and all liability to any person or entity, whether a purchaser of this publication or not, in respect of anything done or omitted, and the consequences of anything done or omitted, by any such person or entity in reliance on the contents of this publication. © International Air Transport Association. All Rights Reserved. No part of this publication may be reproduced, recast, reformatted or transmitted in any form by any means, electronic or mechanical, including photocopying, recording or any information storage and retrieval system, without the prior written permission from: Senior Vice President Member & External Relations International Air Transport Association 33, Route de l’Aéroport 1215 Geneva 15 Airport Switzerland Table of Contents Table of Contents .............................................................................................................................................................................................................. -
In-Flight Wingtip Folding: Inspiration from the XB-70 Valkyrie Gaétan X
International Journal of Aviation, Aeronautics, and Masthead Logo Aerospace Volume 6 | Issue 3 Article 7 2019 In-flight Wingtip Folding: Inspiration from the XB-70 Valkyrie Gaétan X. Dussart Cranfield University, [email protected] Mudassir Lone Cranfield University, [email protected] Ciaran O'Rourke Airbus Ltd, [email protected] Thomas Wilson Airbus Ltd, [email protected] Follow this and additional works at: https://commons.erau.edu/ijaaa Part of the Aeronautical Vehicles Commons, Applied Mechanics Commons, and the Aviation and Space Education Commons Scholarly Commons Citation Dussart, G. X., Lone, M., O'Rourke, C., & Wilson, T. (2019). In-flight Wingtip Folding: Inspiration from the XB-70 Valkyrie. International Journal of Aviation, Aeronautics, and Aerospace, 6(3). Retrieved from https://commons.erau.edu/ijaaa/vol6/iss3/7 This Article is brought to you for free and open access by the Journals at Scholarly Commons. It has been accepted for inclusion in International Journal of Aviation, Aeronautics, and Aerospace by an authorized administrator of Scholarly Commons. For more information, please contact [email protected], [email protected]. Dussart et al.: In-flight Wingtip Folding: Inspiration from the XB-70 Valkyrie Introduction To help develop future aircraft technologies, the authors investigated past developments and applications in the field of folding wingtips for inspiration, focusing on the XB-70 Valkyrie. Arguably the most iconic example of folding wingtip capable vehicle, it included the largest moving lifting surfaces ever flown and provides a good insight on the actuator and systems requirement for wingtip folding. Following a justification for incremental aircraft design changes, the authors introduce past and on-going developments in folding wingtip systems for large civil aircraft. -
In-Flight Wingtip Folding: Inspiration from the XB-70 Valkyrie
International Journal of Aviation, Aeronautics, and Aerospace Volume 6 Issue 3 Article 7 2019 In-flight Wingtip olding:F Inspiration from the XB-70 Valkyrie Gaétan X. Dussart Cranfield University, [email protected] Mudassir Lone Cranfield University, [email protected] Ciaran O'Rourke Airbus Ltd, [email protected] Thomas Wilson Airbus Ltd, [email protected] Follow this and additional works at: https://commons.erau.edu/ijaaa Part of the Aeronautical Vehicles Commons, Applied Mechanics Commons, and the Aviation and Space Education Commons Scholarly Commons Citation Dussart, G. X., Lone, M., O'Rourke, C., & Wilson, T. (2019). In-flight Wingtip olding:F Inspiration from the XB-70 Valkyrie. International Journal of Aviation, Aeronautics, and Aerospace, 6(3). https://doi.org/ 10.15394/ijaaa.2019.1343 This Article is brought to you for free and open access by the Journals at Scholarly Commons. It has been accepted for inclusion in International Journal of Aviation, Aeronautics, and Aerospace by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. Dussart et al.: In-flight Wingtip Folding: Inspiration from the XB-70 Valkyrie Introduction To help develop future aircraft technologies, the authors investigated past developments and applications in the field of folding wingtips for inspiration, focusing on the XB-70 Valkyrie. Arguably the most iconic example of folding wingtip capable vehicle, it included the largest moving lifting surfaces ever flown and provides a good insight on the actuator and systems requirement for wingtip folding. Following a justification for incremental aircraft design changes, the authors introduce past and on-going developments in folding wingtip systems for large civil aircraft. -
In-Flight Folding Wingtip System
