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Month in the Patent Office

Month in the Patent Office 230 AIRCRAFT ENGINEERING August, 1934 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 404,606 . Aircraft fuselages. Dornier Metall- th e lower end forms a chamber j into which con­ baute n Ges., and Dornier, C., Friedrichshafen, densed water collects through holes k, a drain with Lak e Constance, Germany. April 15, 1932, No. a non-return valve being provided at the inner 10875. Void [Abridged as open to inspection end of the slat to return the water to the main unde r Sect. 91 of th e Acts, May 22, 1932]. [Class 4.] system . The steam pressure may be utilized to ope n th e slot by extending th e telescopic supports. I n an aircraft fuselage or motor gondola wherein all th e stresses occurring are taken up by a spatial skeleton structure a, an outer covering is provided 406,118 . Cylinders. Fairey Aviation Co., formed by individual reinforced panels b, c, d, e, Ltd. , Cranford Lane, Hayes, Middlesex, and For­ each covered on one side with fabric, sheet-metal syth , A. G., Venlaw, Burdon Lane, Cheam, Surrey. or plywood f, g, h, i. All the panels may be re­ Dec. 22, 1932, Nos. 36324, 36325, and 36327. movabl y secured to the structure a by means [Class 7 (ii).] of clamps, screws, bolts, or the like, or some only A cylinder block 6 is cast integral, not only with of the panels at places where easy access to the th e upper half of the crankcase, but also with the interio r of the fuselage is desired, the remainder induction passage d and its branches e, an d one or of th e fuselage being provided with a non-removable mor e cooling water manifolds j, a very rigid struc­ covering. Each panel is reinforced by a lattice tur e being thus obtained. In the V engine shown, 405,132 . Aircraft alighting-gear. Fairey structure , or by profiled members, or by other th e induction passage d is located between the Aviation Co., Ltd., Cranford Lane, Hayes, Middle­ mean s and may be mounted with its covered inclined rows of cylinders, and the casting may also sex, and Lobelle, M. J. O., Ludlow, Langley Road, surface towards the interior of the fuselage. The include a housing for the reduction gear. The water Langley, Buckinghamshire. March 22, 1933, No. panels may be interchangeable and some may be manifolds j are connected to the circulating pump 8665. [Class 4.] covered on both sides. b y passages k passing through supporting brackets An aircraf t undercarriage comprises two transverse m, and to the cylinder jackets by ports n, progres­ member s to the ends of which floats or skids are sively increasing in size to ensure uniformity of connected, one of these members being flexible and distributio n of the water. th e other rigid, the floats, etc., being rigidly con­ nected to the flexible member and flexibly con­ nected to th e rigid member, e.g. b y universal joints. Fig. 2 shows the front transverse member which comprises a flexible tube 14, reinforced towards its ends by additional lengths of tube, and rigidly secured at its centre to th e main chassis 13. The ends of the tube 14 are rigidly secured to shock absorber s 12 connected to the floats and con­ nected to the chassis 13 by flexible joints. These joint s may consist of lugs 16, 17 through which a pi n is passed having a barrel-shaped sleeve thereon, th e ends of the hole in the lug 16 being rounded. Similar joints connect the ends of the rear rigid 404,994 . Aircraft planes. Bristol Aeroplane transvers e member to shock absorbers 12 towards Co., Ltd. , and Pollard, H . J., Filton House, Bristol. th e rear ends of the floats. A modified flexible Jul y 23, 1932, No. 20798. [Class 4.] membe r is described comprising two leaf springs thickened by additional plates towards their outer A n aeroplane wing includes one or more spars ends and rigidly secured to a central bracket on the havin g booms of channel form with their open chassis. sides outermost and a plurality of ribs connected crosswise thereto and constructed in separate sections, each of which is directly connected a t its end or end s t o a spar . In one form , a wing structure 406,485 . Aircraft motor accessories . Dor­ includes spars 10, 11 connected by channel section nier Metallbauten Ges., an d Dornier, C., Friedrichs­ rib s 12, 13. The leading edge of th e wing includes hafen, Lake Constance, Germany. March 7, ribs 14, 15 and the trailng edge ribs 16, 17. The 1933, No. 6933. Convention date, May 20, 1932. rib s are cross braced by members 18. Each spar [Class 4.] includes booms built up of corrugated members 20, Fo r cooling aircraft motors and for removing the 21 , Fig. 3, and connected by a flat strip metal boundar y layer of air from the upper surface of the we b 19. The booms are closed in by cover-plates wings, a blower draws air through orifices in the 22 which may be curved to conform to the aerofoil surface and discharges it through a radiator or section. The plates 22 are riveted to the booms radiator s which may bo arranged in the wing. A and to the ribs, gusset-plates 23 spaced along the blower d driven from the engine b draw s air from a