A5067070328- Astro and Planetary Science
- Spacecraft Dynamics and Control
- Space Satellite Systems and Control
- Planetary Science and Exploration
- Spacecraft and Cryogenic Technologies
- Spacecraft Design and Technology
- Stellar, planetary, and galactic studies
- Cancer-related Molecular Pathways
- Aerospace Engineering and Control Systems
- Space Exploration and Technology
- Parallel Computing and Optimization Techniques
- Reservoir Engineering and Simulation Methods
- Simulation Techniques and Applications
- Metaheuristic Optimization Algorithms Research
- Epigenetics and DNA Methylation
- Distributed and Parallel Computing Systems
- Solar and Space Plasma Dynamics
- Paleontology and Stratigraphy of Fossils
- Rocket and propulsion systems research
- TGF-β signaling in diseases
- Gas Dynamics and Kinetic Theory
- Geomagnetism and Paleomagnetism Studies
- Vehicle Routing Optimization Methods
- Astrophysics and Star Formation Studies
- Transportation and Mobility Innovations
Japan Aerospace Exploration Agency
2016
Institute of Space and Astronautical Science
2014-2015
International Society of Automation
2015
Hong Kong University of Science and Technology
1999-2014
University of Hong Kong
1999-2014
Purdue University West Lafayette
2004-2012
European Space Research and Technology Centre
2010-2011
European Space Agency
2010
California Institute of Technology
2002
A software platform for global optimisation, called PaGMO, has been developed within the Advanced Concepts Team (ACT) at European Space Agency, and was recently released as an open-source project. PaGMO is built to tackle high-dimensional optimisation problems, it successfully used find solutions real-life engineering problems among which preliminary design of interplanetary spacecraft trajectories - both chemical (including multiple flybys deep-space maneuvers) low-thrust (limited, moment,...
Low-thrust propulsion is a key technology for space exploration, and much work in astrodynamics has focused on the mathematical modeling optimization of low-thrust trajectories. Typically, nominal trajectory designed deterministic system. To account model execution errors, mission designers heuristically add margins, example, by reducing thrust specific impulse or computing penalties failures. These conventional methods are time-consuming, done hand experts, lead to conservative margins....
The design of a spacecraft trajectory can be formulated as global optimization task. complexity the resulting problem depends greatly on final target planet, chosen intermediate route, and type engine power system available on-board. Few attempts have been made to directly use framework trajectories that make low-thrust propulsion because large scale extreme non-linear programming problem. presence non-convex constraints, in particular, requires solvers able deal with such an added...
We make use of self-adaptation in a Differential Evolution algorithm and the asynchronous island model to design complex interplanetary trajectory touring Galilean Jupiter moons (Io, Europa, Ganymede Callisto) using multiple gravity assist technique. Such problem was recently subject an international competition organized by Jet Propulsion Laboratory (NASA) won designed aerospace experts reaching final score 311/324. apply our method very same finding new surprising designs orbital...
*† * ‡ Nuclear electric propulsion is expected to open new doors in deep space exploration. We study direct rendezvous missions the outer planets which employ a constant-thrust, constant specific-impulse engine. also consider how gravity assist can augment capability of nuclear propulsion. present numerical examples gravity-assist planets, use an engine similar that Jupiter Icy Moons Orbiter. For example, Earth-Venus-Earth-Jupiter-Pluto mission, spacecraft launches with V∞ 2.2 km/s and Pluto...
We build upon some new ideas in direct transcription methods developed within the Advanced Concepts Team to introduce two improvements Sims-Flanagan for low-thrust trajectories. The obtained algorithm is able produce an operational trajectory accounting real spacecraft dynamics and adapting segment duration on-line improving final optimality.
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.
This paper describes the methodologies used to tackle problem of 5th Global Trajectory Optimization Competition within team composed by Advanced Concepts Team European Space Agency and theGlobal Laboratory University Florence. The method pursued is powered two innovative approaches: a linearized model ‘self fly-by’ aiding first broad tree search chemical propulsion options use global optimization techniques (Monotonic Basin Hopping, in this case) applied directly low-thrust trajectory model.
The optimization of spacecraft trajectories can be formulated as a global task. complexity the problem depends greatly on formulation, route to its final target planet, and type engine power system that is available on-board spacecraft. Few attempts have been made use framework design make electric propulsion propel between planets because large scale extreme resulting nonlinear programming problem. presence high number constraints, in particular, requires special attention with respect...
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.
Optimization of interplanetary space mission trajectories have been a long standing challenge. Here novel approach is presented that considers several aspects the simultaneously as many-objective problem. Such problem then solved by decomposition in combination with (massive) parallelization framework employing instances Ant Colony algorithms. Numerical results show here has advantages over classical weighted sum and very suitable to efficiently exploit massive parallelization.
Low-thrust trajectories can be modeled as a series of impulsive ( ΔV) maneuvers connected by conic arcs. We study new ways parameterizin g the ΔV vectors with reduced number variables and constraints. When optimizing low-thrust gravity-assist trajectories, magnitudes parameterized switch on/off times engine; steering angles coefficients Chebyshev series. present numerical results for several missions, including: Earth-Jupiter rendezvous, Earth-MarsVesta flyby, Earth-Mercury rendezvous...
In 2023, the 12th edition of Global Trajectory Competition was organised around problem referred to as "Sustainable Asteroid Mining". This paper reports developments that led solution proposed by ESA's Advanced Concepts Team. Beyond fact approach failed rank higher than fourth in final competition leader-board, several innovative fundamental methodologies were developed which have a broader application. particular, new methods based on machine learning well manipulating laws astrodynamics...