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158 AIRCRAFT ENGINEERING June, 1935 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 414,209 . Controlling aircraft. Ksoll, J., According to the specification as open to 22, Enderstrasse, Breslau, Germany. July 3, 1933, inspection under section 91, a rotary cylindrical No . 18854. [A specification was laid open to propeller has two wires arranged in the oncoming inspection under Sect. 91 of the Acts, Jan. 3, 1934.] fluid. Moveable wires and rods also are referred [Class 4.] to . This subject matter docs not appear in the A flap or aileron capable of being moved rear- specification as accepted. wardly and tilted relatively to the fixed part of an aircraft wing, so as to form a nozzle gap between th e fixed part and the aileron or flap, is supported 416,326 . Controlling aircraft. Hartshrn, by a sliding pivot or a system of pivoted links A. S., Royal Aircraft Establishment, South Farn- arranged so that the flap or aileron has a motion borough, Hampshire. May 11, 1933, No. 13730. compounded of a translation and a rotation. An [Classes 4 and 114.] aileron or flap II, Fig. 2, is pivoted about a pivot 1 A balanced aileron or other control surface has capable of being moved along a slot 10 by a link 8 the whole or a part of its leading portion of a and lever 9 until it is in the position IIa. A gap is section varying in the direction of its span so that thereb y opened between the plane and the aileron a s the trailing edge is moved upwards the leading or flap, bu t it is ineffective until the aileron or flap edge 4 progressively projects below the lower is tilted by a link 2 and lever 4 in order to produce surface of a fixed plane 3. Figs. 1, 2, 3 show a positive pressure at the lower end of the gap. sections through a wing and aileron at three Furthe r tilting of the aileron or flap II does not successive points along the span, the leading edge widen the gap. Fig. 3 shows a modification in 4 of the aileron being continuously inclined with which the flap II is carried by parallel links 15, 16 respect to its hinge axis 2. This inclination may hinged to a lever 12, 13 pivoted at 11 to an arm 7 th e drum 29 until the flap II is in its extreme exten d over a portion only of the aileron, or the on the planes. The lever 12, 13 is normally held position and the drum 29 canno t rotate an y further. aileron may bo divided into two or more portions b y a spring against a stop 14 so that the flap first Movemen t of th e lever 30 the n causes th e depression moves from the position I I to a position IIa as the of th e flap 22 as shown a t 221. A telescopic linkage ma y replace th e cable 26 and spring-drum 29. According to the Specification as open to inspec tion under section 91, th e invention ma y be applied t o elevators. This subject matter docs not appear in the specification as accepted. 416,065 . Engine fairings, Armstrong Sid- deley Motors, Ltd., Green, F. M., and Reynolds, R., Park Side, Coventry. Feb. 8, 1933, No. 3850. [Class 4.] A fairing for an aero-engine comprises an outer each of which has its leading edge so inclined. In par t 5 arranged above, and extending in front of alternativ e constructions the leading edge rises th e engine cylinder 2 and an inner par t 8 extending from the position shown in Fig. 3 at one end to t o the cylinder head; an out-turned flap 17, pivoted tha t shown in Fig. 2 a t the other, or both ends may a t the rear edge on helical springs 18 which tend be shaped as shown in Fig. 3 and the centre section t o keep it in its outward direction, increases the formed as shown in Fig. 2. air-flow past the cylinder a t low speed and reduces th e drag on th e aircraft a t high speed. On a radial- cylinder engine the faring takes the form of a circular or polygonal ring with a frustum-shaped rea r edge, constructed in sections, which may be arrange d for manual or automatic simultaneous lever 4 is actuated. Further movement of the control. Two methods of control arc described, Classified Advertisements lever 4 causes the lever 12, 13 t o tilt owing to the viz.:—(a) By a continuous cable extending over link 15 being incapable of further angular movement pulleys under each flap, and (6) by a series of nuts Minimum (12 Words or Less) : 3s. 6d. relative to the lever 12, 13. Two other similar rotate d by a flexible shaft on the ends of threaded Each additional word: 3d. linkages, but involving non-parallel links, arc links extending from bell-cranks on the flaps. described which cause an immediate tilting of the flap as well as a translational movement. In one case the gap is kept closed during the initial move men t by the flap remaining close against the upper AERONAUTICA L PLYWOOD rear edge of the fixed part of the plane. In the other case the lower end of the gap is kept closed THE Aeronautical & Panel Plywood Co., b y a plate 18, Fig. 4a, urged upwards by a spring Ltd., sole manufacturers of "MALLITE" when the flap reaches the position IIb. The plate and "APPCO" Brands all British Plywood, is returned to its normal position by a cam plate 218/22 6 Kingsland Road, London, E.2. 22 on a rod 20 connected to the lever 4 and having a slot 21 moving over the pivot 17 of the plate 18, Telephone : Bishopsgate 5641 (4 lines) th e plate 22 engaging a projection 19 on the plate 415,268 . Aircraft planes. Mattioli, G. D., 10A , Via Rogati, Padua, Italy. Sept. 6, 1933, No. 18. Another linkage is described having for its 24694. Convention date, Sept. 9, 1932. [Classes effect a continual widening of the gap as the aileron 4 and 114.] Drawings to specification. or flap is tilted. Fig. 7 shows a modification in which an independently operable braking flap 22 TRANSLATION S An aerofoil or hydrofoil such as an aeroplane is mounted beneath the aileron or flap II. This wing or an aerial or marine propeller blade has a FOR Translations at moderate rates by flap 22 is normally kept against the flap II by a wire or a lath of flat section or of any of the specialist in Technical Aeronautical work rubbe r or other spring 23 and is connected by a sections arranged at a point in front of the apply "Translator," Riverside House, Mortlake, cable 26 to a spring drum 29 on a lever 30. As the leading edge where it will render the flow of the flap II moves rearwardly the cable 26 unwinds from London, S.W.14. (Prospect 2743). limiting layer of air over each surface turbu (Reco.n'nented by the Editor, AIRCRAFT ENGINEERING) lent, the thickness of the wires or laths being comparable with the thickness of this layer. Two * These abstracts of complete specifications of patents recently or more wires may be grouped in parallel lines in published arc specially compiled, by permission of H.M. Stationery Office, from abridgments which are issued by the Office classified front of the aeroplane supported a t their ends with into groups. Sets of group abridgments can be obtained from mean s for varying their tension. One or more SITUATIO N WANTED the Patent Office, 25 Southampton Buildings, London, W.C.2, such wires may be placed at th e lower entrance to either sheet by sheet as issued, on payment of a subscription of AN; wide experience of workshop store- 5s. per group volume, or in bound volumes at 2s. each. Copies th e passage through a slotted wing. The laths of the full specifications can he obtained from the same address, keeping accounts, and control of men, seeks ma y be discontinuous and placed in line or displaced price 1s. each. axially from one another. The wire ma y serve also position in aircraft industry. Box No. 501, Except where otherwise stated, the specification is unaccom as a wireless aerial. Aircraft Engineering, 112, Bunhill Row, E.C.I. panied by drawings if none is reproduced.
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Jun 1, 1935
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