An introduction to flight control algorithms. Gertjan Looye 6SX%RQIVOYRKIRZSR71SRXIRIKVS
|
|
|
- Loren Norman
- 6 years ago
- Views:
Transcription
1 An introduction to flight control algorithms Gertjan Looye 6SX%RQIVOYRKIRZSR71SRXIRIKVS
2 About me Name: Gertjan Looye Education: Delft, Faculty of Aerospace Engineering MSc. (1996), PhD. (2008) Career: Institute of System Dynamics and Control (since 1996) Head of Aircraft Systems Dynamics (since 2013)
3 What are the two lectures about? Flight control laws In the following also referred to as FCLs Examples of FCL functions Basic principles of FCLs Focus: aircraft flight path control FCL design aspects Current developments
4 What are the two lectures about? Commanded variables Aircraft response Feedback control Three views: - The hardware view - The software view and - The system dynamics view
5 DLR.de Chart 5 Let s start with some examples
6 DLR.de Chart 6 Boeing 747 First aircraft with new generation of modern Autopilots that use Inertial Navigation Systems )VWXIVHIV;E]TSMRXWEYXSRSQJSPKX
7 DLR.de Chart 7 Hawker-Siddeley HS-121 Trident First aircraft with certified automatic landing system EYGLFIM7MGLX! ZMIP6IHYRHER^
8 DLR.de Chart 8 Lockheed Tristar First aircraft with certified active loads control system First (and only) aircraft with spoiler-based direct lift control (during approach and landing) %RHIV7XIPPIZSRWXEVOI7XVYOXYV LEXXIIWEOXMZI6IKIPYRKKIKIR:IVJSVQYRKI /SQTIRWEXMSRZSR8YVFYPIR^IR
9 DLR.de Chart 9 Airbus A320 NOT the first passenger aircraft with fly-by-wire controls (Concorde) First aircraft with control algorithms commanded by side-stick 4MPSX)MRKEFIRWXIYIVRRMGLXHMVIOXHMI7XIPPYRKHIV7XIPP GLIR WSRHIVR[IVHIRMR7IHMQIRXEXMSRWKIWGL[MRHMKOIMXYQKIVIGLRIX RIYXVEPI4SWMXMSR0SWPEWWIRFIYXIX0EKIFIMFILEPXIR
![7XVYOXYVWGL[MRKYRKIR[IVHIRQMX%IVSH]REQMWGLIR/V](/docs-images/72/66407514/images/10-1.jpg "JXIROSQTIRWMIVX")
10 DLR.de Chart 10 Airbus A /600 First aircraft with certified vibration control functions 7XVYOXYVWGL[MRKYRKIR[IVHIRQMX%IVSH]REQMWGLIR/V JXIROSQTIRWMIVX (MIWOERREYWKIWGLEPXIX[IVHIRJEPPWIWWGLPMQQIV[MVH
11 DLR.de Chart 11 Boeing ER First Boeing aircraft with pilot-commanded control algorithms First aircraft with anti tailstrike control laws 6 HIV[IVHIRFIMQ7XEVXKIRIMKXYQWGLRIPPIVEYJ^YLIFIR
12 DLR.de Chart 12 Boeing First aircraft with certified active flutter suppresion system
13 DLR.de Chart 13 X-31A First aircraft with thrust-vectoring control and post-stall manoeurving capability 7XEFMPFMW+VEHTMXGL 0ERHYRKQMXFMW^Y+VEHTMXGL %OXMZI/SRXVSPPKIKIREYJWIX^IR
14 DLR.de Chart 14 ATTAS DLR s former inflight simulator with experiment facility for flight control law testing *VIMTVSKVEQQMIVFEVI6IGLRIVER&SVH HMI1ERJ VHMI*PYKWXIYIVYRKERWGLPMI IRO RRXI
15 DLR.de Chart 15 Flight control functionalities So, there are quite some types of control functions: Automatic flight path and speed control Manual flightpath and speed control On-ground control Loads control Structural control, Active flutter suppression, Aircraft flight path Aircraft airframe We will focus on flight path control: manual or automatic
16 Planning Tuesday June 16 th o Examples of FCL functions o Aircraft flight dynamics: point-mass equations o Basic principles of flight path control o An autopilot control law that always works o Simulation experiments (RCAM example) Wednesday June 17 th o Aircraft flight dynamics: attitude dynamics o Basic principles of attitude control o Simulation experiments (RCAM example) o Optional: Future trends in flight control law design
17 DLR.de Chart 17 The Research Civil Aircraft Model (RCAM) Provided by Airbus for GARTEUR Project Robust Flight Control FM(AG08) Nonlinear 6DOF equations of motion Simple aerodynamics for landing configuration Used by 15 design teams for robust control design challenge Extensively published (book can be downloaded) Model is public domain (Matlab/Simulink) and available on request
18 DLR.de Chart 18 Equations of motion of a point mass TMXGL Small angle assumptions for aero angles No wind, just for this lecture! m = mass g = gravity acceleration L = Lift D = Drag Φ = Roll attitude angle
19 DLR.de Chart 19 Means of flight path control L T D
20 DLR.de Chart 20 Means of flight path control 0EKIHIW*PYK^YIKW L L 0 *PYKTJEH T,SVM^SRXEP TMXGL VSPP D Lift control: angle of attack
21 DLR.de Chart 21 The lift-drag polar Changing lift means Changing drag!
22 DLR.de Chart 22 Means of control of the flight path trajectory Φ L Lateral control: Tilt the lift vector! Φ
23 DLR.de Chart 23 Trimming the aircraft: straight flight = sin + = cos Φ = 0 8VMQQMRK!!7XIPPYRKWSHEWWHMIHMI0EKIWMGLRMGLXRHIVX %PWS%FPIMXYRK4MXGL!%FPIMXYRK6SPP! WMRHIV+PIMGLYRKWIX^IRYRH+PIMGLYRKYQWXIPPIR YQHMI+IWYGLXI:EVMEFPIRWSPP[IVXI^Y RHIR
24 DLR.de Chart 24 Trimming the aircraft: straight flight, higher flight path angle + =sin( + )+ = cos( + ) Φ = 0 In cosine: usually neglected
25 DLR.de Chart 25 Trimming the aircraft: straight flight, higher airspeed + = sin + + = cos Φ = 0 Why does D change? Does D increase or decrease?
