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Spacecraft attitude equations are usually given by nonlinear equations. However, spacecraft attitude control laws are often designed using a linear approximation of those equations about an operating condition. Thus, the effectiveness of the control laws can be guaranteed only for attitude angles and angular velocities close to the operating condition. There are occasions when the spacecraft motion involves attitude angles and angular velocities that are far from the operating condition. For those motions, the full nonlinear attitude equations must be used for evaluating the effectiveness of the control laws. This course presents the design of attitude control laws for two typical spacecraft operations along with basic tools that are useful to validate the design with nonlinear attitude equations.

Learning objectives: Learning control laws for spacecraft detumbling and spacecraft attitude regulation. Learning mathematical tools for validating attitude control laws using nonlinear attitude equations.

Target audience: doctoral and master students, non-academic professionals.

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Space instrumentation encounters challenges due to the hostile space environment, resource constraints, communication delays, and the demand for precision. Navigating extreme temperatures, radiation, and vacuum conditions necessitates robust designs. Additionally, stringent limitations on power, weight, and budget pose further hurdles, demanding optimal instrument performance within constrained parameters. Moreover, technological aspects and the need for precision and accuracy in measurements present ongoing challenges. Miniaturization enables the development of small, yet powerful instruments, while advanced imaging technologies enhance the resolution of captured data. For example, the development of the MarsTEM temperature sensor for Mars, the JANUS COver Mechanism (COM)  for JUICE mission and the new VENOM astrobiology experiment will be described and challenges presented.

Learning objectives: designing a space instrument: functionality, efficiency, testing and normative aspects.

Target audience: doctoral students, non-academic professionals, and undergraduate students.

Dates and time: 31 October – from 10:30 to 12:30

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Overview and General Information:

Problems of interest in science and engineering are often multi-physics, with complexities stemming from the interactions of various mechanisms, and inherent uncertainties and variabilities. In an industrial setting, we frequently aim to conduct optimization tasks in such complex and high-dimensional domains. For example, the 3D printing of thermoplastics involves heat and mass transfers, where the material undergoes thermo-chemical and thermo-mechanical changes along with several phase transformations. Evaluating the performance of the material under such conditions is challenging due to the complexities of the underlying multi-physics problem, as well as noise/errors in measurements, process uncertainties, and material variabilities. To evaluate or conduct optimization tasks, current practices often rely on methods such as Design of Experiments (DoE), and/or numerical methods.

In the recent decade, the application of data-driven and machine learning (ML) methods has also been explored with varying degrees of success. However, ML methods have been shown to suffer from a variety of shortcomings, including brittleness outside of their training zones. More recently, different families of data-driven methods have evolved to address the complexities of such multi-physics problems, including theory-guided machine learning (TGML), also referred to as scientific AI or physics-informed ML. TGML represents a merger between science-based methods, including finite element (FE) analysis, and ML techniques to overcome the challenges associated with theory-agnostic ML methods in physical domains.

Learning Objectives:

This course aims to introduce participants to TGML and its applications. First, a short overview of theory-agnostic ML methods, including Neural Networks (NN) for large datasets and Gaussian Process Regression (GPR) for small datasets, will be given. Simple engineering applications including heat transfer will be demonstrated. Next, TGML and its notable techniques will be introduced, with examples provided. A combination of experimental data and numerical data will be used to train ML models. Python programming with built-in libraries will be employed to develop ML codes during the course. Participants can follow the instructor to develop codes using Python on their own machines. Python codes and example datasets will be provided as well.

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The aim of this webinar is to deal with the main criticisms related to acoustic simulation and noisesuppression in the aerospace sector. This objective is achieved by initially introducing and discussing the state-of-the-art methods and technologies that are relevant to this field.Subsequently, the fundamentals of analytical (Transfer Matrix Method) and numerical (Wave Finite Element Method) approaches are illustrated, which constitute powerful and efficient techniques to estimate the absorption and transmission properties of a sound package. Lastly, some innovative acoustic meta-material configurations are presented, based on a periodic pattern of porous unit cells, whose main homogenization models are defined and discussed too. These topics address different applications not only in the aerospace industry, but more generally in transportation(automotive, railway), energy and civil engineering sectors, where both weight and space, as well as vibroacoustic comfort, still remain as critical issues.

