Università Roma Tre

FUNDAMENTAL CONCEPTS ON AERODYNAMICS OF WINGS AND PROFILES INCLUDING TURBULENCE AND ANALYSIS OF RANDOM SIGNALS. THE COURSE WILL PROVIDE BASIC INSTRUMMENTS FOR AERODYNAMIC DESIGN WITH STANDARD APPROACHES.

TO INTEGRATE AND TO COMPLETE THE STUDENTS KNOWLEDGE IN STRUCTURAL DYNAMICS, FOCUSING ON SPECIFIC PROBLEMS OF AIRCRAFT STRUCTURES AND ON NUMERICAL METHODS WIDELY USED FOR THEIR ANALYSIS. IN PARTICULAR, THE EMPHASIS WILL BE PLACED ON LINEAR AND NON-LINEAR MODELING OF AIRCRAFT STRUCTURES SUBJECT TO THE COMBINED ACTION OF THERMAL AND EXTERNAL LOADS. IN A FIRST STAGE, THE THEORY NECESSARY FOR THE MODELING OF SPECIFIC AIRCRAFT STRUCTURES PROBLEMS WILL BE PRESENTED AND THE BASIC THEORY OF FINITE ELEMENT METHODS WILL BE PROVIDED, WITH PARTICULAR ATTENTION TO AERONAUTICAL APPLICATIONS. IN A SECOND STAGE, THE STUDENT WILL BECOME FAMILIAR WITH FINITE ELEMENT CODES COMMONLY USED FOR STRUCTURAL DESIGN IN INDUSTRIES. THIS ACTIVITY WILL BE AIMED AT THE STRUCTURAL ANALYSIS OF ONE OF THE MOST IMPORTANT ELEMENTS OF THE AIRCRAFT (WING AND/OR FUSELAGE).

GIVE METHODOLOGIES FOR THE ANALYSIS OF LINEAR AND STATIONARY SISTEMS REPRESENTED WITH CONTINUOUS OR DISCRETE STATE SPACE MODELS. LEARN HOW TO DESIGN A CONTROL SYSTEM ABLE TO ASSIGN DYNAMICS EVENTUALY USING AND OBSERVER OR OPTIMIZING A CONST INDEX.

ACQUISITION OF BASIC KNOWLEDGE ABOUT POLLUTANTS FORMATION IN POWER PLANT AND MOTOR VEHICLE; ACQUISITION OF TOOLS FOR AIR POLLUTION MODELING.
ACQUISITION OF ADVANCED KNOWLEDGE TO ANALYZE SOURCES IN LIGHT OF THEIR POLLUTANTS EMISSIONS; ACQUISITION OF SKILLS NECESSARY TO MEASURE AND CONTROL THE EMISSIONS IN ATMOSPHERE (PRE-COMBUSTION, COMBUSTION AND POST-COMBUSTION CONTROLS).

THE AIM OF THE COURSE IS TO PROVIDE STUDENTS WITH PRELIMINARY DESIGN PROCEDURES AND CRITERIA FOR TURBOMACHINES. (FROM GAS, STEAM, AND HYDRAULIC TURBINES TO PUMPS, FANS, BLOWERS AND COMPRESSORS).
MOVING FROM PERFORMANCE TARGETS AND SPECIFIC DESIGN BOUNDARY CONDITIONS, THE STUDENT WILL LEARN SOME SIMPLIFIED DESIGN METHODOLOGIES TAKING MATERIAL, MECHANICAL AND THERMAL STRESSES, TRANSONIC FLOW LIMITS AND CAVITATION INTO ACCOUNT. THE OPTIMIZATION OF THE DEGREE OF FREEDOM WILL BE IMPLEMENTED IN THE DESIGN PROCEDURES.
THE STUDENT WILL BE ABLE TO ANALYSE MACHINE PERFORMANCE ONCE THE MAIN GEOMETRIC QUANTITIES ARE GIVEN.

