Optimal Mirror Trajectories Using Continuous Thrust

Aerotecnica Missili & Spazio

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Field Value
 
Title Optimal Mirror Trajectories Using Continuous Thrust
 
Creator Pontani, Mauro
 
Subject


 
Description The theorem of mirror trajectories, proven almost six decades ago by Miele, states that for a given path in the restrictedproblem of three bodies (with primaries in mutual circular orbits) there exists a mirror trajectory (in two dimensions) andthree mirror paths (in three dimensions). The theorem at hand regards feasible trajectories and proved extremely usefulfor investigating the spacecraft natural dynamics in the circular restricted problem of three bodies, by identifying specialsolutions, such as symmetric periodic orbits and free return paths. This theorem has recently been extended to optimalmirror trajectories, thus substantiating Miele's conjecture based on numerical evidence. Unlike the theorem of mirrorpaths, which refers to natural (unpowered) orbital motion, the theorem of optimal mirror trajectories establishes theexistence, characteristics, and optimal control time history of the returning path, once the outgoing optimal trajectoryhas been determined. This theorem applies to (i) nite-thrust trajectories, for which a limiting value of the thrustacceleration exists, (ii) constant-thrust-acceleration paths, (iii) impulsive trajectories, and (iv) articial periodic orbits(that use very low thrust propulsion or solar sails). This work illustrates the theorem of optimal mirror trajectoriesapplied to two cases of practical interest: (a) continuous, low-thrust orbit transfer, and (b) continuous-thrust lunardescent (with soft touchdown) and ascent (with nal orbit injection). In both cases, the theorem allows the immediateand straightforward identication of the optimal control law of the returning path, once the outgoing optimal trajectoryhas been determined.
 
Publisher Associazione Italiana di Aeronautica e Astronautica (AIDAA)
 
Contributor
 
Date 2018-02-11
 
Type info:eu-repo/semantics/article
info:eu-repo/semantics/publishedVersion
Peer-reviewed Article

 
Format application/pdf
 
Identifier http://131.114.27.37/index.php/AMS/article/view/328
10.19249/ams.v96i4.328
 
Source Aerotecnica Missili & Spazio; Vol 96, No 4 (2017); 204-215
0365-7442
 
Language eng
 
Relation http://131.114.27.37/index.php/AMS/article/view/328/296
 
Rights Copyright (c) 2018 Aerotecnica Missili & Spazio
 

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