Patent GB-641934-A (GB)
Title: Improvements in radio controlled rockets
IPC: F41G7/30
Filed: 1947-10-07
Abstract: 641,934. Automatic control system for steering rockets. HAMMOND, J. H. Oct. 7, 1947, No. 26895. Convention date, March 22, 1944. [Class 38 (iv)] [Also in Groups XXI and XXXVIII] A jet-propelled radio controlled rocket has two crossed sets of rudders, for steering in four directions which are operated by mechanism comprising a follow-up switch and relay devices, in response to relative movements between the rocket and a pair of spatially stable members freely mounted about axes respectively parallel to those of the sets of rudders. The steering mechanism is also operable in response to radio signals from a ground transmitter, to which a receiver carried by the rocket is sensitive, and a further radio signal may explode the warhead or release a parachute. In Figs. 1, 2, the rocket to be fired from a tube 2 is divided into explosive, control, and propellant compartments 13, 14, 15, and its tail is fitted with a discharge tube 18, fins 20, two perpendicular sets of interconnected rudders 91; 92 and two sets of perpendicular directional radio antennµ 71, 72, 73, 74 (Fig. 8), aligned with the rudders. In the control compartment, two gyroscopes 22, 222, are mounted in gimbals rotatable about perpendicular shafts 29, 229, respectively parallel to the rudder axes. Shaft 29 rotates a contact arm 32 in control box 30, Fig. 4, over two semi-circular conducting insulated segments 33, 34 engaged by brushes 115, 116 and carried by a toothed disc 35 which is rotated by stepping ratchets operated by solenoids 41, 41a, and positioned by a spring detent 40 engaging the teeth. Shaft 229 rotates the contact arm of a similar device in control box 230. When the rocket is in its tube the gyroscopes are locked in their neutral positions by spring-loaded arms 51, 251, retained by members 53, 253 pressing on the inside of the firing tube. The gyrorotors are run up to speed by connecting their motors to generator 67 through contacts. 65, 265, in the rocket surface engaging complementary contacts in the firing tube. The propellant powder is fired electrically through contacts 124 and the rocket leaves the tube. The gyro locking arms are released, and the gyros take up stable spatial positions. On deviation of the rocket from a straight course, the appropriate gyro shaft 29 or 229 rotates relatively to the body, and deflects arm 32 in the appropriate control unit over segments 33 or 34 to energize one of the solenoids 107, 108, and/or one of the solenoids 109, 110, in accordance with the sense and direction of the deviations. The energized solenoids operate spring- loaded piston valves 105, 106 controlling compressed air flow from a tank 102, fed through a tube from a funnel in the rocket nose, to cylinders containing spring-loaded pistons 97, 297 operating the rudders through links 95, 295 to correct for deviations from a straight course. The directional antennµ at the rocket tail receive signals from a ground transmitter (Fig. 9, not shown), which may be selectively frequency modulated by one of 5 control frequencies and apply them to a receiver 24, Fig. 6, frequency selective filters 85 to 89, and amplifiers 85a to 89a which in turn energize respectively the ratchet operating solenoids 41, 41a, 241, 241a of the gyro control boxes 30, 230, and the warhead relay 90. By radiating a pulse of the selected steering frequency, the  appropriate solenoid may be energized to step the associated toothed disc in control box 30 or 230 in the required direction to rotate the contact segments relatively to the contact arm, to energize the solenoid operating the pneumatic steering mechanism to alter the rockets course in the selected one of four perpendicular directions, until the gyroscopes return the contact arm to its normal position between the contact segments. Radiation of a pulse of the 5th frequency operates relay 90 and detonates the warhead, which in a modification may be replaced by a parachute released by the relay operation. Specification 227,489, [Class 38 (iv)], is referred to.