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Month in the Patent Office

Month in the Patent Office October, 1931 AIRCRAFT ENGINEERING 267 A Selection of the More Important Aircraft and Engine Specifications Published Recently 347,488 . Aircraft planes . Boulton & Pau l Ltd., 12 on the carriage 3 which engage with a transverse Riverside Works, and North, J. D., Hill House, pin 20 in the member 13 a t or near the nodal point Eato n Hill, both in Norwich. May 1, 1930. No. 5. The abutmen t 12 is restrained against rearward 13439. [Class 4.] movemen t by a pivoted catch 27. Aeroplane wings, ailerons, &c., comprising trans­ verse diaphragms carried on spars, have bent metal 349,209 . Regulating; spray carburettors. sections with beaded borders sprung into notches Royce, Sir F. II., Nightingale Road, Derby. in the diaphragms to form the curved portions of March 27, 1930, No. 9745. [Classes 7 (iii), 7 (iv), th e wing section. Fig. 1 shows an aileron in which an d 7 (vi).] composite diaphragms consisting of plates 1, 2, 3, I n means for regulating aircraft engines accord­ connected by stays 4, 5, 6, are secured to the spar. ing to altitude, the petrol-metering device, or the Notches such as 8, 12 are formed in the plates ignition timing, or both, are adjusted by an aneroid 1, 2, 3 to take the beaded edges 10 of sections such device acting through a relay comprising a recipro­ as tha t shown in Fig. 3, the surfaces of which are catin g device subjected to the pressure from the flush with the stays 4, 5, 6 when in position so as supercharging-blower. Fig. 1 shows the general to form a smooth support for a fabric covering. arrangemen t of the control means, comprising an The sections are rolled so that they have to be aneroid and relay device a connected by linkage a3, sprung more open as they are fixed in position. position by a setscrew d. Applications to balanced an d unbalanced elevators and to an unbalanced rudde r are described. Fig. 5 shows a balance weight HI, the leverage of which can be varied in flight. The weight m is clamped to an arm n carried by a worm wheel o rotatabl e on the elevator 347,659 . Controlling aeroplanes. Rohrbach, cross-spar t an d turned by a worm on a spindle p A., 12, Ruhrstrasse, Wilmersdorf, Berlin. Oct. 24, when this is rotated by means of a cable r. 1929, No. 32363. Convention date, Oct. 24, 1928. Void [Published under Sect. 91 of the Acts]. [Class 348,845 . Aircraft launching apparatus. Heinkel, E., 15, Seestrasse, Warnemunde, Germany. Aeroplanes fitted with auxiliary planes for auto­ April 17, 1930, No. 12279. Convention date, April matically producing a slot at the leading edge 18, 1929. [Class 4.] of the wing are provided with means for preventing A float seaplane is mounted on the starting the opening of the slot, or for closing it when carriage of a launching track in such a manner open, at will. Where the slot mechanism is inter­ tha t the supporting and accelerating forces are connected to a manually operable rear plane 15, applie d at nodal points of the undercarriage inter­ means are provided also for disengaging the slot mediat e and above the floats. A float under­ mechanism from the plane. A slot-forming plane 3 carriage 1, Fig. 1, comprises front and rear sets of is supported on links 6, 7 so as to open automatic­ triangulate d members 6, front and rare transverse ally at large angles of incidence of the plane, but members, side longitudinal members and a central the arm 6 is connected by a cable 12 to a lever at longitudinal member 13; the points of attachment the pilot's scat. The mechanism is duplicated on of members 6, and the transverse member, to the the two sides of the machine. In the arrangement ends of the member 13 constitute nodal points 5, 9. Th e machine is supporte d at the front by a T-shaped shoe engaging in a grooved guide-member 8, Fig. 3, on the starting carriage 3. At the rear the trans­ verse members are upwardly inclined to the point 9 causing the machine to rest in a tail-down position on a rear support which may be similar to the front one or simply be a rest. Hooks 11, Fig. 4, shown the lever 6 is mounted on a shaft 16 which ma y be provided to prevent the rear of the machine is normall y clutched to a lever 17 connected through a5 to a lever c, which is pivoted a t cl and connected from rising, additional bracing struts 16 may be rods 13, 14 t o the rear plane 15 which tilts and also also to a floating lever c2, th e opposite ends of which attache d to the transverse members at the points varies