초록 ▼

An apparatus and method for separating a warhead to be delivered to a target from a carrier missile flying at high speed in a first aerodynamic trajectory include a rocket motor attached to the warhead in the carrier missile and an ejection tube positioned obliquely in the carrier missile rearwardly

An apparatus and method for separating a warhead to be delivered to a target from a carrier missile flying at high speed in a first aerodynamic trajectory include a rocket motor attached to the warhead in the carrier missile and an ejection tube positioned obliquely in the carrier missile rearwardly and upwardly with respect to a longitudinal axis of the carrier missile from which the warhead is ejected by the rocket motor into a second aerodynamic trajectory having a substantially higher maximum flight altitude then the first trajectory. The warhead is separated from the rocket motor after ejection by aerodynamic forces created from the angle of the ejection of the warhead from the carrier missile and the relative flight velocities of the warhead and the carrier missile. The aerodynamic forces act on a connection between the rocket motor and the warhead, whereby the motor and warhead upon the burnout of the motor follow separate forward trajectories upon separation.

대표청구항 ▼

A method of separating a warhead to be delivered to a target from a carrier missile carrying warheads therein and flying at high speed in a first aerodynamic trajectory, said method comprising the steps of: ejecting said warhead from said carrier missile rearwardly and upwardly at an oblique angle t

A method of separating a warhead to be delivered to a target from a carrier missile carrying warheads therein and flying at high speed in a first aerodynamic trajectory, said method comprising the steps of: ejecting said warhead from said carrier missile rearwardly and upwardly at an oblique angle to said first aerodynamic trajectory to a desired second aerodynamic trajectory by means of a rocket motor connected therewith, the ejection velocity of said rocket motor and said warhead being adjusted in relation to the flight speed of the carrier missile to achieve said desired second trajectory, said second aerodynamic trajectory having a substantially higher maximum flight altitude above ground level than that of said first trajectory; and separating said rocket motor,.after it has burned out, from said warhead by aerodynamic forces acting on said motor and said warhead whereby said motor and said warhead each follow their own forward trajectories, said aerodynamic forces being created from the angle of ejection of said warhead from the carrier missile and the relative flight velocities of said warhead and the carrier missile.