MAXIMIZING THE RANGE OF A GLIDER

Abstract

This thesis reports the methodology and result obtained from studying the optimal trajectory which will maximize the range of a simple aircraft-like gliding projectile model. Previous work done on the same glider model is reported in reference (1). Control Parametrization technique and Quasi Newton method are employed to solve this non-standard optimal control problem. The glider range problem is transformed in this study to an optimal parameter selection and optimal control problem by approximating its control by piecewise linear function, normalizing the time variable in the system of differential equations, which is then solved by Sequential Quadratic Programming algorithm. The piecewise linear control gives rise to smooth continuous control which is realizable, whereas the time-rescaling process is carried out so as to overcome the free terminal time. To ensure a proper mid-course trajectory, a continuous state inequality constraint is imposed. Other than this function, it is discovered that this constraint contributes significantly to the extended range obtained in this report.