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Month in the Patent Office

Month in the Patent Office 148 AIRCRAFT ENGINEERING May, 1934 A Selection of the More Important Aircraft and Engin e Specifications Published Recently used or the wheel axle itself, in which case means 399,887 . Aircraft controls: framework. a t f0 for the reception of locating studs by which ar e provided for locking shock absorbers and th e like Vickers (Aviation), Ltd., and Wallis, B. N., Byfleet the y are held during the machining of the bearing in thei r extended position. Fig. 11 show s an automa­ Road , Weybridge, Surrey. April 19, 1932, No. housing. After this operation the trunnions f are held in position by the outer race g of the tic release mechanism operated by lowering of the 11189. [Class 4.] ball-bearing for shaft a1. This bearing is of the tai l of the upper component; this comprises a hook self-aligning type which resists end thrust and is 21 fixed to th e axl e 14 an d co-operatin g with a sto p 22 More than one such releasing means may be fitted, held in position by a distance piece g2 and ring e.g., two lateral sockets and axles comprising nu t g3. The member e is provided with pins e7 automaticall y freed hooks set to release just prior extendin g outwardly on an axis at right angles to that of a central mounting, the lateral securing to the intersecting axes of the trunnions f and mean s serving to prevent rolling. Various modifi­ shaft a1. Pins e7 attach lugs h carrying fore-and- cations of this device are described. In one form aft tension stays h2, h3 attached to the fuselage. th e locking hook and restraining projection may tak e the form of a rack and pinion which engage together , the pinion being provided with braking 400,292 . Aircraft carrying other aircraft. means. All external mounting parts may be re­ Mayo, R. H., 39, St. James's Street, London. tractable . Locking means of the type shown in April 26, 1932, No. 12013. [Class 4.] Fig. 6 may be releasable only by a combined or A composite aircraft comprises two component consecutive operation of controls located in both aircraft each capable of independent sustained flight components . Alternatively, they may be released mounted one on top of the other and initially automaticall y by lowering of the tail or by the connected together by rigid but releasable locking operation of means for increasing the incidence means in such a manner as to enable the composite or lift of the upper wings which do not involve aircraft to take off, fly and land with the wings chang e of attitude of the upper component. of both components contributing in an efficient Means for mounting two structural members Fig . 7 shows one form of automatic means for manne r towards the total lift required for such on each other about intersecting axes about which preventin g withdrawal of axle 14 should the upper flight, and having means for increasing the angle said members are permitted independent angular componen t have insufficient excess of lift. A trip adjustmen t comprises a locating member, bearings device may be fitted operable on movement of for each of said structural members carried by th e uppe r component out of its socket, which device th e locating member adapted to prevent axial ma y close the throttle of the lower component, movemen t of the structural members while per­ switch off the ignition, or operate a lift spoiling mittin g angular adjustment about their axes device to ensure ready separation of th e two com­ relativ e to the locating member, the locating ponents . Guards may be fitted to prevent undue membe r being held in position solely by the longitudinal tilting of the upper component after structura l members themselves and by bracing release. The upper component may comprise two member s fixed to the locating member. As applied aircraft one carried by the other. t o an aeroplane tail-unit (Fig. 1), which comprises an elevator a, tail planes b, b1, and rudders c, c1, th e elevator is fixed in a shaft a, angularly ad­ 402,895 . Aircraft carrying other aircraft. justabl e in a journal carried by struts a2, the tail Mayo, R. H., 39, St. James's Street, Pall Mall, planes b, b1 are fixed on a shaft b2, passing through London. Aug. 19, 1932, No. 23286. Addition to th e fuselage and angularly adjustable therein, and 400,292. [Class 4.] th e rudders are fixed on rudder posts c2 each I n order to ensure ready separation of the two angularl y adjustable about an axis which inter­ component s of a composite aircraft of the type sects the axis of shafts a1, b2. The rudder posts, described in the parent Specification, the upper are recessed at c3 where they are fitted with componen t is so mounted on the lower component sleeves c4 within each of which a plummcr block d tha t the resultant reaction between the two acts (Fig. 2) is carried. A locating member e carrying behind the centre of gravity of th e lower component. a ball bearing g for the shaft a1 or b2 is mounted In order to ensure that separation does not take between jaws d1, d2 of block d by means of trunnions place until a predetermined excess lift is exerted rotatabl e in bushes d3. The trunnions f are upon the wings of the upper component, one or assembled by inserting them from within the mor e locking devices each comprising a hook 3 bearing housing formed in member e and are associated with one componen t engages a restraining located by flanges f2. The trunnions f are threaded projection 4 on the lower component, the hook or th e projection being arranged to yield as the lift of incidence or otherwise increasing the lift co- coefficient of the wings of the upper component is elficient of the wings of the upper component increased and to give way entirely when the pre­ relatively to th e lower componen t during flight of th e determined excess lift is developed. In one form composite aircraft as such and while the two com­ (Fig. 3) the engaging part of hook 3 comprises an ponent s arc still attached together. Fig 1 shows integra l portion 6 and a pivoted portion 7 held in a n upper component 12 mounted on a lower com­ position by a spring 9. As the angle of incidence ponen t 13 by means comprising co-axial axles 14 of the wings of the upper component is increased, projecting from opposite sides of the floats of the hook 3 moves angularly until part 6 leaves pro­ uppe r component which are received in co-axial jection 4, which is then engaged by pivoted par t 7. sockets 15 mounted above the wings of the lower Axle 1 now moves upwardly in socket 2 and as component , locking pins 16 (Fig. 6) initially pre­ th e excess lift increases, the resistance of spring 9 ventin g disengagement. This arrangement may is overcome until part 7 rotates sufficiently to be reversed, the sockets being then carried by the free the hook 3 from projection 4. According to uppe r component. The slot in the socket is sloped a modification, the whole of the engaging part of to ensure upward and forward disengagement, but hook 3 may be pivoted in the manner of the this may be varied in different cases. An adjust­ portio n 7. able rear support 17 is pivoted at 18 t o component 13 and connected to component 12 a t the tail end. Whe n detached from the upper component member 17 turn s about its pivot and is received in socket 20 as shown in Fig. 11. After release of Member 17, * These abstracts of complete specifications of Patents recently th e tail of the upper component is lowered by published are specially compiled, by permission of H.M. Stationery Office, from abridgments which are issued by the Office classified operation of the elevator to increase the lift co- into groups. Sets of group abridgments can be obtained from efficient of the main planes, whereby the craft the Patent Office, 25 Southampton Buildings, London, W.C.2, will fly clear as soon as pins 16 are withdrawn. either sheet by sheet as issued, on payment of a subscription of 5s. per group volume, or in bound volumes at 2s. each. Copies of Means to prevent lateral movement of the axles the full specifications can be obtained from the same address, ma y be fitted and one continuous axle may be price 1s. each. used. In the case of a land machine (Fig. 11), an Except where otherwise stated, the specification is unaccom­ axl e 14 connected by struts to the body may be panied by drawings if none is reproduced. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Month in the Patent Office

