This course is intended to serve master students interested in understanding and utilizing the concepts of flight dynamics and provides to the student the basic principles based on a classical analytical approach.

Specifically, starting from first principles the student will learn:

how to derive the equations of motion for a rigid aircraft, by combining a rigid body model with a suitable aerodynamic model for aircraft forces and moments;

how to define trim conditions and corresponding linearised models, as well as the classical decoupling between longitudinal and latero-directional dynamics;

how to study aircraft stability and dynamic characteristics;

how to carry out analysis and design of primary flight control systems functions, using both time-domain and frequency-domain methods;

how to estimate aircraft dynamic models from data using model identification methods.

Lectures and exercise sessions will allow students to:

• Understand the modelling framework and the physics underlying aircraft flight dynamics
• Derive nonlinear and linearised equations of motion for a given aircraft
• Analyse the stability and dynamic characteristics of a given aircraft 
• Analyse and design stability and control augmentation systems for aircraft
  

Part 1: Aircraft flight dynamics

Rigid body kinematics and dynamics

Basic aerodynamics

Aircraft forces and moments

Recap on static analysis

Complete nonlinear aircraft model

Decoupling and steady-state flight

Recap on systems theory: equilibria and linearisation

Linearisation of the force terms

Linearisation of the kinematic terms

Recap on systems theory: LTI state-space models

Linearised models for longitudinal and lateral dynamics

Dimensionless derivatives

Modal decomposition of aircraft models

Recap on systems theory: transfer functions and frequency responses

Longitudinal transfer functions and modes

Lateral-directional transfer functions

Part 2: Flight Control Systems

Introduction to Flight Control

Recap on control systems analysis methods

Handling qualities requirements

Recap on control systems design methods

Pitch axis Stability Augmentation System

Lateral-directional SAS/Yaw damper

SAS examples

Pitch rate Control Augmentation System

Normal acceleration CAS

Lateral-directional CAS

Flight control systems Verification & Validation: Monte Carlo method

Introduction to system identification

Identifiability and experiment design

Output error parameter estimation

Students are required to know the principles of aircraft flight mechanics and the methods for analysis and design of single-input/single-output linear time-invariant feedback control systems.

The written examination is a test in English language that assesses the examinee's knowledge of aircraft flight dynamics.

The test takes usually up to 3 hours and it is performed by the examinee in written form as a technical dissertation of 4 specific topics or questions:

-       2 topics: (Section 1) Flight dynamics (basic theory)

-       1 topic: (Section 2) Control systems analysis and design; model identification

-       1 topic: (Section 3) Exercises and other lectures

Each topic must be discussed in detail, with an adequate level of understanding and description (the use of drawings and flow charts may be useful). The use of English language will not be evaluated but the lack of clarity may compromise the result of the exam.