The method of Singular Perturbation analysis is applied to the determination of range-fuel-time optimal aircraft trajectories. The problem is shown to break down into three sub-problems which are studied separately. In particular, the inner layer containing the altitude path-angle dynamics is analyzed in detail. The outer solutions are discussed in an earlier work. As a step in solving the ensuing nonlinear two point boundary-value problem, linearization of the equations is suggested. Conditions for the stability of the equations are discussed. Also, the question of parameter selection to fit the solution to the split boundary conditions is resolved. A sufficient condition permitting this is derived. Generation of feedback laws for the angle-of-attack from linear analysis is discussed. Finally, the techniques discussed are applied to the numerical example of an air-breathing supersonic missile. The linearized feedback solution is compared to the exact solution obtained using a multiple- shooting algorithm.
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