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Month in the Patent Office

Month in the Patent Office 312 AIRCRAFT ENGINEERING November, 1934 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 406,945 . Cooling Cylinders. Siemens & sleeves 20 having slots 22 in which engage pins 21 Halskc Akt.-Ges., Siemcnsstadt, Berlin. Sept. '26, on the shaft 13. Two lovers 23 on the sleeves 20 1933, No. 26492. Convention date, Sept. 27, 1932. are connected by cables 24 to the pins 16 on the [Class 7 (ii) ] two rods 14 so tha t the pins are withdrawn and the Cooling air is forced by a blower 4 into chambers join t broken before the pins 21 engage the ends of 7, 8, whence it is evenly distributed to the cylinders the slots 22 to cause rotation of the shaft 13. by slots 11, 12 which vary in width so tha t more air is supplied to the head ends of the cylinders. The jackets 9, 10 but t on to the cooling iins, which are shorter on the inlet than on the outlet side, where further slots 13, 14 allow the air to How out past push rods 28, 29 of the overhead-valve gear. The Th e shaft 13 is connected to sleeves 26, Fig. 2, sliding on rods 27 against the action of shock aileron is depressed the outboard portion carrying absorbers 29. the aileron is swept forwardly at an angle to the inboard portion, and this angle may be adjustable. 408,698 . Air screws. Barnwell, V. S„ and A single spa r wing is shown having th e inner portion Bristol Aeroplane Co., Ltd., Filton House, Bristol. of the spar set at right angles to the fuselage and Oct. 19, 1932, No. 29270. [Class 114.] the outer portion set at 9 dcg. forward of it. The Air screws in which the blades are lixed in oute r portion may be made relatively longer and cylindrical sockets are provided with bushes 14 set at a smaller angle such as 71 deg. The inner a t the outer extremities of the sockets 10, their portio n of the spar may alternatively be inclined interna l diameter being the same as that of forwardl y or rearwardly. To enable the angle th e sockets. These bushes extend beyond the between the inner and outer portions t o be adjusted, sockets and arc given a tapered edge 16. When the th e spars may be connected at a deep joint h4, Fig. 3, and adjusted from the cockpit by the screw gear shown. Filling pieces k, k1 fill th e gaps between th e adjacent edges of the wing portions. 408,435 . Aircraft landing-gear. Fairey Aviation Co., Ltd., Cranford Lane, Hayes , Williams, D . L. H., Hillside, Swakeley's Road, Ickenham, and Charnley, J. S., Beaumaris, North Hyde Road, Hayes , both in Middlesex. Feb. 27, 1933, No. 5958. [Class 4.] Th e landing-wheel of an aircraft is carried by a frame 12 supported by a rotary shaft 13 and normally stayed by a knuckle-jointed radius rod 14 pivote d to the wing a t 14K, means being provided for sequentially withdrawing a locking-pin 16, socket is in two parts, the bush is similarly made breaking the joint, and rotating the shaft 13 to an d each half is soldered into its corresponding raise the wheel into the wing. Preferably the recess in the socket. According to the Provisional chan bers 7, 8 are integral with the crankcase which member s 12, 14 arc duplicated and the wheel is Specification instead of the bush the socket itself is egg-shaped in section as shown. Further air is carried between them. A pneumatic or hydraulic ma y be extended or provided with a tapered discharged adjacent the exhaust valve housings 221 cylinder 18 acts on two levers 19, Fig. 4, on two resilient edge. which are of good heat-conducting material. In a modification as applied to an upright V-engine, the air is delivered to the space between the lines of cylinders at the opposite end to the blower and leaves outside the rows of cylinders in the direction of the blower. 407,009 . Aircraft wings . Vickers (Aviation), Ltd. , and Wallis, B. N., Byflcet Road, Weybridge, Surrey. Sept. 7, 1932, No. 24942. [Class 4.] To counteract twist on a cantilever wing when an * These abstracts of complete specifications of patents recently published are specially compiled, by permission of ll.M. Stationery Office, from abridgments which arc issued by the Office classified into croups. 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 bcund volumes at 2s. each. Copies of tbc full spccihc&tions can be obtained from the same address, price Is. each. Kxccpt wheic otherwise staled, the specification is unaccom­ panied l>y 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 (11): 1 – Nov 1, 1934
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029877
Publisher site
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Abstract

