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160 AIRCRAFT ENGINEERING May, 1938 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,105,317 . Wheel. Frederick C. Frank , South and means for swinging the contracted shock 2,107,152 . Reversible Fuel Pump . Matthew Bend, Ind., assignor to Bendix Products Corpora absorbers upon their pivots in planes normal to the W . Huber, Chicago, Ill., assignor to Tutbill Pump tion , South Bend, Ind., a corporation of Indiana. pivots through approximately a right angle into Company, Chicago, Ill., a corporation of Illinois. Application Novcmher 19, 1934. Serial No. inoperative position. Application August 13, 1936. Serial No. 95,797. 753,593. 4 claims. [Class 301-6.] 7 claims. [Class 103-117.] 2,106,761 . Aeroplane. Dudley Roberts, New 1. A drop - York , and Frederick William Peel, Yonkers, N.Y., centr e aeroplane assignors to Rubatex Products, Inc., Wilmington wheel compris Del., a corporation of Delaware. Application ing two main Januar y 15, 1934. Serial No. 706,772. 3 claims. cast sections, a [Class. 244-133.] hu b portion car ried by each section, screw thread s formed in a portion of one of said hub sections locking mean s including a threade d sleeve having an abut 1. In an aeroplane, an aerofoil made of a hard men t slidable rigid integral continuous expanded rubber made of throug h a por a minute cellular structure, each of the cells being tion of the other individually scaled from the other cells, each con of said hub taining a gas admitte d at th e relatively high pressure section s and of 3,000 lb. per sq. in.; and reinforcing members 1. A pump unit comprising in combination, a engagin g the imbedded in said rubber for supporting fittings, said pum p housing having a face at one side and a pump thread s in said rubbe r containing a tough crust of rubber along the chambe r opening on to said face, means forming an hu b section, and reinforcing members. inlet duct for fluid terminating adjacent to said means including a pin to lock the sleeve against 2,106,827 . Aluminium Alloy. Robert H. face, a reversible rotor in the pump chamber, an rotation , relative t o said other hub section. Brown, New Kensington, Pa., assignor to Aluminum element having a face positioned in spaced relation Company of America, Pittsburgh, Pa., a corporation 2,105,662 . Air Chamber Diesel Engine. with said face of the pump housing and provided of Pennsylvania. Application May 25, 1936. Fran z Lang, Munich, Germany, assignor, by mesne with a pair of grooves therein, and a plate between Serial No. 81,599. 10 claims. [Class 148-32.] assignments, to Lano\a Corporation, New York, th e two faces having a suction slot, a pressure slot N. Y., a corporation of Delaware. Application and a fluid inlet port, and adapted when disposed December 9, 1935. Serial No. 53,541. In Germany in one position between said faces and the rotor is December 13, 1934. 3 claims. [Class 123-32.] driven in one direction to have th e inlet port thereof 1. In an injection engine of the character register with and effect communication between the described, a cylinder and a piston operating therein, inlet duct and one of th e grooves in th e element and a combustion chamber inwardly offset with respect also to hav e the suction slot register with and effect t o the cylinder and opening downward thereinto, communication between said one groove and the said chamber comprising in plan two lobes and a suction side of the pum p chamber and the pressure construction therebetween de slot register with the pressure side of the pump fining a n element of substantially chamber, and when disposed in a reverse position V-shape in plan projecting and between said faces and the rotor is driven in the tapering inward of said chamber opposite direction to have the inlet port thereof a t one side of said construction, register with and effect communication between the an air storage chamber opening inlet duct and the other groove in the element and into said constriction at the also to have the suction slot register with and effect other side thereof through a communication between said other groove and the 1. A cold worked aluminium base alloy contain restricted orifice aligned with the suction side of the pump chamber and the pressure ing from 5 t o 7 per cent magnesium and a relatively verte x of said element, and an injection nozzle slot register with the pressure side of said chamber. small amount of zinc dependent upon the mag a t said one side of said constriction disposed to nesium content, the proportion of zinc being inject fuel across said combustion chamber toward between 0·25 and 1 per cent for a magnesium con said orifice, said nozzle being disposed in proximity 2,105,682 . Aircraft Having Rotative ten t of 5 t o 6 per cent, and with linearly converging t o one side of said inwardly projecting element Sustainin g Wings. James Allan Jamiesok maximu m and minimum limits of 1 t o 0·75 per cent with its tip adjacent the base of said element, Bennett , Genista, Newton Mourns, and Frederien and 0·25 to 0·75 per cen t zinc, respectively, with an th e latter acting to split the hot blast fluid stream Leighton Hodgess, Clarkston, Scotland, assignors increasing concentration of magnesium of from ejected from said air atorage chamber through said to Autogiro Company of America, Willow Grove, 6 to 7 per cent, said alloy being characterised by orifice toward said element and to deflect the Pa. , a corporation of Delaware. Application substantia l freedom from stress cracking. portion s of the split stream laterally into said lobes Septembe r 13, 1935. Serial No. 40,386. In Great 2,106,934 . Landing Gear for Aircraft. and away from said nozzle, thereby shielding the Britain September 17, 1934. 33 claims. [Class Raymon d Saulnier, Puteaux, France. Application latte r from the hot blast ejected through said 244-18.] March 18, 1936. Serial No. 69,542. In Germany orifice. 2. In a March 19, 1935. 11 claims. [Class 244-108.] multi - 2,106,289 . Collapsible Strut. John F. 1. Landing gear lor aircraft comprising in com b 1 a d e d Wallace, Cleveland, Ohio, assignor to The Cleveland bination , a pair of runners, rigid rods linked t o and ai r craft Pneumati c Tool Company, Cleveland,' Ohio, a cor carrying each runner, and a deformable member sustaining poration of Ohio. Application January 30, 1935. associated with said rods and organised to resist roto r hav Serial No. 4,105. 9 claims. [Class 244-102.] th e aerodynamic stresses acting on the runner, ing a rota- while being capable of yielding to the pressure rive hub actin g on the runner on landing one of said rods part , a being linked at one end to a point near the front flappin g end of the runner, a lover pivotally connected with pivo t th e other end of said rod and with a point of assembl y anothe r of said rods, the bottom end of which is fo r a 1. In an aeroplane, a pair of hydro-pneumatic linked to the rear part of said runner. pluralit y shock absorbers pivotally mounted at their upper of blades, ends, a ground engaging member mounted on the th e as- lower end of each shock absorber an d carried thereby sembly in- exclusively, means controllable from the cockpit of cluding a th e aeroplane for contracting the shock absorbers, pivo t de * The above abstracts or patents granted in the United States vice rota- are taken, by permission of the Department of Commerce, from the t i v e 1 y Official Ga§ette of the United States Patent Office. Printed copies of mounte d the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, Washington, D.C., U.S.A. on the hub part, an d the blades being rotatively Except where otherwise stated, the specification is unaccompanied mounte d on said device. by drawings if none is reproduced.
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: May 1, 1938
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