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Month in the Patent Office

Month in the Patent Office These abstracts of British Patent Specifications are condensed, by permission, from the official specifications. Copies of the full specifications are obtainable from the Patent Office, 25 Southampton Buildings, W.C.2, price 3s. each. 722,247. Artificial feel systems. Northrop Aircraft pilot, and an indicator is fitted in the cockpit to show Inc. Application December 22, 1952. the setting of the stabilizer. Such adjustment eliminates reversal of pilot's stick control during transition from In order to avoid the imposition of excessive acceler­ power-on to power-off conditions when the pitching ation in a direction parallel to the normal axis of an moments are changed by cargo affecting the pitching aircraft the control system for a power-operated ele­ moment of the fuselage. The stabilizer may be fixed, vator 12 includes an artificial feel unit arranged to im­ FIG. 3 showing an arrangement in which two perpen- pose force on the pilot's control column 8 in response pipe 2, but by rotating the inner sleeve 9 the holes 8, dicular triangular portions 64 are secured to the tail to such accelerations. In the arrangement shown in 11 may be brought into alignment to deflect the jet cone 14 and directed outwardly and downwardly FIG. 1 an accelerometer 1 is placed with its axis through the nozzle 3. The apertures may be brought from the cone axis, while FIG. 4 shows a pair of sym­ into register by sliding one of the sleeves axially in­ metrical triangular members carried on stub arms 68 stead of by rotating it. to be clear of the turbulent flow along the cone 14. Vertical fins may be fitted to the stabilizer to give in­ creased directional stability. 723,817. Stowage compartments. Folland Aircraft Ltd. and W. E. W. Petter. Application June 30, 1952. A jet-propelled aircraft is provided with laterally- 722,857. Aircraft structures. L. C. Heal. Applica­ disposed air intakes 13 communicating by ducts 14 tion March 20, 1951. with a gas turbine 11, the compartments 17 between A structure such as a fuselage or engine nacelle is these ducts and the sides 16 of the fuselage being used formed as a longitudinally-divided hollow structure for the stowage of equipment such as guns and the constituted by separately made longitudinally curved undercarriage. In the arrangement shown the guns 18 sections, each section being formed from tapered flat are mounted with their muzzles disposed near the plates as described in 702,981 (see AIRCRAFT ENGIN­ ends of the ducts 14 so as to be capable of firing EERING, April, 1954). FIG. 2 shows a fuselage made from two half sections 1,1A secured together along their longitudinal edges, such construction facilitating the installation of equipment inside the fuselage. In the case of a double-walled engine nacelle the stiffeners parallel to the aircraft's normal axis, its output being for the outer wall are arranged on its interior surface fed to main and rate amplifiers 2, 21, respectively, con­ while those for the inner wall are arranged on its trolling the output of a generator 3 driven by a separ­ exterior surface. ately excited motor 4, the generator driving a torque motor 6 connected to the control column 8 by a belt 7. The provision of the rate amplifier 21 ensures that the force applied to the column 8 will be high if the acceleration is changing rapidly even though the in­ stantaneous magnitude of the acceleration may be low. The circuit is so arranged that positive accelera­ tion produces a forward stick force, so that if the machine is flown hands-off by the pilot accelerations tending to be built up by gusts will be automatically relieved. A trim control 23 may be fitted to the main amplifier 2. through the air intakes 13, closure flaps for the muzzles being opened automatically when the guns are fired. An ammunition box may be mounted below 722,556. Helicopter stabilizers. United Aircraft each gun. The undercarriage units 21 are pivoted for Corporation. Application in U.S.A. September 20, rearward retraction immediately to the rear of the guns. A stabilizer surface for a helicopter is of aerofoil section and triangular plan form with low aspect ratio —less than 3 and preferably between 1·3 and 2·5— 724,019. De-icing equipment. Joseph Halbert. 723,160. Jet Deflectors. Power Jets (Research and and is of symmetrical form with respect to the fore- Application July 15, 1952. Development) Ltd. Application July 8, 1952. and-aft axis. As shown in FIG. 5 the stabilizer 34 is car­ A distributor for de-icing liquid consists of an outer ried on a transverse shaft 38 mounted parallel to and A jet deflector consists of nested outer and inner porous bronze sheet 1 backed by a flexible micro- slightly above the axis 22 of the tail rotor. The shaft is conical or cylindrical sleeves 5, 9 respectively provided porous sheet 2, which is preferably of polyvinyl- rotated by a reversible electric motor controlled by the with sets of apertures 7, 8 and 10, 11, which, by relative chloride treated in the manner described in Specifica­ rotation of the sleeves, may be brought into register tion 565,022, and spaced by washers 3 from a sheet 4 to allow the jet to flow through the tail pipe 2 or of hard neoprene, the space 5 between the sheets through an alternative outlet, such as a downwardly being connected to a metering adaptor 9. The edges of directed nozzle 3. As shown the apertures 7, 10 are the space 5 are sealed by strips 6. The sheet 2 is re­ aligned allowing the jet to discharge through the tail placed by a fresh one when its pores become blocked and impede the flow of liquid. As shown the distri­ butor is arranged as an over-shoe to the leading edge skin 7, but it can be built into the leading edge. June 1955 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 27 (6): 1 – Jun 1, 1955
