FAA-H-8083-3A, Airplane Flying Handbook -- 4 of 7 Files
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China's Aircraft Carrier Ambitions
CHINA’S AIRCRAFT CARRIER AMBITIONS An Update Nan Li and Christopher Weuve his article will address two major analytical questions. First, what are the T necessary and suffi cient conditions for China to acquire aircraft carriers? Second, what are the major implications if China does acquire aircraft carriers? Existing analyses on China’s aircraft carrier ambitions are quite insightful but also somewhat inadequate and must therefore be updated. Some, for instance, argue that with the advent of the Taiwan issue as China’s top threat priority by late 1996 and the retirement of Liu Huaqing as vice chair of China’s Central Military Commission (CMC) in 1997, aircraft carriers are no longer considered vital.1 In that view, China does not require aircraft carriers to capture sea and air superiority in a war over Taiwan, and China’s most powerful carrier proponent (Liu) can no longer infl uence relevant decision making. Other scholars suggest that China may well acquire small-deck aviation platforms, such as helicopter carriers, to fulfi ll secondary security missions. These missions include naval di- plomacy, humanitarian assistance, disaster relief, and antisubmarine warfare.2 The present authors conclude, however, that China’s aircraft carrier ambitions may be larger than the current literature has predicted. Moreover, the major implications of China’s acquiring aircraft carriers may need to be explored more carefully in order to inform appropriate reactions on the part of the United States and other Asia-Pacifi c naval powers. This article updates major changes in the four major conditions that are necessary and would be largely suffi cient for China to acquire aircraft carriers: leadership endorsement, fi nancial affordability, a relatively concise naval strat- egy that defi nes the missions of carrier operations, and availability of requisite 14 NAVAL WAR COLLEGE REVIEW technologies. -
Use of Rudder on Boeing Aircraft
12ADOBL02 December 2011 Use of rudder on Boeing aircraft According to Boeing the Primary uses for rudder input are in crosswind operations, directional control on takeoff or roll out and in the event of engine failure. This Briefing Leaflet was produced in co-operation with Boeing and supersedes the IFALPA document 03SAB001 and applies to all models of the following Boeing aircraft: 707, 717, 727, 737, 747, 757, 767, 777, 787, DC-8, DC-9, DC-10, MD-10, md-11, MD-80, MD-90 Sideslip Angle Fig 1: Rudder induced sideslip Background As part of the investigation of the American Airlines Flt 587 crash on Heading Long Island, USA the United States National Transportation Safety Board (NTSB) issued a safety recommendation letter which called Flight path for pilots to be made aware that the use of “sequential full opposite rudder inputs can potentially lead to structural loads that exceed those addressed by the requirements of certification”. Aircraft are designed and tested based on certain assumptions of how pilots will use the rudder. These assumptions drive the FAA/EASA, and other certifica- tion bodies, requirements. Consequently, this type of structural failure is rare (with only one event over more than 45 years). However, this information about the characteristics of Boeing aircraft performance in usual circumstances may prove useful. Rudder manoeuvring considerations At the outset it is a good idea to review and consider the rudder and it’s aerodynamic effects. Jet transport aircraft, especially those with wing mounted engines, have large and powerful rudders these are neces- sary to provide sufficient directional control of asymmetric thrust after an engine failure on take-off and provide suitable crosswind capability for both take-off and landing. -
The SKYLON Spaceplane
The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration. -
Touring Rudder Sit-On Top Kit Kit to Fit Rudder Enabled Sit-On Tops with a 10Mm Rudder Fixing Point
touring rudder sit-on top kit Kit to fit rudder enabled sit-on tops with a 10mm rudder fixing point. Note: It is easier to fit the Touring Rudder System if you have a screw hatch fitted to the rear stowage area of the kayak. If your kayak does not have this screw hatch and you wish to fit one, please contact a Perception dealer for advice. These instructions explain how to fit the rudder kit to a kayak with or without a rear screw hatch in place. Please make sure you follow the correct steps for your version of sit-on top kayak. This kit should contain the following: 1x rudder assembly with up-haul rope & split ring 4x deck fittings 4x length of rudder hose 5x self tapping screws 2x Dyneema control line - with cord end assembly 2x oval toggle 1x pair of Tip-Toes control footrests with foam washers 1x length of 4mm shock cord 6x footrest screws, washers and nuts - pre-fitted 1x rudder park - inc. hook, shock cord & fixing block You will also require some tools to fit this kit: Drill with 3mm, 5mm and 6mm drill bits Marker pen Short phillips screwdriver Wire cutters Small adjustable spanner or pair of pliers Lighter Tape measure Small amount of sticky tape Please read these instructions carefully before fitting! Step 1 - Control line entry points The rudder will need to have two control lines attached, each one running through hose sections inside the kayak from the rudder to the Tip-Toes footrests. This kit has four hose sections (two pairs) as two sections are needed per control line. -
