Jack Northrop and the Flying Wing
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Flying Wing Concept for Medium Size Airplane
ICAS 2002 CONGRESS FLYING WING CONCEPT FOR MEDIUM SIZE AIRPLANE Tjoetjoek Eko Pambagjo*, Kazuhiro Nakahashi†, Kisa Matsushima‡ Department of Aeronautics and Space Engineering Tohoku University, Japan Keywords: blended-wing-body, inverse design Abstract The flying wing is regarded as an alternate This paper describes a study on an alternate configuration to reduce drag and structural configuration for medium size airplane. weight. Since flying wing possesses no fuselage Blended-Wing-Body concept, which basically is it may have smaller wetted area than the a flying wing configuration, is applied to conventional airplane. In the conventional airplane for up to 224 passengers. airplane the primary function of the wing is to An aerodynamic design tools system is produce the lift force. In the flying wing proposed to realize such configuration. The configuration the wing has to carry the payload design tools comprise of Takanashi’s inverse and provides the necessary stability and control method, constrained target pressure as well as produce the lift. The fuselage has to specification method and RAPID method. The create lift without much penalty on the drag. At study shows that the combination of those three the same time the fuselage has to keep the cabin design methods works well. size comfortable for passengers. In the past years several flying wings have been designed and flown successfully. The 1 Introduction Horten, Northrop bombers and AVRO are The trend of airplane concept changes among of those examples. However the from time to time. Speed, size and range are application of the flying wing concepts were so among of the design parameters. -
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. -
2021-03 Pearcey Newby and the Vulcan V2.Pdf
Journal of Aeronautical History Paper 2021/03 Pearcey, Newby, and the Vulcan S C Liddle Vulcan to the Sky Trust ABSTRACT In 1955 flight testing of the prototype Avro Vulcan showed that the aircraft’s buffet boundary was unacceptably close to the design cruise condition. The Vulcan’s status as one of the two definitive carrier aircraft for Britain’s independent nuclear deterrent meant that a strong connection existed between the manufacturer and appropriate governmental research institutions, in this case the Royal Aircraft Establishment (RAE) and the National Physical Laboratory (NPL). A solution was rapidly implemented using an extended and drooped wing leading edge, designed and high-speed wind-tunnel tested by K W Newby of RAE, subsequently being fitted to the scaled test version of the Vulcan, the Avro 707A. Newby’s aerodynamic solution exploited a leading edge supersonic-expansion, isentropic compression* effect that was being investigated at the time by researchers at NPL, including H H Pearcey. The latter would come to be associated with this ‘peaky’ pressure distribution and would later credit the Vulcan implementation as a key validation of the concept, which would soon after be used to improve the cruise efficiency of early British jet transports such as the Trident, VC10, and BAC 1-11. In turn, these concepts were exploited further in the Hawker-Siddeley design for the A300B, ultimately the basis of Britain’s status as the centre of excellence for wing design in Airbus. Abbreviations BS Bristol Siddeley L Lift D Drag M Mach number CL Lift Coefficient NPL National Physical Laboratory Cp Pressure coefficient RAE Royal Aircraft Establishment Cp.te Pressure coefficient at trailing edge RAF Royal Air Force c Chord Re Reynolds number G Load factor t Thickness HS Hawker Siddeley WT Wind tunnel HP Handley Page α Angle of Attack When the airflow past an aerofoil accelerates its pressure and temperature drop, and vice versa. -
Daniel Egger Papers
http://oac.cdlib.org/findaid/ark:/13030/c87w6jb1 Online items available Daniel Egger papers Finding aid prepared and updated by Gina C Giang. Manuscripts Department The Huntington Library 1151 Oxford Road San Marino, California 91108 Phone: (626) 405-2191 Fax: (626) 449-5720 Email: [email protected] URL: http://www.huntington.org © Finding aid last updated June 2019. The Huntington Library. All rights reserved. Daniel Egger papers mssEgger 1 Descriptive Summary Title: Daniel Egger papers Inclusive Dates: 1927-2019 Collection Number: mssEgger Collector: Egger, Daniel Frederic Extent: 3 boxes, 1 oversize folder, 1 flash drive, and 1 tube (1.04 linear feet) Repository: The Huntington Library, Art Collections, and Botanical Gardens Manuscripts Department 1151 Oxford Road San Marino, California 91108 Phone: (626) 405-2191 Fax: (626) 449-5720 Email: [email protected] URL: http://www.huntington.org Abstract: The Daniel Egger papers include correspondence, printed matter, and photographs related to Daniel