A method of inertial guidance in a boost phase of flight of the device with unstable flight characteristics

Application of the method of program launching of booster aircraft in flight in direction of the pre-empted meeting point leads to the realization of large values of projectile component of miss due to the deviation of the time, and the hauling characteristics of the engine from the design characteristics. Finite value of this miss can be reduced to acceptable levels, periodically forecasting positions of the meetings in a onboard inertial guidance system (based on the identification of the realized ballistic flight characteristics of the aircraft), and adjusting the movement of the aircraft by the control system of booster.