Aircraft Circulars National Advisory
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Modeling an Airframe Tutorial
EAA SOLIDWORKS University p 1/11 Modeling an Airframe Tutorial Difficulty: Intermediate | Time: 1 hour As an Intermediate Tutorial, it is assumed that you have completed the Quick Start Tutorial and know how to sketch in 2D and 3D. If you struggle to recall how to do basic functions, please review the Tips Sheet. The Modeling an Airframe Tutorial guides you through the creation of a tubular airframe in SOLIDWORKS. The objective of the lesson is to teach you how to use the tools to design an aircraft frame. Time limits prevent us from completing this airframe, but you should learn the skills to model an airframe. You will create this part and drawing: This lesson includes: Creating a 3D Sketches Using the Weldment feature to add structural members Trimming structural members Creating a drawing and adding a ‘cut list’ Bill of Materials (BoM) EAA SOLIDWORKS University p 2/11 Modeling an Airframe Tutorial Creating a 3D Sketch for the Airframe In this lesson we will use the weldment feature to create an airframe. Weldments are structural members defined by a cross section picked from a library and a sketch line to define its length. This sketch line can be from multiple 2D sketches, or a single 3D sketch. By using two layout sketches (side and plan elevations), you can control the 3D sketch easily and any future changes will be reflected in your airframe. The layout sketches capture the design intent and the dimensions of the finished frame. 1. Open a New Part, verify Units are inches, and Save As “Airframe” (Top Menu / File / Save As). -
Unit-1 Notes Faculty Name
SCHOOL OF AERONAUTICS (NEEMRANA) UNIT-1 NOTES FACULTY NAME: D.SUKUMAR CLASS: B.Tech AERONAUTICAL SUBJECT CODE: 7AN6.3 SEMESTER: VII SUBJECT NAME: MAINTENANCE OF AIRFRAME AND SYSTEMS DESIGN AIRFRAME CONSTRUCTION: Various types of structures in airframe construction, tubular, braced monocoque, semimoncoque, etc. longerons, stringers, formers, bulkhead, spars and ribs, honeycomb construction. Introduction: An aircraft is a device that is used for, or is intended to be used for, flight in the air. Major categories of aircraft are airplane, rotorcraft, glider, and lighter-than-air vehicles. Each of these may be divided further by major distinguishing features of the aircraft, such as airships and balloons. Both are lighter-than-air aircraft but have differentiating features and are operated differently. The concentration of this handbook is on the airframe of aircraft; specifically, the fuselage, booms, nacelles, cowlings, fairings, airfoil surfaces, and landing gear. Also included are the various accessories and controls that accompany these structures. Note that the rotors of a helicopter are considered part of the airframe since they are actually rotating wings. By contrast, propellers and rotating airfoils of an engine on an airplane are not considered part of the airframe. The most common aircraft is the fixed-wing aircraft. As the name implies, the wings on this type of flying machine are attached to the fuselage and are not intended to move independently in a fashion that results in the creation of lift. One, two, or three sets of wings have all been successfully utilized. Rotary-wing aircraft such as helicopters are also widespread. This handbook discusses features and maintenance aspects common to both fixed wing and rotary-wing categories of aircraft. -
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. -
Aircraft Winglet Design
DEGREE PROJECT IN VEHICLE ENGINEERING, SECOND CYCLE, 15 CREDITS STOCKHOLM, SWEDEN 2020 Aircraft Winglet Design Increasing the aerodynamic efficiency of a wing HANLIN GONGZHANG ERIC AXTELIUS KTH ROYAL INSTITUTE OF TECHNOLOGY SCHOOL OF ENGINEERING SCIENCES 1 Abstract Aerodynamic drag can be decreased with respect to a wing’s geometry, and wingtip devices, so called winglets, play a vital role in wing design. The focus has been laid on studying the lift and drag forces generated by merging various winglet designs with a constrained aircraft wing. By using computational fluid dynamic (CFD) simulations alongside wind tunnel testing of scaled down 3D-printed models, one can evaluate such forces and determine each respective winglet’s contribution to the total lift and drag forces of the wing. At last, the efficiency of the wing was furtherly determined by evaluating its lift-to-drag ratios with the obtained lift and drag forces. The result from this study showed that the overall efficiency of the wing varied depending on the winglet design, with some designs noticeable more efficient than others according to the CFD-simulations. The shark fin-alike winglet was overall the most efficient design, followed shortly by the famous blended design found in many mid-sized airliners. The worst performing designs were surprisingly the fenced and spiroid designs, which had efficiencies on par with the wing without winglet. 2 Content Abstract 2 Introduction 4 Background 4 1.2 Purpose and structure of the thesis 4 1.3 Literature review 4 Method 9 2.1 Modelling -