Egger’s career in the aerospace industry. Language of Material: The records are in English and Spanish. Access Collection is open to qualified researchers by prior application through the Reader Services Department. For more information, please go to following web site . NOT AVAILABLE: The collection contains one flash drive, which is unavailable until reformatted. Please contact Reader Services for more information. RESTRICTED: Tube 1 (previously housed in Box 1, folder 1). Due to size of original, original will be available only with curatorial permission. Publication Rights The Huntington Library does not require that researchers request permission to quote from or publish images of this material, nor does it charge fees for such activities. -
Horten Ho 229 V3 All Wood Short Kit
Horten Ho 229 V3 All Wood Short Kit a Radio Controlled Model in 1/8 Scale Design by Gary Hethcoat Copyright 2007 Aviation Research P.O. Box 9192, San Jose, CA 95157 http://www.wingsontheweb.com Email: [email protected] Phone: 408-660-0943 Table of Contents 1 General Building Notes ......................................................................................................................... 4 1.1 Getting Help .................................................................................................................................. 4 1.2 Laser Cut Parts .............................................................................................................................. 4 1.3 Electronics ..................................................................................................................................... 4 1.4 Building Options ........................................................................................................................... 4 1.4.1 Removable Outer Wing Panels .............................................................................................. 4 1.4.2 Drag Rudders ......................................................................................................................... 4 1.4.3 Retracts .................................................................................................................................. 5 1.4.4 Frise Style Elevons ............................................................................................................... -
Download the PDF File
Nick: Invisibility sounds like something out of a work of Sci-Fi. However, Northrop Grumman’s B2 Spirit is just that. While the B2 is not invisible to the naked eye, it can avoid detection by radar thanks to a specially designed frame and coating that deflects and nullifies radar waves. Radar waves are sent outwards, and bounce off of features such as engines and straight wings. By altering its shape and applying radar absorbent material, the B2 is able to minimize the radar waves that can be analyzed, making the B2 almost impossible to find. On top of being a stealth plane, the B2 is a flying wing, meaning it has no fuselage or tail. The B2 is meant to be a low observable stealth plane used to penetrate anti-aircraft defenses. It can carry both conventional and thermonuclear weapons, and is a unique aircraft that can carry heavy air-to-surface weapons while also remaining in stealth. But where did this technology come from? Daryl: As soon as radar was developed during World War Two, there was a need to evade radar. Efforts were made during and after the war to counter radar, and two German brothers were the first to find a solution. Walter and Reimar Horton were pilots with the German Luftwaffe, but also designed aircraft of their own. One of these was the Horton HO-229 jet, the earliest flying wing propelled by a jet, which also had radar wave absorbing material on the wings. They used a wood-carbon powder to absorb radar waves, making this the earliest stealth plane. -
“Keep the Dream Alive”
February 28, 2015 The 60th Annual Honors and Awards Banquet “Keep the Dream Alive” February 28, 2015 th 60 Honors & Awards Banquet Diamond Anniversary 1 The 60th Annual Honors and Awards Banquet February 28, 2015 National Engineers Week Committees ~ BANQUET COMMITTEE ~ Kenneth Davis, Sonja Domazet, Stephen Guine, William Johnson, Sharlene Katz, Paul Landry, Robert Tarn, Thomas R. Tarn, Charles Volk ~ HONORS & AWARDS COMMITTEE ~ Marek Barylak, Kenneth Davis, Stephen Guine, Sharlene Katz, Paul Landry, Charles Olsefsky, R. Freeman Straub, Robert B. Tarn ~ AWARDS ASSEMBLY ~ Ken Davis, Sonja Domazet, James Flynn, Bill Johnson, Sharlene Katz, Charles Olsefsky ~ HOST / HOSTESSES ~ Olivia Landry, Maria Tarn ~ SOUVENIR PROGRAM GRAPHICS & DESIGN ~ Paul Landry ~ AWARD GRAPHICS ~ Mike Matte ~ AUDIO / VIDEO ~ Swank Audio Visuals, Carlos Guerra ~ BANQUET SETUP / AWARDS DISTRIBUTION ~ Marissa Bayless, Margo Guerra ~ MATH COUNTS ~ Jerry Kraim, Eli Stiny Engineers’ Council Past Presidents 1970 William B. Johnson 1992 Robert Budica 2005 Robert B. Tarn 1980 Clifford B. Shiepe, PE 1993 Lloyd W. Higginbotham, FIAE 2006 Paul F. Landry 1981 Clifford B. Shiepe, PE 1994 Lloyd W. Higginbotham, FIAE 2007 Paul F. Landry 1982 Lloyd W. Higginbotham, FIAE 1995 Lloyd W. Higginbotham, FIAE 2008 Patrick Berbon 1983 William F. Hassel, PE, FIAE 1996 Lloyd W. Higginbotham, FIAE 2009 Dr. Charles H. Volk 1984 Clifford Terry 1997 Lloyd W. Higginbotham, FIAE 2010 Dr. Charles H. Volk 1985 Roland V. Roggero 1998 Lloyd W. Higginbotham, FIAE 2011 Kenneth G. Davis 1986 James P. Ritchey 1999 Lloyd W. Higginbotham, FIAE 2012 Kenneth G. Davis 1987 James P. Ritchey 2000 Lloyd W. Higginbotham, FIAE 2013 Sonja Domazet 1988 Harlan L. Russ 2001 Lloyd W. -