a slot 22 through the plane. When the of engagement of the hooks. The propulsion force ar e connected by a link b9 to the ignition-timing pilot moves the cable 12 to close or lock the slot is transmitte d to the machine b y pivoted abutments mean s b8, and by links b3, b4 to the carburettor mechanism the clutch connecting the lever 17 to throttl e b1 and the pilot's control b5. The lever c the shaft 16 is simultaneously disengaged. is further connected by a link b11 to the petrol- meterin g device b10. The device a comprises a 348,788 . Controlling air and water craft. casing containing an aneroid chamber d, Fig. 2, Fairey Aviation Co., Ltd., Cranford Lane, Hayes, an d having an extension comprising a cylinder d1 Middlesex, and Macmillan, N., Ivory House, Ivcr, in which reciprocates a piston d2. This piston has Buckinghamshire. March 21, 1930, No. 9149. opposite extensions e, e1, the latter of which is [Classes 4 and 114.] connected to the lever a3. Within the extensions Pivoted control surfaces, which may or may not c, el slides a valve ƒ connected at ƒ1 to the aneroid have dynamic balance portions, are provided with a chambe r and formed with a partition g and with counterweight adapted slightly to overbalance the port s g1 . . g4. The port gl is constantly open to surface by bringing its centre of gravity in advance a pipe a1 leading to the outlet of the supercharging- of the pivotal axis. I'n an application to an aero­ blower, and the port g4 to a pipe a2 leading to the plane rudder, Fig. 2, a balance weight c is slidable inlet of the blower, while the ports g2 and g3 control on an arm b formed integrally with a balance respectively pairs of ports il, i5, and i6, i7 connected portion c of th e rudder a. The weight is clamped in t o opposite sides of the piston d2. Thus, when the valv e ƒ is moved in either direction by the aneroid, th e piston d2 is caused to follow the valve and thu s actuates the ignition and/or petrol controls. Fig. 3 shows a petrol-metering device, in which th e flow of petrol through an orifice k5 in a flange k4 is regulated by rotation, by means of the arm b16. of an eccentric member k8 beneath the orifice. 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 3 (10): 1 – Oct 1, 1931
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029466
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Abstract

October, 1931 AIRCRAFT ENGINEERING 267 A Selection of the More Important Aircraft and Engine Specifications Published Recently 347,488 . Aircraft planes . Boulton & Pau l Ltd., 12 on the carriage 3 which engage with a transverse Riverside Works, and North, J. D., Hill House, pin 20 in the member 13 a t or near the nodal point Eato n Hill, both in Norwich. May 1, 1930. No. 5. The abutmen t 12 is restrained against rearward 13439. [Class 4.] movemen t by a pivoted catch 27. Aeroplane wings, ailerons, &c., comprising trans­ verse diaphragms carried on spars, have bent metal 349,209 . Regulating; spray carburettors. sections with beaded borders sprung into notches Royce, Sir F. II., Nightingale Road, Derby. in the diaphragms to form the curved portions of March 27, 1930, No. 9745. [Classes 7 (iii), 7 (iv), th e wing section. Fig. 1 shows an aileron in which an d 7 (vi).] composite diaphragms consisting of plates 1, 2, 3, I n means for regulating aircraft engines accord­ connected by stays 4, 5, 6, are secured to the spar. ing to altitude, the petrol-metering device, or the Notches such as 8, 12 are formed in the plates ignition timing, or both, are adjusted by an aneroid 1, 2, 3 to take the beaded edges 10 of sections such device acting through a relay comprising a recipro­ as tha t shown in Fig. 3, the surfaces of which are catin g device subjected to the pressure from the flush with the stays 4, 5, 6 when in position so as supercharging-blower. Fig. 1 shows the general to form a smooth support for a fabric covering. arrangemen t of the control means, comprising an The sections are rolled so that they have to be aneroid and relay device a connected by linkage a3, sprung more open as they are fixed in position. position by a setscrew d. Applications to balanced an d unbalanced elevators and to an unbalanced rudde r are described. Fig. 5 shows a balance weight HI, the leverage of which can be varied in flight. The weight m is clamped to an arm n carried by a worm wheel o rotatabl e on the elevator 347,659 . Controlling aeroplanes. Rohrbach, cross-spar t an d turned by a worm on a spindle p A., 12, Ruhrstrasse, Wilmersdorf, Berlin. Oct. 24, when this