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U.S. Patent Specifications

U.S. Patent Specifications part extending around portions of each of the power units and each end of the part being connected to each end of the frame section, each of the nacelles having other parts with one end of each of the parts being connected to the opposite ends of the frame section These details and drawings of patents granted in the United States are taken, by permission of the adjacent the points of connection of the first men­ Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies tioned part and extending around major portions of each of the power units to a point substantially of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, medially of the first mentioned part and connected Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, thereto with the ends of the second mentioned parts Southampton Buildings, Chancery Lane, London, W.C.2. being in spaced relationship. 2,516,819. Exhaust System. Frank Whittle, Rugby, England, assignor to Powet Jets (Research & Develop­ 2,515,861. Damped Bearing Support. Paul J. actuating means linked to one arm of the bell crank ment) Limited, London, England. Application August Campbell, East Hartford, Conn., assignor to United for rotating the bell crank about said pivotal axis, 24, 1945. In Great Britain February 1942. Aircraft Corporation, East Hartford, Conn., a cor­ and the other arm being engageable with a fixed An exhaust structure for a turbine comprising an poration of Delaware. Application June 29, 1945. abutment on the aircraft body when the leg comes to outer duct-defining wall, an inner element spaced The combination with a rotatable shaft having a occupy its landing position and having a lost motion from said wall and having a complementary duct- given natural frequency of vibration, of a bearing in connection to said leg comprising a pin engaging in defining surface, and at least two rod-like members which said shaft is adapted to rotate, a support for an aperture, said aperture having a larger diameter passing transversely through said wall and said ele­ said bearing having a natural vibration frequency than said pin, so that movement of the actuating ment and being slidably engaged with said element in different from that of said shaft, a floating ring means in one direction will first release the bell crank, planes at an angle one to the other and to the axis between said bearing and said support, at least one and further movement thereof by said actuating means of said wall. pin on said support projecting freely into said ring, at causes the leg to pivot between extended and retracted least one pin on said bearing projecting freely into said positions. ring, the pins on said support and said bearing being respectively angularly disposed in respect to each other and serving to hold said bearing against sub­ stantial rotation in respect to said support about the axis of said shaft, and vibration damping means between said bearing and said support. BRITISH STANDARD SPECIFICATIONS 2,516,123. Airplane Engine Controller. Clarence H. Copies of the following specifications may be obtained Jorgensen and William H. Taylor, Anderson, lnd., from the BRITISH STANDARDS INSTITUTION, assignors to General Motors Corporation, Detroit, Mich., a corporation of Delaware. Application April Sales Department, 24 Victoria Street, London, S.W.I, at the prices indicated. 10, 1944. 2,516,346. Aircraft Controlling System for Flaps and Landing Gear. Raymond Saulnier, Paris, France. Apparatus for controlling the intake pressure of an Application June 29, 1946. In France March 7, 1946. airplane engine having a main supercharger and an B.S. 328: 1950.—Twist Drills and Combined Drill In an aircraft provided with a retractable landing auxiliary supercharger, variable speed means for and Countersink (Centre Drills). gear and landing flaps, a single actuating mechanism driving the auxiliary supercharger, a member for B.S. 328, 'Twist and Straight Flute Drills', was controlling the variable speed driving means, a for both said landing gear and flaps, comprising a first published in 1928, and B.S. 985, 'Combined throttle valve for controlling intake pressure, a man­ driving shaft, a landing gear operating device, a Drills and Countersinks', was published in 1941. ually operated member, means operated thereby for landing flaps operating device, a control member Both subjects are now combined in this revised moving the throttle valve and for selecting a pressure having a first position for protraction of said landing edition of B.S. 328. The section dealing with twist to be maintained, a servo-motor for moving the gear and a second position for protraction of said throttle valve, means responsive to the pressure landing flaps, locking means for locking said control drills has been amended and extended, special selecting means and to engine intake pressure for member in its first position during the protraction attention having been given to the nomenclature controlling the servo-motor in order to position the movement of the landing gear, and means to release and definitions of drill parts, as a need for this throttle valve for maintaining the selected pressure, automatically said locking means when the landing has long been apparent. The testing requirements a second servo-motor for moving the speed-controlling gear is in its protracted position. have been brought up to date and the penetration member, an aneroid, means under control by the capabilities of the drills modernized and extended. manually operated member and by the aneroid for An important function of standardization is controlling the second servo-motor and means operated by the second servo-motor for modifying the that of reducing the multiplicity of types and in status of the pressure selecting means to increase the this connexion an important innovation in the selected pressure as the speed of the auxiliary super­ specification is the emphasis of 'preferred sizes' charger is increased. and the quotation of alternatives in the tables covering the drill gauge and letter sizes of twist drills. The section dealing with combined drills and 2,516,671. Jet Power Unit Mounting. Herbert L. countersinks (centre drills) has been presented in a Bowers and Robert A. Wolf, Kenmore, N.Y., manner similar to that of twist drills, and a com­ assignors to Bell Aircraft Corporation, Wheatfield, plete range of definitions has been included N.Y. Application March 21, 1946. In an airplane of the jet propulsion type comprising together with tables giving manufacturing limits a body having a frame section composed of girders, of tolerances. This section covers the provisions chord members, diagonal and vertical braces, jet of B.S. 985: 1941, which is accordingly super­ power units on each side of the body in juxtaposed seded. relationship thereto, nacelles enclosing the power units The dimensions of self-drive holding tapers are in space relationship thereto and substantially co­ mentioned in an appendix and are quoted from a extensive therewith, each of the nacelles having one British Standard which is in course of preparation. Price 6s. post free. 2,516,345. Landing Gear for Aircraft. Raymond B.S.G. 127. Power Transformers for Aircraft. Saulnier, Paris. France. Application June 29, 1946. In Applicable to transformers and auto-transformers France March 7, 1946. used in aircraft for supplying power from the aircraft An arrangement for controlling the inward or main A.C. supply, the transformers being rated from outward travel and the locking in the landing position 500 VA upwards. The aircraft A.C. supply may be in of a retractable undercarriage for aircraft, comprising one of two forms—voltage varying with frequency so a wheel-carrying shock absorbing leg pivotally that the ratio of volts to frequency remains substanti­ secured to the aircraft at an intermediate point of its ally constant, or constant voltage with variable length, a pivotal axis carried by said leg near its upper frequency. end, a bell crank pivoted centrally to said axis, Price 2s. 348 Aircraft Engineering http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

