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The Medicine Bow Wind Energy Project
The Medicine Bow Wind Energy Project James Bailey Historic Reclamation Projects Bureau of Reclamation 2014 Table of Contents Table of Contents ............................................................................................................................. i The Medicine Bow Wind Energy Project ....................................................................................... 1 Introduction ................................................................................................................................. 1 Wind Energy: A Historic Context............................................................................................... 3 Enter the Curious Feds ................................................................................................................ 5 The Rise and Fall of Nuclear ...................................................................................................... 7 Energy Crisis: Alternative Sources Revisited ............................................................................. 8 Reclamation’s Early Investigations .......................................................................................... 12 Planning Studies and Project Approval .................................................................................... 15 The Project Gets Underway ...................................................................................................... 20 Project Dedication—and Project Problems ............................................................................. -
Study and Numerical Simulation of Unconventional Engine Technology
STUDY AND NUMERICAL SIMULATION OF UNCONVENTIONAL ENGINE TECHNOLOGY by ANJALI SHEKHAR B.E Aeronautical Engineering VTU, Karnataka, 2013 A thesis submitted in partial fulfillment of the requirements for the degree of Master of Science, Aerospace Engineering, College of Engineering and Applied Science, University of Cincinnati, Ohio 2018 Thesis Committee: Chair: Ephraim Gutmark, Ph.D. Member: Shaaban Abdallah, Ph.D. Member: Mark Turner, Sc.D. An Abstract of Study and Numerical Simulation of Unconventional Engine Technology by Anjali Shekhar Submitted to the Graduate Faculty as partial fulfillment of the requirements for the Master of Science Degree in Aerospace Engineering University of Cincinnati December 2018 The aim of this thesis is to understand the working of two unconventional aircraft propul- sion systems and to setup a two-dimensional transient simulation to analyze its operational mechanism. The air traffic has nearly increased by about 40% in past three decades and calls for alternative propulsion techniques to replace or support the current traditional propulsion methodology. In the light of current demand, the thesis draws motivation from renewed inter- est in two non-conventional propulsion techniques designed in the past and had not been given due importance due to various flaws/drawbacks associated. The thesis emphasizes on the work- ing of Von Ohains thermal compression engine and pulsejet combustors. Computational Fluid Dynamics is used in current study as it offers very high flexibility and can be modified easily to incorporate the required changes. Thermal Compression engine is a design suggested by Von Ohain in 1948. The engine works on the principle of pressure rise caused inside the engine which completely depends on the temperature of working fluid and independent of rotations per minute. -
Semiempirical Simulation of Contemporary Fighter Planes