In-flight folding wingtip system: inspiration from the XB-70 Valkyrie Gaétan Dussart∗ and Mudassir Lone† Cranfield University, Dynamic Simulation and Control Group Cranfield, Bedfordshire, MK43 0AL, United Kingdom Ciaran O’Rourke‡ and Thomas Wilson§ Airbus Operations Ltd Filton, Bristol, BS34 7PA, United Kingdom Wingtip folding can be used to extend aircraft wingspan, allowing designers to take advan- tage of reduced induced drag whilst respecting ground operational limitations. Such devices can also be used in-flight for a variety of other benefits including load alleviation and flight control. The majority of in-flight folding research takes inspiration in past developments made on the XB-70 Valkyrie, which used the folding devices for stability and lift performance benefits. In this paper, the authors investigate the capabilities of the folding wingtip system and potential scaling to large civil aircraft. Manufacturing details are used to size the actuators whilst the aerodynamic loading acting on the wingtip hinges is found from flight test results. Dimensions and aerodynamic loading at cruise of a set of conventional civil aircraft wing are used to evalu- ate the scaling potential of the system for controlled in-flight folding. An estimate of the weight penalty due to the folding device is also given and compared to structural weight savings on the XB-70. The results presented herein help in the evaluation of conventional actuator limits for in-flight folding using arguably the most inspiring military example of wingtip folding so far. I. Project Motivation t is well known that a well designed High Aspect Ratio Wings (HARW) will have better aerodynamic performances Ithan currently used conventional swept wings. -
Amphibious Aircrafts
Amphibious Aircrafts ...a short overview i Title: Amphibious Aircrafts Subtitle: ...a short overview Created on: 2010-06-11 09:48 (CET) Produced by: PediaPress GmbH, Boppstrasse 64, Mainz, Germany, http://pediapress.com/ The content within this book was generated collaboratively by volunteers. Please be advised that nothing found here has necessarily been reviewed by people with the expertise required to provide you with complete, accurate or reliable information. Some information in this book may be misleading or simply wrong. PediaPress does not guarantee the validity of the information found here. If you need specific advice (for example, medical, legal, financial, or risk management) please seek a professional who is licensed or knowledge- able in that area. Sources, licenses and contributors of the articles and images are listed in the section entitled ”References”. Parts of the books may be licensed under the GNU Free Documentation License. A copy of this license is included in the section entitled ”GNU Free Documentation License” All third-party trademarks used belong to their respective owners. collection id: pdf writer version: 0.9.3 mwlib version: 0.12.13 ii Contents Articles 1 Introduction 1 Amphibious aircraft . 1 Technical Aspects 5 Propeller.............................. 5 Turboprop ............................. 24 Wing configuration . 30 Lift-to-drag ratio . 44 Thrust . 47 Aircrafts 53 J2F Duck . 53 ShinMaywa US-1A . 59 LakeAircraft............................ 62 PBYCatalina............................ 65 KawanishiH6K .......................... 83 Appendix 87 References ............................. 87 Article Sources and Contributors . 91 Image Sources, Licenses and Contributors . 92 iii Article Licenses 97 Index 103 iv Introduction Amphibious aircraft Amphibious aircraft Canadair CL-415 operating on ”Fire watch” out of Red Lake, Ontario, c. -
Conceptual Design Optimization of a Strut Braced Wing Aircraft
Master Thesis Conceptual Design Optimization of a Strut Braced Wing Aircraft Author: Víctor Julián Sánchez Barreda Examiner: Prof. Dr.-Ing. Dieter Scholz, MSME Delivery date: 12.07.2013 2 Hochschule für Angewandte Wissenschaften Hamburg Fakultät Technik und Informatik Department Fahrzeugtechnik und Flugzeugbau Berliner Tor 9 20099 Hamburg Author: Víctor Julián Sánchez Barreda Examiner: Prof. Dr.-Ing. Dieter Scholz, MSME 3 Abstract Aircraft design has changed a lot during years. In the beginning everything was done by hand and following a test and error philosophy. With time, scientific methods and empirical results allowed a great improvement on the field. With the arrival of computers, more complicated calculations were possible, as well as an increase in the accuracy of the existing methods. All these improvements made possible the evaluation and optimization of new configurations for the future. These configurations are expected to show an improvement in aircraft cost, as well as in fuel consumption and respect for the environment, which is what currently our World needs. Some of the new configurations rise as the best potential candidates to achieve this goal. Configurations like the Blended Wing Body and the Box Wing are clear examples of what the future aircraft may look like. The goal of this Thesis is the evaluation of the potential benefit of the Strut Braced Wing configuration for a passenger aircraft comparable in size and range to the Airbus A320. This aircraft is designed following the requirements given by the German Aerospace Center (DLR) in the frame of their Design Challenge, aiming to find the future aircraft. With that purpose, an optimization tool based on Microsoft Office Excel is used (OPerA). -
