trajectory optimization

Optimization of interplanetary trajectories using the colliding bodies optimization algorithm

In this paper, a recent physics-based metaheuristic algorithm, the Colliding Bodies Optimization (CBO), already employed to solve problems in civil and mechanical engineering, is proposed for the optimization of interplanetary trajectories by using both indirect and direct approaches. The CBO has an extremely simple formulation and does not depend on any initial conditions.

Performance evaluation methodology for multistage launch vehicles with high-fidelity modeling

Multistage launch vehicles of reduced size, such as ”Super Strypi” or ”Sword” are currently investigated for the purpose of providing launch opportunities for microsatellites. Currently, microsatellites are launched according to timing and orbit requirements of the main payload. The limited costs of microsatellites and their capability to be produced and ready for use in short time make them particularly suitable for ready-on-demand requests, such as facing an emergency. As a result, launch vehicles for the exclusive use of microsatellites would be very useful.

Selecting optimal inspection trajectories for target observation

A challenging aspect regarding proximity operations such as on-orbit servicing, refuelling and dismissal is the selection of optimal trajectories. The path should be conveniently followed by making use of sensors and actuators available on-board Optical hardware has been lately demonstrated to be both accurate and reliable for determining pose estimation in space proximity operations. Nevertheless, when passive cameras are used, accuracy is achieved through clear images which are obtained if the target is in favourable relative illumination conditions.

An accurate modeling and performance of multistage launch vehicles for microsatellites via a firekwokk algorithm

Multistage launch vehicles of reduced size, such as "Super Strypi" or "Sword", are currently investigated for the purpose of providing launch opportunities for microsatellites. This work proposes a general methodology for the accurate modeling and performance evaluation of launch vehicles dedicated to microsatellites. For illustrative purposes, the approach at hand is applied to the Scout rocket, a micro-launcher used in the past. Aerodynamics and propulsion are modeled with high fidelity through interpolation of available data.

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