Design, Simulation, and Error Analysis for Guidance Law of a Satellite Launcher

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Mardani, Mohammad | 2009

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Type of Document: Ph.D. Dissertation
Language: Farsi
Document No: 39906 (05)
University: Sharif University of Technology
Department: Electrical Engineering
Advisor(s): Mobed, Mohammad; Mohammadi, Ali
Abstract:
The problem of launching a satellite to low earth orbit has been considered. Preliminary concepts such as satellite orbits, launcher missiles and their equations of motion, and traditional methods for guidance of launchers are reviewed first. Then a new method for optimizing the launch trajectory under non-ideal conditions is introduced in which the solution of a known ideal trajectory optimization problem is used as an initial guess for the actual optimization problem. Several methods for guiding a launcher to place a satellite in Earth orbit are presented next; they have been titled as (1) launch path re-computation outside the atmosphere, (2) prediction error minimization, and (3) output controllability. The performances of the methods are evaluated through simulations and compared with one another. The comparison criterion is the ability of each method to attenuate important disturbances such as those caused by the atmospheric and the modeling errors. Error analysis is carried out for the second method which has been seen to have the best performance amongst the three.
Keywords:
Guidance ; Satellite Aerial Launch ; Launcher ; Trajectory Optimization ; Turbulence

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