Patent GB-937959-A (GB)
Title: Improvements in explosive missiles and means for their discharge
Inventor: WALLIS BARNES NEVILLE
IPC: F42B21/00
Filed: 1942-08-11
Abstract: 937,959. Missiles for discharge from aircraft. VICKERS-AIRCRAFT HOLDINGS Ltd. July 9, 1943 [Aug. 11, 1942; July 9, 1943], Nos. 11252/42 and 11197/43. Classes 9 (1) and 9 (2). Means are provided to support an explosive missile and impart a spinning motion thereto about a horizontal axis at right-angles to the direction of attack together with release gear to free the missile from the support and means to positively propel the missile towards the target. The missile of Fig. 1, which may be launched from an aircraft, comprises a cylindrical casing 20 enclosed by wooden blocks 21 shaped to give the whole a barrel-like configuration, the blocks being covered by shellplates 24, 25 and the mean density of the missile exceeding that of water. In a modification (not shown) the inner compartment 20 is near spherical and enclosed in an annular casing subdivided into air chambers communicating with the atmosphere, sinking in water in this case being due to the entry of water into the chambers. In a further modification, the annular chamber is sealed and the mean density greater than that of water. When intended for attacking land targets, the outer casing is preferably cylindrical. The compartment 20 contains the explosive charge arranged around an axial tube 31, which houses a hydrostatically-operated detonator and a self-destruction fuze. At each end of tube 31 is an annular member 32 whose inner surface 321 serves as a track for the wheel Launching.-Pivotally mounted beneath the sub-chassis 33, Figs. 5, 6, of an aircraft are two brackets 34, 35 which can be swung to the 64 which provide bearings for a spindle 65 and release position shown in chain-dotted lines in Fig. 6 by telescopic struts 37 connected by linkage 39 to a shackle 40, which may be engaged with a bomb-slip 41 as in Specification 572,794. A hand-wheel 42 on a screw-threaded draw-bar 43 is used to swing the brackets to the closed position and a safety clip 46, Fig. 5, prevents rotation of the wheel 42 due to vibration of the aircraft. Each bracket 34, 35 carries a support 47 for a wheel 49, one or both wheels being rotatable by a motor 50 driving a belt 51. When a missile is held between the brackets 34, 35, the wheels 49 bear against the tracks 321 and support the missile. Shortly before attacking a target, motor 50 is started and rotates the missile at the required speed, which depends on height of aircraft and desired trajectory. At the instant of attack, the bomb-slip 41 is electrically energized, whereupon the brackets are forced to the retracted position and the spinning missile is released. Fuzing.-The self-destruction fuze is tripped by means of a pin 60, Fig. 8, slidably mounted in a plug 61 screwed into the tube 31. A frame mounted on the bracket 35 comprises plates 62, of the supporting and spinning apparatus. a pivot for a lever 66. Spindle 65 carries at its inner end a hooked arm 651 and at its outer end a pawl-quadrant 652 engaged by the lever 66, Fig. 9, which is connected by a cable 661 to the cock-pit. Operation of the lever 66 by the cable 661 releases the quadrant 652, which then rotates the spindle 65 and brings the arm 651 into engagement with the pin 60, so that when the missile is released, the pin 60 is withdrawn and the self-destruction fuze is ready to operate. Specifications 7198/1912 and 10889/1915 also are referred to.