118 AIRCRAF T ENGINEERING May, 1933 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 383,590 . Aircraft control gear. Armstrong 383,378 . Regulating; spray carburettors; casing 27 and the plate 24 may be replaced by a Whitwort h Aircraft, Ltd., Sir \V. G. and Lloyd, J., transverse bar member having arcuate ends closing timin g ignition. Rowledge, A. J., Ellerslie, Whitley , near Coventry. July 8, 1932, No. 19382. slots formed in the casing 27 for the propeller Trowels Lane, Rubbra, A. A., Red Roofs, Carlton [Class 4.] blades. The sectioned engine cowling 14 is sup Road , and Farmer, G. H., Sunnydale, Shamrock Street, all in Derby. Oct. 14, 1931, No. 28537. porte d on a ring 21 having angle section and lugs [Classes 7 (iii), 7 (iv), and 7 (vi).] 23 on an annular exhaust manifold having outlets 16 ; alternatively the fairing 14 may be formed In altitude controls for aircraft engines in which in two hinged parts which are clamped together th e throttle valve is actuated both manually and to embrace overhead valve-gear covers. by an aneroid-controlled relay preventing excessive charging of the engine, means are provided for limiting th e movement of the relay device so tha t it ma y be over-ridden by the manual control for An aircraft control surface moved by a servo- 384,587 . Aerofoil structures. Budd Manu obtainin g extra power at ground levels. flap mounted thereon and connected to th e actuating facturing Co., E. G., 2500, Hunting Park Avenue, Th e ignition timing, the richness of the mixture, means, is connected also to the actuating means Philadelphia , U.S.A.—(Assignees of Ragsdale, and the supply of lubricating-oil to the engine throug h initially stressed resilient devices so that E . J. W. ; Curren Terrace, Norristown, Pennsyl cylinders may be adjusted simultaneously with for small movements the control surface is positively vania, U.S.A.) Juno 23, 1932, No. 17737. Con th e throttle. operated with substantially no servo effect. A rud vention date, June 23, 1931. [Class 4.] Fig . 1 shows an aneroid capsule a subjec t to blower- de r 3 having a balancing portion (not shown) outle t pressure by a connection a4 and connected An aerofoil comprises spaced ribs interconnected extendin g forwardly of its pivot 4 has a servo-flap b y angle-section longitudinal members, each having to a valve b1, which controls communication 5 at its rear edge connected by crossed rods 9 to a n arm extending into marginal slots of the ribs between pipes d, d1 leadin g to the blower outlet and levers 10 connected by cables to a rudder bar 13. and another arm secured to marginal flanges of the inlet respectively and passages c2, e3 leading to Th e levers 10 are connected directly to th e rudder ribs, while a metallic skin is secured to the ribs and opposite sides of the relay piston f. This piston is b y rods 15 havin g telescopic portions 16 containing longitudinal members to constitute therewith a connected to one end of a floating lever g, which is initially stressed springs so that for small dis rigid structure. As applied to one wing or blade connected intermediately to the manual control h1, placement s of the rudder it is positively moved and at its other end to the throttle g3. The move of a rotary wing system ribs 10 formed in one piece with little action on the (lap 5. Larger displace men t of the relay piston in the direction for closing stamping s from light gauge sheet metal have upper ment s involve further compression of one or other th e throttle is limited by an adjustable stop i. an d lower flanges 11 an d oppositely flanged lighten of the springs and consequent movement of the Normally, the manual control is moved only in the ing holes 16. The ribs are spaced closely at the servo-flap 5. The rudder bar pivot may be pro upper part of the segment h2, bu t when extra power root 14 where the blade is to be attached to a hub vided with a friction clamping device 22 to hold it is required at ground levels, th e manual control is membe r and a t 15 wher e a bracing member is to be in set position against the pull of th e resilient device secured, and are interconnected by a scries of angle- moved through a gate slot or th e like to th e bottom 1(5. section longitudinals 18 of light gauge strip metal. of the sector, as shown in Fig. 1, thereby opening Th e Hanged edges of the ribs are formed with a th e throttle farther than that permitted by the series of kerfs 19 corresponding to the number and relay, the piston of which is held against the stop i. 383,792 . Aircraft motor accessories. position of the longitudinals 18. One arm 20 of Th e gate slot serves to give th e pilot warning of the Stevens, A. H., 5, Quality Court, Chancery Lane, th e members 18 is inserted into the corresponding necessity of returning the manual control to its London.—(Wrigh t Aeronautical Corporation ; normal position, but a further indication is given kerfs of the ribs which are held in a jig and the Paterson, New Jersey, U.S.A.). Jan. 13, 1932, b y the action of the relay in moving the throttle othe r ar m 21 spot welded to th e ilanges 11. Vertical No . 1086. [Class 4.] angle members 22, Fig. 1, have one arm welded to past the fully-open A centrifugal blower for engine cooling air is th e web of th e rib an d th e othe r ar m which vertically position as the air arrange d in the spinner of an aircraft propeller. overlaps vertically opposed longitudinals welded craft ascends, there Th e spinner comprises a stream-lined casing 27 t o their arms 20. The sheet-metal wing covering by reducing the havin g an air entrance 30, reinforced by radial is made in upper and lower portions Hanged in power. The middle wardl y a t their forward edges which are located in of the lever g may kerf 28, Fig. 2. Either the lower or upper portion also be connected of the wing covering is first assembled by first to a three-armed engaging the flanged forward edge in kerf 28 then lever connected to spo t welding to longitudinals 18 and rib Ilanges 11. th e ignition-timing Th e remaining portion of the covering is then lever, to the fuel- applied, its edge flange being inserted in kerf 28 meterin g device of and welded to the flange of the other sheet, then th e carburettor , and th e sheet progressively welded to longitudinals and to a cock control ribs from leading to trailing edge, the flange 10 ling the flow of being cu t away a t 13 t o permit easy access of weld lubrican t to the ing tongs to the covering as the trailing edge is cylinders. The con approached . Finally the overlapping trailing edges nection to the of the covering are welded together. In an alter ignition control ad nativ e method, the forward edge flanges of the vances the timing covering sheets are welded together then located as the throttle is in kerf 28, the lower section then welded to the opened by th e nor framework with the upper section bent forwardly mal manual con ou t of the way, and finally the upper section at trol, but when the tache d progressively to the framework as before. manua l control is Th e wing tip 281 is formed from two shaped sheets moved beyond the spokes, and a dished back-plate 24 having circum lap-welded together at the leading edge and spot gate , the ignition ferential ports through which the air, rotated by welded at their abutting trailing edges. The wmg is again retarded th e roots of the propeller blades, is iorced on to ti p is reinforced by ribs 31 welded to the skin, b y the connections curved guide vanes 20 arranged between radial th e inner rib being spaced from the mouth of the passing beyond a cylinders of the engine. The air issues, with ti p to permit the ends 32 of longitudinals 18 to dead-centre posi engine exhaust from ports 16, through an annular telescope some distance into the tip to the skins tion. Specification opening between two fixed fairings 14, 17, a guide of which they are welded. The tip is assembled 356,619 is referred 18 being provided. The spinner may include before the main covering sheets. to . helical blower vanes extending from the hub to the * 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 5s. per group volume, or in bound volumes at 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: May 1, 1933