Patent GB-803030-A (GB)
Title: Aircraft launching system
Inventor: DOOLITTLE DONALD B
IPC: B64F1/06
Filed: 1956-05-07
Abstract: 803,030. Launching aircraft. ALL AMERICAN ENGINEERING CO. May 7, 1956, No. 14061/56. Class 4. [Also in Group XXX] An aircraft launching system comprises a dual shuttle track, a gas turbine driving a pulley, an endless cable reeved around the pulley and an idler pulley so that the reaches of the cable between the pulleys extend longitudinally adjacent the track, and a shuttle detachably connectable to each reach of the cable and to an aircraft, so that the shuttles are slideable along the track in opposite directions when connected to the cable. The shuttle of Fig. 3 comprises a cradle 46 for the aircraft nose wheel NW and a brace 47 held against the wheel leg 50 by a tie 51. Fig. 4 shows a transverse section through a sunken trackway comprising frames 38, 39 supporting guide rails 34, 35, 36, 37 having flanges 40, 42, 43, 44. The shuttle body below the rails comprises a bearing block 54 journalling the axle 54b of track wheels 54c. The base of each block 54 supports a cable grip (see Group XXX) for securing the block to the cable 11. Near the end of each track, the frames 38, 39 have a reduced spacing, which releases the cable grip. In operation, the aircraft and shuttle stand in the launching position, with the cable gripped. The gas turbine is run up to full power with the turbine shaft braked. The brake is released, and the shuttle and aircraft accelerate along the track, until the narrowed end portion thereof is reached, whereupon the cable is released. The turbine brake is re-applied manually or automatically to stop the cable. The brake may also be applied if excessive cable speed is reached. Two gas turbine engines may be coupled to the cable to drive it in opposite directions. Two aircraft may be launched simultaneously in opposite directions from the two tracks. In an alternative embodiment, where a plurality of aircraft are to be launched successively from one track, the latter comprises a rail T, Fig. 8, having flanges 81, 82 for guidance of the shuttle, of which one is provided for each aircraft. An equal number of clamps R, Fig. 15, are lined up behind the starting point. Fig. 8 shows a transverse section of the track and two clamps, each comprising two parts 95,97 connected by a neck 96 co-operating with flanges on the track T. Each clamp has a bore 101 through which the cable 11a passes, and bores 102, 103 containing valve mechanism, an actuating rod 105 of which protrudes forwardly from the clamp, Fig. 15, so that when rod 105 is pushed inwardly, the clamp is secured to the cable (see Group XXX). Fig. 15 is a plan view, and in operation, the next aircraft to be launched is taxied from a branch track (not shown) on to a part of the launching track which is elevated above the line of clamps R. It is then moved forward onto the main part of the track level with the clamps R, so that the shuttle S abuts a stop 130. The foremost clamp is fed forward by a feeder piston and cylinder device 124, 125 until the actuating rod 105 is pressed in by contact with the rear of the shuttle s, whereupon the clamp grips the cable. The gas turbine is brought to full power, and the turbine brake is then released, as is stop 130. The clamp then propels the shuttle. The next aircraft is brought into position and the next clamp fed forward. As the shuttle nears the end of the track, the clamp is braked by a linear friction brake on the track. The shuttle continues unbraked, whereupon rod 105 moves outwardly releasing the clamp from the cable. The clamp and shuttle are then braked separately.