GB525266A - Improvements in or relating to fluid-pressure apparatus for controlling the operation of brakes for aircraft - Google Patents

Abstract

525,266. Brakes for aircraft. DUNLOP RUBBER CO., Ltd., BEHARRELL, G. E., WRIGHT, J., and TREVASKIS, H. Jan. 19, 1939, No. 1874. Addition to 507,162. [Class 4] [Also in Group XXXIV] The fluid-pressure brake operating mechanism described in the parent Specification is modified particularly for the use of compressed air as the operating fluid. The modifications concern in particular the exhaust valve 21, sealing means for the spring-loaded sleeve 24 which is provided with the exhaust port and sealing means for the rod 20, by which the floating-lever is operated. The pair of valves for the brakes on the side of the aircraft is shown. Upward movement of the rod 20 first causes the floating- lever 15 to fulcrum on the rod 14 of the supply valve 5 to slide the plug 21 in the sleeve 24 so as to seat the exhaust valve member 22 on the exhaust port 23 provided on the sleeve and subsequently to lift the valve 5, thus supplying the brake by way of chambers 8, 10, and passage 12. If the rod 20 is held, the brake pressure in chamber 10 acting on the plug 21 and sleeve 24 depresses these against the resistance of the spring 25 and so permits the valve 5 to close, the brake pressure being thus dependent upon the extent of movement of the rod 20. Return movement of the rod 20 unseats the valve 22 as shown and the compressed air from the brake exhausts through the passage 12 channels 32 in the plug 21 and the port 23. The supply valve rod 14 bears on a member 16 pivoted to the lever 15 and slidable in the casing. A screwed plug 17 serves to adjust this member and the valve 5. Leakage from the chamber 10 past the sleeve 24 is prevented by a rubber sleeve 30 attached at its lower part to the casing by a bush 31 and an extension of the screwed cap 26. To prevent leakage from chamber 10 past the rod 20, while permitting tilting of the rod, a spring 37 is secured at its ends respectively to the upper part of the rod and to a disc 38 and a rubber sleeve 39 is fitted over the spring and a flange on the sleeve is clamped between a cap 41 and a sleeve 40. A baffle in the passage between the main pressure supply pipe and the supply valve chamber 8 prevents pressure building up too rapidly in chamber 10. Mechanism for effecting differential control of the brakes on opposite sides of the aircraft is described and is substantially the same as that described in the parent Specification.