METHOD FOR DETERMINATION OF SPIN RATE OF PROJECTILE AND PROJECTILE FOR ITS REALIZATION Russian patent published in 2002 - IPC

FIELD: military equipment, in particular, methods and devices for experimental development of projectiles fires from gun barrels and launching tubes (packs). SUBSTANCE: the method consists in installation in the flight trajectory at the beginning and end of the speed base of devices for registering the time moments of their passage, launching of projectile from the launching tube, and registering of the time of passage of the speed base by the projectile, easily piersable boards are installed at the beginning and end of speed base in the projectile trajectory, after the projectile leaves the launching tube and before it approaches the speed base the knife- type component is opened relative to its lateral surface, the board gets pierced, and the spin angular coordinates of the projectile at the beginning and end of the speed base are determined by reference to the rupture holes on the boards and verticals preliminarily applied onto them, and the projectile spin rate is determined by the following mathematical expression n = (ϕ₂-ϕ₁)/(τ•360), where ϕ₁, ϕ₂- projectile spin angular coordinates at the beginning and end of the speed base, that are determined according to the rupture holes of the knife-type component relative to the verticals applied onto the boards, τ - time of projectile passage of the speed base. The length of the speed base is determined from relation nL/V₀<1, where n-expected spinning rate of projectile. The projectile for realization of the method has a body with centering and swirling members, a longitudinal groove is made on the side surface of the body, installed in the groove in the axis located tangentially within the body is a knife component automatically opening behind the diameter of the projectile caliber after the projectile leaves the launching tube, it is made in the form of a flag-eccentric, the center of mass of the flag-eccentric is installed relative to the axis of its installation so that under the effect of inertial forces of the barrel acceleration overload it provides for action of the closing moment on the flag-eccentric, and the longitudinal groove is provided with stops for the flag eccentric in the closed and open positions. EFFECT: provided determination of the projectile spinning rate, thus purposeful development of the projectile swirling mechanisms. 2 cl, 5 dwg