lengt h of the spars are each riveted to the web 19 chambe r f communicating with pipes h having th e plate 22 and the ribs. Strengthening ribs may be inserted in th e joints between the plate 22 and 405,812 . Aircraft-engine cooling system. th e members 20, 21, and may be partly cut away Faire y Aviation Co., Ltd., Cranford Lane, Hayes, an d replaced by a continuous skin of thin metal. an d Williams, D. L. H., Hillside, Swakeley's Road, Th e cover plates 22 may be replaced by spaced Ickenham , both in Middlesex. Feb. 27, 1933, No. apar t ties and the web 19 may be corrugated or 5955. [Class 4.] lightened, and any of the members may be built Th e slat for forming a slot at the leading edge u p of laminations. The bracing 18 ma y be omitted of a wing is constructed to form part of the engine an d the cover plate 22 may be corrugated. The cooling system. The slat is mounted on telescopic edges of the booms and the cover plates 22 may be supports , which may constitute the flow and retur n pipes, and may be divided by a plate with holes remote from the pipes to cause the flow to travers e both surfaces or, as shown, it ma y be fitted with partitions f forming two thi n chambers through branche s i leading to orifices k in the upper surface which steam passes in parallel. A partition h at of the wing. The air is discharged through a radiato r e and through openings l in the fuselage jus t beneath the wing. Modifications are described in which both the blower and the radiator are * These abstracts of complete specifications of Patents recently arrange d within the wing, the blower in one case published are specially compiled, by permission of H.M. Stationery Office, from abridgments which are issued by the Office classified being driven round by peripheral blades acted upon into groups. Sets of group abridgments can be obtained from b y jets of exhaust gases. In another case two the Patent Office, 25 Southampton Buildings, London, W.C.2, blowers on a common transverse axis aspirate air 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 throug h two radiators from the interior of the wing the full specifications can be obtained from the same address, which has holes in its upper rear surface and the price 1s. each. ai r is discharged through two orifices in the lower Except where otherwise stated, the specification is unaccom­ surface. 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 (8): 1 – Aug 1, 1934
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Emerald Publishing
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Copyright © Emerald Group Publishing Limited
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0002-2667
DOI
10.1108/eb029839
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Abstract

230 AIRCRAFT ENGINEERING August, 1934 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 404,606 . Aircraft fuselages. Dornier Metall- th e lower end forms a chamber j into which con­ baute n Ges., and Dornier, C., Friedrichshafen, densed water collects through holes k, a drain with Lak e Constance, Germany. April 15, 1932, No. a non-return valve being provided at the inner 10875. Void [Abridged as open to inspection end of the slat to return the water to the main unde r Sect. 91 of th e Acts, May 22, 1932]. [Class 4.] system . The steam pressure may be utilized to ope n th e slot by extending th e telescopic supports. I n an aircraft fuselage or motor gondola wherein all th e stresses occurring are taken up by a spatial skeleton structure a, an outer covering is provided 406,118 . Cylinders. Fairey Aviation Co., formed by individual reinforced panels b, c, d, e, Ltd. , Cranford Lane, Hayes, Middlesex, and For­ each covered on one side with fabric, sheet-metal syth , A. G., Venlaw, Burdon Lane, Cheam, Surrey. or plywood f, g, h, i. All the panels may be re­ Dec. 22, 1932, Nos. 36324, 36325, and 36327. movabl y secured to the structure a by means [Class 7 (ii).] of clamps, screws, bolts, or the like, or some only A cylinder block 6 is cast integral, not only with of the panels at places where easy access to the th e upper half of the crankcase, but also with the interio r of the fuselage is desired, the remainder induction passage d and its branches e, an d one or of th e fuselage being provided with a non-removable mor e cooling water manifolds j, a very rigid struc­ covering. Each panel is reinforced by a lattice tur e being thus obtained. In the V engine shown, 405,132 . Aircraft alighting-gear. Fairey structure , or by profiled members, or by other th e induction passage d is located between the Aviation Co., Ltd., Cranford Lane, Hayes, Middle­ mean s and may be mounted with its covered inclined rows of cylinders, and the casting may also sex, and Lobelle, M. J. O., Ludlow, Langley Road, surface towards the interior of the fuselage. The include a housing for the reduction gear. The water Langley, Buckinghamshire. March 22, 1933, No. panels may be interchangeable and some may be manifolds j are connected to the circulating pump 8665. [Class 4.] covered on both sides. b y passages k passing through supporting brackets An aircraf t undercarriage