is rotated by means of a cable r. 1929, No. 32363. Convention date, Oct. 24, 1928. Void [Published under Sect. 91 of the Acts]. [Class 348,845 . Aircraft launching apparatus. Heinkel, E., 15, Seestrasse, Warnemunde, Germany. Aeroplanes fitted with auxiliary planes for auto­ April 17, 1930, No. 12279. Convention date, April matically producing a slot at the leading edge 18, 1929. [Class 4.] of the wing are provided with means for preventing A float seaplane is mounted on the starting the opening of the slot, or for closing it when carriage of a launching track in such a manner open, at will. Where the slot mechanism is inter­ tha t the supporting and accelerating forces are connected to a manually operable rear plane 15, applie d at nodal points of the undercarriage inter­ means are provided also for disengaging the slot mediat e and above the floats. A float under­ mechanism from the plane. A slot-forming plane 3 carriage 1, Fig. 1, comprises front and rear sets of is supported on links 6, 7 so as to open automatic­ triangulate d members 6, front and rare transverse ally at large angles of incidence of the plane, but members, side longitudinal members and a central the arm 6 is connected by a cable 12 to a lever at longitudinal member 13; the points of attachment the pilot's scat. The mechanism is duplicated on of members 6, and the transverse member, to the the two sides of the machine. In the arrangement ends of the member 13 constitute nodal points 5, 9. Th e machine is supporte d at the front by a T-shaped shoe engaging in a grooved guide-member 8, Fig. 3, on the starting carriage 3. At the rear the trans­ verse members are upwardly inclined to the point 9 causing the machine to rest in a tail-down position on a rear support which may be similar to the front one or simply be a rest. Hooks 11, Fig. 4, shown the lever 6 is mounted on a shaft 16 which ma y be provided to prevent the rear of the machine is normall y clutched to a lever 17 connected through a5 to a lever c, which is pivoted a t cl and connected from rising, additional bracing struts 16 may be rods 13, 14 t o the rear plane 15 which tilts and also also to a floating lever c2, th e opposite ends of which attache d to the transverse members at the points varies a slot 22 through the plane. When the of engagement of the hooks. The propulsion force ar e connected by a link b9 to the ignition-timing pilot moves the cable 12 to close or lock the slot is transmitte d to the machine b y pivoted abutments mean s b8, and by links b3, b4 to the carburettor mechanism the clutch connecting the lever 17 to throttl e b1 and the pilot's control b5. The lever c the shaft 16 is simultaneously disengaged. is further connected by a link b11 to the petrol- meterin g device b10. The device a comprises a 348,788 . Controlling air and water craft. casing containing an aneroid chamber d, Fig. 2, Fairey Aviation Co., Ltd., Cranford Lane, Hayes, an d having an extension comprising a cylinder d1 Middlesex, and Macmillan, N., Ivory House, Ivcr, in which reciprocates a piston d2. This piston has Buckinghamshire. March 21, 1930, No. 9149. opposite extensions e, e1, the latter of which is [Classes 4 and 114.] connected to the lever a3. Within the extensions Pivoted control surfaces, which may or may not c, el slides a valve ƒ connected at ƒ1 to the aneroid have dynamic balance portions, are provided with a chambe r and formed with a partition g and with counterweight adapted slightly to overbalance the port s g1 . . g4. The port gl is constantly open to surface by bringing its centre of gravity in advance a pipe a1 leading to the outlet of the supercharging- of the pivotal axis. I'n an application to an aero­ blower, and the port g4 to a pipe a2 leading to the plane rudder, Fig. 2, a balance weight c is slidable inlet of the blower, while the ports g2 and g3 control on an arm b formed integrally with a balance respectively pairs of ports il, i5, and i6, i7 connected portion c of th e rudder a. The weight is clamped in t o opposite sides of the piston d2. Thus, when the valv e ƒ is moved in either direction by the aneroid, th e piston d2 is caused to follow the valve and thu s actuates the ignition and/or petrol controls. Fig. 3 shows a petrol-metering device, in which th e flow of petrol through an orifice k5 in a flange k4 is regulated by rotation, by means of the arm b16. of an eccentric member k8 beneath the orifice.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Oct 1, 1931

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