FAIRING OF ROCKET LAUNCHER Russian patent published in 2008 - IPC B64C21/08 B64G1/22 

FIELD: aviation.

SUBSTANCE: invention concerns devices for improvement of aerodynamic properties of aircrafts, mostly rocket launchers (RL). The fairing comprises nose cone (1), cylindrical compartment (2), rear extension (3) of the last stage (4) of RL. The fairing features permeable porous rim (5) and insert (6) that damp pressure fluctuation (in the flow separation zones). Biconical nose cone (1) is preferred, and semi-vertex angle of the first cone (7) is 25°- 35°, while semi-vertex angle of the second cone (8) is 13°- 25°. Length of the first cone is 0.2 - 0.25 of the total nose cone (1) length. The rim (5) and insert (6) are both as long as 0.11 of the cylindrical compartment (2) length. Total length of this compartment exceeds its diametre at least by 1.11 times. The extension (3) can have partition ribs made of permeable or pressure pulsation-damping material.

EFFECT: lower aerodynamic load at RL head.

10 cl, 2 dwg