FIELD: aviation.
SUBSTANCE: invention relates to aircraft control systems. Gas-dynamic control system for hypersonic aircraft consists of a working part and a command system. Working part is arranged in the nose fairing of the aircraft fuselage and consists of main and additional vertical and lateral turn engines arranged on four sides of the fairing and shutters, which close holes in the fairing near each turn engine. Command system is a set of electro-switches reacting on the steering wheel position and wires connecting the electro-switches with the working part. Main and additional turn engines of each direction are started in series. Each turn engine is started after complete opening of the corresponding shutter.
EFFECT: invention is aimed at higher maneuverability at hypersonic speeds.
7 cl, 6 dwg