Sherman Oaks, California
Sherman Oaks, California Theodore von Kármán Engineer of the Year Educator of the Year Achievement Award Mr. Eric D. Knutson Dr. Melvin A. Breuer Dr. Buzz Aldrin Director of Advanced Projects Professor Astronaut, Apollo XI Lockheed Martin Skunkworks University of Southern Retired Colonel, USAF Palmdale, California California Author and Space Los Angeles, California Advocate th 56 Annual HONORS AND AWARDS BANQUET Saturday, February 26, 2011 In Celebration of National Engineers Week, February 20-26, 2011 National Engineers Week Committees Banquet Committee: Marek Barylak, Robert Budica, Larry Dalton, Kenneth Davis, Sonja Domazet, Carlos & Margo Guerra, Stephen Guine, William Johnson, Jerry Kraim, Diane Kulisek, Paul Landry, Charles Olsefsky, S. K. Ramesh, Rick Ratcliffe, Ramin Roosta, Noelle Segura, R. Freeman Straub, Robert Tarn, Charles Volk Honors & Awards Committee: Kenneth Davis, Diane Kulisek, Paul Landry, Charles Olsefsky, R. Freeman Straub, Robert Tarn Visual Media Services: Warren Huskey, Mike Matte Awards Assembly Marek Barylak, Larry Dalton, Kenneth Davis, Sonja Domazet, William Johnson, Diane Kulisek, Sharlene Katz, Charles Olsefsky, Ramin Roosta, R. Freeman Straub, Charles Volk Hostesses: Mary Claire Jensen, Mickey Knobloch, Olivia Landry, Maria Tarn Audio/Video: Swank Audio Visuals Award Presenters: Sonja Domazet, Stephen Guine, William Johnson, Paul Landry, Robert Tarn, Charles Volk Banquet Setup/Awards Distribution: Margo Guerra, CSUN Engineering Students Math Counts: Jerry Kraim LA County Science Bowl: Larry Dalton First Robotics: R. Freeman Straub The Engineers’ Council Board of Directors President Vice President Treasurer Secretary Kenneth G. Davis Sonja Domazet Dr. Charles H. Volk Robert B. Tarn Trustees: Dr. Robert J. Budica, Paul F. Landry, Dr. A. F. Ratcliffe, Robert B. -
Development of a Flight Dynamics Model of a Flying Wing Configuration
Master thesis in Aeronautical Engineering Development of a Flight Dynamics Model of a Flying Wing Configuration Candidate Supervisor Jacopo Tonti Prof. Guido De Matteis External supervisor Prof. Arthur Rizzi (Kungliga Tekniska högskolan) Academic Year 2013/2014 cbn 2014 by Jacopo Tonti Some rights reserved. This thesis is available under a Creative Commons CC BY-NC-3.0 IT License. (creativecommons.org/licenses/by-nc/3.0/it/) Alla mia musa , a Vale «As ailerons, these damn spoilers make great rudders!» Bruce Miller, after flying the Marske Pioneer 1A Abstract The subject of UCAV design is an important topic nowadays and many countries have their own programmes. An international group, under the initiative of the NATO RTO AVT-201 Task group, titled “Extended Assessment of Reliable Stability & Control Pre- diction Methods for NATO Air Vehicles”, is currently performing intensive analysis on a generic UCAV configuration, named SACCON. In this thesis the stability and control characteristics of the SACCON are investigated, with the purpose of carrying out a compre- hensive assessment of the flying qualities of the design. The study included the generation of the complete aerodynamic database of the aircraft, on the basis of the experimental data measured during TN2514 and TN2540 campaigns at DNW-NWB low speed wind tunnel. Moreover, system identification techniques were adopted for the extraction of dynamic derivatives from the time histories of forced oscillation runs. The trim of the aircraft was evaluated across the points of a reasonable test envelope, so as to define a set of plausible operative conditions, representing the reference conditions for subsequent linearization of the dynamic model. -
On the Handling Qualities of Two Flying Wing Aircraft Configurations
