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U.S. Patent Specifications

U.S. Patent Specifications able to said wing and so shaped as to shift the mean aerodynamic chord of said wing in parallel relation thereto outwardly from the fuselage, said wing tip and tank maintaining the centre of gravity of said wing fuselage, tip and tank within an allowable per­ These details and drawings of patents granted in the United States are taken, by permission of the centage range of movement along said last-mentioned Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies chord; and means for releasing said droppable wing of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, tip and tank from said wing after said fuel tank has Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, been emptied so that the centre of gravity of said wing Southampton Buildings, Chancery Lane, London, W.C.2. and fuselage is maintained within allowable percent­ age range of movement along the first-mentioned mean aerodynamic chord of said wing. 2,532,753. Transonic Airfoil Design. W.W.Breman, lower end thereof, a scissors linkage comprising Glendale, Calif., assignor to Lockheed Aircraft pivotally connected links one of which is pivoted to 2,537,477. Valve and Turbine Steels. Gunther Corporation, Burbank. Calif. Application July 5, the lower strut section and the other of which is Mohling, Loudonville and Thomas Y. Wilson, 1947. pivoted to the upper strut section, a roller carried by Albany, N.Y., assignors to Allegheny Ludlum Steel A high speed airfoil having a dominant basic sec­ the last-mentioned one of the links, a wheel-aligning cam mounted on said yoke and engaged by said roller Corporation, a corporation of Pennsylvania. Applica­ tion, and one or more depressions in the surfaces of when said shock strut is extended by the removal of tion January 15, 1947. Serial No. 722, 118. 8 Claims. the airfoil within the profile of said basic section, said ground load from the gear, a motor for turning the (Cl. 75—128.) depressions being generally triangular in shape and having one side, parallel to the line of airflow over the strut in the yoke for steering the aircraft on the ground, An improved, inexpensive, heat resistant alloy that airfoil, forming a relatively abrupt ridge, another side said motor comprising a cylinder and piston unit will withstand temperature variations and that has a being formed by the trailing edge of the airfoil and the connected to and arranged to act between the yoke better corrosion resistance at high temperatures with­ third side gradually merging into the basic airfoil sec­ and the upper strut section, and means connecting out an excessive loss of strength, said alloy containing tion in a line diagonally disposed relative to the line and acting between the aircraft and said yoke for below about 1 per cent carbon, about 12-26 per cent. of airflow over said airfoil, said diagonally disposed swinging the latter as a unit with said motor and chromium, about 3-20 per cent, nickel; molybdenum, line being so disposed as to predetermine the crest of shock strut and wheel about said transverse axis to tungsten, and columbium in a minimum total amount the compressibility shock wave formed at transonic raise the gear into retracted position within the air­ of about 1·2 per cent, and up to a total amount of airflow speeds. craft. substantially less than 6 per cent. and the remainder iron; all of the named elements as its essential elements, with usual commercial amounts of the elements 2,537,240. Air Speed Indicator. Richard Shaw, Jr., manganese and silicon. Bcrgenficld, N.J., assignor to Bendix Aviation Cor­ poration, Tetcrboro, N.J., a corporation of Delaware. Application February 1, 1946. Serial No. 644,838. 7 Claims. (Cl. 73—182.) 