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Overview and General Information:

Modern combat aircraft design is governed by signature reduction requirements, both in the electromagnetic and infrared spectra. At present it is commonly accepted to sacrifice other aspects of the design, such as aerodynamic and propulsion performance, to achieve low observability. Still, the final mission requirements might require a minimum trade-off according to the airframe mission (air dominance, surveillance, strike). In this webinar, the concept of signature reduction/control applied to combat aircraft will be discussed. Attendees will learn to quantify the performance characteristics attainable from different solutions. The basics of radar and infrared signature requirements (applied to aircraft), and their effect on final airframe shape will be analysed, considering the relative importance in current and future designs. The course will end with a trade-off analysis of some current designs.

Learning Objectives:

• Definition of survivability.
• Basic of Radar Cross Section and Infrared signature.
• Design requirements and major challenges in stealth airframe design.
• Trade-off considerations.

Target audience

Doctoral and post-graduate students, aerospace and defence industry professionals, and military officers.

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Fiber-reinforced polymeric (FRP) composites are high-performance materials used in the aerospace industry due to their excellent fatigue resistance, durability, and high stiffness- and strength- to weight ratios. Composites allow the design of lightweight structures with tailorable properties that minimize energy usage and contaminant emissions. These materials are currently utilized in fuselages, wings, tails, doors, and interiors of modern aerospace structures.

Despite the excellent mechanical properties, adoption and certification of composite aerospace structures is a challenge primarily due to (1) the current knowledge gap in the technology, manufacturing, process-induced defects, maintenance and repair methods for aerospace-grade FRP composites, and (2) the complex and highly varying behavior and damage formation/evolution of these materials.

This course discusses some of the main challenges for the use of composite materials in aerospace applications, emphasizing four main aspects: manufacturing defects and signatures, identification of defects via non-destructive evaluation (NDE) methods, effect of defects on the mechanical performance, and NDE for assessment of structural integrity.

The current manufacturing techniques for fabricating aerospace-grade FRP composite structures are discussed. The common defects associated with these methods (e.g., fiber and ply waviness, voids/porosity, inclusions, resin-rich regions) are reviewed, and the effect of these manufacturing defects on the strength and life of composite structures is analyzed. The state-of-the art techniques for identifying and characterizing defects in aerospace structural components using NDE methods are discussed, giving particular attention to ultrasonic testing, guided waves, infrared thermography and X-Ray computed tomography. Finally, the current challenges for assessing structural integrity of aerospace composite structures via NDE techniques are presented and the main areas of opportunity in this field are highlighted.

MODULE 1 – Manufacturing Defects and Signatures (90 minutes)

1. Overview of composite materials systems used in the aerospace industry.
2. Manufacturing processes for aerospace composite materials.
3. Defects developed during the manufacturing processes.

MODULE 2 – Non-destructive Evaluation Methods (90 minutes)

4. Non-destructive evaluation (NDE) techniques for the detection and characterization of defects in the aerospace industry.

MODULE 3 – Effect of Defects (90 minutes)

5. Experimental and modeling approaches for predicting the effect of defects on the damage modes and mechanical performance of composites.

MODULE 4 – Structural Integrity Assessment using NDE Methods (90 minutes)

6. Damage developed in composites during operational life.
7. NDE methods for assessment of structural integrity of composite structures.

Learning objectives

At the end of this course, the attendees should be able to:

1. Explain the difference between thermoplastic and thermoset polymer systems, in terms of the microstructure and mechanical properties.
2. List the main applications of carbon fiber reinforced polymeric (CFRP) composites in aerospace structural components.
3. Explain the different manufacturing methods for fabricating aerospace-grade composite materials, and identify the advantages and disadvantages of each of these techniques.
4. Describe the common defects in CFRP composites developed during the manufacturing.
5. Describe the needs, constraints and outcomes of NDE inspections in the aerospace field.
6. Understand the physical principles and basic implementation of the presented NDE techniques (i.e., ultrasonic testing, ultrasonic guided waves, infrared thermography, X-ray computed tomography).
7. Assess the effect of manufacturing defects on the mechanical properties, strength and life of composite structures.
8. Describe damage formation and/or evolution in CFRP due to fatigue, impacts and environmental conditions.
9. Assess advantages and limitations of NDE techniques with respect to specific defects and damages in the aerospace field.