STUDENTS ARE INTRODUCED TO THE METHODOLOGIES APPLIED IN AERONAUTICS FOR THE ANALYSIS OF AEROELASTIC PROBLEMS. THESE CONCERN FLUID-STRUCTURE INTERACTIONS, WITH ATTENTION TO INSTABILITY PHENOMENA LIKE FLUTTER AND DIVERGENCE. AEROELASTIC FORMULATIONS FOR 2D AND 3D WING MODELS ARE OBTAINED BY COUPLING STRUCUTRAL DYNAMMICS EQUATIONS WITH UNSTEADY AERODYNAMIC THEORIES, AND THEN SOLUTION METHODS ARE PRESENTED AND DISCUSSED.

EQUATIONS OF MOTION OF THE AERIAL VEHICLE AND ITS PERFORMANCE. MATERIAL POINT AND RIGID BODY STUDIES. CHARACTERISTIC FLIGHT SEGMENTS. STABILITY AND CONTROL.

INTRODUCTION TO THE BASIC COMPONENTS OF AERONAUTICAL STRUCTURES: ANALYSIS OF STRESS AND STRAIN. COMPLEX AERONAUTICAL STRUCTURES WITH EMPHASIS ON WING BOX AND FUSELAGE: THEIR MATHEMATICAL MODELING FOR PRELIMINARY DESIGN PURPOSES AND STRUCTURAL INSTABILITY ANALYSIS.

THE AIM OF THE CLASS IS TO GAIN THE KNOWLEDGE FOR THE BEST MATERIALS CHOICE IN THE FIELD OF AERONAUTICS. THE CLASS IS FOCUSED ON THE STUDY OF THE STRUCTURE, COMPOSITION, PROPERTIES TECHNOLOGICAL PROCESSES AND APPLICATION OF STRUCTURAL MATERIALS SUCH AS COMPOSITES IN A POLYMERIC MATRIX AND LIGHTWEIGHT ALLOYS. THE CLASS WILL ALSO DEAL WITH HIGH TEMPERATURE MATERIALS SUCH AS TITANIUM ALLOYS AND SUPER-ALLOYS, CERAMIC MATERIALS AND COATINGS FOR THE COMPONENTS OF THE PROPULSION SYSTEM.

TO GIVE A GENERAL KNOWLEDGE OF THE BASIC CHARACTERISTICS OF AIR BREATHING ENGINES, PROPELLERS, INCLUDING NAVAL APPLICATIONS, AND ROTATING BLADES. THE COMPLETION OF THE KNOWLEDGE ON COMPRESSIBLE FLUID FLOWS AND FUNDAMENTAL OF COMBUSTION ARE ALSO PRESENTED.

AIM OF THE COURSE IS TO PROVIDE THE FUNDAMENTAL METHODOLOGIES ADOPTED FOR THE CONCEPTUAL DESIGN OF COMMERCIAL AIRCRAFT STARTING FROM THE MISSION REQUIREMENTS AND TAKING INTO ACCOUNT ALL THE MAJOR TECHNICAL, REGULATION AND ENVIRONMENTAL CONSTRAINTS. THE DESIGN IS CONCEIVED IN AN INTEGRATED MULTIDISCIPLINARY FASHION, WITH A CAREFUL ANALYSIS OF THE MOST ADVANCED OPTIMIZATION TECHNIQUES. DURING THE COURSE, THE STUDENTS ARE INVOLVED IN THE COMPLETE DESIGN OF A REALISTIC CONFIGURATION.

The specific aim of this module is to achieve cognitive and practical skills in experimental aerodynamics applied to the aeronautic field and more generally to the industrial and environmental engineering fields.

Lectures are also focused on arguments that deal with the fundamental theory of aeroacoustics, including theoretical design problems. Practical exercises and experimental experiences in the department laboratory will deepen aspects related to noise measurements with particular attention on their application in the aeronautical field (ex.: compressible jets and wall flows ).