U.S. Patent Specifications

Aircraft Engineering and Aerospace Technology , Volume 22 (11): 1 – Nov 1, 1950

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb031972
Publisher site
See Article on Publisher Site

Abstract

part extending around portions of each of the power units and each end of the part being connected to each end of the frame section, each of the nacelles having other parts with one end of each of the parts being connected to the opposite ends of the frame section These details and drawings of patents granted in the United States are taken, by permission of the adjacent the points of connection of the first men­ Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies tioned part and extending around major portions of each of the power units to a point substantially of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, medially of the first mentioned part and connected Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, thereto with the ends of the second mentioned parts Southampton Buildings, Chancery Lane, London, W.C.2. being in spaced relationship. 2,516,819. Exhaust System. Frank Whittle, Rugby, England, assignor to Powet Jets (Research & Develop­ 2,515,861. Damped Bearing Support. Paul J. actuating means linked to one arm of the bell crank ment) Limited, London, England. Application August Campbell, East Hartford, Conn., assignor to United for rotating the bell crank about said pivotal axis, 24, 1945. In Great Britain February 1942. Aircraft Corporation, East Hartford, Conn., a cor­ and the other arm being engageable with a fixed An exhaust structure for a turbine comprising an poration of Delaware. Application June 29, 1945. abutment on the aircraft body when the leg comes to outer duct-defining wall, an inner element spaced The combination with a rotatable shaft having a occupy its landing position and having a lost motion from said wall and having a complementary duct- given natural frequency of vibration, of a bearing in connection to said leg comprising a pin engaging in defining surface, and at least two rod-like members which said shaft is adapted to rotate, a support for an aperture, said aperture having a larger diameter passing transversely through said wall and said ele­ said bearing having a natural vibration frequency than said pin, so that movement of the actuating ment and being slidably engaged with said element in different from that of said shaft, a floating ring means in one direction will first release the bell crank, planes at an angle one to the other and to the axis between said bearing and said support, at least one and further movement thereof by said actuating means of said wall. pin on said support projecting freely into said ring, at causes the leg to pivot between extended and retracted least one pin on said bearing projecting freely into said positions. ring, the pins on said support and said bearing being respectively angularly disposed in respect to each other and serving to hold said bearing against sub­ stantial rotation in respect to said support about the axis of said shaft, and vibration damping means between said bearing and said support. BRITISH STANDARD SPECIFICATIONS 2,516,123. Airplane Engine Controller. Clarence H. Copies of the following specifications may be obtained Jorgensen and William H. Taylor, Anderson, lnd., from the BRITISH STANDARDS INSTITUTION, assignors to General Motors Corporation, Detroit, Mich., a corporation of Delaware. Application April Sales Department, 24 Victoria Street, London, S.W.I, at the prices indicated. 10, 1944. 2,516,346. Aircraft Controlling System for Flaps and Landing Gear. Raymond Saulnier, Paris, France. Apparatus for controlling the intake pressure of an Application June 29, 1946. In France March 7, 1946. airplane engine having a main supercharger and an B.S. 328: 1950.