Hangar 9 Ultimate Manual
TM® WE GET PEOPLE FLYING 46% TOC Ultimate 10-300 ASSEMBLY MANUAL Specifications Wingspan ..........................................................................................100 in (2540 mm) Length ................................................................................................110 in (2794 mm) Wing Area.........................................................................................3310 sq in (213.5 sq dm) Weight ...............................................................................................40–44 lb (18–20 kg) Engine.................................................................................................150–200cc gas engine Radio ..................................................................................................6-channel w/15 servos Introduction Thank you for purchasing the Hangar 9® 46% TOC Ultimate. Because size and weight of this model creates a higher degree for potential danger, an added measure of care and responsibility is needed for both building and flying this or any giant-scale model. It’s important that you carefully follow these instructions, especially those regarding hinging and the section on flying. Like all giant-scale aerobatic aircraft, the Hangar 9® TOC Ultimate requires powerful, heavy-duty servos. Servos greatly affect the flight performance, feel and response of the model. To get the most out of your Ultimate, it’s important to use accurate, powerful servos on all control surfaces. In the prototype models, we used JR 8411 digital servos with excellent -
February 2002 Alerts
February 2002 FAA AC 43-16A CONTENTS AIRPLANES AERONCA ................................................................................................................................. 1 BEECH ........................................................................................................................................ 2 CESSNA ..................................................................................................................................... 6 EXTRA........................................................................................................................................ 9 MAULE..................................................................................................................................... 10 PIPER........................................................................................................................................ 10 SOCATA .................................................................................................................................. 13 HELICOPTERS BELL ......................................................................................................................................... 14 EUROCOPTER ......................................................................................................................... 14 MCDONNELL DOUGLAS ...................................................................................................... 15 AMATEUR, EXPERIMENTAL, AND SPORT AIRCRAFT AVID FLYER ........................................................................................................................... -
For Improved Airplane Performance
BLENDED WINGLETS FORFOR IMPROVEDIMPROVED AIRPLANEAIRPLANE PERFORMANCEPERFORMANCE New blended winglets on the Boeing Business Jet and the 737-800 commercial airplane offer operational benefits to customers. Besides giving the airplanes a distinctive appear- ance, the winglets create more efficient flight characteristics in cruise and during takeoff and climbout, which translate into additional range with the same fuel and payload. ROBERT FAYE ROBERT LAPRETE MICHAEL WINTER TECHNICAL DIRECTOR ASSOCIATE TECHNICAL FELLOW PRINCIPAL ENGINEER BOEING BUSINESS JETS AERODYNAMICS TECHNOLOGY STATIC AEROELASTIC LOADS BOEING COMMERCIAL AIRPLANES BOEING COMMERCIAL AIRPLANES BOEING COMMERCIAL AIRPLANES TECHNOLOGY/PRODUCT DEVELOPMENT AERO 16 vertical height of the lifting system (i.e., increasing the length of the TE that sheds the vortices). The winglets increase the spread of the vortices along the TE, creating more lift at the wingtips (figs. 2 and 3). The result is a reduction in induced drag (fig. 4). The maximum benefit of the induced drag reduction depends on the spanwise lift distribution on the wing. Theoretically, for a planar wing, induced drag is opti- mized with an elliptical lift distribution that minimizes the change in vorticity along the span. For the same amount of structural material, nonplanar wingtip 737-800 TECHNICAL CHARACTERISTICS devices can achieve a similar induced drag benefit as a planar span increase; however, new Boeing airplane designs Passengers focus on minimizing induced drag with 3-class configuration Not applicable The 737-800 commercial airplane wingspan influenced by additional 2-class configuration 162 is one of four 737s introduced BBJ TECHNICAL CHARACTERISTICS The Boeing Business Jet design benefits. 1-class configuration 189 in the late 1990s for short- to (BBJ) was launched in 1996 On derivative airplanes, performance Cargo 1,555 ft3 (44 m3) medium-range commercial air- Passengers Not applicable as a joint venture between can be improved by using wingtip Boeing and General Electric. -
