| 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 an aircraft in the atmospheric flight by using a parametric optimization method. In this thesis, the aircraft is assumed to be a particle and the thrust and the load factor the controls which are assumed to be piecewisely continuous polynomial functions of time. The minimum-fuel problem and the maximum-range problem are mutual complementary.By using the range of flight as the performance index, the necessary conditions for optimality are derived. They and the terminal constraints form a set of nonlinear simultaneous algebraic equations which are used for solving the optimal parameters.In order to validate the theory, a numerical example is investigated. Due to the complication of nonlinear algebraic equations of which the number is too large, only several simplified cases are successfully solved. Although the optimal trajectories for minimum-fuel flight are still not understood globally, the results obtained in this study have already established a cornerstone for further investigation of the problem along this line.
|
|---|