FEDERAL REGISTER VOLUME 30 • Liulvibeil 249
FEDERAL REGISTER VOLUME 30 • liulviBEil 249 Tuesday, December 28, 1965 • Washington, D.C. Pages 16099-16180 Agencies in this issue— Agricultural Research Service Agricultural Stabilization and Conservation Service Atomic Energy Commission Civil Aeronautics Board Commodity Credit Corporation Consumer and Marketing Service Federal Aviation Agency Federal Home Loan Bank Board Federal Housing Administration Federal Maritime Commission Federal Power Commission Federal Trade Commission Food and Drug Administration General Services Administration Interstate Commerce Commission Land Management Bureau Maritime Administration Public Health Service Reclamation Bureau Detailed list of Contents appears inside. Volume 7 8 UNITED STATES STATUTES AT LARGE [88th Cong., 2d Sess.l Contains laws and concurrent resolu merical listing of bills enacted into tions enacted by the Congress during public and private law, and a guide 1964, the twenty-fourth amendment to the legislative history of bills en to the Constitution, and Presidential acted into public law. proclamations. Included is a nu- Price: $8.75 Published by Office of the Federal Register, National Archives and Records Service, General Services Administration Order from Superintendent of Documents, U.S. Government Printing Office, Washington, D.C., 20402 ¿f' Published, daily, Tuesday through Saturday (no publication on Sundays, Mondays, or on the day after an official Federal holiday), by the Office of the Federal Register, National FERERAL*REGISTER Archives and Records Service, General Services Administration (mail address National Area Code 202 V , »3 4 Phone 963-3261 Archives Building, Washington, D.C. 20408), pursuant to the authority contained in the Federal Register Act, approved July 26, 1935 (49 Stat. 500, as amended; 44 U.S.C., ch. -
Off Airport Ops Guide
Off Airport Ops Guide TECHNIQUES FOR OFF AIRPORT OPERATIONS weight and balance limitations for your aircraft. Always file a flight plan detailing the specific locations you intend Note: This document suggests techniques and proce- to explore. Make at least 3 recon passes at different levels dures to improve the safety of off-airport operations. before attempting a landing and don’t land unless you’re It assumes that pilots have received training on those sure you have enough room to take off. techniques and procedures and is not meant to replace instruction from a qualified and experienced flight instruc- High Level: Circle the area from different directions to de- tor. termine the best possible landing site in the vicinity. Check the wind direction and speed using pools of water, drift General Considerations: Off-airport operations can be of the plane, branches, grass, dust, etc. Observe the land- extremely rewarding; transporting people and gear to lo- ing approach and departure zone for obstructions such as cations that would be difficult or impossible to reach in trees or high terrain. any other way. Operating off-airport requires high perfor- mance from pilot and aircraft and acquiring the knowledge Intermediate: Level: Make a pass in both directions along and experience to conduct these operations safely takes either side of the runway to check for obstructions and time. Learning and practicing off-airport techniques under runway length. Check for rock size. Note the location of the supervision of an experienced flight instructor will not the touchdown area and roll-out area. Associate land- only make you safer, but also save you time and expense. -
Aerosport Modeling Rudder Trim
