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Alessandro Masat

Alessandro Masat

PhD Candidate | PoliMi - DAER - COMPASS | ESA - ESOC - Mission Analysis

About

19
Publications
1,272
Reads
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16
Citations
Citations since 2017
19 Research Items
16 Citations
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2017201820192020202120222023024681012
Additional affiliations
May 2020 - October 2023
Politecnico di Milano
Position
  • PhD Student
Description
  • Robust trajectory design, uncertainty propagation, astrodynamics, regularisation, applied optimisation, high performance computing
Education
May 2020 - October 2023
Politecnico di Milano
Field of study
  • Aerospace Engineering
August 2018 - February 2020
KTH Royal Institute of Technology
Field of study
  • Applied and Computational Mathematics - Vehicle Engineering Degree
September 2017 - December 2019
Politecnico di Milano
Field of study
  • Space Engineering

Publications

Publications (19)
Article
Full-text available
The orbital propagation of large sets of initial conditions under high accuracy requirements is currently a bottleneck in the development of space missions, e.g. for planetary protection compliance analyses. The proposed approach can include any force source in the dynamical model through efficient Picard-Chebyshev (PC) numerical simulations. A two...
Preprint
Full-text available
The orbital propagation of large sets of initial conditions under high accuracy requirements is currently a bottleneck in the development of space missions, e.g. for planetary protection compliance analyses. The proposed approach can include any force source in the dynamical model through efficient Picard-Chebyshev (PC) numerical simulations. A two...
Preprint
Full-text available
The orbital propagation of large sets of initial conditions under high accuracy requirements is currently a bottleneck in the development of space missions, e.g. for planetary protection compliance analyses. The proposed approach can include any force source in the dynamical model through efficient Picard-Chebyshev (PC) numerical simulations. A two...
Conference Paper
Full-text available
Uncertainty propagation features many of modern orbital dynamics-related engineering analyses. A solid understanding of how inaccurate measurements affect the subsequent phases of a mission is a crucial task to ensure its safety and success. Typical techniques to assess how uncertain phenomena impact the development of a mission all rely on Monte C...
Conference Paper
Full-text available
An analytical solution is presented that captures the bulk of the dynamics of close flybys about oblate celestial bodies. The solution is obtained by perturbations. More specifically, an infinitesimal contact transformation is found that reduces the perturbed hyperbolic Keplerian motion to a hyperbolic Kepler problem with varied angular momentum. I...
Preprint
Full-text available
A popular intermediary in the theory of artificial satellites is obtained after the elimination of parallactic terms from the J2-problem Hamiltonian. The resulting quasi-Keplerian system is in turn converted into the Kepler problem by a torsion. When this reduction process is applied to unbounded orbits the solution is made of Keplerian hyperbolae....
Conference Paper
Full-text available
The detection of flybys in the numerical propagation of interplanetary trajectories is a key aspect to enable planetary protection analyses. Their much faster dynamics, compared to the pure heliocentric motion, hinders the development of advanced orbital integrators: regularisation-based approaches and variation of parameters implementations are ex...
Article
Full-text available
Orbital resonances can be leveraged in the mission design phase to target planets at different energy levels. On the other side, precise models are needed to predict possible threatening returns of natural and artificial objects closely approaching a target planet. To this aim, we propose a semi-analytic extension of the b-plane resonance model to...
Article
Full-text available
Planetary protection in trajectory design aims to assess the impact probability of space-mission-disposed objects based on their initial uncertain conditions, to avoid contaminating other planetary environments. High-precision dynamic models and propagation methods are required to reach high confidence levels on small estimated impact probabilities...
Article
Full-text available
Orbital resonances have been exploited in different contexts, with the latest interplanetary application being the ESA/NASA mission Solar Orbiter, which uses repeated flybys of Venus to change the ecliptic inclination with low fuel consumption. The b-plane formalism is a useful framework to represent close approaches at the boundaries of the sphere...
Preprint
Full-text available
Orbital resonances can be leveraged in the mission design phase to target planets at different energy levels. On the other side, precise models are needed to predict possible threatening returns of natural and artificial objects closely approaching a target planet. To this aim, we propose a semi-analytic extension of the b-plane resonance model to...
Preprint
Full-text available
Orbital resonances have been exploited in different contexts, with the latest interplanetary application being the ESA/NASA mission Solar Orbiter, which uses repeated flybys of Venus to change the ecliptic inclination with low fuel consumption. The b-plane formalism is a useful framework to represent close approaches at the boundaries of the sphere...
Preprint
Full-text available
Planetary protection in trajectory design aims to assess the impact probability of space mission disposed objects based on their initial uncertain conditions, to avoid contaminating other planetary environments. High precision dynamical models and propagation methods are required to reach high confidence levels on small estimated impact probabiliti...
Conference Paper
Full-text available
View Video Presentation: https://doi.org/10.2514/6.2022-1275.vid The computational intensity of the trajectory design problem severely affects the development time of any space mission, both in its preliminary phase and in the consequent optimization. This paper presents a formulation of the design problem that can account for any force source in t...
Conference Paper
Full-text available
The implementation of resonant gravity assist maneuvers is an essential prerequisite for interplanetary missions requiring complex trajectory solutions. A convenient formalism to design resonant trajectories is the b-plane, as post-encounter orbits with prescribed semi-major axis can be easily mapped on this plane and thus targeted a priori. This r...
Conference Paper
Full-text available
Planetary protection in trajectory design aims to assess the impact probability of space mission disposed objects based on their initial uncertain condition, to avoid contaminating other planetary environments. High precision dynamical models and propagation methods are required to reach high confidence levels on small estimated impact probabilitie...
Conference Paper
Full-text available
Orbital resonances have been exploited in different contexts, with the latest in-terplanetary application being the ESA/NASA mission Solar Orbiter, which uses repeated flybys of Venus to change the ecliptic inclination with low fuel consumption. The b-plane formalism is a clever framework to represent close approaches at the boundaries of the spher...
Thesis
Full-text available
Many space engineering and orbital mechanics applications seek for the usage of focused mathematical models, capable of providing useful insight into particular phenomena or exploiting some theoretical and physical tools to reduce the computational costs and/or increase the level of accuracy reached. Orbital resonances are one of the phenomena that...
Conference Paper
Full-text available
The study of close approaches and resonant returns features several applications, from monitoring near-Earth asteroids to the fulfilment of planetary protection requirements when injecting end-of-life spacecrafts into deep space orbits. Such studies are often performed using the b-plane, a reference frame where resonant returns are identified by ci...

