A5048946550- Spacecraft Dynamics and Control
- Astro and Planetary Science
- Space Satellite Systems and Control
- Planetary Science and Exploration
- Stellar, planetary, and galactic studies
- Solar and Space Plasma Dynamics
- Spacecraft Design and Technology
- Satellite Communication Systems
- Spacecraft and Cryogenic Technologies
- Aerospace Engineering and Control Systems
- Aerospace Engineering and Energy Systems
- Astrophysics and Star Formation Studies
- Scientific Research and Discoveries
- Structural Analysis and Optimization
- Inertial Sensor and Navigation
- Guidance and Control Systems
- Rocket and propulsion systems research
- Fluid Dynamics Simulations and Interactions
- Cosmology and Gravitation Theories
- Field-Flow Fractionation Techniques
- Atmospheric aerosols and clouds
- Heat transfer and supercritical fluids
- Polymer composites and self-healing
- Machine Learning and ELM
- Radiation Effects in Electronics
Sapienza University of Rome
2015-2024
Applied Energetics (United States)
2017
The hopping rover is a promising solution for small celestial body surface mobility. How to predict its locomotion and landing area challenging when considering the complex dynamical environment rough terrain. In this study, new concept of hop reachable domain proposed evaluate mobility treated as point mass. two key velocities, i.e., liftoff velocity escape velocity, are derived in detail based on equations, respectively. Numerical simulations performed with their applications...
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...
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...
The aim of this paper is to propose a refined mathematical model for describing the acceleration experienced by solar sail. Unlike conventional characterized constant coefficients, force coefficients sail are now assumed depend on light incidence angle, surface roughness, and sun–sail distance. new elaborated with support experimental data that show how main variable affecting angle. To emphasize differences between respect one, comparison established through analysis circle-to-circle...
In this work, we introduce a modified double-averaging approach by considering the short-term effects and formulate more accurate double-averaged Hamiltonian (in comparison to classical octupole-level Hamiltonian) for hierarchial triple systems. The is expressed as power series in ratio of semi-major axes inner outer binaries. Both Delaunay's elements orbit are adopted describe motion. To derive secular Hamiltonian, oscillations averaged out means approach. particular, during average over...
Investigating the impact process between hopping lander and regolith surfaces is of great significance for in situ asteroid explorations. The high-efficiency description regolith-interaction dynamics remains to be analyzed. This paper presents a new method effectively simulating six-degree-of-freedom motion when it impacts at low velocity. Bekker terramechanics theory utilized calculating force torque, considering notable deformable characteristic regolith. Deformation tracked simulate...
Abstract This study employed a quantum-annealing framework to solve spacecraft trajectory optimization problems. Quantum annealing belongs the field of quantum computing and is promising technique for tackling hard binary problems by employing annealers. To address optimal control using annealing, transcription procedure was introduced express problem in form required. The proposed leverages pseudospectral method discretize represents dynamical constraints as algebraic equality at specific...
In this paper, the use of north and south families halo orbits, around L1 L2 collinear libration points Earth–Moon system, to realize a lunar global positioning system (LGPS) is proposed. The computation reference trajectories required station-keeping manoeuvres with associated ΔV are described, as well different configurations for satellites' constellation. combination orbits results in an X-shaped configuration allowing optimal performances. A visibility study, from locations on surface,...
A novel approach for minimum-time reconfiguration of satellite formations is proposed considering the perturbation forces as control variables. Planning appropriate attitude maneuvers each satellite, atmospheric drag and solar radiation pressure are properly controlled, formation given inputs to achieve imposed reconfiguration. Limits advantages presented examined low Earth orbits, medium geostationary orbits. The recent inverse dynamics particle swarm optimization involved; integration...
Following an approach based on the Milankovitch elements, equations able to describe long-term evolution of trajectory a probe orbiting celestial body (primary body) have been analytically determined, taking into account perturbative effects deriving from planetary oblateness and one or more perturbing bodies lying equatorial plane primary body. Using these equations, three families orbits, characterized by constant orbit elements average, obtained. Whereas first family, composed elliptical...
The lifetime of a probe moving at low altitude around Europa is strictly correlated, other than to the effects due interaction with Jupiter's magnetic field, but also eccentricity variations its orbit because possible collision lunar surface. Thus, knowledge such plays key role in designing missions that provide remotely sensed images this moon high spatial resolution. Accordingly, behavior element has been investigated here, taking into account nonperfect coplanarity between orbital plane...
A three-axis solar sail attitude control system for interplanetary missions is proposed: required steering achieved by means of a small mass in the plane, whereas roll-axis through rotation ballast with two masses at extremities. The satellite fixed geometrical centre: this solution avoids difficulties arising from employment an out-of-plane boom end, i.e. pointing problems optical payloads and communication antennas. circular sailcraft 220 kg characteristic acceleration c = 0.5 mm/s 2...