| Mathematics | UDC 629.735.33.015.075 Zhelonkin M. V. Semiempirical simulation of contemporary fighter planes engaging in dogfight in order to estimate the possibility of using supermanoeuvrability modes The paper presents investigation results concerning employing supermanoeuvrability modes in dogfight. We selected one of the standard manoeuvres and demonstrated the efficiency of using it. Keywords: features, supermanoeuvrability, dogfight, semi-empirical simulation, tactical employment, Split S manoeuvre. Introduction of attack, which lead to intense deceleration of Fighter aviation is mostly used for dogfighting the aircraft and to a decrease in energy height, and one of the main tasks of preparation for en- therefore a Split S manoeuvre will compensate gaging enemy air targets is the training of flight such a decrease to some extent. personnel in operating fighter aircraft weapons in Thus, in order to evaluate the efficiency of order to achieve the best performance to destroy supermanoeuvrability modes, we have selected enemy aircraft during dogfighting in various a Split S manoeuvre. Fig. 1 shows the aircraft weather and operational conditions when acting flight path when making the manoeuvre. solo or as part of an aircraft group. Modern 4++ The most important parameter that defines and 5th generation fighters are able to fly in a su- tolerable conditions for making a Split S man- permanoeuvrability mode, i.e. at angles of attack oeuvre is minimum altitude loss during the ma- beyond stall while maintaining balanced control. noeuvre, which depends on the entry speed and That is why flight personnel need to be properly altitude, as well as on the current g-load and air- trained in order to use all the aircraft capabilities. -
NASA Technical Memorandum 102629
NASA Technical Memorandum 102629 QUALITATIVE EVALUATION OF A CONFORMAL VELOCITY VECTOR DISPLAY FOR USE AT HIGH ANGLES-OF-ATTACK IN FIGHTER AIRCRAFT DENISE R. JONES JAMES R. BURLEY II JUNE 1990 (NA_A-F_-10752_) .._tJALITATIVL i_VALLIATIjN I-!F A L.'_;_:,JPi,!,_.L V_Lr)CI'IV VLzfi[i!K ,..;[SPLAY l--,.}E US.'_- AT _IGH A_C, LzS-OF-ATTACK IN FIuHI-_H, AIRCRAFT (NASA) i1 D L;SCL Oi.r, National Aeronautics and Space Administration Langley Research Center Hampton, Virginia 23665-5225 SUMMARY A piloted simulation study has been conducted in the Langley Differential Maneuvering Simulator (DMS) to evaluate the utility of a display device designed to illustrate graphically and conformally the approximate location of a fighter aircraft's velocity vector. The display device consisted of two vertical rows of light- emitting diodes (LED's) located toward the center of the cockpit instrument panel, with one row of lights visible to the left of the control stick and the other row visible to the right of the control stick. The light strings provided a logical extension of the head-up display (HUD) velocity vector symbol at flight-path angles which exceeded the HUD field-of-view. Four test subjects flew a modified F/A-18 model with this display in an air-to-air engagement task against an equally capable opponent. Their responses to a questionnaire indicated that the conformal velocity vector information could not be used during the scenarios investigated due to the inability to visually track a target and view the lights simultaneously. INTRODUCTION During the course of fighter aircraft display format research, many pilots have expressed a desire to have the direction in which the aircraft is traveling (aircraft's velocity vector) presented in the cockpit. -
Design, Analyses, and ,. Simulation Results
NASA Technical Paper 3446 _:i,2 _ .,/, ! High-Alpha Research Vehicle (HARV) Longitudinal Controller: Design, Analyses, and ,. Simulation Results Aaron J. Ostroff Langley Research Center • Hampton, Virginia Keith D. Hoffler ViGYAN, Inc. • Hampton, Virginia Melissa S. Proffitt Lockheed Engineering & Sciences Company • Hampton, Virginia :' National Aeronautics and Space Administration Langley Research Center • Hampton, Virginia 23681-0001 • : J July 1994 /: The use of trademarks or names of manufacturers in this i! report is for accurate reporting and does not constitute an official endorsement, either expressed or implied, of such products or manufacturers by the National Aeronautics and Space Administration. Acknowledgment The authors wish to acknowledge the following individuals who made important contributions to the research described in this paper: Philip W. Brown, Michael R. Phillips, and Robert A. Rivers, all from NASA Langley Research Center, who served as test pilots and provided ratings and insightful comments for the piloted simulation tasks. Michael D. Messina, Lockheed Engineering & Sciences Company, Hampton, VA, who maintained the nonlinear batch simulation and organized test cases for transportingreal-time code. Susan W. Carzoo, Unisys Corporation, who maintained the real- time software for the piloted simulation. Dr. Barton J. Bacon, NASA Langley Research Center, who constructed and tested the real-lt algorithms used for robustness analysis. John V. Foster, NASA Langley Research Center, who performed some engineering-test -
