In the context of a research work conducted on multi-objective global optimization techniques, the paper presents their application to the combined optimization of launcher high level architecture and ascent trajectories. The applicative scenario has been developed in two steps: first, the trajectory optimization has been implemented for existing launchers with fixed design parameters, and then the launcher architecture has been introduced in the optimization cycle. The proposed high level architecture modelling is intended to provide a tool in the early stage of new conceptual design optimization and analysis for Earth or planetary launchers. Hence, the algorithms concentrate on the number, type, thrust and propellant mass of stages and boosters as optimization variables. The resulting search space is extremely vast and multi-modal, with a mixed continuous-discrete nature, making the global approach necessary. After a detailed comparison work of various optimization techniques, the well known NSGA-II (Non-dominated Sorting Genetic Algorithm-II) and a newly developed version of Particle Swarm Optimization method, called DG-MOPSO (Double-Grid Multi-Objective Particle Swarm Optimization), have been selected for the applicative scenario. The paper presents in detail the models, their validation and the results obtained for two applicative cases. Both the selected algorithms provide reliable ascent trajectory design results for several different target orbits, showing a non negligible advantage of DG-MOPSO over NSGA-II, and the validity of the developed architecture for the concurrent optimization of launcher architectures and ascent trajectories has been proved, though the parametric models need to be refined to obtain more realistic results. This work is to be intended as the first step towards a complete multi-disciplinary design optimization (MDO) approach, potentially capable of providing a versatile automatic launchers preliminary design environment.

Concurrent Optimization of Launcher Architectures and Ascent Trajectories with Global Optimization Algorithms

CASTELLINI, FRANCESCO;LAVAGNA, MICHÈLE;
2008-01-01

Abstract

In the context of a research work conducted on multi-objective global optimization techniques, the paper presents their application to the combined optimization of launcher high level architecture and ascent trajectories. The applicative scenario has been developed in two steps: first, the trajectory optimization has been implemented for existing launchers with fixed design parameters, and then the launcher architecture has been introduced in the optimization cycle. The proposed high level architecture modelling is intended to provide a tool in the early stage of new conceptual design optimization and analysis for Earth or planetary launchers. Hence, the algorithms concentrate on the number, type, thrust and propellant mass of stages and boosters as optimization variables. The resulting search space is extremely vast and multi-modal, with a mixed continuous-discrete nature, making the global approach necessary. After a detailed comparison work of various optimization techniques, the well known NSGA-II (Non-dominated Sorting Genetic Algorithm-II) and a newly developed version of Particle Swarm Optimization method, called DG-MOPSO (Double-Grid Multi-Objective Particle Swarm Optimization), have been selected for the applicative scenario. The paper presents in detail the models, their validation and the results obtained for two applicative cases. Both the selected algorithms provide reliable ascent trajectory design results for several different target orbits, showing a non negligible advantage of DG-MOPSO over NSGA-II, and the validity of the developed architecture for the concurrent optimization of launcher architectures and ascent trajectories has been proved, though the parametric models need to be refined to obtain more realistic results. This work is to be intended as the first step towards a complete multi-disciplinary design optimization (MDO) approach, potentially capable of providing a versatile automatic launchers preliminary design environment.
2008
59th International Astronautical Congress (IAC)
9781615671601
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11311/545752
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