Device for guiding a missile

DETAILED DESCRIPTION The above object is achieved according to the present invention by a device for guiding a missile having a missile tip and a cylindrical section adjoining the tip of the missile, with the device being provided with at least one control block with exhaust openings of corresponding nozzle bodies arranged perpendicularly in relation to the missile's surface; and wherein the control block contains a plurality of small, fast-burning rocket motors which are arranged radially on the missile's periphery and which are ignitable in a predeterminable sequence and number.
Additional advantageous embodiments and features of the invention likewise are disclosed.
Substantially, the invention is based on the idea that instead of using a control block with a central propellant source and rotating nozzles, the control block is provided with a plurality of small, fast-burning rocket motors (e.
g.
, microreaction engines) arranged radially on the periphery of the missile.
The selection and number of rocket motors necessary for the required lateral thrust are ignited by an ignition device which does not have to be part of the control block.
In a non-rotating missile, the rocket motors are arranged in a rotating control block.
In a particularly advantageous modification of a non-rotating missile, two control blocks rotating counter to one another are seated on the hub formed by the missile.
The fact that the control blocks are rotating counter to one another leads, on the one hand, to a fast provision of all existing rocket motors for the generation of a suitable lateral thrust and thus for guiding the missile.
On the other hand, a gyroscopic effect--when applying a lateral momentum and canting the tip of the missile accordingly--is avoided through the angular momentum compensation.
Additional details and advantages of the invention may be gleaned from the following exemplary embodiments explained on the basis of Figures.
The Figures show: