| 摘要 |
PCT No. PCT/SE94/00233 Sec. 371 Date Sep. 26, 1995 Sec. 102(e) Date Sep. 26, 1995 PCT Filed Mar. 17, 1994 PCT Pub. No. WO94/23266 PCT Pub. Date Oct. 13, 1994An 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.
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