...INTRODUCTION An exactly analysis of the landing gear, as designed on modern aircraft’s, is necessary to understand the construction and systems of the landing gear of the Airbus A320. Operation of the landing gear is made possible through extension/retraction, steering, braking and damping systems. In order to maintain the safety of the aircraft, the design of the landing is satisfied to the legislation of the European Aviation Safety Agency . With the knowledge of the landing gear construction of the Airbus A320, the forces on the construction calculated during different flight phases. In these flight phases the aircraft endures several forces. The materials that are used depends on the forces at the aircraft . Then, with a good insight of the A320’s landing gear I’m able to provide an in detail overview of the common faults and problems of the A320’s landing gear. These faults and problems have consequences for the aircrafts airworthiness. Change in the aircraft’s airworthiness requires maintenance with inevitable costs for the airline . The used main sources, serve as information to learn how the landing gear of the Airbus A320 operates. Literature review The Airbus A320 family consists of short- to medium-range, narrow-body, commercial passenger jet airliners manufactured by Airbus. The family includes the A318, A319, A320 and A321, and the ACJ business jet. Final assembly of the family in Europe takes place in Toulouse, France, and Hamburg, Germany. Since 2009...
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...------------------------------------------------- LANDING GEAR SYSTEM Prepared by: KHALID WALI MOHAMMAD 53259209393 Date: OCTOBER 12, 2011 TABLE OF CONTENT: TOPIC | PAGE | INTRODUCTION | 2 | GULFSTREAM G200 LANDING GEAR SYSTEM (GENERAL, MAIN LG) | 3 | NOSE LANDING GEAR AND EMERGENCY GEAR EXTENSION | 5 | LANDING GEAR SYSTEM CONROLS AND INDICATORS | 7 | WHEEL AND BRAKES | 8 | ANTI SKID SYSTEM | 10 | NOSE WHEEL STEERING SYSTEM | 13 | AIR BRAKES | 14 | BOEING 747 LANDING GEAR SYSTEM (GENERAL, MAIN GEAR AND DOORS) | 15 | NOSE GEAR AND DOORS | 16 | LANDING GEAR EXTENSION AND RETRACTION, WHEEL AND BRAKES AND STEERING | 18 | POSITION AND WARNING | 19 | CONCLUSION AND REFERENCES | 20 | INTRODUCTION: The undercarriage or landing gear in aviation is the structure that supports an aircraft on the ground and allows it to taxi, takeoff and land. Typically wheels are used, but skids, skis, floats or a combination of these and other elements can be deployed, depending on the surface. Landing gear usually includes wheels equipped with shock absorbers for solid ground, but some aircraft are equipped with skis for snow or floats for water, and/or skids or pontoons(helicopters). The undercarriage is a relatively heavy part of the vehicle, it can be as much as 7% of the takeoff weight, but more typically is 4-5%. Gulfstream G200 Landing Gear System General The G200 has 4 main landing gear tires and two nose landing gear tires. ...
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...DESIGN OF AN AUTOMATIC LANDING SYSTEM FOR A UAV USING FEEDBACK LINEARIZATION METHOD Ghassan. Atmeh1 and Zeaid, Hasan2 1 Mechanical and Aerospace Engineering Department, The University of Texas at Arlington, Arlington, Texas, email: atmehg@gmail.com 2 Mechanical Engineering Department, Texas A&M University, College Station, Texas, email: zeadnws@hotmail.com CmδE Cn CY CYo CYβ CYδR CYδA c d D g J L L m q R = = = = = = = = = = = = = = = = = Pitching moment coefficient due to elevator deflection Yawing moment coefficient Side-force coefficient Side-force coefficient for zero angle of attack Side-force coefficient contribution due to side-slip angle Side-force coefficient contribution due to rudder deflection Side-force coefficient contribution due to aileron deflection Wing cord (m) UAV displacement from glide path (m) Drag fore (N) Acceleration due to gravity (m/s2) Inertia matrix Lift force (N) Applied moment vector (N.m) Mass (kg) Dynamic pressure Slant range (m) ABSTRACT An automatic landing system for an unmanned aerial vehicle (UAV) is presented in the following paper. The nonlinear aircraft model with elevator deflection and thrust as control inputs is established using the appropriate aerodynamic data, followed by the definition of the flight trajectory the airplane is expected to travel during landing, which is divided into glide path and flare. Nonlinear control using feedback linearization method is employed to develop the automatic landing controller for the UAV...
