A5055411162- Spacecraft Dynamics and Control
- Astro and Planetary Science
- Space Satellite Systems and Control
- Solar and Space Plasma Dynamics
- Spacecraft and Cryogenic Technologies
- Aerospace Engineering and Energy Systems
- Spacecraft Design and Technology
- Aerospace Engineering and Control Systems
- Planetary Science and Exploration
- Advanced Aircraft Design and Technologies
- Stellar, planetary, and galactic studies
- Inertial Sensor and Navigation
- Distributed Control Multi-Agent Systems
- Guidance and Control Systems
- Rocket and propulsion systems research
- Underwater Vehicles and Communication Systems
- Air Traffic Management and Optimization
- Astrophysics and Star Formation Studies
- Particle accelerators and beam dynamics
- Robotic Path Planning Algorithms
- Control and Dynamics of Mobile Robots
- Fluid Dynamics Simulations and Interactions
- Structural Analysis and Optimization
- Fluid dynamics and aerodynamics studies
- Geophysics and Gravity Measurements
University of Pisa
2016-2025
Northwestern Polytechnical University
2016
The electric solar wind sail (E-sail) is a space propulsion concept that uses the natural dynamic pressure for producing spacecraft thrust. In its baseline form, E-sail consists of number long, thin, conducting, and centrifugally stretched tethers, which are kept in high positive potential by an onboard electron gun. gains efficiency from fact effective area, i.e., structure can be millions times larger than physical area thin tethers wires, offsets very weak. Indeed, according to most...
The Helianthus mission proposal is based on maintaining an artificial L1-type equilibrium point in the Sun-Earth gravitational field by means of a square solar sail, which should provide required propulsive acceleration without any consumption propellant. That vantage would enable scientific observation Sun and guarantee effective monitoring its activity, thus ensuring early warning event catastrophic flares. Due to intrinsic instability points, spacecraft dynamics regulated advanced...
In this paper, a spacecraft formation control framework is presented aimed at guaranteeing long-term bounded relative motion in the asteroid's uncertain dynamical environment. The mean-orbital-elements-based invariant boundedness conditions via an approximate gravitational field are adopted to develop nominal steering strategy, while correction resulting from Lyapunov redesign method devised account for uncertainties, i.e. gravity uncertainty and solar perturbations. Contrary traditional...
Covers advancements in spacecraft and tactical strategic missile systems, including subsystem design application, mission analysis, materials structures, developments space sciences, processing manufacturing, operations, applications of technologies to other fields.
Solar-sail mission analysis and design is currently performed assuming constant optical mechanical properties of the thin metalized polymer films that are projected for solar sails. More realistically, however, these likely to be affected by damaging effects space environment. The standard solar-sail force models can therefore not used investigate consequences on performance. aim this paper propose a new parametric model describing sail film's degradation with time. In particular,...
Missions towards the boundaries of Solar System require long transfer times and advanced propulsion systems. An interesting option is offered by electric sails, a new concept that uses solar wind dynamic pressure for generating continuous thrust without need reaction mass. The aim this paper to investigate performance such system obtaining escape conditions from planning mission reach heliosphere boundaries. problem studied in an optimal framework, minimizing time given distance or...
The transfer between two circular, coplanar Keplerian orbits of a spacecraft equipped with continuous thrust propulsion system is usually studied in an optimal framework by maximizing given performance index. Using indirect approach, the trajectory and maximum value index are obtained numerically solving two-point boundary problem (TPBVP). In this context, computation time required numerical solution TPBVP depends on guess unknown initial costates. aim paper to describe analytical procedure...
This paper studies the performance of an interplanetary CubeSat equipped with a continuous-thrust primary propulsion system in heliocentric mission scenario, which models nodal flyby potential near-Earth asteroid. In particular, mathematical model discussed this work considers small array (commercial) miniaturized electric thrusters installed onboard typical CubeSat, whose power-generation is based on use classic solar panels. The also discusses impact size thrusters’ nominal transfer by...
Covers advancements in spacecraft and tactical strategic missile systems, including subsystem design application, mission analysis, materials structures, developments space sciences, processing manufacturing, operations, applications of technologies to other fields.
Abstract. The electric solar wind sail (E-sail) is a new type of propellantless propulsion system for Solar System transportation, which uses the natural to produce spacecraft propulsion. E-sail consists thin centrifugally stretched tethers that are kept charged by an onboard electron gun and, as such, experience Coulomb drag through high-speed plasma stream. This paper discusses mass breakdown and performance model hosts mission-specific payload prescribed mass. In particular, able estimate...
The electric solar wind sail, or E-sail, is a novel deep space propulsion concept which has not been demonstrated in yet. While the authentic operational environment of its fundamentals can be ionosphere where E-sail used as plasma brake for deorbiting. Two missions to launched 2023, Foresail-1p and ESTCube-2, will attempt demonstrate Coulomb drag (an umbrella term brake) low Earth orbit. This paper presents next step bringing space—we provide initial modelling trajectory analysis...
Abstract Orbits that are frozen in an averaged model, including the effect of a disturbing body laying on equatorial plane primary and influence oblateness body, have been applied to probes orbiting Moon. In this scenario, main is represented by Earth, which characterized certain obliquity with respect As consequence this, perturbing effects not included such solutions perfectly frozen. However, orbit eccentricity, inclination, argument pericenter present limited variations can be set...