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high speed flight the wings 19, 20 may be wholly or partially retracted rcarwardly within the fuselage for Month in the Patent Office which purpose each wing comprises a rigid leading edge structure 22 provided with spanwisc channel rails 24 in which slide rollers 25 mounted on the fabric These abstracts of British Patent Specifications are taken, by permission, from the officially prepared covered ribs 23. Before the members 22 are folded abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, rcarwardly the ribs 23 and the fabric covering are col lapsed concertina-wise against the sides of the fuse 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies lage. During landing or take-off of the aircraft the of the full specifications are obtainable at the same address, price 2s. 8d. each. lower vertical high speed wing may be retracted in a manner similar to that employed for the wings 19, 20. In another embodiment the whole aeroplane is rotated 626,940. Aircraft propulsion. Soc. Ratcau, and 14. The compressor 8 is driven by a turbine 9 supplied a quarter of a turn about its longitudinal axis by Anxionnaz, R. Feb. 20, 1946. No. 5,323. Convention through ducts 12 with air admitted centrally at the movement of the aileron controls, the forward crew date March 31, 1945. (Class 4.) nose of the aircraft, compressed by a compressor 10, compartment 11 being dissociated from such rotation Air is sucked from the boundary layer at the rear of driven by a reciprocating motor 11, and heated by by a gyroscopic stabilizing device. In a further embodi an aircraft surface through apertures connected to an fuel injection nozzles 13. The exhaust from the turbine ment the cruciform stabilizing surfaces 14, 15 may be air compressor delivering to a jet propulsion expan 9 is to the jet 14. In FIG. 13, air entering a wing 15 located at the forward end of the fuselage. sion nozzle and may comprise the whole of the airflow through slots 16, 17 passes through the wing spar 18. through the nozzle or alternatively air from in front to the first stage 19 of a compressor in a nacelle be 629,006. Aircraft Controls. Svenska Acroplan of the aircraft may also be passed through the com neath the wing. Part then flows by an annular passage Aktiebolagct. February 7, 1947. Convention date pressor, or through some stages only of a multi-stage 19a to a propulsion nozzle 20. Part passes through a February 15, 1946. compressor. All or part of the air may be heated by second stage 21 of the compressor to a combustion An arrangement for giving 'feel' to aircraft controls fuel injected through combustion nozzles, and the chamber 22 fitted with combustion nozzles and that are normally insensitive owing to the inclusion compressor may be driven by a gas turbine on the through a gas turbine 23 to the propulsion nozzle 20. therein of servomotors or power actuators, comprises same shaft or by a reciprocating engine. The com The turbine 23 drives a propeller 24. Specification masses 4 mounted on pendulums pivoted on shafts 5, bustion air may be preheated by a heat-exchanger in 512,064 is referred to. the exhaust. The jet nozzle may be the sole propulsive 628,047. Controlling Aircraft. Robert, R. A. April means or an airscrew may be mounted forwardly on 24, 1947. Convention date April 13, 1946. the compressor shaft. Slots for intake of boundary An aeroplane is provided with two pairs of wings layer air may be provided at the points at which the transversely disposed substantially at right-angles to boundary layer tends to break away and may be formed as divergent channels or may comprise merely each other, one pair being adapted for high speed a scries of holes in the aircraft surface. A scries of such flight and the other for low speed flight cither pair of slots may be provided with means by which selected wings being brought into active position of lift by slots only are in operation at any given time, and a rotation about the longitudinal axis of the fuselage. pitot tube projecting into the boundary layer in front The centre section 12 of the fuselage is rotably arranged symmetrically at each side of an aeroplane of a slot may be employed to indicate the condition of mounted in bearings and is driven by a motor (FIG. 5, wing, and connected by cables 6, 7 to the control the boundary layer before that slot. In landing air may not shown) and carries a pair of wings 16, 17 adapted column 8 in such a way that when the control surfaces for high speed flight and another pair of wings, 19,20 be ejected through supplementary nozzles directed 2 are adjusted, the rolling movement of the aeroplane adapted for low speed flight and for landing and take forwardly and downwardly to provide aerodynamic produces inertia and centrifugal forces which acton off, the respective pair of wings being brought into braking. The air may be passed for cooling a radiator the masses 4 and thereby tend to oppose the initial an active position of lift by a quarter turn of the mounted in the wing or fuselage. Air taken in for deflection of the control column 8. The masses 4 may centre section 12 about its longitudinal axis. During wardly of the aircraft may be compressed by a com be divided in two parts Aa and 4b mounted on separate pressor in the fuselage and then distributed, after heat pendulums so coupled that one swings through a ing by fuel injection nozzles, to jet tubes in nacelles in smaller angle than the other. The invention may also the wing through which also passes the boundary be applied to rudder and elevator controls. layer air As shown in FIG. 9, air extracted at the trail ing edges of the wing of an aircraft passes forwardly 628,699. Helicopters. Cierva Autogiro Co. Ltd., through a nacelle and through the first stage CI of a and Pullin, C. G. October 1, 1947. compressor. Part then flows directly to a propulsion The torque-reaction compensating tail rotor of a nozzle at the rear of the nacelle while part passes helicopter is adjustable about a longitudinal axis for through a further stage C2 to a combustion chamber trimming the aircraft, the arrangement being such fitted with combustion nozzles cli and through a gas that displacement in either sense from its neutral turbine T and heat exchanger E, which heats air by position is accompanied by an increased thrust such passing the combustion chamber and turbine, to the that the horizontal component remains substantially propulsion nozzle. The turbine T drives the com pressor CI, C2 and an airscrew. In FIG. 11, air is constant. In the construction shown, the blades 5 of the tail rotor are adjusted in pitch by an axially- passed from slots 1 in the wings through ducts 2 to a displaccablc rod 23 which may be moved by pilot- central compressor 4 and thence to a reaction nozzle controlled cables 31 passing around a pulley 30 on a 6. The compressor 4 is driven by a reciprocating shaft 29 formed with a screw-threaded portion 27 motor 5 which also drives an airscrew 3. In FIG. 12, air engaging a fixed sleeve 28. The propeller is driven by from slots 7 in the wings passes through compressors 8 shafts 6, 11 through bevel gearing 9, 10, and is carried in nacelles in the wings and thence to a reaction nozzle by a casing 8, 8a, the latter of which may be rotated about the axis O—O of the shaft 11, to vary the direction of thrust, by worm-gearing 19, 20 operated by chain-and-sprockct 15, 16. The rod 23 is connected to the shaft 29 by a joint 25 displaced from the axis O—O, whereby rotation of the casing 8, 8a results in axial displacement of the rod 23 to effect the desired variation of pitch of the blades 5. Alternatively, the thrust may be varied by adjusting the speed of the tail propeller without altering the blade pitch. 60 /(ircrafl Engineering
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Feb 1, 1953
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