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...controlled in National Airspace System (NAS) in the future. The goal of the effort behind the Next Generation Air Transportation System (NextGen) is to provide for safer and more efficient operations in the NAS. The backbone of this modernization will rely on celestial based systems such as the Global Position System (GPS) to provide the primary source of all navigation information during all phases of flight from taxiing, take-off, enroute, approach, and landing. It is the final two phases of flight, approach and landing, that require the greatest level of precision and continuity, and which will witness the largest change; the eventual elimination of the Instrument Landing System (ILS). Today, ILS offers the most accurate method of safely guiding pilots into a landing in low to almost no visibility conditions. NextGen plans for the elimination of this system in favor of a combination of GPS and Automatic Dependent Surveillance-Broadcast (ADS-B), and eventually ILS would not even be available for redundancy purposes. For such a critical phase of flight not only is an ILS currently the most accurate system, it should also be available for the foreseeable future to mitigate the lapses in the available GPS and INS technologies. Keywords: Instrument Landing System (ILS), Next Generation Air Transportation System (NextGen), Air Traffic Control (ATC), Global Positioning System (GPS), Wide Area Augmentation System (WAAS), Local Area Augmentation System (LAAS) Approaching ILS in NextGen ...
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...Report Currently I’ve been working on one gadget that belong to the Electronic flight instrument systems (EFIS) which is the primary flight display. This PFD will display the attitude and system control commands. Additionally it will be distributed in the following way. First, the attitude indicator will be displayed in the centre, this specifies the pitch, roll and stall angle of the aircraft. Second, at the left hand side the airspeed. This speed is measured in knots which are taken above mean sea level. Third at the right hand side the attitude indicator shown as numbers and next to it, the vertical attitude indicator which indicates how many feet per minute the aircraft is ascending. This V indicator illustrates in one or two unit number. For instance if is indicating number two (2) that means 2000 feet pre minute or 2 X 103 . There are some parts in the PFD that are going to be omitted, because some of the inputs are taken from other gadgets. For example: SPD: this allows the automatic pilot to take control of the velocity and other matters. CMD: indicates that the automatic pilot is on. Approach Reference: Displays the selected ILS identifier or frequency approach course and ILS DME distance. Glideslope and localizer Scales: appears when the previews frequency is in tune. At low altitudes and with the autopilot or flight director engage. Moreover, the package will have the functions or classes in order to enable these facilities if the other gadgets exist. PROBLEMS...
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...TABLE OF CONTENTS LIST OF FIGURES ................................................................................................................. ii LIST OF TABLES ................................................................................................................... ii ABSTRACT............................................................................................................................ iii CHAPTER 1: INTRODUCTION ............................................................................................ 1 1.1. 1.2. 1.3. 1.4. Introductory of the Title ........................................................................................... 1 Objective and Purpose ............................................................................................. 2 Problem Statement and Problem Solving ................................................................ 3 Limitation of the Project .......................................................................................... 4 CHAPTER 2: LITERITURE REVIEW ................................................................................... 5 2.1. 2.2. Research Theory, Ideology and Concept ................................................................. 5 Previous Research and Proposed Project Comparison........................................... 11 CHAPTER 3: METHODOLOGY ......................................................................................... 12 3.1.0 3.2.0. 3.2.1. 3.2.2. 3...
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...first officer, who was flying the aircraft, requested the wing flaps be extended to 15 degrees, then asked that the landing gear be lowered. As the landing gear extended, an unusual sound was heard and the aircraft yawed. Upon request, Portland approach then vectored the aircraft in a holding pattern southeast of the airport. After about an hour and a half of circling southeast of the airfield while the flight crew coped with the landing gear malfunction and prepared the passengers for a possible emergency landing, the captain finally decided to begin the approach to runway 28L. The plane crashed during the approach about 6 nautical miles southeast of the airport in a wooded populated of suburban Portland due to fuel exhaustion. The aircraft was destroyed and thankfully because there was no fuel in the fuel tanks, there was no fire. Of the 181 passengers and 8 crewmembers aboard, 8 passengers, the flight engineer, and a flight attendant were killed and 21 passengers and 2 crewmembers were seriously injured (National Transportation Safety Board, 1979). II. Problem The problem here is that there was absolutely no use of Crew Resource Management, there was an apparent fear of sternness and assertiveness from the copilot and flight engineer, and a huge lack of communication between crew members, which allowed all of the crew members to become so lost in the landing gear problem, allowing the aircraft fuel tanks to be run dry and...
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...The Major Aircraft Components ASCI 202 – Introduction to Aeronautical Science Embry Riddle Aeronautical University Abstract It is amazing to think that airplanes have been around for more than 100 years. From the Wrights brothers first flight on a handmade fixed-wing aircraft to the most technologically advanced aircraft in the world, the F-35 Lightning II Fighter jet. Despite their vast differences, these aircrafts have some things in common; they are run by major components and aerodynamics that make flying possible. The major components of an airplane and their functions are what make an aircraft fly into the air. An aircraft has five major components: fuselage, wings, landing gears, empennage, and power plants. The many complex parts of an aircraft and schematics are all responsible for making the aircraft design. In an effort to understand the design, it is imperative to break down the most common basic components to reflect how they work together to make an aircraft fly into the air. The fuselage is the part of an aircraft that is designed to carry cargo, equipment, people etc. Each major component is attached to the fuselage. The most common shape of a fuselage is a cylinder like tube that was designed to decrease drag and produce a little lift. The fuselage material is made of steel/aluminum. The different shapes are welded together to create the strength and bond it needs to hold together. The shaped pieces are called trusses ("Aircraft structure...
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... Institute of Engineering and Technology Philippine State College of Aeronautics Piccio Garden, Villamor, Pasay City ACKNOWLEDGEMENT Name: Chester Allan Mill D. Fetalino 2nd Semester S.Y. 2014-2015 Institute of Engineering and Technology Philippine State College of Aeronautics Piccio Garden, Villamor, Pasay City Table of Content Plate NO. | Title | Grade | 1 | 3 views | 1.25 | 2 | A/C Specification | 1.00 | 3 | Engine Description | 1.00 | 4 | Weight Estimation | 1.00 | 5 | Wing tips | 1.00 | 6 | Aft tail variations | 1.00 | 7 | Other tail configuration | 1.00 | 8 | Propulsion system options | 1.00 | 9 | Inlet locations-buried engines | 1.00 | 10 | Inlet locations-podded engines | 1.00 | 11 | Propeller location matrix | 1.00 | 12 | Landing gear arrangement | 1.00 | 13 | Gear/shock arrangement | 1.00 | 14 | A home for the gear | 1.00 | 15 | Flap types | 1.00 | 16 | Leading edge devices | 1.00 | 17 | Average cockpit dimensions needed to provide adequate room for the pilot | 1.00 | 18 | Suggested dimension for windows, doors, and spacing for passengers | 1.00 | 19 | Normal tandem seating arrangement | 1.00 | 20 | Average dimensions for seating when the leg is vertical | 1.00 | 21 | Average dimensions for seating when the lower leg is 45 degree to the vertical | 1.00 | 22 | Interior arrangement of a cabin | 1.00 | 23 | Toilet seating | 1.00 | 24 | A few governing dimensions are given in this illustration | 1.00 | 25...
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...ABNORMAL EVENTS All aircraft are designed to withstand the normal flight and landing loads expected during a typical flight cycle. These loads will include the normal manoeuvres the aircraft is expected to make. The designer will build in a safety factor to compensate for loads slightly larger than normal. Sometimes extreme circumstances occur which cause stresses outside the normal design limits. If the design limits are exceeded, then damage may occur to the aircraft. If it is known or suspected that the aircraft has be en subjected to excessive loads, then an inspection should be made, to ascertain the nature of any damage that may have occurred. The manufacturer will normally have anticipated the nature of some of these occurrences and detailed special checks for these µAbnormal Occurrences¶. 1.1 T YPES OF ABNORMAL OCCURRENCES The aircraft maintenance manual will normally list the types of abnormal occurrences needing special inspection. The list may vary, depending on the aircraft. The following items are a selection from a typical aircraft: y y y y y y y y y y y Lightning strikes High-intensity radiated fields penetration Heavy or overweight landing Flight through severe turbulence Burst tyre Flap or slat over-speed Flight through volcanic ash Tail strike Mercury spillage Dragged engine or e ngine seizure High-energy stop. 1.2 T YPES OF DAMAGE It is not intended to describe the types of damage applicable to every type of occurrence. It is more important...