2,534,791. Temperature Compensated Control Rod. In an airspeed indicator having a dial and a pointer, Edward L. Moyer, Reynoldsburg, Ohio, assignor to and means for rotating the pointer to show airspeed; Curtiss-Wright Corporation, a corporation of Dela­ the combination comprising a pressure responsive ware. Application October 14, 1948. member subjected to atmospheric pressure, a link In an aircraft control system having a push-pull pivoted to said member and movable thereby, a pin in rod passing through a zone subjected to substantial said link, a shaft, a pin in said shaft extending radially temperature variation, said rod comprising three tele­ therefrom and adapted to abut said first pin for rotat­ scoped tubes, one pair of said three tubes being ing said shaft upon movement of said link, a second secured together adjacent one end thereof and pointer coaxial with said first pointer adapted to be another pair of said three tubes being secured together rotated with respect to said dial upon rotation of said adjacent the opposite end thereof by fasteners which shaft for indicating the maximum airspeed in compari­ extend substantially diametrically through the tubes, son with the airspeed indicated by said first pointer, the ends of the tubes not so secured by said fasteners and means for moving said link in a direction trans­ having elongated openings passing said fasteners, said verse to its movement by said member to vary the ends of the tubes not so secured being axially slidable rotation of said shaft by said link in conformity with relative to the secured tube ends and being connected the Mach number of the particular aircraft in which to the control system, the two tubes which have their 2,537,580. Servo-Anemometer Device. Eugene the instrument is mounted. ends so connected to the control system being of steel Francois Gilbert Gamier, Nice, Alpes-Maritimes, and the other tube being of aluminium, whereby said France. Application March 3, 1948. Serial No. last mentioned two tubes have a temperature co­ 12,818. In France June 15, 1945. 3 Claims. (Cl. 73— efficient of expansion approximately half that of the 182.) material of the other tube and whereby the length of In a servo-anemometer of the type described for the rod is therefore substantially unaffected by the inducing a movement the speed of which is in direct temperature changes which it will encounter in said ratio with the air speed of an aircraft, a frame, drive zone. means mounted on said frame, a rotatable shaft on said frame, transmission means from said drive means to said shaft, means for maintaining the speed of said shaft constant, a cam of revolution secured on said shaft and the generatrix of which is a curve representative of a function of a support movable with respect to said frame, a second shaft on said movable support parallel with said first shaft and rotatable at a speed in direct ratio to the air speed of 2,535,167. Aircraft Wheel Centering Mechanism. the aircraft, a rotatable member movable parallel with Clovis W. Smith, Worthington and John E. Warner, said first rotatable shaft, supported on and drivingly Columbus, Ohio, assignors to Curtiss-Wright Cor­ 2,537,369. Droppable Wing Tank Incorporating connected with said second shaft and adapted to re­ poration, a corporation of Delaware. Application Additional Wing Area. Alexander E. Ostroff, St Louis, main tangent with the surface of said cam, resilient June 11, 1948. Serial No. 32,346. 9 Claims. (Cl. 244— Mo., assignor to McDonnell Aircraft Corporation, means urging the support and thereby said movable 50.) St. Louis, Mo., a corporation of Maryland. Applica­ member against said cam, and means for moving Jn a steerable and retractable aircraft landing gear, a tion January 29, 1948. Serial No. 5,036. 8 Claims. (Cl. said movable member as a function of the current yoke pivoted about a transverse axis to the aircraft, 244—135.) a shock strut having an upper section journaled in the In an aircraft, a fuselage; a swept-back wing value of yoke for turning about an axis that is substantially secured to said fuselage, whose mean aero-dynamic upright when the gear is lowered, said shock strut also chord is in one position; an auxiliary fuel tank; a having a lower section telescoping with respect to said droppable wing tip for supporting said tank and secur- upper section and carrying a landing wheel at the 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 23 (4): 1 – Apr 1, 1951
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032026
Publisher site
See Article on Publisher Site

