Choice of Rocket Engine Parameters at the Optimization of Flight Trajectories

Abstract

The choice of parameters for designing the rocket engine providing the maximum range of missile flight is considered. The choice problem is stated as a problem of conditional optimization, in which the criterion function is inversely proportional to the range of missile flight. The problem solution is carried out by the Newton's method, the method of a deformable polyhedron and by the genetic algorithm. It is shown that the solved problem contains some local minima, which are easily established, by the Newton's method and the method of a deformable polyhedron. The global minimum established by genetic algorithm, corresponds to missile flight along an unstable trajectory. In this case, the maximum range of missile flight can be provided by application of regulating devices.