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...DEVRY Development of Boeing 787 Dreamliner Course Project II Prepared for: Professor James Hiegel Project Risk Management Course PM595 Prepared by: Muzammil Qurashi February 19, 2012 [Type the abstract of the document here. The abstract is typically a short summary of the contents of the document. Type the abstract of the document here. The abstract is typically a short summary of the contents of the document.] Table of Contents Introduction Page 3 Sources of Construction Project Risk Page 4 Systems to Address Construction Project Risk Page 6 Catastrophic Failure Fault Tree Page 8 Discussion of Fault Tree Page 8 Fault Tree One Page 10 Discussion of Fault Tree One Page 10 Fault Tree Two Page 11 Discussion of Fault Tree Two Page 11 Conclusions Page 14 Works Cited Page 15 Introduction Boeing Commercial Airplanes' launched the 787 Dreamliner, a super-efficient airplane in order to meet the growing needs and preferences of an international audience across the globe. An international team of top aerospace companies is building the airplane, led by Boeing at its Everett, Wash. facility near Seattle (Boeing.com), According to Boeing’s statement, t\he 787-8 Dreamliner will carry 210 - 250 passengers on routes of 7,650 to 8,200 nautical miles (14,200 to 15,200 kilometers), while the 787-9 Dreamliner will carry 250 - 290 passengers on routes of 8,000 to 8,500 nautical miles (14,800 to 15,750 kilometers)....
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...IKARUS HUB & BLADE Faculty Advisor Easir Arafat Papon Group Members Shoyon Panday Adib Belhaj Hasan Nafiz Ahmed Khan Borhan Uddin Manam Table Of Contents Executive Summary Conceptual Design Preliminary Design Detail Design Flow Simulation Of Whole Aircraft Manufacturing Process & Plan CG Location Reference * ACRONYMS, ABBREVIATIONS, AND SYMBOLS NACA National Advisory Committee on Aeronautics | AR Aspect Ratio | Re Reynolds number | b Span | c Chord | s Wing area | t/c Thickness-to-chord ratio | MAC Mean Aerodynamic Chord | Cd0 Airfoil minimum coefficient of drag | CDi Aircraft induced drag coefficient (vortex drag) | CD0 Aircraft parasite drag coefficient | CD Aircraft drag coefficient | | CL Lift Co-efficient | * a) Executive Summary This report encompasses the design and manufacturing processes, conducted by the MILITARY INSTITUTE OF SCIENCE & TECHONOLOGY (MIST), DHAKA, where team ‘Hub & Blade’ is destined for their design report entry in the 1ST NATIONAL AERO-DESIGN COMPETITION & EXHIBITION . The theme of the competition is to design an aircraft. The goal of this competition is that the design will be in such a way that can fly with the highest advantageous materialistic body, having the lowest possible cost and weight. Team “Hub & Blade” is well on its way to bring a competitive fixed wing...
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...A 767 MAINTENANCE MANUAL AWAS ~¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼¼ ¦ PAGE DATE CODE ¦ PAGE DATE CODE ¦ PAGE DATE CODE ¦ ¦ ¦ ¦ ¦ ¦ ¦57-05-05 ¦57-31-01 ¦ ¦CHAPTER 57 TAB ¦ 201 DEC 22/09 01 ¦ 401 APR 22/01 01 ¦ ¦ ¦ 202 AUG 22/09 01 ¦ 402 APR 22/02 01 ¦ ¦WINGS ¦ 203 AUG 22/09 01 ¦ 403 APR 22/02 01 ¦ ¦ ¦ 204 AUG 22/09 01 ¦ 404 BLANK ¦ ¦EFFECTIVE PAGES ¦ 205 AUG 22/09 01 ¦ ¦ ¦SEE LAST PAGE OF LIST FOR ¦ 206 AUG 22/09 01 ¦57-41-56 ¦ ¦NUMBER OF PAGES ¦ 207 AUG 22/09 01 ¦ 401 APR 22/05 09 ¦ ¦ ¦ 208 AUG 22/09 01 ¦ 402 AUG 22/01 01 ¦ ¦ ¦ 209 AUG 22/09 01 ¦ 403 APR 22/09 03 ¦ ¦57-CONTENTS ¦ 210 AUG 22/09 03 ¦ 404 APR 22/09 03 ¦ ¦ 1 DEC 22/09 AWW ¦ 211 AUG 22/09 03 ¦ 405 DEC 22/08 02 ¦ ¦ 2 APR 22/09 AWW ¦ 212 AUG 22/09 03 ¦ 406 DEC 22/08 09 ¦ ¦ ¦ ¦ ¦ ¦57-00-00 ¦57-05-06 ¦57-41-57 ¦ ¦ 1 DEC 22/06 01 ¦ 201 DEC 22/09 