—Twist Drills and Combined Drill In an aircraft provided with a retractable landing auxiliary supercharger, variable speed means for and Countersink (Centre Drills). gear and landing flaps, a single actuating mechanism driving the auxiliary supercharger, a member for B.S. 328, 'Twist and Straight Flute Drills', was controlling the variable speed driving means, a for both said landing gear and flaps, comprising a first published in 1928, and B.S. 985, 'Combined throttle valve for controlling intake pressure, a man­ driving shaft, a landing gear operating device, a Drills and Countersinks', was published in 1941. ually operated member, means operated thereby for landing flaps operating device, a control member Both subjects are now combined in this revised moving the throttle valve and for selecting a pressure having a first position for protraction of said landing edition of B.S. 328. The section dealing with twist to be maintained, a servo-motor for moving the gear and a second position for protraction of said throttle valve, means responsive to the pressure landing flaps, locking means for locking said control drills has been amended and extended, special selecting means and to engine intake pressure for member in its first position during the protraction attention having been given to the nomenclature controlling the servo-motor in order to position the movement of the landing gear, and means to release and definitions of drill parts, as a need for this throttle valve for maintaining the selected pressure, automatically said locking means when the landing has long been apparent. The testing requirements a second servo-motor for moving the speed-controlling gear is in its protracted position. have been brought up to date and the penetration member, an aneroid, means under control by the capabilities of the drills modernized and extended. manually operated member and by the aneroid for An important function of standardization is controlling the second servo-motor and means operated by the second servo-motor for modifying the that of reducing the multiplicity of types and in status of the pressure selecting means to increase the this connexion an important innovation in the selected pressure as the speed of the auxiliary super­ specification is the emphasis of 'preferred sizes' charger is increased. and the quotation of alternatives in the tables covering the drill gauge and letter sizes of twist drills. The section dealing with combined drills and 2,516,671. Jet Power Unit Mounting. Herbert L. countersinks (centre drills) has been presented in a Bowers and Robert A. Wolf, Kenmore, N.Y., manner similar to that of twist drills, and a com­ assignors to Bell Aircraft Corporation, Wheatfield, plete range of definitions has been included N.Y. Application March 21, 1946. In an airplane of the jet propulsion type comprising together with tables giving manufacturing limits a body having a frame section composed of girders, of tolerances. This section covers the provisions chord members, diagonal and vertical braces, jet of B.S. 985: 1941, which is accordingly super­ power units on each side of the body in juxtaposed seded. relationship thereto, nacelles enclosing the power units The dimensions of self-drive holding tapers are in space relationship thereto and substantially co­ mentioned in an appendix and are quoted from a extensive therewith, each of the nacelles having one British Standard which is in course of preparation. Price 6s. post free. 2,516,345. Landing Gear for Aircraft. Raymond B.S.G. 127. Power Transformers for Aircraft. Saulnier, Paris. France. Application June 29, 1946. In Applicable to transformers and auto-transformers France March 7, 1946. used in aircraft for supplying power from the aircraft An arrangement for controlling the inward or main A.C. supply, the transformers being rated from outward travel and the locking in the landing position 500 VA upwards. The aircraft A.C. supply may be in of a retractable undercarriage for aircraft, comprising one of two forms—voltage varying with frequency so a wheel-carrying shock absorbing leg pivotally that the ratio of volts to frequency remains substanti­ secured to the aircraft at an intermediate point of its ally constant, or constant voltage with variable length, a pivotal axis carried by said leg near its upper frequency. end, a bell crank pivoted centrally to said axis, Price 2s. 348 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Nov 1, 1950

There are no references for this article.