Patent GB-714892-A (GB)
Title: Improvements in airborne bodies and in particular in self-propelled missiles
IPC: F42B15/00
Filed: 1952-07-29
Abstract: 714,892. Self-propelled and anti-tank missiles. ZBOROWSKI, H. P. G. A. R. VON. July 29, 1952 [Aug. 2, 1951], No. 19113/52. Classes 9(1) and 9(2) An anti-tank missile having a warhead enclosing a hollow charge 1, an armour-piercing nose 2, ignition means 3 such as a delayed action detonator at the base of the charge, a main propelling system 4 and a primary propelling system 5, is provided with means for maintaining an aerodynamic lift such that at least a part of the projectile's trajectory is rectilinear. Means are also provided for controlling the ratio of the weight of the projectile to the aerodynamic lift. The primary propelling system 5 which is used to launch the projectile contains two groups of propellant charges 5a, 5b, the tubular charges 5b being more widely spaced and fewer in number than those in the front group 5a. After ignition, preferably electrical, of the charges 5a, 5b, when the pressure of the combustion gases reaches a predetermined value, a diaphragm 7 is ruptured and the gases escape through a nozzle 8. The casing surrounding the charges 5a, 5b is slightly convergent forwardly to provide room for an annular discharge nozzle 6 for the main propellant charge 4. To control the incidence of the projectile on its trajectory, a rotatable ring 9, preferably mounted on ball bearings 10, Figs. 1 and 3, is placed between the charge 1 and the main propellant 4. The ring carries a counterweight 11 and a spoiler 12 projecting through the lower part of the casing to interrupt the air flow. A stabilizing 'tail 13 extends beyond the nozzle 8 and adjustable deflectors 14 placed round the nozzle may be moved into the path of the combustion gases to deflect the jet and hence modify the thrust. Each deflector 14 is mounted at one end of a lever pivoted on an angle 16, the other end of the lever engaging a projection 17a on a flexible ring 17 so that diametrically opposed levers are coupled together, Fig. 4. When four deflectors are provided there are two rings 17, one beyond the other, so that adjacent levers are not connected to each other. Air entering through apertures 19 presses against the flexible inner walls of chambers 18 which in turn bear against the forward ends of the levers 15 and so adjust the deflectors 14. The rear edge of each aperture may be sharply bevelled and may have a raised edge projecting from the casing to increase the air inflow. The apertures 19 may be replaced by small perforations, contact of the walls of the chambers 18 with the levers being located between the fulcrums and the deflectors 14. Since the counterweight 11 tends to displace the centre of gravity of the projectile from the axis of symmetry, the levers are loaded to deflect the thrust through the centre of gravity. This is done by the weight of the rings 17 or by a special counterweight. To reduce the transverse component of the pressure on the deflectors 14, the deflectors may be inclined towards the axis of the projectile or alternatively they may be curved. The projectile may be of light metal or an alloy and may be fitted with a target-seeking head for correcting its trajectory at the end of its travel. This head may be housed in an axial recess in the forward end and may operate supplementary control members.