Aircraft Engineering and Aerospace Technology , Volume 6 (5): 1 – May 1, 1934

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029802
Publisher site
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Abstract

148 AIRCRAFT ENGINEERING May, 1934 A Selection of the More Important Aircraft and Engin e Specifications Published Recently used or the wheel axle itself, in which case means 399,887 . Aircraft controls: framework. a t f0 for the reception of locating studs by which ar e provided for locking shock absorbers and th e like Vickers (Aviation), Ltd., and Wallis, B. N., Byfleet the y are held during the machining of the bearing in thei r extended position. Fig. 11 show s an automa­ Road , Weybridge, Surrey. April 19, 1932, No. housing. After this operation the trunnions f are held in position by the outer race g of the tic release mechanism operated by lowering of the 11189. [Class 4.] ball-bearing for shaft a1. This bearing is of the tai l of the upper component; this comprises a hook self-aligning type which resists end thrust and is 21 fixed to th e axl e 14 an d co-operatin g with a sto p 22 More than one such releasing means may be fitted, held in position by a distance piece g2 and ring e.g., two lateral sockets and axles comprising nu t g3. The member e is provided with pins e7 automaticall y freed hooks set to release just prior extendin g outwardly on an axis at right angles to that of a central mounting, the lateral securing to the intersecting axes of the trunnions f and mean s serving to prevent rolling. Various modifi­ shaft a1. Pins e7 attach lugs h carrying fore-and- cations of this device are described. In one form aft tension stays h2, h3 attached to the fuselage. th e locking hook and restraining projection may tak e the form of a rack and pinion which engage together , the pinion being provided with braking 400,292 . Aircraft carrying other aircraft. means. All external mounting parts may be re­ Mayo, R. H., 39, St. James's Street, London. tractable . Locking means of the type shown in April 26, 1932, No. 12013. [Class 4.] Fig. 6 may be releasable only by a combined or A composite aircraft comprises two component consecutive operation of controls located in both aircraft each capable of independent sustained flight components . Alternatively, they may be released mounted one on top of the other and initially automaticall y by lowering of the tail or by the connected together by rigid but releasable locking operation of means for increasing the incidence means in such a manner as to enable the composite or lift of the upper wings which do not involve aircraft to take off, fly and land with the wings chang e of attitude of the upper component. of both components contributing in an efficient Means for mounting two structural members Fig . 7 shows one form of automatic means for manne r towards the total lift required for such on each other about intersecting axes about which preventin g withdrawal of axle 14 should the upper flight, and having means for increasing the angle said members are permitted independent angular componen t have insufficient excess of lift. A trip adjustmen t comprises a locating member, bearings device may be fitted operable on movement of for each of said structural members carried by th e uppe r component out of its socket, which device th e locating member adapted to prevent axial ma y close the throttle of the lower component, movemen t of the structural members while per­ switch off the ignition, or operate a lift spoiling mittin g angular adjustment about their axes device to ensure ready separation of th e two com­ relativ e to the locating member, the locating ponents . Guards may be fitted to prevent undue membe r being held in position solely by the longitudinal tilting of the upper component after structura l members themselves and by bracing release. The upper component may comprise two member s fixed to the locating member. As applied aircraft one carried by the other. t o an aeroplane tail-unit (Fig. 1), which comprises an elevator a, tail planes b, b1, and rudders c, c1, th e elevator is fixed in a shaft a, angularly ad­ 402,895 . Aircraft carrying other aircraft. justabl e in a journal carried by struts a2, the tail Mayo, R. H., 39, St. James's Street, Pall