| 摘要 |
The method is intended for controlling the flight path of a projectile (I) launched from a tube (7) at a low initial velocity, e.g. 20 m.sec. and using a propulsion system in the form of a combustible charge (1a,b,2). The propulsion system is arranged such that it provides an axially directed propelling force and, at the same time, lateral components (via nozzles 3a,b) as flight path controlling forces. - The axial position of the centre of gravity (G) as a function of the burning up on the propulsion charge varies such that, on leaving the tube, the centre (G) lies on the lines of action of the path controlling forces. In flight, the displacement of that centre causes aerodynamic reaction moments to superimpose path controlling forces on the propulsive action.
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