fuel to motor 24 alternator 3 feeds into microprocessor 34 which controls valve 6a causes its opening and provides the ignition pulse of motor 24 gyroscope 19 triggered by hydraulic pressure goes into operation and through microprocessor 34 acts on the electrically controlled slide valves of hydraulic actuators 20 21 which react to pitching and possible bankings of the unit in flight when it has been released this nay cause motor 24 to be misaligned which motor with its jet corrects by reaction the flight of the unit spiraled part 33 of the motor feed line assisted by the reaction of hydraulic actuators 14 15 brings the motor and its jet back to the correct and pre established course the liquid oxygen contained in tank 12 12a after overcoming the blockage of diaphragmed valve 31 through line 32 provides for cooling of the ejector nozzle and then cooling of the combustion chamber of motor 24 the air which by aerodynamic effect penetrates into front mouth or air intake 35 by a space provided between the shell of tanks 12 and its housing provides for warming of the tank and the contained liquid oxygen by pressurizing it the flight of the unit lasts until the pre established target is reached on which a is released one of the characteristics of the unit described derives from the absence of avionic interface between the aircraft and the munition other characteristics reside in the fact that following the launching direction and altitude of flight which initially were provided by the carrier are preserved by the automatic functioning of the on board systems comprising a gyroscope variometer and swiveling motor another but not final characteristic derives from the inexpensiveness of the unit and its versatility particularly in.