FIELD: astronautics.
SUBSTANCE: invention relates to aerospace engineering. Aerodynamic control system of a hypersonic aircraft contains differentially deflected aerodynamic flaps installed on the body of the aircraft, located diametrically in mutually perpendicular planes, as well as steering gears, hinged by rods with aerodynamic flaps, which have a heat-shielding coating. All aerodynamic shields are located in the stern of the aircraft and are hingedly fixed to the cut of its body. Shields in the folded state are located on the bottom of the body. Stems of the steering gears of the flaps are made sliding and equipped with a device for their single driving into the working position. Thermal protective coating of aerodynamic flaps is made of carbon-carbon composite material with a skeleton and a binder reinforced with carbon nanotubes.
EFFECT: invention is aimed at increasing the control aerodynamic moment in the channels of pitch and yaw.
1 cl, 2 dwg
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