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A Selection of the More Important Aircraft and Engin e Specifications Published Recently 371,442 . Slotted wings. Page, F. H., and ar c keyed. A third pulley 3 is loose on the shaft Page , Ltd., H., 40, Claremont Road, Cricklewood, bu t has a projection engaging abutments on the London . Jan. 23, 1931, No. 2290. [Class 4.] wheel 2. The pillar 37 is mounted on a transverse tub e 17 carrying a lever 16 t o which the elevator I n aircraft wings of th e type having automatic cables are connected, and cables from the pulleys slat s connected to pivoted flaps in such a manner 1, 2, 3 ar c led around the pulleys shown and through tha t each flap is angularly adjusted to a high th e tube 17 to the rudder, ailerons, and wheel incidence position when its slat moves away from brake s respectively. A fixed casing 39 encloses the th e wing and is returned to a small incidence pillar 37. An eccentric 40 with actuating lever 41 position when its slat moves towards the wing, is mounted on a support 42 on the pillar to lock the th e connecting mechanism is so constructed as pulley 1 in any adjusted position. t o prevent the flap when in its high incidence position from moving the slat to close the slot. 372,585 . Aircraft control gear. Bernardi, I n one form (Fig. 2) a slat b is connected to a flap c M. de, 42, Via Della Mercede, Rome. June 9, 1931, throug h toggle levers d1, d2 which are pivotally No. 16817. Addition to 371,526. [Class 4.] connected at d5, and of which the lever d1 is pivoted G of a metal having high heat-resisting and low a t d3. The arrangement is such that as the slat Apparatu s for simultaneously adjusting the conductin g properties, the plug being loosely fitted advance s and pulls down the flap c the toggle rudde r and ailerons of an aeroplane as described in int o the mouth of a water-cooled pocket so as to part s d1, d2 cross over dead points preventing the th e parent Specification has means for adjusting leav e an insulating air gap F 1 ; a securing ring G2 flap from overpowering th e slat. In a modification th e rudder control relatively to the aileron control of non-ferrous material may engage a flange G3 on th e connecting members comprise an eccentric a s desired and relocking it to the aileron control. th e plug or alternatively the ring may be omitted, rotate d by movement of the slat and operating Elasti c restraint to restore the hand-wheel to any th e plug being retained by virtue of its offset th e flap through an eccentric strap. In the full- adjustabl e mean position also is provided. The position in the cylinder head relative to the bore. open position of the slat the eccentric is past the A fuel injector H is so located as to cause a jet of fuel to impinge on the plug G adjacent the inner end of the passage G4, without entering th e passage, th e axis of the jet passing through or near the centr e of volume of th e chamber F . According t o a modified construction the passage G4 may be pro vided by a groove formed on the outer face of the plug, the direction of rotation of the charge then being opposite to tha t of th e first-described arrange ment . The seating of the fuel injector is water- cooled. An electric hot-wire igniter J is used temporaril y at starting. 371,526 . Aircraft control gear. Bernardi, M. de, 42, Via Delia Mercede, Rome. Feb. 23, 1931, No. 5682. [Class 4.] Th e elevator, ailerons, rudder, and wheel brakes rudde r control pulley 1 an d its sprocket 5 1 is loosely dead-centr e point and the flap is ineffective to of an aeroplane are controlled by a single device mounte d on it s shaft 4 an d is connecte d by a chain 7 1 mov e the slat. In a further modification (Fig 5. comprising a hand-wheel 11 mounte d on a pillar 37, t o a sprocket 81 loose on th e hand-wheel shaft 10. 5, 7, and 9), pawl-and-ratchet mechanism is em 3S capable of fore-and-aft rocking movements. The sprocket 81 has a lever 82 provided with a ployed to lock the flap in its adjusted position Rotatio n of the hand-wheel 11 moves the rudder. clam p 84 for locking it to the hand-wheel 11 after unti l moved therefrom by the slat. Coaxially ailerons, and brakes, simultaneously, and rocking th e rudder has been adjusted to connect for any mounte d levers f3, g3 are connected to slat and movement s of the pillar control the elevator. A asymmetr y of thrust or resistance on the aircraft. flap respectively and are interconnected through second control wheel ma y be provided mounted on A hand-grip 8 3 is provided on the lever 82 an d has stop s g4, g5, permittin g a certain amount of lost anothe r arm set on the pillar symmetrically to the a n indicator moving over a scale marked on the motion. Lever g3 carries a spring-pressed pawl h2 par t 3S. The shaft of th e wheel 11 ha s a sprocket 8 hand-wheel. In order to restore the control to a engaging with a fixed ratchet h3. Fig. 9 shows connected by a chain to a sprocket 5 on a shaft 4, predetermine d and adjustable position, an elastic th e mechanism with the slat fully open and the to which a double grooved pulley 2 and a pulley I cord 46, Fig. 3, connected to a lever 47 is secured to flap locked. Fig. 7 shows how the pawl h2 is re a pulley 45 on th e shaft 4. The lever 47 is adjustable leased on backward movement of the slat by b y a rod 49 and nut 50. Alternatively a cable 51, means of an extension f5 of the lever f3. According Fig . 5, may be secured to the pulley 45 an d passed t o the Provisional Specification a release mechanism aroun d pulleys 53 . . 56, springs 62 being interposed ma y be interposed between the slat and the flap in the cable lengths. The top par t of th e cable can which may be automatically or manually operated be fixed against movement by a clamp 57 after the whe n the flap tends to overcome the slat and may shaft 4 ha s been turned to the required position. provide for elongation or release of the connecting links . 371,025 . Oil engines. Ricardo, H. R., 21, Suffolk Street, Pall Mall, London. Jan. 13, 1931, No. 1189. [Class 7 (iii).] Substantiall y the whole of the charge of a compression-ignition engine is forced into a spher oidal combustion chamber F through a tapering tangentia l passage G4, the small end of which has a n area of approximately three-fifths that of the larger end. The lower portion of the chamber F is formed by a n externally removable cylindrical plug * These abstracts of complete specifications of Patents recently published are specially compiled, by permission of H.M. Stationery Office, from abridgments which are issued by the Office classified into groups. Sets of group abridgments can be obtained from the Patent Office, 25 , Southampton Buildings, London, W.C.2. either sheet by sheet as issued, on payment of a subscription of 1s. per group volume, or in bound volume s a t 2s. each. Copies of the full specifications can be obtained from the same address price 1s. each. Except where otherwise stated, the specification is unaccom panied by drawings if none is reproduced.
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Dec 1, 1932
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