Having successfully complete the module, the student will be able to recognize, acquire and analyze aeroacoustics and aerodynamics problems with conventional and advanced instrumentation and elaboration techniques.

ACQUISITION OF TOOLS FOR ANALYZING RECIPROCATING INTERNAL COMBUSTION ENGINES PERFORMANCES, SPARK IGNITION AND DIESEL ONES, FOR USE IN BOTH INDUSTRIAL, AND TRANSPORT SECTORS.
REFINEMENT OF KNOWLEDGE ON OPERATIONAL ISSUES RELATED TO THE THERMO-FLUID DYNAMICS OF RECIPROCATING ENGINES, COMBUSTION, POLLUTION CONTROL AND MANAGEMENT OF ENGINE POWER TRAIN
ACQUISITION OF TOOLS FOR THE ANALYSIS OF FUNCTIONAL CHARACTERISTICS OF PLANTS WITH GAS TURBINE ENGINES FOR BOTH THE INDUSTRY AND FOR THE AVIATION, MARINE AND TERRESTRIAL PROPULSION.
ACQUISITION OF OPERATIONAL SKILLS NECESSARY FOR PROFESSIONAL ACTIVITY IN PLANTS WITH GAS TURBINES.

TO FAMILIARIZE THE STUDENT WITH THE METHODOLOGIES FOR MODELLING AND SIMULATION TYPICALLY USED IN AERONAUTICAL ENGINEERING AND THEIR UTILIZATION. MODELLING COMPRISES THOSE MATHEMATICAL MODELS (SUCH AS THE MODAL APPROACH) THAT ARE QUITE EFFICIENT IN PROVIDING AN APPROXIMATION OF THE PHYSICAL PHENOMENON, ALONG WITH THE CORRESPONDING SOLUTION METHODOLOGIES. ON THE OTHER HAND, SIMULATION REFERS TO THOSE NUMERICAL METHODS (SUCH AS THE FINITE ELEMENT METHODS) THAT DESCRIBE THE PHYSICAL PHENOMENON IN GREATER DETAIL.

FUNDAMENTAL CONCEPTS ON AERODYNAMICS OF WINGS AND PROFILES INCLUDING TURBULENCE AND ANALYSIS OF RANDOM SIGNALS. THE COURSE WILL PROVIDE BASIC INSTRUMMENTS FOR AERODYNAMIC DESIGN WITH STANDARD APPROACHES.

GIVE METHODOLOGIES FOR THE ANALYSIS OF LINEAR AND STATIONARY SISTEMS REPRESENTED WITH CONTINUOUS OR DISCRETE STATE SPACE MODELS. LEARN HOW TO DESIGN A CONTROL SYSTEM ABLE TO ASSIGN DYNAMICS EVENTUALY USING AND OBSERVER OR OPTIMIZING A CONST INDEX.

ACQUISITION OF BASIC KNOWLEDGE ABOUT POLLUTANTS FORMATION IN POWER PLANT AND MOTOR VEHICLE; ACQUISITION OF TOOLS FOR AIR POLLUTION MODELING.
ACQUISITION OF ADVANCED KNOWLEDGE TO ANALYZE SOURCES IN LIGHT OF THEIR POLLUTANTS EMISSIONS; ACQUISITION OF SKILLS NECESSARY TO MEASURE AND CONTROL THE EMISSIONS IN ATMOSPHERE (PRE-COMBUSTION, COMBUSTION AND POST-COMBUSTION CONTROLS).

The specific aim of this module is to achieve cognitive and practical skills in experimental aerodynamics applied to the aeronautic field and more generally to the industrial and environmental engineering fields.

Lectures are also focused on arguments that deal with the fundamental theory of aeroacoustics, including theoretical design problems. Practical exercises and experimental experiences in the department laboratory will deepen aspects related to noise measurements with particular attention on their application in the aeronautical field (ex.: compressible jets and wall flows ).

Having successfully complete the module, the student will be able to recognize, acquire and analyze aeroacoustics and aerodynamics problems with conventional and advanced instrumentation and elaboration techniques.