312 AIRCRAFT ENGINEERING November, 1934 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 406,945 . Cooling Cylinders. Siemens & sleeves 20 having slots 22 in which engage pins 21 Halskc Akt.-Ges., Siemcnsstadt, Berlin. Sept. '26, on the shaft 13. Two lovers 23 on the sleeves 20 1933, No. 26492. Convention date, Sept. 27, 1932. are connected by cables 24 to the pins 16 on the [Class 7 (ii) ] two rods 14 so tha t the pins are withdrawn and the Cooling air is forced by a blower 4 into chambers join t broken before the pins 21 engage the ends of 7, 8, whence it is evenly distributed to the cylinders the slots 22 to cause rotation of the shaft 13. by slots 11, 12 which vary in width so tha t more air is supplied to the head ends of the cylinders. The jackets 9, 10 but t on to the cooling iins, which are shorter on the inlet than on the outlet side, where further slots 13, 14 allow the air to How out past push rods 28, 29 of the overhead-valve gear. The Th e shaft 13 is connected to sleeves 26, Fig. 2, sliding on rods 27 against the action of shock aileron is depressed the outboard portion carrying absorbers 29. the aileron is swept forwardly at an angle to the inboard portion, and this angle may be adjustable. 408,698 . Air screws. Barnwell, V. S„ and A single spa r wing is shown having th e inner portion Bristol Aeroplane Co., Ltd., Filton House, Bristol. of the spar set at right angles to the fuselage and Oct. 19, 1932, No. 29270. [Class 114.] the outer portion set at 9 dcg. forward of it. The Air screws in which the blades are lixed in oute r portion may be made relatively longer and cylindrical sockets are provided with bushes 14 set at a smaller angle such as 71 deg. The inner a t the outer extremities of the sockets 10, their portio n of the spar may alternatively be inclined interna l diameter being the same as that of forwardl y or rearwardly. To enable the angle th e sockets. These bushes extend beyond the between the inner and outer portions t o be adjusted, sockets and arc given a tapered edge 16. When the th e spars may be connected at a deep joint h4, Fig. 3, and adjusted from the cockpit by the screw gear shown. Filling pieces k, k1 fill th e gaps between th e adjacent edges of the wing portions. 408,435 . Aircraft landing-gear. Fairey Aviation Co., Ltd., Cranford Lane, Hayes , Williams, D . L. H., Hillside, Swakeley's Road, Ickenham, and Charnley, J. S., Beaumaris, North Hyde Road, Hayes , both in Middlesex. Feb. 27, 1933, No. 5958. [Class 4.] Th e landing-wheel of an aircraft is carried by a frame 12 supported by a rotary shaft 13 and normally stayed by a knuckle-jointed radius rod 14 pivote d to the wing a t 14K, means being provided for sequentially withdrawing a locking-pin 16, socket is in two parts, the bush is similarly made breaking the joint, and rotating the shaft 13 to an d each half is soldered into its corresponding raise the wheel into the wing. Preferably the recess in the socket. According to the Provisional chan bers 7, 8 are integral with the crankcase which member s 12, 14 arc duplicated and the wheel is Specification instead of the bush the socket itself is egg-shaped in section as shown. Further air is carried between them. A pneumatic or hydraulic ma y be extended or provided with a tapered discharged adjacent the exhaust valve housings 221 cylinder 18 acts on two levers 19, Fig. 4, on two resilient edge. which are of good heat-conducting material. In a modification as applied to an upright V-engine, the air is delivered to the space between the lines of cylinders at the opposite end to the blower and leaves outside the rows of cylinders in the direction of the blower. 407,009 . Aircraft wings . Vickers (Aviation), Ltd. , and Wallis, B. N., Byflcet Road, Weybridge, Surrey. Sept. 7, 1932, No. 24942. [Class 4.] To counteract twist on a cantilever wing when an * These abstracts of complete specifications of patents recently published are specially compiled, by permission of ll.M. Stationery Office, from abridgments which arc issued by the Office classified into croups. 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 bcund volumes at 2s. each. Copies of tbc full spccihc&tions can be obtained from the same address, price Is. each. Kxccpt wheic otherwise staled, the specification is unaccom­ panied l>y drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Nov 1, 1934

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