A5054420456- Spacecraft Dynamics and Control
- Rocket and propulsion systems research
- Spacecraft Design and Technology
- Spacecraft and Cryogenic Technologies
- Space Satellite Systems and Control
- Probabilistic and Robust Engineering Design
- Astro and Planetary Science
- Planetary Science and Exploration
- Aerospace Engineering and Control Systems
- Advanced Multi-Objective Optimization Algorithms
- Matrix Theory and Algorithms
- Numerical methods for differential equations
- Aerospace Engineering and Energy Systems
- Vehicle Dynamics and Control Systems
- Gas Dynamics and Kinetic Theory
- Advanced Optimization Algorithms Research
- Space Science and Extraterrestrial Life
- Geophysics and Gravity Measurements
- Target Tracking and Data Fusion in Sensor Networks
- Robotic Path Planning Algorithms
- Energetic Materials and Combustion
- Aerospace and Aviation Technology
- Electrohydrodynamics and Fluid Dynamics
- Advanced Battery Technologies Research
- Iterative Methods for Nonlinear Equations
Université Paris-Saclay
2018-2024
Office National d'Études et de Recherches Aérospatiales
2004-2016
This paper presents an interior-point approach for solving optimal control problems. We combine the idea of logarithmic penalization (used to solve large-scale problems with relatively few iterations) dedicated linear algebra solvers (QR factorization band matrices). The method also takes advantage recent progress in analysis discretization errors. At each major iteration algorithm (i.e., at a solution penalized problem given value penalty parameter), we determine whether points should be...
At early design phases, taking into account uncertainty in the optimization of a multidisciplinary system is essential to assess optimal characteristics and performance. Uncertainty methods aim at efficiently organizing not only different disciplinary analyses, propagation, but also handling interdisciplinary couplings under uncertainty. A new decoupled formulation (named Individual Discipline Feasible/Polynomial Chaos Expansion) ensuring coupling satisfaction for all realizations uncertain...
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.
Launch vehicle design is a complex problem involving series of disciplines. These disciplines present conflicting objectives and require multidisciplinary optimization methods in order to handle the couplings make search compromises easier. specific because it combines optimizations trajectory variables. In this article, we new approach, called StageWise decomposition for Optimal Rocket Design (SWORD). This method splits up process into different stages transforms initial coordination...
Optimal design of launch vehicles is a complex multidisciplinary problem. The traditional way to optimize such decompose the problem into different disciplines and combine specific solvers global optimizer. This paper presents new MDO method configuration an expendable vehicle describes application this optimization small liquid fueled multi-stage vehicle. objective payload mass maximization. proposed bi-level splits up original flight phases optimizes concurrently stages transversal...
The aim of this paper is to investigate the feasibility an Earth-to-Mars transfer with reduced time using a high-power electric propulsion system. study involved multidisciplinary analysis combining general performance calculations for power-limited systems, nuclear power source that might be available in future, and series mission analyses, including trajectory optimization. quantified importance specific mass system regard objective fast transfer. A very less than six weeks appears...
At early design phases, taking into account uncertainty in the optimization of a multidis- ciplinary system is essential to establish its optimal characteristics and performances. Uncer- tainty Multidisciplinary Design Optimization (UMDO) methods aim at eciently organizing not only dierent disciplinary analyses, propagation, optimization, but also handling interdisciplinary couplings under uncertainty. A new decoupled UMDO formulation (named Individual Discipline Feasible - Polynomial Chaos...
Optimal design of launch vehicles is a complex process which gathers series disciplines. The classical method used to solve such problems consists in decomposing the problem into dierent disciplines and associating global optimizer disciplinary analyzers (MultiDiscipline Feasible - most vehicle design). This paper presents new MDO based on transversal decomposition more appropriate multistage architecture. proposed bi-level splits up optimization stages performs concurrent optimizations...
Recent advances in electric propulsion technologies such as magnetoplasma rockets gave a new momentum to the study of nuclear concepts for Mars missions. Some recent works have been focused on very short Earth-to-Mars transfers about 40 days with high-power, variable specific impulse systems [1]. While interest appears clearly regard payload mass ratio (due high level impulse), its transfer time is more complex define, it depends many design parameters. In this paper, general analysis...