aerospace Article On the Handling Qualities of Two Flying Wing Aircraft Configurations Luís M. B. C. Campos 1,† and Joaquim M. G. Marques 2,*,† 1 CCTAE, IDMEC, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1049-001 Lisbon, Portugal; [email protected] 2 CCTAE, IDMEC, Escola de Ciências e Tecnologia, Departamento de Mecatrónica, Colégio Luís António Verney, Universidade de Évora, Rua Romão Ramalho, 59, 7000-671 Évora, Portugal * Correspondence: [email protected] † These authors contributed equally to this work. Abstract: The coupling of the longitudinal and lateral stability modes of an aeroplane is considered in two cases: (i) weak coupling, when the changes in the frequency and damping of the phugoid, short period, dutch roll, and helical modes are small, i.e., the square of the deviation is negligible compared to the square of the uncoupled value; (ii) strong coupling, when the coupled values may differ significantly from the uncoupled values. This allows a comparison of three values for the frequency and damping of each mode: (i) exact, i.e., fully coupled; (ii) with the approximation of weak coupling; (iii) with the assumption of decoupling. The comparison of these three values allows an assessment of the importance of coupling effects. The method is applied to two flying wing designs, concerning all modes in a total of eighteen flight conditions. It turns out that lateral-longitudinal coupling is small in all cases, and thus classical handling qualities criteria can be applied. The handling qualities are considered for all modes, namely the phugoid, short period, dutch roll, spiral, and roll modes. -
A Look Back at Flying Wings Part 1
NORTHROP FLYING WING S - P A R T 1 AVION MODEL 1, N - 1 M & N - 9M EDITED BY:TONY R. LANDIS WRITER/ARCHIVIST, HQ AFMC HISTORY OFFICE DISTRIBUTION STATEMENT A: APPROVED FOR PUBLIC RELEASE NORTHROP FLYING WING S - P A R T 1 Northrop’s latest aircraft, the B-21A Raider is the culmination of John K. Northrop’s dream of all wing design whose evolution stretches back to 1929. This is the first in a series of articles that will take a look back to the early days of aviation to show the birth of John Northrop’s dream. The Avion (Northrop) Model 1, commonly known as the 1929 Flying Wing, was the first rudimentary attempt at an all-wing vehicle, though it retained a simple boom- mounted tail assembly for added stability. Breaking away from the standard protocol of using wood for the structural assembly, Northrop chose 24S Alclad aluminum for the Model-1. Powered by a 90 HP 4 cylinder, inline, inverted Cirrus engine center- mounted inside the fuselage in a pusher (rear mounted) arrangement, the Avion Model 1 made its first flight at Mines Field, California on July 30, 1929 when test pilot Eddie Bellande performed two short hops during high speed taxi runs. Shortly there- after the aircraft was trucked to Muroc Dry Lake in California’s Mojave Desert. The vast expanse of the dry lake gave the small test team plenty of room to test their new design. The first ‘official’ flight of the Model-1 came on September 26th at Muroc. Bel- lande performed two brief flights totaling 5 minutes on the 26th and three days later made its final Muroc flight during a 5 minute test hop around the lakebed before operations moved to United Air Terminal in Burbank where flight operations continued on November 18th. -
Flight Dynamics of the Flying Wing
26TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES FLIGHT DYNAMICS OF THE FLYING WING S. D’Urso* and R. Martinez-Val *Universita Federico II, Naples, Italy **Universidad Politecnica de Madrid, Spain Keywords: flying wing, stability, performances Abstract years. But this tremendous demand will occur in an epoch of continued pressure to achieve Flying wings are one of the most promising significant reductions in both direct operating concepts for the future of commercial aviation, cost and environmental impact. regarding the market, technology and Commercial airplanes have evolved from environmental driving factors. The research uncomfortable converted bombers after World reported here is part of a long term project on War I into what is currently called the the 300 seats category flying wings. In several conventional layout, appeared six decades ago. previously published works the feasibility, This ubiquitous arrangement is characterised by efficient performance and airport compatibility a slender fuselage mated to a high aspect ratio of the concept have been assessed. The present wing, with aft-mounted empennage and pod- paper concentrates on the flight dynamic mounted engines under the wing [6]. A variant aspects of the aircraft, which have been with engines attached to the rear fuselage has scarcely analysed in open literature. The results also been used, mainly in business and regional obtained show that the flying wing jets. However, it seems that this paradigmatic configuration can be dynamically stable; configuration is approaching an asymptote however, the longitudinal and lateral- around the size of A380 [7, 8]. directional oscillations decay so slowly that a The ever changing market and technology stability augmentation system would be required scenario is strongly leading to new designs and to assure an acceptable dynamic response of the concepts: three-surface layout, joined wings, aircraft.