26 DLR.de Chart 26 The backside of the power curve
27 DLR.de Chart 27 The Phugoid motion: linearised equations ( +sin +cos = + 1 2, +, ( +sin sin = 1 2,+ +, ( + ) = 1 2, ( sin = 1 2 +, = 1, 1, sin
28 DLR.de Chart 28 The Phugoid motion: exchange between kinetic and potential enery
29 DLR.de Chart 29 Flight control at last! Today: automatic flight path and speed control Most aircraft use a combination of Autopilot control flight path angles via aircraft attitude, and Autothrottle control speed using thrust Modern autopilots / autothrottles have quite some modes:. 2MGLX-HIEP QERWSPPEYJV YQIR "L]VEVGLMGLIJYROXMSRIR source: T. Lambregts
30 DLR.de Chart 30 Design requirements (qualitatively) Stability and stability margins in any flight condition (remember: feedback control!) Smooth command responses (no overshoots, no excessive accelerations, ) Smooth control commands (engines!!) Decoupling Envelope protection Response to failure cases Interactions with other disciplines (loads, flutter, )
31 DLR.de Chart 31 An autopilot control law that always works Let s go one step back, now reasoning the other way around: Specific excess energy This equation tells us: Thrust affects acceleration and flight path angle As an autopilot / autothrottle have to control both: Use thrust to control the specific excess energy!!
32 DLR.de Chart 32 An autopilot control law that always works Question: how to distribute between potential and kinetic energy? Answer: Use aircraft attitude to control:
33 DLR.de Chart 33 The Total Energy Control System (TECS)! " + =T - D + $ $ &' ( )" = KTI *!( " + $! " + KTP! " + Control Algorithm! $ = KEI% $ $ KEP
34 DLR.de Chart 34 The Total Energy Control System (TECS) Inventor: Tony Lambregts
35 DLR.de Chart 35 Mode implementation becomes easy! V c WSPP8EVKIX: HM!IVV +! $ %YXSXVLXXPI7GLYFVIKIPYRK QYWWEPPIWOSVVMKMIVIR[EW HIV%YXSTMPSKVYMRMIVX V TAS MWX+IQIWWIR h c WSPP +, $ %YXSTMPSX 0EKI h MWX
36 DLR.de Chart 36 TECS as an autopilot core
37 DLR.de Chart 37 Means of flight path control: lateral Φ L TMXGL Φ $ = χ $ = + χ $ χ Φ Control Algorithm!
38 DLR.de Chart 38 Online demo
39 DLR.de Chart 39 The effect of wind The following shows an example of a flight test with focus on wind effects So far, we did not discuss this, but wind, turbulence and wind shears have a massive inpact on the design of flight control laws
40 Flight test: Definition of approach trajectory Spiral Runway G/A LOC / Alt / CAS hold ILS FPA ~ -3deg Hinit ILS Standard ILS approach Hend Rturn Dturn Ground Track
41 Background motivation: Helical Noise Abatement Procedure (HeNAP) 66 db Kontur Standartanflug 66 db Kontur Spiralanflug maximale Schalldruckpegel am Boden
42 Wind (kts) Results Go-arounds Runway EDVE Helical approaches h [m] Steep approaches X [m] Ground tracks 1000 Y [m]
43 Results: roll and side slip angles Roll angle Side slip angle (sensor) Side slip angle (synth.) 25 Varying roll 20angle due to varying Ground speed 15 (airspeed is held constant) φ, β [deg] time [s]
44 Results: velocities 105 Ground speed V CAS, V, V compl [m/s] V CAS V V compl Air speed time [s] Go-around
45 Turning flight in constant wind V not constant! Simplification: Level flight µ mg/cos(µ) Y [m] Adapting bank angle mv rhelix mv 2 r helix 2 mg 2 V = mg tan µ = tan µ gr helix r helix Bank angle µ [deg] Constant bank angle X [m] No Wind Wind 20 kts, χ W = Track angle χ [deg] 4 1 Folie 45> Vortrag > Autor Dokumentname > Datum
46 Results: crab angle wind Aircraft heading
47 DLR.de Chart 47 Dealing with noisy airdata: complement airdata and inertial data
48 DLR.de Chart 48 Two complicated figures (1/2)
49 DLR.de Chart 49 Definition of pitch attitude L 0 D
50 DLR.de Chart 50 Two complicated figures (2/2)
51 DLR.de Chart 51 The Newton-Euler moment equations of motion See for example: Flugregelung, R. Brockhaus, Springer
52 DLR.de Chart 52 Rolling moment control - =./ & & Simplified: - =./ &- -
53 DLR.de Chart 53 Yawing moment control : - =./ ; ; ; 6 7+ ;&8 8 + ; &
54 DLR.de Chart 54 Couplings - =./ & &- - : - =./ ; ; ; 6 7+ ;&8 8 + ; &- -
55 DLR.de Chart 55 Pitching moment control < - =./ ) + ) =. 3 + ) + )&> > - 8
56 DLR.de Chart 56 A very common approach for attitude control: Nonlinear Dynamic Inversion Invert the equation: Angular rates Angular accelerations are commanded, control surface deflections computed! We will use the roll example to explain ist principles: - =./ &- -
57 DLR.de Chart 57 NDI applied to roll 23 =./ &- - - = $ Ideal case: 23 = 2$
58 Completing the control loop pc ' p c 1 s Perfect inversion p b Far better: p c 1 s y c p& c y& c Command shaping (reference model) y Disturbance rejection
