| 摘要 |
FIELD: weapons. ^ SUBSTANCE: invention concerns area of rocket technics, namely to rocket missiles of systems of a volley fire. In a rocket missile of an axis of blades are parallel to a longitudinal axis of a shell, and longitudinal axes snuffled are inclined to a longitudinal axis of a shell in a skew opposite direction forward edges of blades within the values defined under the formula: gamma=(0.05...0.15) betad (H+dst)/dnbo. Where - betaa skew angle of edges of blades in a plane, perpendicular to edges, d - shell calibre, dn - diameter of the circle which are passing through the centres of target sections of a jet engine nozzles, H - scope of blades of the stabiliser, dst - diameter of the case of a shell in an installation site of blades of the stabiliser, bo - an onboard chord of the blade. ^ EFFECT: increase of flying range, reliability of operation improvement of the characteristic of a compactness of a shell. ^ 2 dwg |