comprises two transverse m, and to the cylinder jackets by ports n, progres­ member s to the ends of which floats or skids are sively increasing in size to ensure uniformity of connected, one of these members being flexible and distributio n of the water. th e other rigid, the floats, etc., being rigidly con­ nected to the flexible member and flexibly con­ nected to th e rigid member, e.g. b y universal joints. Fig. 2 shows the front transverse member which comprises a flexible tube 14, reinforced towards its ends by additional lengths of tube, and rigidly secured at its centre to th e main chassis 13. The ends of the tube 14 are rigidly secured to shock absorber s 12 connected to the floats and con­ nected to the chassis 13 by flexible joints. These joint s may consist of lugs 16, 17 through which a pi n is passed having a barrel-shaped sleeve thereon, th e ends of the hole in the lug 16 being rounded. Similar joints connect the ends of the rear rigid 404,994 . Aircraft planes. Bristol Aeroplane transvers e member to shock absorbers 12 towards Co., Ltd. , and Pollard, H . J., Filton House, Bristol. th e rear ends of the floats. A modified flexible Jul y 23, 1932, No. 20798. [Class 4.] membe r is described comprising two leaf springs thickened by additional plates towards their outer A n aeroplane wing includes one or more spars ends and rigidly secured to a central bracket on the havin g booms of channel form with their open chassis. sides outermost and a plurality of ribs connected crosswise thereto and constructed in separate sections, each of which is directly connected a t its end or end s t o a spar . In one form , a wing structure 406,485 . Aircraft motor accessories . Dor­ includes spars 10, 11 connected by channel section nier Metallbauten Ges., an d Dornier, C., Friedrichs­ rib s 12, 13. The leading edge of th e wing includes hafen, Lake Constance, Germany. March 7, ribs 14, 15 and the trailng edge ribs 16, 17. The 1933, No. 6933. Convention date, May 20, 1932. rib s are cross braced by members 18. Each spar [Class 4.] includes booms built up of corrugated members 20, Fo r cooling aircraft motors and for removing the 21 , Fig. 3, and connected by a flat strip metal boundar y layer of air from the upper surface of the we b 19. The booms are closed in by cover-plates wings, a blower draws air through orifices in the 22 which may be curved to conform to the aerofoil surface and discharges it through a radiator or section. The plates 22 are riveted to the booms radiator s which may bo arranged in the wing. A and to the ribs, gusset-plates 23 spaced along the blower d driven from the engine b draw s air from a lengt h of the spars are each riveted to the web 19 chambe r f communicating with pipes h having th e plate 22 and the ribs. Strengthening ribs may be inserted in th e joints between the plate 22 and 405,812 . Aircraft-engine cooling system. th e members 20, 21, and may be partly cut away Faire y Aviation Co., Ltd., Cranford Lane, Hayes, an d replaced by a continuous skin of thin metal. an d Williams, D. L. H., Hillside, Swakeley's Road, Th e cover plates 22 may be replaced by spaced Ickenham , both in Middlesex. Feb. 27, 1933, No. apar t ties and the web 19 may be corrugated or 5955. [Class 4.] lightened, and any of the members may be built Th e slat for forming a slot at the leading edge u p of laminations. The bracing 18 ma y be omitted of a wing is constructed to form part of the engine an d the cover plate 22 may be corrugated. The cooling system. The slat is mounted on telescopic edges of the booms and the cover plates 22 may be supports , which may constitute the flow and retur n pipes, and may be divided by a plate with holes remote from the pipes to cause the flow to travers e both surfaces or, as shown, it ma y be fitted with partitions f forming two thi n chambers through branche s i leading to orifices k in the upper surface which steam passes in parallel. A partition h at of the wing. The air is discharged through a radiato r e and through openings l in the fuselage jus t beneath the wing. Modifications are described in which both the blower and the radiator are * These abstracts of complete specifications of Patents recently arrange d within the wing, the blower in one case published are specially compiled, by permission of H.M. Stationery Office, from abridgments which are issued by the Office classified being driven round by peripheral blades acted upon into groups. Sets of group abridgments can be obtained from b y jets of exhaust gases. In another case two the Patent Office, 25 Southampton Buildings, London, W.C.2, blowers on a common transverse axis aspirate air 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 throug h two radiators from the interior of the wing the full specifications can be obtained from the same address, which has holes in its upper rear surface and the price 1s. each. ai r is discharged through two orifices in the lower Except where otherwise stated, the specification is unaccom­ surface. panied by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Aug 1, 1934

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