59 Completing the control loop pc ' p c 1 s Perfect inversion p b Command shaping and disturbance rejection Far better: p c 1 s y c p& c y& c Command shaping (reference model) y Disturbance rejection
60 DLR.de Chart 60 Online demo
61 Dynamic Inversion: advantages/disadvantages Advantages: Application to aircraft is straight forward Excellent nominal performance: decoupling and linearization of A/C dynamics Potentially elaborate gain-scheduling is avoided Disadvantages: No inherent robustness to modeling errors and model simplifications Control laws inherit complexity of the aircraft model Inversion, implementation, and verification may be tedious and error-prone Saturation Also note: Requires state feedback Internal stability of zero-dynamics has to be checked afterwards
62 DLR.de Chart 62 Some future trends: adaptive / fault tolerant control - = $ online Determination (system identification) - = $ Messen
63 DLR.de Chart 63 Control design integrated into aircraft design process
64 DLR.de Chart 64 New configurations
65 DLR.de Chart 65 End Thank you for your attention! Also see the RCAM example models!
66 DLR.de Chart 66 Contact Gertjan Looye Deutsches Zentrum für Luft- und Raumfahrt e.v. (DLR) German Aerospace Center Oberpfaffenhofen Institute of System Dynamics and Control Department of Aircraft Systems Dynamics A: Wessling Germany T: 08153/ F: 08153/ E: I:
Department of Aerospace Engineering and Mechanics University of Minnesota Written Preliminary Examination: Control Systems Friday, April 9, 2010
Department of Aerospace Engineering and Mechanics University of Minnesota Written Preliminary Examination: Control Systems Friday, April 9, 2010 Problem 1: Control of Short Period Dynamics Consider the
Mech 6091 Flight Control System Course Project. Team Member: Bai, Jing Cui, Yi Wang, Xiaoli
Mech 6091 Flight Control System Course Project Team Member: Bai, Jing Cui, Yi Wang, Xiaoli Outline 1. Linearization of Nonlinear F-16 Model 2. Longitudinal SAS and Autopilot Design 3. Lateral SAS and Autopilot
FLIGHT DYNAMICS. Robert F. Stengel. Princeton University Press Princeton and Oxford
FLIGHT DYNAMICS Robert F. Stengel Princeton University Press Princeton and Oxford Preface XV Chapter One Introduction 1 1.1 ELEMENTS OF THE AIRPLANE 1 Airframe Components 1 Propulsion Systems 4 1.2 REPRESENTATIVE
A SIMPLIFIED ANALYSIS OF NONLINEAR LONGITUDINAL DYNAMICS AND CONCEPTUAL CONTROL SYSTEM DESIGN
A SIMPLIFIED ANALYSIS OF NONLINEAR LONGITUDINAL DYNAMICS AND CONCEPTUAL CONTROL SYSTEM DESIGN ROBBIE BUNGE 1. Introduction The longitudinal dynamics of fixed-wing aircraft are a case in which classical
Autopilot design for small fixed wing aerial vehicles. Randy Beard Brigham Young University
Autopilot design for small fixed wing aerial vehicles Randy Beard Brigham Young University Outline Control architecture Low level autopilot loops Path following Dubins airplane paths and path management
CHAPTER 1. Introduction
CHAPTER 1 Introduction Linear geometric control theory was initiated in the beginning of the 1970 s, see for example, [1, 7]. A good summary of the subject is the book by Wonham [17]. The term geometric
Chapter 9. Nonlinear Design Models. Beard & McLain, Small Unmanned Aircraft, Princeton University Press, 2012, Chapter 9, Slide 1
Chapter 9 Nonlinear Design Models Beard & McLain, Small Unmanned Aircraft, Princeton University Press, 2012, Chapter 9, Slide 1 Architecture Destination, obstacles Waypoints Path Definition Airspeed, Altitude,
Mechanics of Flight. Warren F. Phillips. John Wiley & Sons, Inc. Professor Mechanical and Aerospace Engineering Utah State University WILEY
Mechanics of Flight Warren F. Phillips Professor Mechanical and Aerospace Engineering Utah State University WILEY John Wiley & Sons, Inc. CONTENTS Preface Acknowledgments xi xiii 1. Overview of Aerodynamics
Flight Dynamics, Simulation, and Control
Flight Dynamics, Simulation, and Control For Rigid and Flexible Aircraft Ranjan Vepa CRC Press Taylor & Francis Group Boca Raton London New York CRC Press is an imprint of the Taylor & Francis Group, an
Localizer Hold Autopilot
Localizer Hold Autopilot Prepared by A.Kaviyarasu Assistant Professor Department of Aerospace Engineering Madras Institute Of Technology Chromepet, Chennai Localizer hold autopilot is one of the important
Aim. Unit abstract. Learning outcomes. QCF level: 6 Credit value: 15
Unit T23: Flight Dynamics Unit code: J/504/0132 QCF level: 6 Credit value: 15 Aim The aim of this unit is to develop learners understanding of aircraft flight dynamic principles by considering and analysing
Chapter 1 Lecture 2. Introduction 2. Topics. Chapter-1