A Design Study of a Proposed Four-Seat, Amateur-Built Airplane
University of Tennessee, Knoxville TRACE: Tennessee Research and Creative Exchange Masters Theses Graduate School 8-2003 A Design Study of a Proposed Four-Seat, Amateur-Built Airplane D. Andrew Moore University of Tennessee - Knoxville Follow this and additional works at: https://trace.tennessee.edu/utk_gradthes Part of the Mechanical Engineering Commons Recommended Citation Moore, D. Andrew, "A Design Study of a Proposed Four-Seat, Amateur-Built Airplane. " Master's Thesis, University of Tennessee, 2003. https://trace.tennessee.edu/utk_gradthes/2113 This Thesis is brought to you for free and open access by the Graduate School at TRACE: Tennessee Research and Creative Exchange. It has been accepted for inclusion in Masters Theses by an authorized administrator of TRACE: Tennessee Research and Creative Exchange. For more information, please contact [email protected]. To the Graduate Council: I am submitting herewith a thesis written by D. Andrew Moore entitled "A Design Study of a Proposed Four-Seat, Amateur-Built Airplane." I have examined the final electronic copy of this thesis for form and content and recommend that it be accepted in partial fulfillment of the requirements for the degree of Master of Science, with a major in Mechanical Engineering. Dr. Gary Flandro, Major Professor We have read this thesis and recommend its acceptance: Dr. Louis Deken, Dr. Peter Solies Accepted for the Council: Carolyn R. Hodges Vice Provost and Dean of the Graduate School (Original signatures are on file with official studentecor r ds.) To the Graduate Council: I am submitting herewith a thesis written by D. Andrew Moore entitled “A Design Study of a Proposed Four-Seat, Amateur-Built Airplane.” I have examined the final electronic copy of this thesis for form and content and recommend that it be accepted in partial fulfillment of the requirements for the degree of Master of Science, with a major in Mechanical Engineering. -
Class 244 Aeronautics and Astronautics 244 - 1
CLASS 244 AERONAUTICS AND ASTRONAUTICS 244 - 1 244 AERONAUTICS AND ASTRONAUTICS 1 R MISCELLANEOUS 168 ..By solar pressure 1 N .Noise abatement 169 ..By jet motor 1 A .Lightning arresters and static 170 ..By nutation damper eliminators 171 ..With attitude sensor means 1 TD .Trailing devices 171.1 .With propulsion 2 COMPOSITE AIRCRAFT 171.2 ..Steerable mount 3 .Trains 171.3 ..Launch from surface to orbit 3.1 MISSILE STABILIZATION OR 171.4 ...Horizontal launch TRAJECTORY CONTROL 171.5 ..Without mass expulsion 3.11 .Remote control 171.6 .Having launch pad cooperating 3.12 ..Trailing wire structure 3.13 ..Beam rider 171.7 .With shield or other protective 3.14 ..Radio wave means (e.g., meteorite shield, 3.15 .Automatic guidance insulation, radiation/plasma 3.16 ..Optical (includes infrared) shield) 3.17 ...Optical correlation 171.8 ..Active thermal control 3.18 ...Celestial navigation 171.9 .With special crew accommodations 3.19 ..Radio wave 172.1 ..Emergency rescue means (e.g., escape pod) 3.2 ..Inertial 172.2 .With fuel system details 3.21 ..Attitude control mechanisms 172.3 ..Fuel tank arrangement 3.22 ...Fluid reaction type 172.4 .Rendezvous or docking 3.23 .Stabilized by rotation 172.5 ..Including satellite servicing 3.24 .Externally mounted stabilizing appendage (e.g., fin) 172.6 .With deployable appendage 3.25 ..Removable 172.7 .With solar panel 3.26 ..Sliding 172.8 ..Having solar concentrator 3.27 ..Collapsible 172.9 ..Having launch hold down means 3.28 ...Longitudinally rotating 173.1 .With payload accommodation 3.29 ...Radially rotating -
The US Army Air Forces in WWII