Hydromatic Propeller
HYDROMATIC PROPELLER International Historic Engineering Landmark Hamilton Standard The American Society of A Division of United Technologies Mechanical Engineers Windsor Locks, Connecticut November 8, 1990 Historical Significance The text of this International Landmark Designation: The Hamilton Standard Hydromatic propeller represented INTERNATIONAL HISTORIC MECHANICAL a major advance in propeller design and laid the groundwork ENGINEERING LANDMARK for further advancements in propulsion over the next 50 years. The Hydromatic was designed to accommodate HAMILTON STANDARD larger blades for increased thrust, and provide a faster rate HYDROMATIC PROPELLER of pitch change and a wider range of pitch control. This WINDSOR LOCKS, CONNECTICUT propeller utilized high-pressure oil, applied to both sides of LATE 1930s the actuating piston, for pitch control as well as feathering — the act of stopping propeller rotation on a non-functioning The variable-pitch aircraft propeller allows the adjustment engine to reduce drag and vibration — allowing multiengined in flight of blade pitch, making optimal use of the engine’s aircraft to safely continue flight on remaining engine(s). power under varying flight conditions. On multi-engined The Hydromatic entered production in the late 1930s, just aircraft it also permits feathering the propeller--stopping its in time to meet the requirements of the high-performance rotation--of a nonfunctioning engine to reduce drag and military and transport aircraft of World War II. The vibration. propeller’s performance, durability and reliability made a The Hydromatic propeller was designed for larger blades, major contribution to the successful efforts of the U.S. and faster rate of pitch change, and wider range of pitch control Allied air forces. -
The Market for Aviation APU Engines
The Market for Aviation APU Engines Product Code #F644 A Special Focused Market Segment Analysis by: Aviation Gas Turbine Forecast Analysis 2 The Market for Aviation APU Engines 2011 - 2020 Table of Contents Executive Summary .................................................................................................................................................2 Introduction................................................................................................................................................................2 Methodology ..............................................................................................................................................................2 Trends..........................................................................................................................................................................3 The Competitive Environment...............................................................................................................................3 Market Statistics .......................................................................................................................................................3 Table 1 - The Market for Aviation APU Engines Unit Production by Headquarters/Company/Program 2011 - 2020 ..................................................5 Table 2 - The Market for Aviation APU Engines Value Statistics by Headquarters/Company/Program 2011 - 2020.................................................10 Figure 1 - The Market -
Sept09frontiers.Pdf