Chapter 1 Lecture 2 Introduction 2 Topics 1.4 Equilibrium of airplane 1.5 Number of equations of motion for airplane in flight 1.5.1 Degrees of freedom 1.5.2 Degrees of freedom for a rigid airplane 1.6
CDS 101/110a: Lecture 8-1 Frequency Domain Design
CDS 11/11a: Lecture 8-1 Frequency Domain Design Richard M. Murray 17 November 28 Goals: Describe canonical control design problem and standard performance measures Show how to use loop shaping to achieve
Lecture AC-1. Aircraft Dynamics. Copy right 2003 by Jon at h an H ow
Lecture AC-1 Aircraft Dynamics Copy right 23 by Jon at h an H ow 1 Spring 23 16.61 AC 1 2 Aircraft Dynamics First note that it is possible to develop a very good approximation of a key motion of an aircraft
Fundamentals of Airplane Flight Mechanics
David G. Hull Fundamentals of Airplane Flight Mechanics With 125 Figures and 25 Tables y Springer Introduction to Airplane Flight Mechanics 1 1.1 Airframe Anatomy 2 1.2 Engine Anatomy 5 1.3 Equations of
Chapter 2 Review of Linear and Nonlinear Controller Designs
Chapter 2 Review of Linear and Nonlinear Controller Designs This Chapter reviews several flight controller designs for unmanned rotorcraft. 1 Flight control systems have been proposed and tested on a wide
Longitudinal Automatic landing System - Design for CHARLIE Aircraft by Root-Locus
International Journal of Scientific and Research Publications, Volume 3, Issue 7, July 2013 1 Longitudinal Automatic landing System - Design for CHARLIE Aircraft by Root-Locus Gaber El-Saady, El-Nobi A.Ibrahim,
Flight and Orbital Mechanics
Flight and Orbital Mechanics Lecture slides Challenge the future 1 Flight and orbital mechanics Flight Mechanics practice questions Dr. ir. Mark Voskuijl 20-11-2013 Delft University of Technology Challenge
Introduction to Flight Dynamics
Chapter 1 Introduction to Flight Dynamics Flight dynamics deals principally with the response of aerospace vehicles to perturbations in their flight environments and to control inputs. In order to understand
Flight and Orbital Mechanics
Flight and Orbital Mechanics Lecture slides Challenge the future 1 Flight and Orbital Mechanics Lecture 7 Equations of motion Mark Voskuijl Semester 1-2012 Delft University of Technology Challenge the
FAULT DETECTION AND FAULT TOLERANT APPROACHES WITH AIRCRAFT APPLICATION. Andrés Marcos
FAULT DETECTION AND FAULT TOLERANT APPROACHES WITH AIRCRAFT APPLICATION 2003 Louisiana Workshop on System Safety Andrés Marcos Dept. Aerospace Engineering and Mechanics, University of Minnesota 28 Feb,
A Nomenclature and Acronyms A.1 List of Acronyms
A Nomenclature and Acronyms A.1 List of Acronyms Acronym Definition AA Absolute Amplitude ADMIRE Aero-Data Model In Research Environment AG Action Group Airbus Airbus Deutschland GmbH AoA Angle of Attack
Chapter 4 The Equations of Motion
Chapter 4 The Equations of Motion Flight Mechanics and Control AEM 4303 Bérénice Mettler University of Minnesota Feb. 20-27, 2013 (v. 2/26/13) Bérénice Mettler (University of Minnesota) Chapter 4 The Equations
State Estimation for Autopilot Control of Small Unmanned Aerial Vehicles in Windy Conditions
University of Colorado, Boulder CU Scholar Aerospace Engineering Sciences Graduate Theses & Dissertations Aerospace Engineering Sciences Summer 7-23-2014 State Estimation for Autopilot Control of Small
Fault-Tolerant Control of a Unmanned Aerial Vehicle with Partial Wing Loss
Preprints of the 19th World Congress The International Federation of Automatic Control Fault-Tolerant Control of a Unmanned Aerial Vehicle with Partial Wing Loss Wiaan Beeton J.A.A. Engelbrecht Stellenbosch
Flight and Orbital Mechanics
Flight and Orbital Mechanics Lecture slides Challenge the future 1 Flight and Orbital Mechanics Lecture hours 3, 4 Minimum time to climb Mark Voskuijl Semester 1-2012 Delft University of Technology Challenge
Chapter 1. Introduction. 1.1 System Architecture
Chapter 1 Introduction 1.1 System Architecture The objective of this book is to prepare the reader to do research in the exciting and rapidly developing field of autonomous navigation, guidance, and control
M 21 M 22 1 S. . x. x u B D A C
Robstness Assessment of Flight Controllers for a Civil Aircraft sing,analysis. G.H.N. Looye ;2, S. Bennani 2, A. Varga, D. Moormann, G. Grbel Detsches Zentrm fr Lft- nd Ramfahrt (DLR) Institt fr Robotik
Aircraft Stability and Performance 2nd Year, Aerospace Engineering
Aircraft Stability and Performance 2nd Year, Aerospace Engineering Dr. M. Turner March 6, 207 Aims of Lecture Part. To examine ways aircraft turn 2. To derive expressions for correctly banked turns 3.
