METHOD FOR CONTROLLING THE STEERING OF A FLYING MACHINE IN HIGH ORDER SUPERSONIC FLIGHT AND FLYING MACHINES OF THIS TYPE

摘要

Fuel is injected into the turbulent boundary layer encasing the front region of a missile which is moving at a high Mach number. This fuel is mixed with the external air and burnt in this boundary layer. Local detachment regions, which are associated with pressure increases at the relevant points, can be produced in a controlled manner, as a result of the increased temperature and hence the reduced Mach number of the combustion gases, by suitable shaping of the missiles or by means of special attachments. In consequence, a lateral force is in each case produced which is suitable for influencing the missile longitudinal axis and hence the direction of flight of the missile. Since only small fuel quantities are required to bring about adequate orientation correction of the missile, only relatively small control valves, which respond quicker than larger valves, are required to control the fuel supply. The missile according to the invention has one or more outlet nozzles which are distributed over its circumference and each have an associated control valve.