Frontierswww.boeing.com/frontiers SEPTEMBERAUGUSTJUNE 2009 20092009 / / / Volume VolumeVolume VIII, VIII,VIII, Issue IssueIssue IV VII Space for growth The arrival of Boeing’s newest satellite is opening doors to opportunities in the commercial market SEPTEMBER 2009 / BOEING FRONTIERS BOEING FRONTIERS / SEPTEMBER 2009 / VOLUME VIII, ISSUE V On the Cover 14 New bird Nearly one-third of the approximately 300 commercial satellites in orbit today were built by Boeing at its million- square-foot satellite factory in El Segundo, Calif. The latest model, known as the Boeing 702B, opens the door to many opportunities in the commercial market, where customers are looking for adaptable, medium- power satellites. Four years in development, the 702B from Boeing Space and Intelligence Systems made its debut in July. COVer IMAge: MiKE ConneLLY, Boeing InteLSAT PROGRAM DIRECTOR OF DIVISION OPERATIONS (LEFT), AND MIKE NEUMAN, 702B PROGRAM DIRECTOR, LEAD SPACE AND INTELLIGENCE SYSTEMS’ 702B SATELLITE PROGRAM. DANA REIMER/BOEING AND BOB FERGUSON/BOEING PHOTO: SPACECRAFT TECHNICIAN PAUL IM OF BOEING’S EL SEGUNDO, CALIF., SATELLITE FACTORY, ASSEMBLES A BATTERY PANEL USED ON THE 702B. BOB FERGUSON/BOEING BOEING FRONTIERS / SEPTEMBER 2009 / VOLUME VIII, ISSUE V 3 Frontiers Publisher: Tom Downey Table of contents Editorial director: Anne Toulouse EDITORIAL TEAM Executive editor: Paul Proctor: 312-544-2938 Editor: James Wallace: 312-544-2161 Managing editor: Vineta Plume: 312-544-2954 Art director: Brandon Luong: 312-544-2118 24 Commercial Airplanes editor: Julie O’Donnell: 206-766-1329 Super trip in 82 days Engineering, Operations & Technology Earlier this year, a Boeing-led team that included two Super Hornets circled the globe, editor: stopping in a number of countries to perform at air shows and display the jet fighters. -
22. Maneuvering at High Angle and Rate
12/3/18 Maneuvering at High Angles and Angular Rates Robert Stengel, Aircraft Flight Dynamics MAE 331, 2018 Learning Objectives • High angle of attack and angular rates • Asymmetric flight • Nonlinear aerodynamics • Inertial coupling • Spins and tumbling Flight Dynamics 681-785 Airplane Stability and Control Chapter 8 Copyright 2018 by Robert Stengel. All rights reserved. For educational use only. http://www.princeton.edu/~stengel/MAE331.html 1 http://www.princeton.edu/~stengel/FlightDynamics.html Tactical Airplane Maneuverability • Maneuverability parameters – Stability – Roll rate and acceleration – Normal load factor – Thrust/weight ratio – Pitch rate – Transient response – Control forces • Dogfights – Preferable to launch missiles at long range – Dogfight is a backup tactic – Preferable to have an unfair advantage • Air-combat sequence – Detection – Closing – Attack – Maneuvers, e.g., • Scissors • High yo-yo – Disengagement 2 1 12/3/18 Coupling of Longitudinal and Lateral-Directional Motions 3 Longitudinal Motions can Couple to Lateral-Directional Motions • Linearized equations have limited application to high-angle/high-rate maneuvers – Steady, non-zero sideslip angle (Sec. 7.1, FD) – Steady turn (Sec. 7.1, FD) – Steady roll rate " F FLon % F = $ Lon Lat−Dir ' $ FLat−Dir F ' # Lon Lat−Dir & Lon Lat−Dir FLat−Dir , FLon ≠ 0 4 2 12/3/18 Stability Boundaries Arising From Asymmetric Flight Northrop F-5E NASA CR-2788 5 Stability Boundaries with Nominal Sideslip, βo, and Roll Rate, po NASA CR-2788 6 3 12/3/18 Pitch-Yaw Coupling Due To Steady -
Development and Application of Management Tools Within a High-Mix, Low-Volume Lean Aerospace Manufacturing Environment
Development and Application of Management Tools within a High-Mix, Low-Volume Lean Aerospace Manufacturing Environment By Kevin McKenney S.B. Mechanical Engineering, Massachusetts Institute of Technology (2000) Submitted to the Department of Mechanical Engineering and the Sloan School of Management in Partial Fulfillment of the Requirements for the Degrees of Master of Science in Mechanical Engineering and Master of Business Administration MASSACHUSETTS INST E OF TECHNOLOGY In Conjunction with the Leaders for Manufacturing Program at the J Massachusetts Institute of Technology June 2005 LIBRARIES @2005 Massachusetts Institute of Technology. All rights reserved. Signature of Author Department of Mechanical EngiiYeering Sloan School of Management May 6, 2005 Certified by DavidHardt, Thesis Supervisor Professor of Mechanical Engineering Certified by Stephen Graves, Thesis Supervisor Abraham Siegel Professor of Management Accepted by David CapodiJatpoxeciti Director of Mastof's Prowgram Slan School of