| 摘要 |
FIELD: rocketry, applicable in spin-stabilized guided missiles and rockets of high-accuracy weapon systems. ^ SUBSTANCE: the method provides for a successive deployment in pairs of control surfaces opposite relative to the missile longitudinal axis at the instants when the missile gains a definite flight speed. Simultaneously with deployment of the first pair of control surfaces a partial deployment of the second pair of control surfaces or structural components linked with them is performed. The value of their projection over the missile body exceeds the thickness of the boundary layer of the flow for provision of a guaranteed break-away of it in the plane of lateral flow-around of the missile. The missile structure provides for folding and deployment of the control surfaces, ii particular, partial deployment of them in compliance with the claimed method. ^ EFFECT: enhanced aerodynamic stability and improved controllability of the spin-stabilized missile due to reductor of its angle-of-attack pitching oscillations caused by the asymmetric lateral flow-around of the body at missile spinning without a special stability device. ^ 2 cl, 7 dwg |