DEMONSTRATION OF THE OPTIMAL CONTROL MODIFICATION FOR GENERAL AVIATION: DESIGN AND SIMULATION. A Thesis by. Scott Reed
DEMONSTRATION OF THE OPTIMAL CONTROL MODIFICATION FOR GENERAL AVIATION: DESIGN AND SIMULATION A Thesis by Scott Reed Bachelor of Science, Wichita State University, 2009 Submitted to the Department of Aerospace
What is flight dynamics? AE540: Flight Dynamics and Control I. What is flight control? Is the study of aircraft motion and its characteristics.
KING FAHD UNIVERSITY Department of Aerospace Engineering AE540: Flight Dynamics and Control I Instructor Dr. Ayman Hamdy Kassem What is flight dynamics? Is the study of aircraft motion and its characteristics.
6th USA/Europe ATM 2005 R&D Seminar Statistical performance evaluation between linear and nonlinear designs for aircraft relative guidance
direction des services de la Navigation aérienne direction de la Technique et de Presented by Thierry MIQUE 6th USA/Europe ATM 005 R&D Seminar Statistical performance evaluation between linear and nonlinear
Modeling of a Small Unmanned Aerial Vehicle
Modeling of a Small Unmanned Aerial Vehicle A. Elsayed Ahmed, A. Hafez, A. N. Ouda, H. Eldin Hussein Ahmed, H. Mohamed Abd-Elkader Abstract Unmanned aircraft systems (UAS) are playing increasingly prominent
MAE 142 Homework #5 Due Friday, March 13, 2009
MAE 142 Homework #5 Due Friday, March 13, 2009 Please read through the entire homework set before beginning. Also, please label clearly your answers and summarize your findings as concisely as possible.
A Blade Element Approach to Modeling Aerodynamic Flight of an Insect-scale Robot
A Blade Element Approach to Modeling Aerodynamic Flight of an Insect-scale Robot Taylor S. Clawson, Sawyer B. Fuller Robert J. Wood, Silvia Ferrari American Control Conference Seattle, WA May 25, 2016
Adaptive Augmentation of a Fighter Aircraft Autopilot Using a Nonlinear Reference Model
Proceedings of the EuroGNC 13, 2nd CEAS Specialist Conference on Guidance, Navigation & Control, Delft University of Technology, Delft, The Netherlands, April -12, 13 Adaptive Augmentation of a Fighter
Fullscale Windtunnel Investigation of Actuator Effectiveness during Stationary Flight within the Entire Flight Envelope of a Tiltwing MAV
Fullscale Windtunnel Investigation of Actuator Effectiveness during Stationary Flight within the Entire Flight Envelope of a Tiltwing MAV M. Schütt, P. Hartmann and D. Moormann Institute of Flight System
PRINCIPLES OF FLIGHT
1 Considering a positive cambered aerofoil, the pitching moment when Cl=0 is: A infinite B positive (nose-up). C negative (nose-down). D equal to zero. 2 The angle between the aeroplane longitudinal axis
Lecture 10. Example: Friction and Motion
Lecture 10 Goals: Exploit Newton s 3 rd Law in problems with friction Employ Newton s Laws in 2D problems with circular motion Assignment: HW5, (Chapter 7, due 2/24, Wednesday) For Tuesday: Finish reading
Aerobatic Maneuvering of Miniature Air Vehicles Using Attitude Trajectories
Brigham Young University BYU ScholarsArchive All Faculty Publications 28-8 Aerobatic Maneuvering of Miniature Air Vehicles Using Attitude Trajectories James K. Hall Brigham Young University - Provo, hallatjk@gmail.com
AEROSPACE ENGINEERING
AEROSPACE ENGINEERING Subject Code: AE Course Structure Sections/Units Topics Section A Engineering Mathematics Topics (Core) 1 Linear Algebra 2 Calculus 3 Differential Equations 1 Fourier Series Topics
Pitch Control of Flight System using Dynamic Inversion and PID Controller
Pitch Control of Flight System using Dynamic Inversion and PID Controller Jisha Shaji Dept. of Electrical &Electronics Engineering Mar Baselios College of Engineering & Technology Thiruvananthapuram, India
Autonomous Robotic Vehicles
Autonomous Robotic Vehicles Ground, Air, Undersea Jim Keller July 15, 2005 Types of Vehicles Ground Wheeled Tracked Legged Crawling/snake Air Fixed wing Powered gliders Rotary wing Flapping wing Morphing
AFRL MACCCS Review. Adaptive Control of the Generic Hypersonic Vehicle
AFRL MACCCS Review of the Generic Hypersonic Vehicle PI: Active- Laboratory Department of Mechanical Engineering Massachusetts Institute of Technology September 19, 2012, MIT AACL 1/38 Our Team MIT Team
Performance. 7. Aircraft Performance -Basics
Performance 7. Aircraft Performance -Basics In general we are interested in finding out certain performance characteristics of a vehicle. These typically include: how fast and how slow an aircraft can
Quadrotor Modeling and Control
16-311 Introduction to Robotics Guest Lecture on Aerial Robotics Quadrotor Modeling and Control Nathan Michael February 05, 2014 Lecture Outline Modeling: Dynamic model from first principles Propeller
Flight and Orbital Mechanics. Exams
1 Flight and Orbital Mechanics Exams Exam AE2104-11: Flight and Orbital Mechanics (23 January 2013, 09.00 12.00) Please put your name, student number and ALL YOUR INITIALS on your work. Answer all questions
8 The HIRM+ Flight Dynamics Model
8 The HIRM+ Flight Dynamics Model Dieter Moormann EADS Deutschland GmbH, Military Aircraft MT62 Flight Dynamcis, 81663 München, Germany Dieter.Moormann@m.eads.net Summary. The major objective of the GARTEUR
VN-100 Velocity Compensation
VN-100 Velocity Compensation Velocity / Airspeed Aiding for AHRS Applications Application Note Abstract This application note describes how the VN-100 can be used in non-stationary applications which require
Turn Performance of an Air-Breathing Hypersonic Vehicle
Turn Performance of an Air-Breathing Hypersonic Vehicle AIAA Aircraft Flight Mechanics Conference Derek J. Dalle, Sean M. Torrez, James F. Driscoll University of Michigan, Ann Arbor, MI 4809 August 8,