THE AIM OF THE COURSE IS TO PROVIDE STUDENTS WITH PRELIMINARY DESIGN PROCEDURES AND CRITERIA FOR TURBOMACHINES. (FROM GAS, STEAM, AND HYDRAULIC TURBINES TO PUMPS, FANS, BLOWERS AND COMPRESSORS).
MOVING FROM PERFORMANCE TARGETS AND SPECIFIC DESIGN BOUNDARY CONDITIONS, THE STUDENT WILL LEARN SOME SIMPLIFIED DESIGN METHODOLOGIES TAKING MATERIAL, MECHANICAL AND THERMAL STRESSES, TRANSONIC FLOW LIMITS AND CAVITATION INTO ACCOUNT. THE OPTIMIZATION OF THE DEGREE OF FREEDOM WILL BE IMPLEMENTED IN THE DESIGN PROCEDURES.
THE STUDENT WILL BE ABLE TO ANALYSE MACHINE PERFORMANCE ONCE THE MAIN GEOMETRIC QUANTITIES ARE GIVEN.

STUDENTS ARE INTRODUCED TO THE METHODOLOGIES APPLIED IN AERONAUTICS FOR THE ANALYSIS OF AEROELASTIC PROBLEMS. THESE CONCERN FLUID-STRUCTURE INTERACTIONS, WITH ATTENTION TO INSTABILITY PHENOMENA LIKE FLUTTER AND DIVERGENCE. AEROELASTIC FORMULATIONS FOR 2D AND 3D WING MODELS ARE OBTAINED BY COUPLING STRUCUTRAL DYNAMMICS EQUATIONS WITH UNSTEADY AERODYNAMIC THEORIES, AND THEN SOLUTION METHODS ARE PRESENTED AND DISCUSSED.

EQUATIONS OF MOTION OF THE AERIAL VEHICLE AND ITS PERFORMANCE. MATERIAL POINT AND RIGID BODY STUDIES. CHARACTERISTIC FLIGHT SEGMENTS. STABILITY AND CONTROL.

INTRODUCTION TO THE BASIC COMPONENTS OF AERONAUTICAL STRUCTURES: ANALYSIS OF STRESS AND STRAIN. COMPLEX AERONAUTICAL STRUCTURES WITH EMPHASIS ON WING BOX AND FUSELAGE: THEIR MATHEMATICAL MODELING FOR PRELIMINARY DESIGN PURPOSES AND STRUCTURAL INSTABILITY ANALYSIS.

THE AIM OF THE CLASS IS TO GAIN THE KNOWLEDGE FOR THE BEST MATERIALS CHOICE IN THE FIELD OF AERONAUTICS. THE CLASS IS FOCUSED ON THE STUDY OF THE STRUCTURE, COMPOSITION, PROPERTIES TECHNOLOGICAL PROCESSES AND APPLICATION OF STRUCTURAL MATERIALS SUCH AS COMPOSITES IN A POLYMERIC MATRIX AND LIGHTWEIGHT ALLOYS. THE CLASS WILL ALSO DEAL WITH HIGH TEMPERATURE MATERIALS SUCH AS TITANIUM ALLOYS AND SUPER-ALLOYS, CERAMIC MATERIALS AND COATINGS FOR THE COMPONENTS OF THE PROPULSION SYSTEM.

TO GIVE A GENERAL KNOWLEDGE OF THE BASIC CHARACTERISTICS OF AIR BREATHING ENGINES, PROPELLERS, INCLUDING NAVAL APPLICATIONS, AND ROTATING BLADES. THE COMPLETION OF THE KNOWLEDGE ON COMPRESSIBLE FLUID FLOWS AND FUNDAMENTAL OF COMBUSTION ARE ALSO PRESENTED.

