Courses

This webinar will present the main criteria needed to optimize the design of Low Earth Orbit (LEO) constellations for global and local coverage.  It will describe the main drivers in defining constellation architecture and provide mathematical means to implement trade off and optimization studies. Orbital evolution will be analyzed using perturbed two-body Keplerian equations and expressions for repeated ground track and revisit time orbits will be derived. Starting from an overview of constellations for global coverage (Walker and Street of Coverage) the webinar will focus on local coverage patterns using special architectures for regional constellation design (flower constellations) aimed at continuous monitoring of areas of interest. Optimization approaches based on genetic algorithms and particle swarm will be described. Applications of constellations for analysis of dedicated areas (Veneto region) will be presented along with examples of configuration achieving maximized visibility from multiple ground stations.

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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

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Space debris represent a real threat to the Earth orbit access and utilization. In the development and management of a space mission, it is important to focus on the evaluation of impact risk, the protection of spacecraft from debris impact, and the modelling of impact-induced fragmentation.

This webinar will focus on the current status and the most promising advancements in this field, introducing the best practices suggested by the scientific community and focusing on specific case studies. Attendees will learn about recent advances in catastrophic fragmentation modelling due to hypervelocity impact, impact risk assessment, spacecraft protection.

The last hour of the webinar will focus on impact testing, with details on the existing technologies and facilities and the current perspectives for the sector.

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Deliver robotic platforms and, in the next future, human missions on a planetary body with an atmosphere is a significant technological challenge. Onboard data acquired during Entry Descent and Landing (EDL) mission phases are typically used to verify the engineering system performances. Nevertheless, such data carry out much information of great scientific value. This webinar introduces the post-flight analysis of EDL mission data with a particular focus on the reconstruction of atmospheric profiles building upon the experience with past missions such as Huygens end ExoMars-2016 and presenting real-world case studies.

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Syllabus

The symposium “Multi-scale mechanics of composites” aims at outlining the state-of-the-art and the perspectives of the research in the field of multi-scale modelling for advanced composites materials and structures. Scientists and experts will be invited to share their latest research ideas and results in this research direction. This symposium is supported by the International Joint Research Center for Impact Dynamics and Its Engineering Applications, and the Structural Mechanics Behavior Science and Technology Innovation Intelligence Base.

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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, Debris, Severe Temperature Cycles, and, for some systems, the Re-Entry Environment. It is important to note that these environmental characteristics do simultaneously affect the space systems, materials, and structures, with a remarkable synergistic effect. In order to understand these synergistic effects, whether experimental or theoretical, numerical approaches are of essential importance, as the comprehension of the operative environment becomes a key point to extending the operative life of satellites and structures and withstanding aggressive conditions.

The course is based on 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 such as ESA and NASA.

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This webinar deals with structural dynamics and acoustic design of aerospace and air transportation vehicles. The vibroacoustic response of aerospace and air vehicles is a rather complex phenomenon, which is normally studied considering the dynamics and acoustics of sub-components, such as fuselage sections, wings, flaps, and landing gears, etc. Therefore, the webinar will focus specifically on the vibro-acoustics analysis of elementary mechanical components (e.g. lightweight aluminium framework and panel structures, double-wall structures, composite panels and shells, etc.), from a different point of view (theoretical, numerical and experimental). Several topics will be discussed, such as interior noise mitigation, noise transmission control and vibration attenuation. The physics, design and implementation of both passive vibration attenuation and sound insulation treatments/techniques and active semi-active control systems will be discussed in detail.

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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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The aim of this course is to present an overview of high-order accurate numerical methods for mathematical problems that arise in aeronautical and aerospace engineering. Numerical schemes are referred to as high-order accurate when a suitably defined error measure e is a function of the mesh size h as e∼h^p, with p≥3. High-order accuracy is of significant engineering interest in numerical methods because it allows the solution of computational problems with a smaller number of degrees of freedom and higher convergence rates of the error with respect to low-order numerical schemes. The aim of this course is to present an overview of high-order accurate numerical methods for mathematical problems that arise in aeronautical and aerospace engineering. Numerical schemes are referred to as high-order accurate when a suitably defined error measure e is a function of the mesh size h as e∼h^p, with p≥3. High-order accuracy is of significant engineering interest in numerical methods because it allows the solution of computational problems with a smaller number of degrees of freedom and higher convergence rates of the error with respect to low-order numerical schemes.

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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.

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