GB563226A - Improvements in and relating to mountings for aircraft engines - Google Patents

Abstract

563,226. Mounting aircraft engines. MARTIN, J., and MARTIN-BAKER AIRCRAFT CO., Ltd. Feb. 6, 1943, No. 2017. [Class 4] Mounting for aircraft engines, particularly such of H-, X- or V-form that present a small frontal aspect, comprises cantilever side frames,rear and front cross-members or beams supported at their ends by resilient connections to the side frames and means intermediate the ends of the cross-members for securing the engine thereto. The side frames are braced by a vertical transverse quadrilateral assembly of struts in the vertical plane containing the rear beam. Each side frame comprises tubular members 5, 28, 10, 21, 43, 44 secured by lugs 43c, 21a to the aircraft structure. A front cross-bearer 2 is secured to stubs 3 extending from sleeves 4 on the members 5, with the interposition of rubber bushes 37. The front feet of the engine are fastened by bolts 41 to pads 40 disposed near the ends of the bearer 2 and between the side frames, a spigot 42 being provided' on the starboard pad to. register with the corresponding foot of the engine. The rear and main crossbeam comprises a tube 1 into which are fitted tubes 1b the ends of which are received in the inner bushes 45 of rubber collars 46 that are compressed between the bushes 45 and sleeves 47 and disposed in housings 9 forming the heads of the struts 10. The members 45, 47 are secured and play of the beam in the housings 9 is limited by collars 52 co-operating with caps 48 on the housings 9 and by ledges 49 on the housings. The pads 53 for the rear engine feet are disposed at a substantial distance from the 'housings 9 and have a universal connection with the beam 1 provided by spherical bearing surfaces 57, to allow for bending of the beam. The bearing for one of the pads also has limited freedom of movement laterally between stop collars 58 to take care of variations of distance between the feet due, for instance, to temperature changes. Cross-members 11, 12 bolted by means of collars 15, 19, to the struts 10 and diagonal members 13 form with the struts a quadrilateral frame beneath the beam 1 that enables the structure to take the side loads when, for example, the aircraft turns on to one side. Extending rearwardly from the member 12 to each member 21 is a Y-arrangement of tie members 23, 24, 25. A similar arrangement of the tie-members 30, 31, 32, extends forwardly from member 12 to member 28. The arms 5 are braced at the front end by a cross-member 35 which is braced by diagonals 36 extending to the members 28. Lugs 59, 60 are provided for the attachment of means for jacking-up the engine and mounting. With the rubber damping devices spaced laterally from the engine feet, a precise degree of hardness is rendered unnecessary and the selection of the kind of rubber suitable to meet the several requirements of the mounting is facilitated.