Robot Control Basics CS 685
Robot Control Basics CS 685 Control basics Use some concepts from control theory to understand and learn how to control robots Control Theory general field studies control and understanding of behavior
Stability and Control Analysis in Twin-Boom Vertical Stabilizer Unmanned Aerial Vehicle (UAV)
International Journal of Scientific and Research Publications, Volume 4, Issue 2, February 2014 1 Stability and Control Analysis in Twin-Boom Vertical Stabilizer Unmanned Aerial Vehicle UAV Lasantha Kurukularachchi*;
Fault-Tolerant Flight Control Using One Aerodynamic Control Surface
Fault-Tolerant Flight Control Using One Aerodynamic Control Surface Raghu Venkataraman and Peter Seiler University of Minnesota, Minneapolis, Minnesota 55455 This paper considers a statically stable unmanned
Numeric Simulation of Glider Winch Launches. Andreas Gäb, Christoph Santel
Numeric Simulation of Glider Winch Launches Andreas Gäb, Christoph Santel Communicated by Prof. Dr.-Ing. D. Moormann Institute of Flight System Dynamics RWTH Aachen University Jul. 28-Aug. 4, 2010 XXX
AE Stability and Control of Aerospace Vehicles
AE 430 - Stability and ontrol of Aerospace Vehicles Static/Dynamic Stability Longitudinal Static Stability Static Stability We begin ith the concept of Equilibrium (Trim). Equilibrium is a state of an
/ m U) β - r dr/dt=(n β / C) β+ (N r /C) r [8+8] (c) Effective angle of attack. [4+6+6]
![/ m U) β - r dr/dt=(n β / C) β+ (N r /C) r [8+8] (c) Effective angle of attack. [4+6+6]](/thumbs/91/105418625.jpg "/ m U) β - r dr/dt=(n β / C) β+ (N r /C) r [8+8] (c) Effective angle of attack. [4+6+6]")
Code No: R05322101 Set No. 1 1. (a) Explain the following terms with examples i. Stability ii. Equilibrium. (b) Comment upon the requirements of stability of a i. Military fighter aircraft ii. Commercial
Stability and Control
Stability and Control Introduction An important concept that must be considered when designing an aircraft, missile, or other type of vehicle, is that of stability and control. The study of stability is
JAA Administrative & Guidance Material Section Five: Licensing, Part Two: Procedures
Introduction: 1 - To fully appreciate and understand subject 032 Performance (Aeroplanes), the applicant will benefit from background knowledge in Subject 081 Principles of Flight (Aeroplanes). 2 For JAR-FCL
Problem 1: Ship Path-Following Control System (35%)
Problem 1: Ship Path-Following Control System (35%) Consider the kinematic equations: Figure 1: NTNU s research vessel, R/V Gunnerus, and Nomoto model: T ṙ + r = Kδ (1) with T = 22.0 s and K = 0.1 s 1.
Glide-Path Stability of an Aircraft under Speed Constraint
ttg3 N. & M. No. 3705 e 3 2: -it ' ),'~4 t4. ~ MINISTRY OF DEFENCE (PROCUREMENT EXECUTIVE) AERONAUTICAL RESEARCH COUNCIL REPORTS AND MEMORANDA Glide-Path Stability of an Aircraft under Speed Constraint
The Role of Zero Dynamics in Aerospace Systems
The Role of Zero Dynamics in Aerospace Systems A Case Study in Control of Hypersonic Vehicles Andrea Serrani Department of Electrical and Computer Engineering The Ohio State University Outline q Issues
A WAVELET BASED FLIGHT DATA PREPROCESSING METHOD FOR FLIGHT CHARACTERISTICS ESTIMATION AND FAULT DETECTION
A WAVELET BASED FLIGHT DATA PREPROCESSING METHOD FOR FLIGHT CHARACTERISTICS ESTIMATION AND FAULT DETECTION Masaru Naruoka Japan Aerospace Exploration Agency Keywords: Flight analyses, Multiresolution Analysis,
Design of Robust Dynamic Inversion Control Laws using Multi-Objective Optimization
AIAA--485 Design of Robust Dynamic Inversion Control Laws using Multi-Objective Optimization Gertjan Looye and Hans-Dieter Joos German Aerospace Center DLR-Oberpfaffenhofen Institute for Robotics and Mechatronics
Trajectory tracking & Path-following control
Cooperative Control of Multiple Robotic Vehicles: Theory and Practice Trajectory tracking & Path-following control EECI Graduate School on Control Supélec, Feb. 21-25, 2011 A word about T Tracking and
Efficient Modelling of a Nonlinear Gust Loads Process for Uncertainty Quantification of Highly Flexible Aircraft
Efficient Modelling of a Nonlinear Gust Loads Process for Uncertainty Quantification of Highly Flexible Aircraft SciTech, 8 th -12 th January 2018 Kissimmee, Florida Robert Cook, Chris Wales, Ann Gaitonde,
Applications Linear Control Design Techniques in Aircraft Control I
Lecture 29 Applications Linear Control Design Techniques in Aircraft Control I Dr. Radhakant Padhi Asst. Professor Dept. of Aerospace Engineering Indian Institute of Science - Bangalore Topics Brief Review
MODIFICATION OF AERODYNAMIC WING LOADS BY FLUIDIC DEVICES
Journal of KONES Powertrain and Transport, Vol. 21, No. 2 2014 MODIFICATION OF AERODYNAMIC WING LOADS BY FLUIDIC DEVICES Institute of Aviation Department of Aerodynamics and Flight Mechanics Krakowska
MODELING OF A SMALL UNMANNED AERIAL VEHICLE
MODELING OF A SMALL UNMANNED AERIAL VEHICLE AHMED ELSAYED AHMED Electrical Engineering Dept., Shoubra Faculty of Engineering, Benha University, Qaliuobia, Egypt (Telephone: +201007124097), Email: eng_medoelbanna
Flight Test Results for Circular Path Following by Model Predictive Control
Preprints of the 19th World Congress The International Federation of Automatic Control Flight Test Results for Circular Path Following by Model Predictive Control Yoshiro Hamada Taro Tsukamoto Shinji Ishimoto
Aircraft Operation Anomaly Detection Using FDR Data
Aircraft Operation Anomaly Detection Using FDR Data Lishuai Li, Maxime Gariel, R. John Hansman IAB/Airline Industry Consortium Nov 4, 2010 1 Motivation Commercial aircraft accident rate has dropped significantly.
