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High order optimal feedback control of lunar landing and rendezvous trajectories

Di Lizia, P, Armellin, R, Bernelli Zazzera, F and Berz, M (2011) High order optimal feedback control of lunar landing and rendezvous trajectories In: Conference of the European Aerospace Societies (CEAS) 2011, 2011-10-24 - 2011-10-28, Venice, Italy.

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Abstract

Optimal feedback control is classically based on linear approximations, whose accuracy drops off rapidly in highly nonlinear dynamics. A high order optimal control strategy is proposed in this work, based on the use of differential algebraic techniques. In the frame of orbital mechanics, differential algebra allows the dependency of the spacecraft state on initial conditions and environmental parameters to be represented by high order Taylor polynomials. The resulting polynomials can be manipulated to obtain the high order expansion of the solution of two-point boundary value problems. Based on the reduction of the optimal control problem to an equivalent two-point boundary value problem, differential algebra is used in this work to compute the high order expansion of the solution of the optimal control problem about a reference trajectory. New optimal control laws for displaced initial states are then obtained by the mere evaluation of polynomials.

Item Type: Conference or Workshop Item (Conference Paper)
Subjects : Electronic Engineering
Divisions : Faculty of Engineering and Physical Sciences > Electronic Engineering
Authors :
NameEmailORCID
Di Lizia, PUNSPECIFIEDUNSPECIFIED
Armellin, RUNSPECIFIEDUNSPECIFIED
Bernelli Zazzera, FUNSPECIFIEDUNSPECIFIED
Berz, MUNSPECIFIEDUNSPECIFIED
Date : 24 October 2011
Contributors :
ContributionNameEmailORCID
http://www.loc.gov/loc.terms/relators/PBLConfine Edizioni, UNSPECIFIEDUNSPECIFIED
Related URLs :
Depositing User : Symplectic Elements
Date Deposited : 09 Jan 2017 15:56
Last Modified : 31 Oct 2017 19:02
URI: http://epubs.surrey.ac.uk/id/eprint/813239

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