SUPERSONIC PROJECTILE

FIELD: weapons and ammunition.SUBSTANCE: in a supersonic projectile the rudders are placed on the pointed nose of the hull at a distance from the front end of the projectile selected within the values calculated by the formula:. Each of them is equipped with an aerodynamic fairing made in the form of a rotation body, protruding beyond the front edge of the rudder by the value (0.10-0.25)a. The longitudinal axis of the fairing is displaced from the root chord by a distance (0.15-0.35)b. The arc-shaped blades of the stabiliser are shifted from the bottom cross section of the jet engine towards the nose of the hull by (0.3...0.6) d and are fixed on the axes parallel to the longitudinal axis of the projectile shell. The arc-shaped blades of the stabiliser are oriented by convex surfaces in the clockwise direction in a rear view, where Lis the distance from the nose to the middle of the root chord of the rudders; Lis the distance from the nose of the projectile to its mass center after fuel burnup of the jet engine; L is the length of the projectile; Lis the distance from the nose of the projectile to the middle of the root chord of the stabiliser blades;is the relative area of the projections of 2 stabiliser blades; Sis the area of the projections of 2 stabiliser blades;is the area of the midship section of the projectile; d is the calibre of the projectile; k=(8-16)[1+0.1(n-3)] is the coefficient which takes into account the number of the stabiliser blades; n=3-6 is number of stabiliser blades;is the relative area of 2 rudders; Sis the area of the projections of 2 opposite rudders; bis swing of one rudder; ais the length of the root chord of the rudder.EFFECT: invention allows to create a supersonic projectile of multiple-launch system with increased firing range due to the rational selection of the ratios of the airframe geometric parameters and to ensure maximum aerodynamic quality, increased combat effectiveness due to reduced dispersion of aeroballistic characteristics, increased accuracy of firing.1 dwg Изобретение относится к области ракетной техники, а именно к реактивным снарядам реактивных систем залпового огня. В сверхзвуковом реактивном снаряде рули размещены на заостренной носовой части корпуса на расстоянии от переднего торца снаряда, выбираемом в пределах значений, рассчитываемых по формуле:, при этом каждый из них снабжен аэродинамическим обтекателем, выполненным в виде тела вращения, выступающего за переднюю кромку руля на величину (0,10-0,25)