GB690186A - Improvements in apparatus for aircraft-refuelling in flight and aircraft-towing - Google Patents

Abstract

690,186. Refuelling and towing aircraft in flight. FLIGHT REFUELLING, Ltd., and NEEDHAM, C. H. LATIMER-. Aug. 27, 1951. [Aug. 29, 1950] No. 21321/50. Class 4. Apparatus for coupling two aircraft for flight refuelling or/and towage purposes including a self-engaging plug and socket coupling of which the plug member, in the form either of a nozzle having a fuel passage or a spigot without such passage, has a circumferential groove engageable by spring loaded latches carried by the socket member is characterised by the fact that the socket member is recessed into a rearwardly or forwardly facing part of the structure of one of the aircraft to be coupled, the plug member being mounted at the extremity of a telescopic boom, with or without a fuel conveying passage, extending forwardly or rearwardly from the other such aircraft, on which it is mounted by means of a universal joint, being provided with spring centering means tending to hold the boom substantially in the line of flight. The socket S, mounted in the nose ot a following aircraft B, is provided with pivoted latches 3 which carry rollers 4 and are loaded by spring plungers 5. The plug member P, attached to the tail of a leading aircraft A, has an external circumferential groove 6 engagable by the latch rollers 4 and terminates in a tapered nozzle 7 which seats on the throat of the socket when the rollers 4 enter the groove 6. The plug member P forms the movable member of a telescopic structure comprising an outer tube 8 and a spring 9 tending to extend the plug member. The tube 8 is connected by a ball and socket joint 10 to a fixed fuel pipe 11 and is centred by means of tension springs or rubber cords 12. The socket S is similarly connected to a fixed fuel pipe 14 by a ball and socket joint 13. The socket S is extended by a conical funnel 15 flanged at 18 to overlap and slide on the aircraft skin 19 when the socket moves on its ball joint 13 and the gap between the tube 8 and the edge of the opening in the aircraft skin is sealed by a flexible membrane 17. The telescopic structure 8, P may be formed as a hydraulic or pneumatic jack and retracted when not is use and the latches 3, 4, 5 may be locked in engagement with groove 6. Specification 676,430 is referred to.