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AIRCRAF T ENGINEERING April, 1933 A Selection of the More Important Aircraft and Engin e Specifications Published Recently b and having a radially extending arm/ 1 to which a 377,312 . Aircraft framework. Boulton & A covering for a hollow, metal structure such as membe r such as k i s fixed. Paul, Ltd., Riverside Works, and North, J. D., a fuselage or float comprises thin metal planks, Hill House, Eaton Hill, both in Norwich. April of tapering width, with edges tha t are flanged and 28, 1931, No. 12505. [Class 4.] wit h longitudinal surface grooves mainly of uniform 379,194 . Valve seats and guides. Siemens A fitting for the attachment of struts, tension widt h but converging towards one another and & Ilalske Akt.-Gcs., Siemensstadt, Berlin. Jan. members, etc., to spars or like structural members decreasing in number as the surface becomes 5, 1932, No. 320. Convention date, Dec. 23, 1931. of the type comprising a boom wholly or partly narrower. Fig. 1 show s a float of which th e surface [Classes 7 (ii) and 7 (vi).] of circular or polygonal cross section and with its is built up from metal planks 2 of approximately Part s of valves, such as edges lying wholly or partly on a circular are, is fifteen-thousandths of an inch in thickness. The valv e seats and valve- plank s have straight or regularly curved edges. adapte d to be rotated about the axis of the boom spindle guides of internal- One edge of each plank is flanged at 3, Fig. 3, and and to be fixed in any position within a given combustion engines, which grooves 4, 4 are formed on the surface parallel to range to suit th e inclination of the struts, tension ar e highly stressed thermic- th e flange 3, th e grooves dying out if they tend to members and the like. As applied to a spar ally and are unevenly ex ru n into the other edge of th e plank. The partly- comprising a circular boom a, Fig. 1, joined to posed to high temperatures, formed plank is the n marked out in position for the anothe r boom by a web a1 th e fitting comprises a ar e made of a tempered U-shaped piece b whic h fits closely t o th e boom over beryllium alloy, as 5 and 7, a n are of 180 deg. and is extended downward by i n particular a copper-beryllium alloy contain parallel arms b1, b- to form seatings b3, b4 for a in g up to about 6 per cent of beryllium (2-5 per iixing bolt c. The side edges of the fitting con cen t being particularly suitable), which retains a verge as shown in Fig. 2. Integral lugs d1, d1 are high-hea t conductivity, and are coated or covered formed with their sides parallel to a radius of the wit h a layer of another alloy, as 4 and 6, capable boom and serve for attachment of a strut. Bolt c of retaining its hardness under the high working is passed throug h a sleeve g of th e typ e described in temperatures . Such covering layer 4 or 6 may Specification 352,767 and serves to secure link consist of a tempered copper-beryllium,alloy with plates f1, f2, connected by a yoke piece f3 to which a a n addition of manganese or zinc in quantities up tension member f is attached. The hole for bolt c t o 15 per cent, or a nickel steel alloyed with beryl is formed after the fitting has been assembled and lium, and in some cases wit h a content of chromium. adjusted to correct alignment with the strut and Othe r covering materials usable are a tempered beryllium alloy having iron as a basis, or, alter natively , the covering layer may consist of an alloy of copper-silicon or iron-titanium, or an alloy on a basis of iron, or one containing tantalum. 381,919 . Variable - pitch propellers. Faire y Aviation Co., Ltd., Cranford Lane, Hayes, an d Williams, D. L. II., Hill Side, Swakelcy's Road, Ickenham , both in Middlesex. July 3, 1931, No. flange 3a on th e other side edge and is completed by 19261. [Class 114.] forming further grooves 4a, Aa parallel to th e edge Variable-pitch propellers wherein the blades are 3a. The grooves are formed by stretching the mounte d in sockets on the boss are provided with metal, th e forming rolls gripping th e metal on cither pitc h changing mechanism comprising a number of side of the groove being formed, and are caused to projections on the blade roots engaging helical die out by relieving th e pressure on th e rolls. The slots in the sockets, such projections having screw flanges of adjoining planks are united by a clamping thread s on thei r peripherics engaging a nu t rotatable stri p 8, Fig. 4, th e edges of the flanges being out on th e socket. The blade root a has secured to it a wardl y turned as a t 9, an d string or other absorbent flange member c wit h projections thereon the outer packin g 10 saturated with marine glue compressed edge of which is threaded. The socket e is pro in the recess so formed. The invention may be vided with inclined slots d through which the applied to internal structures such as tapered wing projections c pass. The screw member c engages spars . a n internal screw ring f detachably and rotatably mounte d upon th e outside of th e socket and carries 383,435 . Valve gear. Armstrong Siddeley tension member. A similar fitting is described for a bevel segment r meshing with the common bevel Motors, Ltd., and Viale, S. M., of Armstrong Sidde a polygonal boom, the bolt c being located per t in order to provide equal pitch changes for each ley Works, Park Side, Coventry. Nov. 27, 1931, pendicula r to a diametrally opposed pair of poly blade. The screw ring No . 32907. [Class 7 (vi).] gonal boom faces. If th e lines of force of stru t and f has a projection k Th e cam shafts of a radial-cylinder engine are tension members are not a t right-angles to th e bolt carryin g a key mem drive n by toothed wheels carried non-rotatably c th e fitting may be aligned with the strut and the ber j, which can be b y an eccentric strap on the crankshaft. An tension member offset on th e yoke/ 3 th e links/ 1 ,/ 2 operate d by the pilot, eccentric 5 on the crankshaft is surrounded by a being then made stiffcr. The tension members of which the key stra p 6 formed with radial extensions reaching to ma y be attached to bolt e2 securing a strut e or to n engages the corre bolts in similar lugs. The bolt c in thi s case passes sponding lock k on th e throug h a compression member i such as is shown end of the blade. The in Fig. 5, and which may extend for some distance pitc h of the blade can along the boom. In a further modification the only alter when this fitting a embraces th e boom over a greater are than lock is released and 180 deg. and is therefore made in two halves with only vary in one direc a division between th e lugs dl, d*. In a still further tion, th e blade having modification, Fig. 5, th e fitting b is similarly shaped t o be reset by hand t o th e foregoing but is of sufficient internal diameter when the propeller is to slip over th e boom on whic h i t is locate d by shaped stationary . In order packin g pieces hl, /<2 an d by bolt c. Bracing mem t o control the rate of bers may be attache d t o th e boom by angle brackets pitc h change, th e bevel havin g a part / fixed to th e outer side of the fitting member s t axe provided wit h a cam surface v against whic h abut s th e ra m of an hydraulic th e positions of the cam shafts, where they are buffer u. fitted with pinions 9 engaging internal gears 12 on th e cam shafts. The pinions 9 are adjustably fixed in the strap extensions by nuts 11, and a 381,959 . Aircraft structures ; floats. Arm Z-crank 14 is mounted between each pair of gear stron g Whitworth Aircraft, Ltd., Sir W. G., and wheels for strengthening purposes. The strap Wylie, H. N., Whitley, near Coventry. July 15, membe r may serve as a crankshaft balance weight. 1931, No. 20315. [Classes 4 and 113 (ii).]
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Apr 1, 1933
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