System Identification of Flight Mechanical Characteristics.

• Superior document: Linköping Studies in Science and Technology. Thesis Series ; v.1599
• Author: Larsson, Roger.
• Place / Publishing House: Linköping : : Linkopings Universitet,, 2013.; {copy}2013.
• Year of Publication: 2013
• Edition: 1st ed.
• Language: English
• Series: Linköping Studies in Science and Technology. Thesis Series
• Physical Description: 1 online resource (138 pages)

Table of Contents

• Abstract
• Populärvetenskaplig sammanfattning
• Acknowledgments
• Contents
• Notation
• 1 Introduction
• 1.1 Research Motivation
• 1.2 Goal
• 1.3 Contributions
• 1.4 Thesis Outline
• 2 System Identification
• 2.1 Dynamical Systems
• 2.2 Modeling
• 2.3 Identification Methods
• 2.3.1 Prediction-Error Method
• 2.3.2 State and Parameter Estimation Method
• 2.3.3 Instrumental Variable Method
• 2.3.4 State Estimation Method
• 2.4 Simple Example
• 3 Aeronautics
• 3.1 Definitions
• 3.2 Flight Mechanical System Description
• 3.3 Modeling
• 3.3.1 System Modeling
• 3.3.2 Noise Modeling
• 4 Sequential Identification
• 4.1 Problem Formulation
• 4.2 Methods
• 4.2.1 Sequential Frequency Domain Method
• 4.2.2 Recursive Time-Domain Method
• 4.2.3 Improved Sequential Frequency Domain Method
• 4.3 Estimation on Simulated Data
• 4.4 Estimation on Real Data
• 4.5 Conclusions
• 5 Identification of Unstable Nonlinear Systems
• 5.1 Problem Formulation
• 5.2 Methods
• 5.2.1 Prediction Error Methods
• 5.2.2 State Estimation Method
• 5.2.3 Parameter and State Optimization Method
• 5.3 Estimation on Simulated Data
• 5.4 Identification on Real Data
• 5.5 Conclusions
• 6 Discussion and Future Work
• A Nonlinear Aircraft Model
• B Kalman Filters
• B.1 Extended Kalman Filter (EKF)
• B.2 Unscented Kalman Filter (UKF)
• C Complementary Results to the Identification of Unstable Nonlinear Systems
• C.1 Tuning Results from Noise (SNR) Sensitivity Study
• C.2 Complementary Results for the SNR Sensitivity Study
• C.3 Tuning Results from Initial Offset (0) Sensitivity Study
• Bibliography.