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Title:Optimal, impulsive, direct ascent, time-fixed orbital interception
Author(s):Heckathorn, William G.
Director of Research:Prussing, John E.
Doctoral Committee Chair(s):Prussing, John E.
Doctoral Committee Member(s):Scott, Edward J.; Hilton, Harry H.; Conway, Bruce A.
Department / Program:Department of Aerospace Engineering
Discipline:Aeronautical and Astronautical Engineering
Degree Granting Institution:University of Illinois at Urbana-Champaign
Degree:Ph.D. (doctoral)
Subject(s):Astronautical Engineering
Abstract:A method for determining the optimal impulsive trajectories is applied to minimum fuel, direct ascent, time-fixed intercept trajectories. The optimal trajectory is obtained by satisfying Lawden's necessary conditions expressed in terms of the primer vector. The vehicle is initially at rest on the surface of a spherical planet and the target is assumed to be in a circular, equatorial orbit around the planet. Results are presented and compared for two planetary models: a non-rotating planet, and one rotating with an angular velocity approximating that of the Earth. Each model is investigated for transfers in which the launch point is in the same plane as the target orbit (coplanar) and in which the launch point is not in the target orbit plane (noncoplanar). Parameters varied during the analysis include transfer time, target radius, initial position of the target in relation to the launch point, the latitude of the launch point, and the direction of the transfer trajectory, i.e. posigrade or retrograde. Cost comparisons are made between various cases, and generalizations indicated.
Issue Date:1985-08
Genre:Dissertation / Thesis
Date Available in IDEALS:2021-09-14

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