DEPARTMENT OF THE AIR FORCE HEADQUARTERS UNITED STATES AIR FORCE Air Force Historical Studies Office 28 June 2011 Errata Sheet for the Air Force History and Museum Program publication: With Courage: the United States Army Air Forces in WWII, 1994, by Bernard C. Nalty, John F. Shiner, and George M. Watson. Page 215 Correct: Second Lieutenant Lloyd D. Hughes To: Second Lieutenant Lloyd H. Hughes Page 218 Correct Lieutenant Hughes To: Second Lieutenant Lloyd H. Hughes Page 357 Correct Hughes, Lloyd D., 215, 218 To: Hughes, Lloyd H., 215, 218 Foreword In the last decade of the twentieth century, the United States Air Force commemorates two significant benchmarks in its heritage. The first is the occasion for the publication of this book, a tribute to the men and women who served in the U.S. Army Air Forces during World War 11. The four years between 1991 and 1995 mark the fiftieth anniversary cycle of events in which the nation raised and trained an air armada and com- mitted it to operations on a scale unknown to that time. With Courage: U.S.Army Air Forces in World War ZZ retells the story of sacrifice, valor, and achievements in air campaigns against tough, determined adversaries. It describes the development of a uniquely American doctrine for the application of air power against an opponent's key industries and centers of national life, a doctrine whose legacy today is the Global Reach - Global Power strategic planning framework of the modern U.S. Air Force. The narrative integrates aspects of strategic intelligence, logistics, technology, and leadership to offer a full yet concise account of the contributions of American air power to victory in that war. -
Development of an Advanced Composite Aileron for the L-101 1 Transport Aircraft
NASA Contractor Report 3517 Development of an Advanced Composite Aileron for the L-101 1 Transport Aircraft C. F. Griffin and E. G. Dunning CONTRACT NASl-1506y FEBRUARY 1982 TECH LIBRARY KAFB, NM I1#111 Ill11lllllIll11lllll Ill1 lllll HI II 0062222 FEDD DOCUMENT Note that this document bears the label "FEDD," an acronym for "FOR EARLY DOMESTIC DISSEMINATION.’ The FEDD label is affixed to documents that may contain information having high commercial potential. The FEDD concept was developed as a result of the desire to maintain U.S. leadership in world trade markets and encourage a favorable balance of trade. Since the availability of tax- supported U.S. technology to foreign business interests could represent an unearned benefit, research results that may have high commercial potential are being distributed to U.S. industry in advance of general release. The recipient of this report must treat the information it contains according to the conditions of the FEDD label on the front cover. I -- -y NASA Contractor Report 3517 Development of an Advanced Composite Aileron for the L-101 1 Transport Aircraft C. F. Griffin Lockheed Corporation Burbank, California E. G. Dunning Avco Corporation Nasbde, Tennessee Prepared for Langley Research Center under Contract NAS l-15069 National Aeronautics and Space Administration Scientific and Technical Information Branch 1982 FOREWORD This report was prepared by the Lockheed-California Company, Lockheed Corporation, Burbank, California, under contract NASl-15069 and it is the summary report for the aileron program. The program is sponsored by the National Aeronautics and Space Administration (NASA), Langley Research Center. The Program Manager for Lockheed is F. -
Federal Register/Vol. 64, No. 123/Monday, June 28, 1999/Rules
34528 Federal Register / Vol. 64, No. 123 / Monday, June 28, 1999 / Rules and Regulations (2) Remove the temporary revision titled Federal Aviation Regulations (14 CFR 21.197 (k) This amendment becomes effective on ``Electrical Cables,'' dated March 7, 1996, and 21.199) to operate the airplane to a August 17, 1999. from the Pilot Operating Handbook (POH) location where the requirements of this AD Issued in Kansas City, Missouri, on June and insert a temporary revision titled can be accomplished. 18, 1999. ``Electrical Cables'' Rev. 1, dated July 12, (g) An alternative method of compliance or Michael Gallagher, 1996. Accomplish this action in accordance adjustment of the compliance times that with the Accomplishment Instructions provides an equivalent level of safety may be Manager, Small Airplane Directorate, Aircraft section in Pilatus PC XII SB No. 24±002, Rev. approved by the Manager, Small Airplane Certification Service. No. 1, dated September 20, 1996. Directorate, 1201 Walnut, suite 900, Kansas [FR Doc. 99±16277 Filed 6±25±99; 8:45 am] (b) For airplanes incorporating City, Missouri 64106. BILLING CODE 4910±13±U manufacturer serial numbers 101 through (1) The request shall be forwarded through 147, within the next 50 hours TIS after the an appropriate FAA Maintenance Inspector, effective date of this AD, replace the placard who may add comments and then send it to DEPARTMENT OF TRANSPORTATION installed near the standby magnetic compass the Manager, Small Airplane Directorate. that is required by AD 98±13±08, with a new (2) Alternative methods of compliance Federal Aviation Administration placard that incorporates the following words approved in accordance with AD 98±13±08 (using at least 1¤8inch letters): are not considered approved as alternative 14 CFR Part 39 STANDBY COMPASS FOR CORRECT methods of compliance for this AD.