2018-19 Design, Build, Fly Q&A #1
2018-19 Design, Build, Fly Q&A #1 Fuselage 1. How do you define a fuselage? How is underneath or bottom of the fuselage defined? Answer: The fuselage is defined as the main body of the airplane that is not the wings, stabilizers, or other control surfaces or features and is typically along the centerline of the airplane. In the case of a non-conventional airplane design such as a blended wing body, the fuselage will be defined for this competition as the center 20% of the total wing span in the flight configuration. The underneath of the fuselage is defined as any part of the fuselage below the center waterline of the fuselage. The attachment point for the stores must be below the center waterline but the shape of the store itself can extend above the waterline. 2. What if the aircraft does not have a fuselage, but rather a twin tail boom? Answer: The tail boom can act as the fuselage for attachment of additional stores. 3. Does the fuselage of the airplane need to be explicitly defined? Answer: No 4. Does the bottom of the fuselage have to be uniform or in the same horizontal plane? Answer: No 5. Can attack stores be placed inside the fuselage? Answer: No Radome 6. Can the radome spin using aerodynamic forces in flight? Answer: Yes, but it still must meet the requirement of no rotation until completion of the first 180 degree turn and stop rotation after the completion of the final 180 degree turn. During the ground mission, if aerodynamic forces are used for rotation, the ability to lock the radome must be demonstrated along with remote release capability and ability to spin freely. -
Print 02Pp001.Tif
AIRCRAFT DESIGN INTEGRATION AND AFFORDABILITY 1. INTRODUCTION The design of combat aircraft has traditionally been at the forefront of the introduction of new technologies in the aerospace sector. This was hue during both World Wars, and perhaps even mcxe so during the Cold War, when the technology race accelerated. In that period, the pursuit of superior military capability, through the use of advanced technologies, had few constraints other than technical feasibility. The ‘victory’ of the West In the Cold War, or the collapse of the former Soviet Union, brought the eagernessto earn a ‘peace dividend’, made possible by the perception of a lesser threat. In fact, the former monolithic, readily identified enemy, has been replaced by a variety of threats, such as proliferation of weapons of mass destruction, regional conflicts and tensions, civil wars and terrorism. Thus upgrades of existing aircraft, and their future replacements, face a wider variety of no less stringent missions. The increase of the unit cost of combat aircraft has been identified for a few decades as a potential problem. The perception of a lesser threat, and reduced defence budgets, conspire with the wider variety of threats and the cost of advanced to technology, to pose an unprecedented challenge to the combat aircraft designer: to break the increasing cost spiral, thereby ensuring that new generations of combat aircraft remain affordable in sufficient quantities, while still meeting more stringent and diversified requirements. A brief review of the evolution over the last half-a-cenhuy, since the end of World War II, will highlight the cost and technology trends, which have led to the present situation of a difficult compromise between capability and affordability. -
Development of Deployable Wings for Small Unmanned Aerial Vehicles Using Compliant Mechanisms
Brigham Young University BYU ScholarsArchive Theses and Dissertations 2007-07-06 Development of Deployable Wings for Small Unmanned Aerial Vehicles Using Compliant Mechanisms Steven D. Landon Brigham Young University - Provo Follow this and additional works at: https://scholarsarchive.byu.edu/etd Part of the Mechanical Engineering Commons BYU ScholarsArchive Citation Landon, Steven D., "Development of Deployable Wings for Small Unmanned Aerial Vehicles Using Compliant Mechanisms" (2007). Theses and Dissertations. 952. https://scholarsarchive.byu.edu/etd/952 This Thesis is brought to you for free and open access by BYU ScholarsArchive. It has been accepted for inclusion in Theses and Dissertations by an authorized administrator of BYU ScholarsArchive. For more information, please contact [email protected], [email protected]. DEVELOPMENT OF DEPLOYABLE WINGS FOR SMALL UNMANNED AERIAL VEHICLES USING COMPLIANT MECHANISMS by Steven D. Landon A thesis submitted to the faculty of Brigham Young University in partial fulfillment of the requirements for the degree of Master of Science Department of Mechanical Engineering Brigham Young University August 2007 Copyright © 2007 Steven D. Landon All Rights Reserved BRIGHAM YOUNG UNIVERSITY GRADUATE COMMITTEE APPROVAL of a thesis submitted by Steven D. Landon This thesis has been read by each member of the following graduate committee and by majority vote has been found to be satisfactory. ___________________________ ______________________________________ Date Spencer P. Magleby, Chair ___________________________