Stabilisation and guidance device for sounding rockets and rocket-propelled ballistic vehicles

摘要

1,102,625. Controlling rocket propelled missiles. SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. 21 Oct., 1965 [22 Oct., 1964], No. 44580/65. Heading B7G. A sounding rocket is propelled by liquid propellant and oxidant forced into a rocket motor from tanks (2, 3, Fig. 1, not shown) by gas pressure, e.g. from a gas reservoir (4). During powered flight the attitude of the rocket in pitch and yaw is controlled by propellant or oxidant forced by gas pressure through inwardly directed nozzles 10, 11 in the walls of the jet pipe 9, thus deflecting the propulsive jet. Roll control is effected by supplying gas from the reservoir (4) to tangentially directed nozzles 12 outside the rocket. During unpowered flight, roll, pitch and yaw control are all effected by externally directed nozzles supplied with gas from the reservoir, and different roll control nozzles, smaller than those for powered flight are used. The changeover to these nozzles is made either by a timer set to the duration of the powered flight, or by a pressure switch responsive to combustion chamber pressure. The attitude is controlled by gyroscopes 13 and rate gyros 15 and by an attitude reference 17, the signals from which are summed and used to control valves such as 19.