A Simple Design Approach In Yaw Plane For Two Loop Lateral Autopilots
A Simple Design Approach In Yaw Plane For Two Loop Lateral Autopilots Jyoti Prasad Singha Thakur 1, Amit Mukhopadhyay Asst. Prof., AEIE, Bankura Unnayani Institute of Engineering, Bankura, West Bengal,
Digital Autoland Control Laws Using Direct Digital Design and Quantitative Feedback Theory
AIAA Guidance, Navigation, and Control Conference and Exhibit 1-4 August 6, Keystone, Colorado AIAA 6-699 Digital Autoland Control Laws Using Direct Digital Design and Quantitative Feedback Theory Thomas
Adaptive Trim and Trajectory Following for a Tilt-Rotor Tricopter Ahmad Ansari, Anna Prach, and Dennis S. Bernstein
7 American Control Conference Sheraton Seattle Hotel May 4 6, 7, Seattle, USA Adaptive Trim and Trajectory Following for a Tilt-Rotor Tricopter Ahmad Ansari, Anna Prach, and Dennis S. Bernstein Abstract
ONE OF THE major problems in the design of flight
IEEE TRANSACTIONS ON CONTROL SYSTEMS TECHNOLOGY, VOL. 13, NO. 1, JANUARY 2005 15 Robust Nonlinear Flight Control of a High-Performance Aircraft Qian Wang, Member, IEEE, and Robert F. Stengel, Fellow, IEEE
MAV Unsteady Characteristics in-flight Measurement with the Help of SmartAP Autopilot
MAV Unsteady Characteristics in-flight Measurement with the Help of SmartAP Autopilot S. Serokhvostov, N. Pushchin and K. Shilov Moscow Institute of Physics and Technology Department of Aeromechanics and
Maneuver of fixed-wing combat aircraft
Loughborough University Institutional Repository Maneuver of fixed-wing combat aircraft This item was submitted to Loughborough University's Institutional Repository by the/an author. Citation: RENDER,
Basic Information to Help Select the Correct Propeller
Propeller Performance Factors - Basic Information to Help Select the Correct Propeller The performance of a propeller in flight involves several complex subjects, and the high performance propellers we
Aerodynamics and Flight Mechanics
Aerodynamics and Flight Mechanics Principal Investigator: Post Doc s: Graduate Students: Undergraduate Students: Mike Bragg Eric Loth Andy Broeren Sam Lee Jason Merret Kishwar Hossain Edward Whalen Chris
16.400/453J Human Factors Engineering. Manual Control I
J Human Factors Engineering Manual Control I 1 Levels of Control Human Operator Human Operator Human Operator Human Operator Human Operator Display Controller Display Controller Display Controller Display
PROGRESS IN THE PREDICTION OF AEROSERVOELASTIC INSTABILITIES ON LARGE CIVIL TRANSPORT AIRCRAFT
ICAS 2000 CONGRESS PROGRESS IN THE PREDICTION OF AEROSERVOELASTIC INSTABILITIES ON LARGE CIVIL TRANSPORT AIRCRAFT M.LACABANNE, A.LAPORTE AEROSPATIALE MATRA AIRBUS, 31060 Toulouse Cedex 03, France Abstract
Filtering and Fusion based Reconstruction of Angle of Attack
Filtering and Fusion based Reconstruction of Angle of Attack N Shantha Kuar Scientist, FMC Division NAL, Bangalore 7 E-ail: nskuar@css.nal.res.in Girija G Scientist, FMC Division NAL, Bangalore 7 E-ail:
Flight Dynamics and Control
Flight Dynamics and Control Lecture 1: Introduction G. Dimitriadis University of Liege Reference material Lecture Notes Flight Dynamics Principles, M.V. Cook, Arnold, 1997 Fundamentals of Airplane Flight
Suboptimal adaptive control system for flight quality improvement
Suboptimal adaptive control system for flight uality improvement Andrzej Tomczyk Department of Avionics and Control, Faculty of Mechanical Engineering and Aeronautics Rzeszów University of Technology,
ANALYSIS OF MULTIPLE FLIGHT CONTROL ARCHITECTURES ON A SIX DEGREE OF FREEDOM GENERAL AVIATION AIRCRAFT. A Thesis by. John Taylor Oxford, Jr.
ANALYSIS OF MULTIPLE FLIGHT CONTROL ARCHITECTURES ON A SIX DEGREE OF FREEDOM GENERAL AVIATION AIRCRAFT A Thesis by John Taylor Oxford, Jr. Bachelor of Science, Georgia Institute of Technology, 2007 Submitted
Nonlinear Fault-Tolerant Guidance and Control for Damaged Aircraft. Gong Xin Xu
Nonlinear Fault-Tolerant Guidance and Control for Damaged Aircraft by Gong Xin Xu A thesis submitted in conformity with the requirements for the degree of Master of Applied Science Graduate Department
LONGITUDINAL STABILITY AUGMENTATION DESIGN WITH TWO DEGREE OF FREEDOM CONTROL STRUCTURE AND HANDLING QUALITIES REQUIREMENTS
LONGITUDINAL STABILITY AUGMENTATION DESIGN WITH TWO DEGREE OF FREEDOM CONTROL STRUCTURE AND HANDLING QUALITIES REQUIREMENTS Francisco J. Triveno Vargas, Fernando J. O. Moreira, Pedro Paglione *EMBRAER,
Linearized Equations of Motion!
Linearized Equations of Motion Robert Stengel, Aircraft Flight Dynamics MAE 331, 216 Learning Objectives Develop linear equations to describe small perturbational motions Apply to aircraft dynamic equations
Aircraft Maneuver Regulation: a Receding Horizon Backstepping Approach
Aircraft Maneuver Regulation: a Receding Horizon Backstepping Approach Giuseppe Notarstefano and Ruggero Frezza Abstract Coordinated flight is a nonholonomic constraint that implies no sideslip of an aircraft.
Design and Implementation of an Unmanned Tail-sitter
1 IEEE/RSJ International Conference on Intelligent Robots and Systems (IROS) Congress Center Hamburg Sept 8 - Oct, 1. Hamburg, Germany Design and Implementation of an Unmanned Tail-sitter Roman Bapst,
Simulation of Non-Linear Flight Control Using Backstepping Method
Proceedings of the 2 nd International Conference of Control, Dynamic Systems, and Robotics Ottawa, Ontario, Canada, May 7 8, 2015 Paper No. 182 Simulation of Non-Linear Flight Control Using Backstepping
Frequency Domain System Identification for a Small, Low-Cost, Fixed-Wing UAV
Frequency Domain System Identification for a Small, Low-Cost, Fixed-Wing UAV Andrei Dorobantu, Austin M. Murch, Bernie Mettler, and Gary J. Balas, Department of Aerospace Engineering & Mechanics University
Towards Reduced Order Modeling (ROM) for Gust Simulations
Towards Reduced Order Modeling (ROM) for Gust Simulations S. Görtz, M. Ripepi DLR, Institute of Aerodynamics and Flow Technology, Braunschweig, Germany Deutscher Luft und Raumfahrtkongress 2017 5. 7. September
Advanced Aerospace Control. Marco Lovera Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano
Advanced Aerospace Control Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano ICT for control systems engineering School of Industrial and Information Engineering Aeronautical Engineering
Aerodynamics and Flight Mechanics
Aerodynamics and Flight Mechanics Principal Investigator: Mike Bragg Eric Loth Post Doc s: Graduate Students: Undergraduate Students: Sam Lee Jason Merret Kishwar Hossain Edward Whalen Chris Lamarre Leia
GUIDANCE AND CONTROL FOR D-SEND#2
GUIDANCE AND CONTROL FOR D-SEND#2 Jun ichiro Kawaguchi, Tetsujiro Ninomiya, Hirokazu Suzuki Japan Aerospace Exploration Agency kawaguchi.junichiroh@jaxa.jp; ninomiya.tetsujiro@jaxa.jp; suzuki.hirokazu@jaxa.jp
Keywords : ESTOL, X-31A, CONTROL LAWS, VECTOR
ICAS2002 CONGRESS HIGH ANGLE OF ATTACK APPROACH AND LANDING CONTROL LAW DESIGN FOR THE X31A B. Fischer and Dr. A. Knoll European Aeronautic Defense and Space Company Military Aircraft Flight Dynamics 81663
MODELING OF DUST DEVIL ON MARS AND FLIGHT SIMULATION OF MARS AIRPLANE
MODELING OF DUST DEVIL ON MARS AND FLIGHT SIMULATION OF MARS AIRPLANE Hirotaka Hiraguri*, Hiroshi Tokutake* *Kanazawa University, Japan hiraguri@stu.kanazawa-u.ac.jp;tokutake@se.kanazawa-u.ac.jp Keywords:
Multi-layer Flight Control Synthesis and Analysis of a Small-scale UAV Helicopter
Multi-layer Flight Control Synthesis and Analysis of a Small-scale UAV Helicopter Ali Karimoddini, Guowei Cai, Ben M. Chen, Hai Lin and Tong H. Lee Graduate School for Integrative Sciences and Engineering,
Aero-Propulsive-Elastic Modeling Using OpenVSP
Aero-Propulsive-Elastic Modeling Using OpenVSP August 8, 213 Kevin W. Reynolds Intelligent Systems Division, Code TI NASA Ames Research Center Our Introduction To OpenVSP Overview! Motivation and Background!
18. Linearization: the phugoid equation as example
79 18. Linearization: the phugoid equation as example Linearization is one of the most important and widely used mathematical terms in applications to Science and Engineering. In the context of Differential