Management Accepted by____ LallBRa rnt Mehancal um ttee BARKER Department of Mechanical Engineering 2 Development and Application of Management Tools within a High-Mix, Low-Volume Lean Aerospace Manufacturing Environment By Kevin McKenney Submitted to the Department of Mechanical Engineering and the Sloan School of Management on May 6, 2005 in partial fulfillment of the Requirements for the Degrees of Master of Science in Mechanical Engineering and Master of Business Administration Abstract The design and implementation of a lean production system is a complex task requiring an intimate understanding of the fundamental lean principles. Much of the published lean literature is written at a high level of abstraction and contains very basic examples. When lean tools are applied blindly to complex, highly constrained systems, lean implementation becomes challenging and often ineffective. -
00002-X Challenges in High-Alpha Vehicle
Pergan~,on Prog. Aerospace ScL Vol. 31, pp. 291-334, 1995 Copyright © 1995 Elsevier Science Ltd Printed in Great Britain. All rights reserved 0376-0421(95)00002-X 0376-0421/95 $29.00 CHALLENGES IN HIGH-ALPHA VEHICLE DYNAMICS Lars E. Ericsson Engineering Consultant, Mountain View, California, U.S.A. Abstract--The evolution of aerospace vehicles towards ever-increasing maneuverability, including flight at high angles of attack and vehicle motions of large amplitudes and high angular rates, has led to the need for prediction of veh:Lcleaerodynamics that are dominated by unsteady separated flow effects. The existing data base is reviewed lo determine to what degree the following critical issues are understood: 1. Cause and effect of asymmetric fo:~ebody flow separation with associated vortices. 2. Cause of slender wing rock. 3. Effect of vehicle motion on dynamic airfoil stall. 4. Extrapolation from subscale tests to full-scale free flight. To extend the present knowledge to include the coupling existing between novel aerodynamic controls and the vehicle dynamics is the challenge facing designers of future agile aircraft operating at high angles of attack. CONTENTS NOTATION 1. INTRODUCTION 292 2. ASYMMETI~:IC FOREBODY FLOW SEPARATION 292 2.1. Introduction 292 2.2. Yaw characteristics 294 2.2.1. Moving wall effects 295 2.2.2. Flat spin 296 2.2.3. Reversal of coning motion 300 2.3. Roll characteristics 300 2.3.1. Dynamic forebody/leading-edge vortex interaction 301 2.4. Summary 306 3. SLENDER WING ROCK 306 3.1. Introduction 306 3.2. Recent e~perimental results and discussion 307 3.3. -
WPP Presentation
AE705 /153M/ 152 Introduction to Flight Fatima Salehbhai Third Year U G Student Mechanical Engg. Deptt. IIT Bombay Types of Propulsion Systems AE-705 Introduction to Flight Lecture No 11 Capsule-06 What is propulsion? • Moving or Pushing an object forward Propulsion = pro (forward) + pellere (drive) Why is propulsion needed in aircraft? • Getting aloft - thrust + lift • produces thrust to push an object • used to accelerate, gain altitude, and to maneuver AE-705 Introduction to Flight Lecture No 11 Capsule-06 Revising Thrust • Drives an airplane forward • To sustain lift and counteract drag http://howthingsfly.si.edu/media/thrust • Energy required • Heat by the combustion • Propulsion system • A machine that accelerates air backwards https://www.nasa.gov/audience/forstudents/k-4/stories /nasa-knows/what-is-aerodynamics-k4.html AE-705 Introduction to Flight Lecture No 11 Capsule-06 Propulsion Systems Mechanisms to produce thrust for flight AE-705 Introduction to Flight Lecture No 11 Capsule-06 Types of Propulsion Systems We'll discuss the following : • Pistonpropeller • Pulsejet • Turbojet • Ramjet • Afterburning Turbojet • Scramjet • Turbofan • Electric Propulsion • Turboprop • Ionic Propulsion • Turboshaft AE-705 Introduction to Flight Lecture No 11 Capsule-06 Powerplant Selection based on mission Source: D. P. Raymer, Aircraft Design, A Conceptual Approach, AIAA Education Series, 4th edition, 2006 AE-705 Introduction to Flight Lecture No 11 Capsule-06 Reciprocating Engines Primary powerplant for general aviation image source: https://www.comsol.com/blogs/improving-the-operational-lifetime-of-a-reciprocating-engine/