Network

Projects

Project (1)
Project
Space benefits mankind through the services it provides to Earth. Future space activities progress thanks to space transfer and are safeguarded by space situation awareness. Natural orbit perturbations are responsible for the trajectory divergence from the nominal two-body problem, increasing the requirements for orbit control; whereas, in space situation awareness, they influence the orbit evolution of space debris that could cause hazard to operational spacecraft and near Earth objects that may intersect the Earth. However, this project proposes to leverage the dynamics of natural orbit perturbations to significantly reduce current extreme high mission cost and create new opportunities for space exploration and exploitation. The COMPASS project will bridge over the disciplines of orbital dynamics, dynamical systems theory, optimisation and space mission design by developing novel techniques for orbit manoeuvring by “surfing” through orbit perturbations. The use of semi-analytical techniques and tools of dynamical systems theory will lay the foundation for a new understanding of the dynamics of orbit perturbations. We will develop an optimiser that progressively explores the phase space and, though spacecraft parameters and propulsion manoeuvres, governs the effect of perturbations to reach the desired orbit. It is the ambition of COMPASS to radically change the current space mission design philosophy: from counteracting disturbances, to exploiting natural and artificial perturbations. COMPASS will benefit extensive international, including the ESA, NASA, JAXA, CNES, and ASI. Indeed, the proposed idea of optimal navigation through orbit perturbations will address various major engineering challenges in space situation awareness, for application to space debris evolution and mitigation, missions to asteroids for their detection, exploration and deflection, and in space transfers, for perturbation-enhanced trajectory design.