Patent GB-708462-A (GB)
Title: Improvements in destruction engines containing a liquid explosive charge
IPC: F42B12/20
Filed: 1951-11-12
Abstract: 708,462. Explosive devices. ZBOROWSKI, H. P. G. A. R. VON. Nov. 12, 1951 [Nov. 10, 1950], No. 26397/51. Class 9(1) An explosive device is provided containing a liquid charge confined in a tank the forward wall of which is so shaped that the body of liquid has the form of a hollow charge, means being provided to keep the liquid in contact with the forward wall irrespective of volume variations such as may result from changes in temperature. The self-propelled missile shown in Fig. 1 has a streamlined body 1 and is provided with a tail unit containing in addition to a liquid explosive charge e, the propelling device and means for controlling the missile. The charge e is a solution in concentrated nitric acid of a liquid fuel of the alcohol group, such as methanol or ethanol or a mixture of these alcohols. The proportions of nitric acid and liquid fuel may be in the stoichiometric ratio of the two substances or there may be an excess of nitric acid of 2 per cent to 20 per cent, preferably 7 per cent, above the stoichiometric proportion. The two components are transported separately and introduced into the missile immediately before launching. Within the missile the charge is held in a tank 2, of metal or other suitable material, having a re-entrant front wall giving the charge the appearance of the socalled hollow charges. The cavity so formed may be parabolic or trapezoidal in section. The charge is initiated by means of a striker 4 acting on a detonator 7 when a nose fuze 5 hits a target. The ignition circuit may include a'relay 6, as in Fig. 4. To compensate for variations in volume of the tank brought about by changes in temperature a chamber 2b may be provided communicating with the tank. On filling, the tank, displaced air enters the chamber forming an air cushion. The chamber 2b may be replaced by a gas-filled flexible body placed in the tank. Alternatively part of the tank wall may be flexible and formed with corrugations 2c, Fig. 4. The tank 2 may be toroidal in shape, an annular groove being formed in the forward end and a plurality of detonator elements 7 placed in the tank. The tank is filled when the missile is placed in the launcher, by apparatus having at least one filling nozzle 9 aligned with a check valve 3a in the tank. Nitric acid and alcohol are fed to the nozzle 9 from tanks 10, 11 by means of pumps 12, 13 driven by a motor 14 controlled through a relay box 15 by a contact 16. As the liquid enters, air check valves 3a, 17 by means of a spring-pressed is driven out of the tank through a discharge orifice normally closed by a check valve 17 and opened by a movable discharge nozzle 18. The nozzles 9, 18 are controlled by means 19, 20 operated by relay 15, so that closing contact 16 simultaneously starts the pumps and applies the nozzles 9, 18 to the wall of the tank to open the ball 21 within each nozzle. When the tank is full, any excess liquid escapes through nozzle 18 and enters an electrolytic contactor 22 connected to relay box 15 to stop the drive to the pumps. At the same time, one of the nozzles 9, 18 co-operates with a contact 23, so that when the nozzle returns to its position of rest a circuit 24 is closed, thereby launching the missile. A second contact 25 in this circuit is closed after a predetermined delay when contact 16 is closed.