| 摘要 |
A missile 1 is arranged to be guided during the final phase of the trajectory using a rocket drive of which the thrust may be selectively directed in an appropriate direction to steer the missile to the target. The missile may include a hollow charge 4 with a stand- off detonator head 8 and guidance means 12,14, or may be guided from the launch point. The rocket drive has a solid charge 20 within a chamber with combustion zone 21 communicating with three thrust nozzles 17 evenly spaced and which can be selectively opened for directional control. The rocket drive is aligned along the missile axis and faces forwardly with the thrust line of the nozzles extending forwardly to meet on the missile axis between the centre of pressure and centre of mass. Tracer compositions 23 are located immediately adjacent the nozzles 17, and each composition emits a radiation of a different visible wavelength. <IMAGE> |