Target audience: undergraduate, graduate and doctoral students, academic and non-academic professionals. CTNA-Cluster Exploore Marche members.

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This webinar Introduces the fundamentals of thermochemical modeling and numerical simulation of high-temperature hypersonic flows in the laminar and turbulent regimes.

Syllabus

• Introduction to hypersonic flows
• Properties and thermophysical modeling of high-temperature flows
• Compressibility effects on high-speed turbulence
• Classical shock-capturing schemes
• High-order numerical schemes for compressible turbulent flows

Target audience

This webinar is addressed to graduate/undergraduate engineering students, aerospace Ph.D. students.

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The Space Tether consists of a complex structure where there are three main parts: 1) the primary satellite; 2) a secondary
satellite; 3) a cable (of variable lengths) that is used to join the two spacecraft together. This cable allows the transfer of energy and momentum between the two spacecraft, and this transfer can be present in both directions and, in some cases,
can switch direction. Space tethers can be classified into two different areas: Passive tethers, which are used simply for mechanical connection and mainly transfer momentum from one part to the other; and Electrodynamic tethers, conductive wires or tapes or more complex structures), in which an electric current can flow and pass from one end to the other. The simplest application involves using the tether system as a de-orbit system; a drag Force is induced on the tether due to its relative motion with respect to the rotating plasma and the satellite.
An opposite application is the injection of electric current from one satellite which has an effect opposite to the deorbiting;
this effect can be used to increase the SMA of the system or produce movements in the orbital plane. The Electrodynamic tether is a system that can act as an orbital control for small and relatively big structures (depending on the tether length and on the produced current). Even if the tethers’ dynamics (passive or electrodynamic) are complex and not at all completely understood, the current knowledge in materials and technology is bridging the gap between theory and extensive application in current Space missions.

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Overview and General Information:

In order to use space for scientific and commercial purposes it is necessary to understand the Low Earth Orbit (LEO) space environment where most of the activities are now, and will be in the future, carried out. LEO environment includes severe hazards such as Atomic Oxygen (AO), Ultraviolet (UV) Radiation, Ionizing Radiation, High Vacuum, Plasma, Micrometeoroids and Debris, Severe Temperature Cycles and, for some systems, the Re-Entry Environment. It is important to note that these environmental characteristics do affect the space systems, the materials and the structures at the same time, with a remarkable synergistic effect. In order to understand these synergistic effects, whether experimental or theoretical and numerical approaches are of essential importance, as the comprehension of the operative environment becomes a key point to extend operative life of satellites and structures and to withstand aggressive conditions.

The course is based on the analysis of the physics of Space Environment and it is completed with an in-depth analysis of both ground testing methods and the validation of experimental tests according to current regulations given by the major agencies as ESA and NASA.

Syllabus

• Part 1: Physics of the Space Environment (2 hours)
• Part 2: Test Technology, Ground-Test Facilities (2 hours)
• Part 3: Experimental Validation (2 hours)

Learning Objectives:

Aim of the course is to give to the attendee the instruments to understand both the Space Environment and the related techniques for Environmental Tests on Space Systems, Materials and Structures.

Target audience

The course is dedicated to Ph.D students, non-academic professionals and undergraduate students.

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Overview and General Information: 

Spacecraft attitude control laws are often designed using linear control design techniques. As a result, their effectiveness can be guaranteed only for small attitude angles and small angular velocities since in that situation a linear approximation of the attitude equations can be employed. However, there are occasions when the spacecraft motion involves large attitude angles and large angular velocities. For those motions, the full nonlinear attitude equations must be used for evaluating the effectiveness of attitude control laws. In this course, basic results of Lyapunov stability theory will be presented and applied to nonlinear spacecraft attitude control.

Learning objectives: 

• Spacecraft detumbling
• Stability of nonlinear systems
• Lyapunov theorems
• Nonlinear spacecraft attitude stabilization
• La Salle’s theorem
• Lyapunov indirect method

Target audience

Doctoral students, non-academic professionals.

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