GB1380531A - Fire ranging method for launchers of self-propelled missiles - Google Patents

Abstract

1380531 A fire ranging method CONSTRUCTIONS NAVALES ET INDUSTRIELLES DE LA MEDITERRANEE 28 March 1973 [19 April 1972] 14994/73 Heading F3C In a fire-ranging method for launchers of selfpropelled missiles the angular deviation between the theoretical trajectory of the missile and the point where combustion of the acceleration propulsive charge ceases is measured, and the launcher is subjected to angular movement in the opposite direction and with an amplitude proportional to that of the measured deviation, the proportion factor being constant for the type of missle in question and determined experimentally. The angular deviation is measured by logging on a grid the position of the missile at the end of the combustion phase or by following the missile with a reticle. A television camera and receiver assembly may serve as a sight. In a trajectory deviation of a self propelled missile as shown in Fig. 1, the straight line AX represents the trajectory without wind effect and the curve AY represents the trajectory when the missile is subjected to a side wind V. The speed of the missile at A is very low and deviation caused by the wind is at a maximum. The deviation then decreases to maintain a stable value from the instant at which the combustion of the propulsive acceleration charge is completed. The trajectory of the missile is now purely ballistic. An angle c to obtain the desired correction of the trajectory is acquired from the formula c=a/k where a is the angle defined by the straight lines AB and AX and K is the proportion factor.