Abstract

able to said wing and so shaped as to shift the mean aerodynamic chord of said wing in parallel relation thereto outwardly from the fuselage, said wing tip and tank maintaining the centre of gravity of said wing fuselage, tip and tank within an allowable per­ These details and drawings of patents granted in the United States are taken, by permission of the centage range of movement along said last-mentioned Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies chord; and means for releasing said droppable wing of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, tip and tank from said wing after said fuel tank has Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, been emptied so that the centre of gravity of said wing Southampton Buildings, Chancery Lane, London, W.C.2. and fuselage is maintained within allowable percent­ age range of movement along the first-mentioned mean aerodynamic chord of said wing. 2,532,753. Transonic Airfoil Design. W.W.Breman, lower end thereof, a scissors linkage comprising Glendale, Calif., assignor to Lockheed Aircraft pivotally connected links one of which is pivoted to 2,537,477. Valve and Turbine Steels. Gunther Corporation, Burbank. Calif. Application July 5, the lower strut section and the other of which is Mohling, Loudonville and Thomas Y. Wilson, 1947. pivoted to the upper strut section, a roller carried by Albany, N.Y., assignors to Allegheny Ludlum Steel A high speed airfoil having a dominant basic sec­ the last-mentioned one of the links, a wheel-aligning cam mounted on said yoke and engaged by said roller Corporation, a corporation of Pennsylvania. Applica­ tion, and one or more depressions in the surfaces of when said shock strut is extended by the removal of tion January 15, 1947. Serial No. 722, 118. 8 Claims. the airfoil within the profile of said basic section, said ground load from the gear, a motor for turning the (Cl. 75—128.) depressions being generally triangular in shape and having one side, parallel to the line of airflow over the strut in the yoke for steering the aircraft on the ground, An improved, inexpensive, heat resistant alloy that airfoil, forming a relatively abrupt ridge, another side said motor comprising a cylinder and piston unit will withstand temperature variations and that has a being formed by the trailing edge of the airfoil and the connected to and arranged to act between the yoke better corrosion resistance at high temperatures with­ third side gradually merging into the basic airfoil sec­ and the upper strut section, and means connecting out an excessive loss of strength, said alloy containing tion in a line diagonally disposed relative to the line and acting between the aircraft and said yoke for below about 1 per cent carbon, about 12-26 per cent. of airflow over said airfoil, said diagonally disposed swinging the latter as a unit with said motor and chromium, about 3-20 per cent, nickel; molybdenum, line being so disposed as to predetermine the crest of shock strut and wheel about said transverse axis to tungsten, and columbium in a minimum total amount the compressibility shock wave formed at transonic raise the gear into retracted position within the air­ of about 1·2 per cent, and up to a total amount of airflow speeds. craft. substantially less than 6 per cent. and the remainder iron; all of the named elements as its essential elements, with usual commercial amounts of the elements 2,537,240. Air Speed Indicator. Richard Shaw, Jr., manganese and silicon. Bcrgenficld, N.J., assignor to Bendix Aviation Cor­ poration, Tetcrboro, N.J., a corporation of Delaware. Application February 1, 1946. Serial No. 644,838. 7 Claims. (Cl. 73—182.) 2,534,791. Temperature Compensated Control Rod. In an airspeed indicator having a dial and a pointer, Edward L. Moyer, Reynoldsburg, Ohio, assignor to and means for rotating the pointer to show airspeed; Curtiss-Wright Corporation, a corporation of Dela­ the combination comprising a pressure responsive ware. Application October 14, 1948. member subjected to atmospheric pressure, a link In an aircraft control system having a push-pull pivoted to said member and movable thereby, a pin in rod passing through a zone subjected to substantial said link, a shaft, a pin in said shaft extending radially temperature variation, said rod comprising three tele­ therefrom and adapted to abut said first pin for rotat­ scoped tubes, one pair of said three tubes being ing said shaft upon movement of said link, a second secured together adjacent one end thereof and pointer coaxial with said first pointer adapted to be another pair of said three tubes being secured together rotated with respect to said dial upon rotation of said adjacent the opposite end thereof by fasteners which shaft for indicating the maximum airspeed in compari­ extend substantially diametrically through the tubes, son with the airspeed indicated by said first pointer, the ends of the tubes not so secured by said fasteners and means for moving said link in a direction trans­ having elongated openings passing said fasteners, said verse to its movement by said member to vary the ends of the tubes not so secured being axially slidable rotation of said shaft by said link in conformity with relative to the secured tube ends and being connected the Mach number of the particular aircraft in which to the control system, the two tubes which have their 2,537,580. Servo-Anemometer Device. Eugene the instrument is mounted. ends so connected to the control system being of steel Francois Gilbert Gamier, Nice, Alpes-Maritimes, and the other tube being of aluminium, whereby said France. Application March 3, 1948. Serial No. last mentioned two tubes have a temperature co­ 12,818. In France June 15, 1945. 3 Claims. (Cl. 73— efficient of expansion approximately half that of the 182.) material of the other tube and whereby the length of In a servo-anemometer of the type described for the rod is therefore substantially unaffected by the inducing a movement the speed of which is in direct temperature changes which it will encounter in said ratio with the air speed of an aircraft, a frame, drive zone. means mounted on said frame, a rotatable shaft on said frame, transmission means from said drive means to said shaft, means for maintaining the speed of said shaft constant, a cam of revolution secured on said shaft and the generatrix of which is a curve representative of a function of a support movable with respect to said frame, a second shaft on said movable support parallel with said first shaft and rotatable at a speed in direct ratio to the air speed of 2,535,167. Aircraft Wheel Centering Mechanism. the aircraft, a rotatable member movable parallel with Clovis W. Smith, Worthington and John E. Warner, said first rotatable shaft, supported on and drivingly Columbus, Ohio, assignors to Curtiss-Wright Cor­ 2,537,369. Droppable Wing Tank Incorporating connected with said second shaft and adapted to re­ poration, a corporation of Delaware. Application Additional Wing Area. Alexander E. Ostroff, St Louis, main tangent with the surface of said cam, resilient June 11, 1948. Serial No. 32,346. 9 Claims. (Cl. 244— Mo., assignor to McDonnell Aircraft Corporation, means urging the support and thereby said movable 50.) St. Louis, Mo., a corporation of Maryland. Applica­ member against said cam, and means for moving Jn a steerable and retractable aircraft landing gear, a tion January 29, 1948. Serial No. 5,036. 8 Claims. (Cl. said movable member as a function of the current yoke pivoted about a transverse axis to the aircraft, 244—135.) a shock strut having an upper section journaled in the In an aircraft, a fuselage; a swept-back wing value of yoke for turning about an axis that is substantially secured to said fuselage, whose mean aero-dynamic upright when the gear is lowered, said shock strut also chord is in one position; an auxiliary fuel tank; a having a lower section telescoping with respect to said droppable wing tip for supporting said tank and secur- upper section and carrying a landing wheel at the Aircraft Engineering

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Apr 1, 1951

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