Mall, planes b, b1 are fixed on a shaft b2, passing through London. Aug. 19, 1932, No. 23286. Addition to th e fuselage and angularly adjustable therein, and 400,292. [Class 4.] th e rudders are fixed on rudder posts c2 each I n order to ensure ready separation of the two angularl y adjustable about an axis which inter­ component s of a composite aircraft of the type sects the axis of shafts a1, b2. The rudder posts, described in the parent Specification, the upper are recessed at c3 where they are fitted with componen t is so mounted on the lower component sleeves c4 within each of which a plummcr block d tha t the resultant reaction between the two acts (Fig. 2) is carried. A locating member e carrying behind the centre of gravity of th e lower component. a ball bearing g for the shaft a1 or b2 is mounted In order to ensure that separation does not take between jaws d1, d2 of block d by means of trunnions place until a predetermined excess lift is exerted rotatabl e in bushes d3. The trunnions f are upon the wings of the upper component, one or assembled by inserting them from within the mor e locking devices each comprising a hook 3 bearing housing formed in member e and are associated with one componen t engages a restraining located by flanges f2. The trunnions f are threaded projection 4 on the lower component, the hook or th e projection being arranged to yield as the lift of incidence or otherwise increasing the lift co- coefficient of the wings of the upper component is elficient of the wings of the upper component increased and to give way entirely when the pre­ relatively to th e lower componen t during flight of th e determined excess lift is developed. In one form composite aircraft as such and while the two com­ (Fig. 3) the engaging part of hook 3 comprises an ponent s arc still attached together. Fig 1 shows integra l portion 6 and a pivoted portion 7 held in a n upper component 12 mounted on a lower com­ position by a spring 9. As the angle of incidence ponen t 13 by means comprising co-axial axles 14 of the wings of the upper component is increased, projecting from opposite sides of the floats of the hook 3 moves angularly until part 6 leaves pro­ uppe r component which are received in co-axial jection 4, which is then engaged by pivoted par t 7. sockets 15 mounted above the wings of the lower Axle 1 now moves upwardly in socket 2 and as component , locking pins 16 (Fig. 6) initially pre­ th e excess lift increases, the resistance of spring 9 ventin g disengagement. This arrangement may is overcome until part 7 rotates sufficiently to be reversed, the sockets being then carried by the free the hook 3 from projection 4. According to uppe r component. The slot in the socket is sloped a modification, the whole of the engaging part of to ensure upward and forward disengagement, but hook 3 may be pivoted in the manner of the this may be varied in different cases. An adjust­ portio n 7. able rear support 17 is pivoted at 18 t o component 13 and connected to component 12 a t the tail end. Whe n detached from the upper component member 17 turn s about its pivot and is received in socket 20 as shown in Fig. 11. After release of Member 17, * These abstracts of complete specifications of Patents recently th e tail of the upper component is lowered by published are specially compiled, by permission of H.M. Stationery Office, from abridgments which are issued by the Office classified operation of the elevator to increase the lift co- into groups. Sets of group abridgments can be obtained from efficient of the main planes, whereby the craft the Patent Office, 25 Southampton Buildings, London, W.C.2, will fly clear as soon as pins 16 are withdrawn. either sheet by sheet as issued, on payment of a subscription of 5s. per group volume, or in bound volumes at 2s. each. Copies of Means to prevent lateral movement of the axles the full specifications can be obtained from the same address, ma y be fitted and one continuous axle may be price 1s. each. used. In the case of a land machine (Fig. 11), an Except where otherwise stated, the specification is unaccom­ axl e 14 connected by struts to the body may be panied by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: May 1, 1934

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