FIELD: aircraft.
SUBSTANCE: invention relates to aircraft with thermal ablation protection. Tip of the hypersonic aircraft is made of a carbon-carbon composite. Fiber diameter (d) forming the structural unit of the carbon-carbon composite in the central part of the tip, has a lower value with regard to the fiber diameter (D) forming the structural unit of the carbon-carbon composite in the main part of the tip. Properties of the composite are selected depending on the diameter of the structural unit, the diameter of the fibers, speed of material carryover (mass rate of material loss) and braking pressure. Ratio of the radius of the central part to the radius of the spherical blunting of the tip correlates from 0.04 to 0.06.
EFFECT: invention is aimed at increasing the stability of the aerodynamic characteristics of the hypersonic aircraft.
4 cl, 5 dwg
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