TO INTEGRATE AND TO COMPLETE THE STUDENTS KNOWLEDGE IN STRUCTURAL DYNAMICS, FOCUSING ON SPECIFIC PROBLEMS OF AIRCRAFT STRUCTURES AND ON NUMERICAL METHODS WIDELY USED FOR THEIR ANALYSIS. IN PARTICULAR, THE EMPHASIS WILL BE PLACED ON LINEAR AND NON-LINEAR MODELING OF AIRCRAFT STRUCTURES SUBJECT TO THE COMBINED ACTION OF THERMAL AND EXTERNAL LOADS. IN A FIRST STAGE, THE THEORY NECESSARY FOR THE MODELING OF SPECIFIC AIRCRAFT STRUCTURES PROBLEMS WILL BE PRESENTED AND THE BASIC THEORY OF FINITE ELEMENT METHODS WILL BE PROVIDED, WITH PARTICULAR ATTENTION TO AERONAUTICAL APPLICATIONS. IN A SECOND STAGE, THE STUDENT WILL BECOME FAMILIAR WITH FINITE ELEMENT CODES COMMONLY USED FOR STRUCTURAL DESIGN IN INDUSTRIES. THIS ACTIVITY WILL BE AIMED AT THE STRUCTURAL ANALYSIS OF ONE OF THE MOST IMPORTANT ELEMENTS OF THE AIRCRAFT (WING AND/OR FUSELAGE).

AIM OF THE COURSE IS TO PROVIDE THE FUNDAMENTAL METHODOLOGIES ADOPTED FOR THE CONCEPTUAL DESIGN OF COMMERCIAL AIRCRAFT STARTING FROM THE MISSION REQUIREMENTS AND TAKING INTO ACCOUNT ALL THE MAJOR TECHNICAL, REGULATION AND ENVIRONMENTAL CONSTRAINTS. THE DESIGN IS CONCEIVED IN AN INTEGRATED MULTIDISCIPLINARY FASHION, WITH A CAREFUL ANALYSIS OF THE MOST ADVANCED OPTIMIZATION TECHNIQUES. DURING THE COURSE, THE STUDENTS ARE INVOLVED IN THE COMPLETE DESIGN OF A REALISTIC CONFIGURATION.

ACQUISITION OF TOOLS FOR ANALYZING RECIPROCATING INTERNAL COMBUSTION ENGINES PERFORMANCES, SPARK IGNITION AND DIESEL ONES, FOR USE IN BOTH INDUSTRIAL, AND TRANSPORT SECTORS.
REFINEMENT OF KNOWLEDGE ON OPERATIONAL ISSUES RELATED TO THE THERMO-FLUID DYNAMICS OF RECIPROCATING ENGINES, COMBUSTION, POLLUTION CONTROL AND MANAGEMENT OF ENGINE POWER TRAIN
ACQUISITION OF TOOLS FOR THE ANALYSIS OF FUNCTIONAL CHARACTERISTICS OF PLANTS WITH GAS TURBINE ENGINES FOR BOTH THE INDUSTRY AND FOR THE AVIATION, MARINE AND TERRESTRIAL PROPULSION.
ACQUISITION OF OPERATIONAL SKILLS NECESSARY FOR PROFESSIONAL ACTIVITY IN PLANTS WITH GAS TURBINES.

TO FAMILIARIZE THE STUDENT WITH THE METHODOLOGIES FOR MODELLING AND SIMULATION TYPICALLY USED IN AERONAUTICAL ENGINEERING AND THEIR UTILIZATION. MODELLING COMPRISES THOSE MATHEMATICAL MODELS (SUCH AS THE MODAL APPROACH) THAT ARE QUITE EFFICIENT IN PROVIDING AN APPROXIMATION OF THE PHYSICAL PHENOMENON, ALONG WITH THE CORRESPONDING SOLUTION METHODOLOGIES. ON THE OTHER HAND, SIMULATION REFERS TO THOSE NUMERICAL METHODS (SUCH AS THE FINITE ELEMENT METHODS) THAT DESCRIBE THE PHYSICAL PHENOMENON IN GREATER DETAIL.