METHOD FOR CONTROL OF MISSILE AND MISSILE GUIDANCE SYSTEM FOR ITS REALIZATION Russian patent published in 2004 - IPC

FIELD: armament, in particular, rocketry, applicable in development of missile complexes, for example, with carriers on the ground, in which beam teleguidance systems are used.

SUBSTANCE: a correction control command is formed on board the missile in the pitch channel, taking into account the variation of the missile flight speed determined by the burning rate of fuel depending on its temperature and hence on the temperature on board the missile. In the offered method of missile control the eletromagnetic radiation from the control point is transformed to the missile heading and pitch co-ordinates, and a heading control command is formed from the heading co-ordinate, and the temperature is measured on the missile, the temperature is converted to a code, which forms the correction command, sums up this command with the value of the pitch co-ordinate, and a missile pitch control command is produced from the obtained value. Described is the missile guidance system based on this method, it has a control point equipment, and on the missile - a series-connected receiver and a co-ordinate separation unit, whose heading output is connected to the first input of the autopilot, the control point equipment is connected to the receiver input, use is also made of an adder, temperature sensor, temperature-to-code converter and a correction command driver.

EFFECT: enhanced accuracy of missile introduction to the beam.

2 cl, 3 dwg