A5050692324- Spacecraft Dynamics and Control
- Space Satellite Systems and Control
- Astro and Planetary Science
- Spacecraft Design and Technology
- Inertial Sensor and Navigation
- Adaptive Control of Nonlinear Systems
- Aerospace Engineering and Control Systems
- Dynamics and Control of Mechanical Systems
- Spacecraft and Cryogenic Technologies
- Planetary Science and Exploration
- Geophysics and Gravity Measurements
- Robotic Path Planning Algorithms
- GNSS positioning and interference
- Modular Robots and Swarm Intelligence
- Guidance and Control Systems
- Control and Dynamics of Mobile Robots
- Solar and Space Plasma Dynamics
- Scientific Research and Discoveries
- Stability and Control of Uncertain Systems
- Numerical methods for differential equations
- Engineering Education and Curriculum Development
- Target Tracking and Data Fusion in Sensor Networks
- Quantum chaos and dynamical systems
- Space Exploration and Technology
- Robotics and Sensor-Based Localization
Politecnico di Milano
2016-2025
University of Milan
2016-2019
Universidad Politécnica de Madrid
2015
European Space Agency
2002
A comprehensive design procedure based on extremum seeking for minimum power demand formation e ight is presented, the rst with performance guarantees. The involves of a new wake robust hold autopilot and transformation closed-loop aircraft dynamics to form in which newly available rigorous applicable. applied Lockheed C-5s, extending use maximum large transports. By availableexperimental data C-5, model wakeis developed that models aerodynamic interference as feedback nonlinearities. Thus,...
A method to incorporate low-thrust propulsion into the invariant manifolds technique is presented in this paper. The introduced by means of special attainable sets that are used conjunction with define a first-guess solution. This later optimized more refined model where an optimal control formalism used. Planar low-energy transfers moon, as well spatial stable manifold halo orbits Earth–moon system, presented. These solutions not achievable via patched-conics methods or standard techniques....
Minimizingvibrationsofamaneuverede exiblemanipulatorisachallengingtask.Resultsarepresentedofaseries of experimental tests carried out on the Space Robot Simulator assembly, which has been set up at Spacecraft Research and Design Center Naval Postgraduate School. The manipulator is planar with two rotational degrees freedom links, either one or both can be e exible in bending. oats air cushions a granite table. task experiments was to test effectiveness command input shaping technique...
This paper presents a state-dependent method for solving nonlinear, control-affine, finite-time optimal control problems. The problem is set in form and solved as sequence of time-varying linear-quadratic regulators, which an approach based on state transition matrices has been developed. novelty the consists possibility managing number different coefficient factorizations uncontrolled dynamics, use with various methods. At each iteration, nonlinear programming to select combination that...
The H2020 ReDSHIFT project aims at finding passive means to mitigate the proliferation of space debris. This goal is pursued by a twofold research activity based on theoretical astrodynamics, computer simulations and analysis legal aspects debris, coupled with an experimental advanced additive manufacturing (3D printing) applied production novel small satellite. Several different related design debris compliant spacecraft are treated, including shielding, area augmentation devices for...
Views Icon Article contents Figures & tables Video Audio Supplementary Data Peer Review Share Twitter Facebook Reddit LinkedIn Tools Reprints and Permissions Cite Search Site Citation G. Mingotti, F. Topputo, Bernelli‐Zazzera; Combined Optimal Low‐Thrust Stable‐Manifold Trajectories to the Earth‐Moon Halo Orbits. AIP Conf. Proc. 7 February 2007; 886 (1): 100–112. https://doi.org/10.1063/1.2710047 Download citation file: Ris (Zotero) Reference Manager EasyBib Bookends Mendeley Papers EndNote...