01 ¦ 401 APR 22/03 01 ¦ ¦ 2 DEC 22/01 01 ¦ 202 AUG 22/09 01 ¦ 402 AUG 22/08 02 ¦ ¦ 3 FEB 10/94 01 ¦ 203 AUG 22/09 01 ¦ 403 APR 22/03 01 ¦ ¦ 4 AUG 22/99 01 ¦ 204 AUG 22/09 01 ¦ 404 AUG 22/08 02 ¦ ¦ 5 AUG 22/99 02 ¦ 205 AUG 22/09 01 ¦ 405 AUG 22/08 02 ¦ ¦ 6 BLANK ¦ 206 AUG 22/09 01 ¦ 406 AUG 22/08 02 ¦ ¦ ¦ 207 AUG 22/09 01 ¦ 407 AUG 22/08 01 ¦ ¦57-05-03 ¦ 208 AUG 22/09 01 ¦ 408 BLANK ¦ ¦ 201 DEC 22/09 03 ¦ 209 AUG 22/09 01 ¦ ¦ ¦ 202 AUG 22/09 06 ¦ 210 AUG 22/09 01 ¦57-41-58 ¦ ¦ 203 AUG 22/09 06 ¦ 211 AUG 22/09 01 ¦ 401 AUG 22/08 03 ¦ ¦ 204 AUG 22/09 06 ¦ 212 AUG 22/09 01 ¦ 402 AUG 22/08 03 ¦ ¦ 205 AUG 22/09...
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...Please do not call or email me and ask for an up dated resume… This is an up to date resume go to http://arthurwilson.vze.com And get a WORD DOC RESUME there. Thank You ARTHUR WILSON CLEVELAND, OHIO Home: (216) 441-3840 Cell : (216) 216 246-6422 Email : arthurwilson3rd@hotmail.com To see sample 3D models and Download Word doc of my resume, please go to my website at http://arthurwilson.vze.com http://www.turbosquid.com/Beta/Search/Index.cfm?keyword=arthurwilson3rd BACKGROUND: Over 20 years of practical work experience and on the job training in the engineering field. Experienced, capable and innovative mechanical designer with record of effective participation and leadership in vitally important and complex projects Demonstrated management competence and broad engineering comprehension by coordinating diverse mechanical engineering ,mechanical design and design drafting disciplines to effect optimum results in adhering to completion schedules and maintaining high quality, safe design and construction relating to the aerospace and defense industry per ANSI-Y-14.5 & DOD-D-100/DOD-STD-1000. EDUCATION: 1980 - 1983 Los. Angeles Trade Technical College Major Course of Study and Details of Classes Mechanical Design Drafting Computer Aided Drafting Tech. Illustration College Level Mathematics Mathematics for engineers ANSI-Y-14.5 Geometric Tolerances and Dimensioning Tolerance analysis and application in design/manufacturing practice. Tolerance...
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...Boeing’s ‘Dreamliner’ – an Operations Nightmare 1 a) Boeing is the world’s largest aerospace company and leading manufacturer of commercial jetliners and defence, space and security systems. Boeing’s products and services include commercial and military aircraft. It also includes satellites, weapons electronic and defence systems. 1 b) There are many issues Boeing had faced in introducing new technology to its ‘Dreamliner’ plane. Firstly, they had ditched the more traditional hydraulic systems for the landing gear and had gone for electric systems instead, and because of this, Boeing had left themselves working with something less familiar than the traditional landing gear to work with, therefore increasing the risks of the 787 plane and its landing. Although the technological leap was always likely to cause teething issues, it worsened when they decided to bring a high percentage of their plane parts from outside contractors. Again, by introducing new, foreign technology to its Dreamliner plane, Boeing had faced more issues than they would have because not only did it take longer for them to get the parts (delayed by 3 years) but it had also led to the parts not even fitting together properly, which causes even more delay and money to ‘fix’ the parts in order for them to somehow fit. 2 a) The use of sub-contracting may have been an unwise decision in the case of the Boeing Dreamliner because sub-contracting means employing a firm outside one’s company to do the work...
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