Indirect Optimization of Satellite Deployment into a Highly Elliptic Orbit | Zendy

Francesco Simeoni | Zendy; Lorenzo Casalino | Zendy; Alessandro Zavoli | Zendy; Guido Colasurdo | Zendy

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Indirect Optimization of Satellite Deployment into a Highly Elliptic Orbit

Author(s) -

Francesco Simeoni,

Lorenzo Casalino,

Alessandro Zavoli,

Guido Colasurdo

Publication year - 2012

Publication title -

international journal of aerospace engineering

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.361

H-Index - 22

eISSN - 1687-5974

pISSN - 1687-5966

DOI - 10.1155/2012/152683

Subject(s) - software deployment , spacecraft , satellite , elliptic orbit , orbit (dynamics) , aerospace engineering , geocentric orbit , radiation pressure , medium earth orbit , convergence (economics) , computer science , solar sail , low earth orbit , physics , control theory (sociology) , control (management) , engineering , astronomy , artificial intelligence , economic growth , economics , operating system

The analysis of the optimal strategies for the deployment of a spacecraft into a highly elliptic orbit is carried out by means of an indirect optimization procedure, which is basedon the theory of optimal control. The orbit peculiarities require that several perturbationsare taken into account: an 8 × 8 model of the Earth potential is adopted and gravitationalperturbations from Moon and Sun together with solar radiation pressure are considered.A procedure to guarantee convergence and define the optimal switching structure is outlined. Results concerning missions with up to 4.5 revolutions around the Earth are given, andsignificant features of this kind of deployment are highlighted

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