AEROSPORT MODELING RUDDER TRIM Segment: MOBILITY PARTS PROVIDERS | Engineering companies Application vertical: MOBILITY AND TRANSPORTATION | AircraFt Application type: FINAL PART: Short runs THE CUSTOMER FINAL PART: SHORT RUNS AEROSPORT MODELING RUDDER TRIM COMPANY DESCRIPTION APPLICATION TRADITIONAL MANUFACTURING Some planes are equipped with small tabs on the control surfaces (e.g., rudder trim Assembly of 26 different machined and standard parts Aerosport Modeling & Design was established in tabs, aileron tabs, elevator tabs) so the pilot can make minute adjustments to pitch, September 1996, and since then, they have worked to yaw, and roll to keep the airplane flying a true, clean line through the air. This produce the highest-possible quality prototypes, improves speed by reducing drag from the larger, constant movements of the full appearance models, working models, and machined rudder, aileron, and elevator. parts, and to meet or exceed client expectations. The company strives to be seen as a partner to their Many airplanes also have rudder and/or aileron trim systems. On some, the rudder clients and an extension of their design and trim tab is rigid but adjustable on the ground by bending: It is angled slightly to the development team, not just a supplier of prototyping left (when viewed from behind) to lessen the need for the pilot to push the rudder services. pedal constantly in order to overcome the left-turning tendencies of many prop- driven aircraft. Some aircraft have hinged rudder trim tabs that the pilot can adjust Aerosport Products spun off from sister company in flight. Aerosport Modeling & Design in 2009 to develop products for experimental aircraft, the first of which When a servo tab is employed, it is moved into the slipstream opposite of the was the RV-10 Carbon Fiber Instrument Panel. -
Runway Excursions Study
NLR-CR-2010-259 Executive summary A STUDY OF RUNWAY EXCURSIONS FROM A EUROPEAN PERSPECTIVE Report no. NLR-CR-2010-259 Author(s) G.W.H. van Es Report classification UNCLASSIFIED Date May 2010 Knowledge area(s) ) Vliegveiligheid (safety & security) Problem area on the European context. The Vliegoperaties Safety statistics show that study was limited to civil Luchtverkeersmanagement(A runway excursions are the most transport type of aircraft (jet and TM)- en luchthavenoperaties common type of accident turboprop) involved in Descriptor(s) reported annually, in the commercial or business Runway safety European region and worldwide. transport flights. Overrun Veeroff Description of work Results and conclusions Runway friction Causal and contributory factors The final results are used to RTO that may lead to a runway define preventive measures for excursion are identified by runway excursions. analysing data of runway excursions that occurred during the period 1980-2008. The scope of this report includes runway excursions that have taken place globally with a focus UNCLASSIFIED NLR-CR-2010-259 NLR Air Transport Safety Institute Anthony Fokkerweg 2, 1059 CM Amsterdam, UNCLASSIFIED P.O. Box 90502, 1006 BM Amsterdam, The Netherlands Telephone +31 20 511 35 00, Fax +31 20 511 32 10, Web site: http://www.nlr-atsi.nl NLR-CR-2010-259 A STUDY OF RUNWAY EXCURSIONS FROM A EUROPEAN PERSPECTIVE G.W.H. van Es This report may be cited on condition that full credit is given to NLR, the author and EUROCONTROL. This report has also been published as a EUROCONTROL report. This document has been given an NLR report identifier to facilitate future reference and to ensure long term document traceability. -
Nonlinear Control of an Aerobatic RC Airplane
Nonlinear Control of an Aerobatic RC Airplane MASSA CHUSETTS INSTITUTE by 0F TECHNOLOGY Joshua John Bialkowski J UN 2 3 2010 B.S., Georgia Institute of Technology (2007) LIBRARIES Submitted to the Department of Aeronautics and Astronautics in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics ARCHIVES at the MASSACHUSETTS INSTITUTE OF TECHNOLOGY May 2010 @ Massachusetts Institute of Technology 2010. All rights reserved. Author .......... .~. .....-.--...--.-.- D ar o % autics and Astronautics May 21, 2010 Certified by..... Prof Emilio Frazzoli Associate Professor of Aeronautics and Astronautics Thesis Supervisor / / IA Accepted by............. / Eytan H. Modiano Associate Professor of Aeronautics and Astronautics Chair, Committee on Graduate Students Nonlinear Control of an Aerobatic RC Airplane by Joshua John Bialkowski Submitted to the Department of Aeronautics and Astronautics on May 21, 2010, in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics Abstract An automatic flight controller based on the ideas of backstepping is applied to an aerobatic RC airplane. The controller asymptotically tracks a time-parameterized position reference, and depends on an orientation look-up rule to detemine the vehicle orientation from a desired acceleration. A coordinated-flight look-up rule compatible with the controller provides a nominal level of capability for traditional flight trajec- tories. A generalized coordinated look-up rule compatible with the controller provides more advanced capability, including stability for high angle of attack and hovering maneuvers, at the expense of an additional requirement from the reference trajectory. Basic simulation results are used to verify the controller, and a simulation software framework is described which will enable more extensive simulation and provide a platform for the final controller implementation. -
