| 摘要 |
FIELD: aviation.SUBSTANCE: present invention relates to structures of aircraft elements subjected to hot gas streams. Fairing (10) of the aircraft horizontal stabilizer tip (3) comprises a front part (11) and a rear part (12). Front part (11) covers a limited extent of the surface of the fairing (10) surface, which is the part of the fairing (10), receiving hot air stream (6) coming from the engines (4) of an aircraft. Front part (11) is made from an anti-erosion material. Rear part (12) covers the rest of the surface of the fairing (10). Rear part (12) is made of a material resistant to the aerodynamic loads existing on the fairing (10).EFFECT: improved protection against erosion while the weight of the stabiliser tip is reduced.15 cl, 4 dwg |
