| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系碩博士班 === 92 === The objective of this thesis is to analyze the minimum-fuel trajectory of a three-stage rocket from the earth surface to a designated orbit in order to determine the maximum payload which the rocket can carry.The nonlinear optimal control problem is solved by using an approximate parametric optimization method.As a result, the original optimal control problem is converted to a set of simultaneous nonlinear algebraic equations with a set of unknown parameters. Newton-Raphson method is then used to solve the set of simultaneous equations to determine the unknow parameters. Accordingly, the optimal control, and then the optimal trajectory and the maximum payload are determined.In this thesis, the fuel consumption rate is assumed to be constant and thrust maintain at four times of the initial weight of rocket in each stage.Based on these assumptions, the effects of the specific impulse, the thrust-to-weight ratio and burning time in each stage on the maximum payload are studied.Given a set of weight and specific impulse, in this thesis, the optimal time of burning and the thrust-to-weight ratio for each stage of rocket are obtained upon vast parametric studies.
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