Ing Ind - Inf (Mag.)(ord. 270) - BV (469) AERONAUTICAL ENGINEERING - INGEGNERIA AERONAUTICA
055736 - AIRPLANE PERFORMANCE AND DYNAMICS
This first module of the “Airplane Performance and Dynamics” integrated course aims at providing the student the means to analyse the aircraft from a sizing point of view, as a fundamental engineering ability and as a preparation to further studies, such as aircraft dynamics and control, vehicle and system design, and flight testing. The students are exposed to the relationship between the weight, geometry and major subsystem sizing and performance, static stability and controllability, in the frame of given mission and other design requirements, including airworthiness specifications. The mathematical modelling of the rigid aircraft is introduced and applied to the analysis of steady flight conditions, control and static stability. As such, it provides a convenient introduction to the second module of the course, which deals with “Dynamics and Flying Qualities”.
The second module of the “Airplane Performance and Dynamics” integrated course aims at providing the student the means to analyze problems connected with the dynamics of flight. Starting from the non-linear dynamic equations of motion for a rigid aircraft in three-dimensional space, developed in the first module, the students are guided through a rigorous linearization of these equations. In the process, the aerodynamic forcing term is linearized too, producing stability- and control-related derivatives. The obtainment of a linearized model provides a key asset in understanding model hierarchy: what type of model is suitable for assigned simulation, performance measurement, static and dynamic stability, control design or identification tasks. Furthermore, the estimation of each of these derivatives based on simple empirical or analytical models from basic geometrical measures pertaining to a specific aircraft is carried out. These models are analyzed in detail, providing an understanding of what features of an aircraft impact its behavior and how. Under more stringent simplifications, the longitudinal and lateral-directional motions are decoupled, and the corresponding lower order systems analyzed showing the direct impact of certain aircraft characteristics on eigen dynamics. This provides a deep understanding of the relationship between aircraft inertia and shape/geometry (i.e. design characteristics) and aircraft dynamics, with application to dynamic performance analysis and control design. A basic outline of more advanced phenomena for which further modeling would be necessary will be also provided, helping in understanding the limits of the adopted models.
Risultati di apprendimento attesi
After successfully completing the course, the student will be able to: • analyse the design requirements and their impact on the specifications of an aircraft; • analyse the performance, the equilibrium conditions, the static stability and controllability characteristics of an aircraft; • perform the preliminary sizing of an aircraft based on performance, static stability and controllability requirements. • master the model hierarchy leading from a non-linear model to a set of linearized and decoupled models for aircraft dynamics; • understand the capabilities, potential uses (e.g. for control design or performance assessment) and limitations of each mathematical model; • analyze the impact of aircraft geometry and configurational choices on stability and control; • analyze the impact of inertia and aerodynamics, in turn influenced by aircraft geometry and configuration, on some basic dynamic characteristics typical to aircraft motion; • understand the effect of design choices on the dynamics of an aircraft.
Introduction to design requirement analysis: mission requirements, flight profile, design specifications, airplane certification, weight performance, design weight determination. Performance and sizing: flight envelope; point, integral and field performance; preliminary sizing based on performance requirements. Aircraft mathematical model: reference systems, airplane equations of motion, steady maneuvers. Stability, control and sizing: longitudinal and latero-directional equilibrium, control and static stability; civili and military certification requirements; preliminary sizing based on static stability and control requirements.
Linearized equations of motion, longitudinal/latero-directional decoupling, stability and control derivatives. Dynamic response and stability, simulation of flight, flying qualities. Introduction to the architecture of stability and control augmentation systems (SAS, CAS, autopilot) in relation to the aircraft stability and flying qualities. Introduction to more complex phenomena like control reversal, inertial coupling, high-angle-of-attack flight and spin.
Basic notions on aircraft configuration and fundamental of flight mechanics (trajectory analysis, drag polar and performance attitudes, basic performance).
Modalità di valutazione
The evaluation will take place through a single written exam for the two modules.
At the teacher's discretion, it may necessary to complete the assessment through an additional oral exam.
Tipo Forma Didattica
Ore di attività svolte in aula
Ore di studio autonome
Laboratorio Di Progetto
Informazioni in lingua inglese a supporto dell'internazionalizzazione
Insegnamento erogato in lingua
Disponibilità di materiale didattico/slides in lingua inglese
Disponibilità di libri di testo/bibliografia in lingua inglese
Possibilità di sostenere l'esame in lingua inglese
Disponibilità di supporto didattico in lingua inglese