Small Lightweight Aircraft Navigation in the Presence of Wind Cornel-Alexandru Brezoescu
Small lightweight aircraft navigation in the presence of wind Cornel-Alexandru Brezoescu To cite this version: Cornel-Alexandru Brezoescu. Small lightweight aircraft navigation in the presence of wind. Other. Université de Technologie de Compiègne, 2013. English. NNT : 2013COMP2105. tel-01060415 HAL Id: tel-01060415 https://tel.archives-ouvertes.fr/tel-01060415 Submitted on 3 Sep 2014 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. Par Cornel-Alexandru BREZOESCU Navigation d’un avion miniature de surveillance aérienne en présence de vent Thèse présentée pour l’obtention du grade de Docteur de l’UTC Soutenue le 28 octobre 2013 Spécialité : Laboratoire HEUDIASYC D2105 Navigation d'un avion miniature de surveillance a´erienneen pr´esencede vent Student: BREZOESCU Cornel Alexandru PHD advisors : LOZANO Rogelio CASTILLO Pedro i ii Contents 1 Introduction 1 1.1 Motivation and objectives . .1 1.2 Challenges . .2 1.3 Approach . .3 1.4 Thesis outline . .4 2 Modeling for control 5 2.1 Basic principles of flight . .5 2.1.1 The forces of flight . .6 2.1.2 Parts of an airplane . .7 2.1.3 Misleading lift theories . 10 2.1.4 Lift generated by airflow deflection . -
A Conceptual Design of a Short Takeoff and Landing Regional Jet Airliner
A Conceptual Design of a Short Takeoff and Landing Regional Jet Airliner Andrew S. Hahn 1 NASA Langley Research Center, Hampton, VA, 23681 Most jet airliner conceptual designs adhere to conventional takeoff and landing performance. Given this predominance, takeoff and landing performance has not been critical, since it has not been an active constraint in the design. Given that the demand for air travel is projected to increase dramatically, there is interest in operational concepts, such as Metroplex operations that seek to unload the major hub airports by using underutilized surrounding regional airports, as well as using underutilized runways at the major hub airports. Both of these operations require shorter takeoff and landing performance than is currently available for airliners of approximately 100-passenger capacity. This study examines the issues of modeling performance in this now critical flight regime as well as the impact of progressively reducing takeoff and landing field length requirements on the aircraft’s characteristics. Nomenclature CTOL = conventional takeoff and landing FAA = Federal Aviation Administration FAR = Federal Aviation Regulation RJ = regional jet STOL = short takeoff and landing UCD = three-dimensional Weissinger lifting line aerodynamics program I. Introduction EMAND for air travel over the next fifty to D seventy-five years has been projected to be as high as three times that of today. Given that the major airport hubs are already congested, and that the ability to increase capacity at these airports by building more full- size runways is limited, unconventional solutions are being considered to accommodate the projected increased demand. Two possible solutions being considered are: Metroplex operations, and using existing underutilized runways at the major hub airports. -
The Influence of Wing Loading on Turbofan Powered Stol Transports with and Without Externally Blown Flaps
https://ntrs.nasa.gov/search.jsp?R=19740005605 2020-03-23T12:06:52+00:00Z NASA CONTRACTOR NASA CR-2320 REPORT CXI CO CNI THE INFLUENCE OF WING LOADING ON TURBOFAN POWERED STOL TRANSPORTS WITH AND WITHOUT EXTERNALLY BLOWN FLAPS by R. L. Morris, C. JR. Hanke, L. H. Pasley, and W. J. Rohling Prepared by THE BOEING COMPANY WICHITA DIVISION Wichita, Kans. 67210 for Langley Research Center NATIONAL AERONAUTICS AND SPACE ADMINISTRATION • WASHINGTON, D. C. • NOVEMBER 1973 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA CR-2320 4. Title and Subtitle 5. Reoort Date November. 1973 The Influence of Wing Loading on Turbofan Powered STOL Transports 6. Performing Organization Code With and Without Externally Blown Flaps 7. Author(s) 8. Performing Organization Report No. R. L. Morris, C. R. Hanke, L. H. Pasley, and W. J. Rohling D3-8514-7 10. Work Unit No. 9. Performing Organization Name and Address The Boeing Company 741-86-03-03 Wichita Division 11. Contract or Grant No. Wichita, KS NAS1-11370 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Contractor Report National Aeronautics and Space Administration Washington, D.C. 20546 14. Sponsoring Agency Code 15. Supplementary Notes This is a final report. 16. Abstract The effects of wing loading on the design of short takeoff and landing (STOL) transports using (1) mechanical flap systems, and (2) externally blown flap systems are determined. Aircraft incorporating each high-lift method are sized for Federal Aviation Regulation (F.A.R.) field lengths of 2,000 feet, 2,500 feet, and 3,500 feet, and for payloads of 40, 150, and 300 passengers, for a total of 18 point-design aircraft.