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032570
Publisher site
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Abstract

These abstracts of British Patent Specifications are condensed, by permission, from the official specifications. Copies of the full specifications are obtainable from the Patent Office, 25 Southampton Buildings, W.C.2, price 3s. each. 722,247. Artificial feel systems. Northrop Aircraft pilot, and an indicator is fitted in the cockpit to show Inc. Application December 22, 1952. the setting of the stabilizer. Such adjustment eliminates reversal of pilot's stick control during transition from In order to avoid the imposition of excessive acceler­ power-on to power-off conditions when the pitching ation in a direction parallel to the normal axis of an moments are changed by cargo affecting the pitching aircraft the control system for a power-operated ele­ moment of the fuselage. The stabilizer may be fixed, vator 12 includes an artificial feel unit arranged to im­ FIG. 3 showing an arrangement in which two perpen- pose force on the pilot's control column 8 in response pipe 2, but by rotating the inner sleeve 9 the holes 8, dicular triangular portions 64 are secured to the tail to such accelerations. In the arrangement shown in 11 may be brought into alignment to deflect the jet cone 14 and directed outwardly and downwardly FIG. 1 an accelerometer 1 is placed with its axis through the nozzle 3. The apertures may be brought from the cone axis, while FIG. 4 shows a pair of sym­ into register by sliding one of the sleeves axially in­ metrical triangular members carried on stub arms 68 stead of by rotating it. to be clear of the turbulent flow along the cone 14. Vertical fins may be fitted to the stabilizer to give in­ creased directional stability. 723,817. Stowage compartments. Folland Aircraft Ltd. and W. E. W. Petter. Application June 30, 1952. A jet-propelled aircraft is provided with laterally- 722,857. Aircraft structures. L. C. Heal. Applica­ disposed air intakes 13 communicating by ducts 14 tion March 20, 1951. with a gas turbine 11, the compartments 17 between A structure such as a fuselage or engine nacelle is these ducts and the sides 16 of the fuselage being used formed as a longitudinally-divided hollow structure for the stowage of equipment such as guns and the constituted by separately made longitudinally curved undercarriage. In the arrangement shown the guns 18 sections, each section being formed from tapered flat are mounted with their muzzles disposed near the plates as described in 702,981 (see AIRCRAFT ENGIN­ ends of the ducts 14 so as to be capable of firing EERING, April, 1954). FIG. 2 shows a fuselage made from two half sections 1,1A secured together along their longitudinal edges, such construction facilitating the installation of equipment inside the fuselage. In the case of a double-walled engine nacelle the stiffeners parallel to the aircraft's normal axis, its output being for the outer wall are arranged on its interior surface fed to main and rate amplifiers 2, 21, respectively, con­ while those for the inner wall are arranged on its trolling the output of a generator 3 driven by a separ­ exterior surface. ately excited motor 4, the generator driving a torque motor 6 connected to the control column 8 by a belt 7. The provision of the rate amplifier 21 ensures that the force applied to the column 8 will be high if the acceleration is changing rapidly even though the in­ stantaneous magnitude of the acceleration may be low. The circuit is so arranged that positive accelera­ tion produces a forward stick force, so that if the machine is flown hands-off by the pilot accelerations tending to be built up by gusts will be automatically relieved. A trim control 23 may be fitted to the main amplifier 2. through the air intakes 13, closure flaps for the muzzles being opened automatically when the guns are fired. An ammunition box may be mounted below 722,556. Helicopter stabilizers. United Aircraft each gun. The undercarriage units 21 are pivoted for Corporation. Application in U.S.A. September 20, rearward retraction immediately to the rear of the guns. A stabilizer surface for a helicopter is of aerofoil section and triangular plan form with low aspect ratio —less than 3 and preferably between 1·3 and 2·5— 724,019. De-icing equipment. Joseph Halbert. 723,160. Jet Deflectors. Power Jets (Research and and is of symmetrical form with respect to the fore- Application July 15, 1952. Development) Ltd. Application July 8, 1952. and-aft axis. As shown in FIG. 5 the stabilizer 34 is car­ A distributor for de-icing liquid consists of an outer ried on a transverse shaft 38 mounted parallel to and A jet deflector consists of nested outer and inner porous bronze sheet 1 backed by a flexible micro- slightly above the axis 22 of the tail rotor. The shaft is conical or cylindrical sleeves 5, 9 respectively provided porous sheet 2, which is preferably of polyvinyl- rotated by a reversible electric motor controlled by the with sets of apertures 7, 8 and 10, 11, which, by relative chloride treated in the manner described in Specifica­ rotation of the sleeves, may be brought into register tion 565,022, and spaced by washers 3 from a sheet 4 to allow the jet to flow through the tail pipe 2 or of hard neoprene, the space 5 between the sheets through an alternative outlet, such as a downwardly being connected to a metering adaptor 9. The edges of directed nozzle 3. As shown the apertures 7, 10 are the space 5 are sealed by strips 6. The sheet 2 is re­ aligned allowing the jet to discharge through the tail placed by a fresh one when its pores become blocked and impede the flow of liquid. As shown the distri­ butor is arranged as an over-shoe to the leading edge skin 7, but it can be built into the leading edge. June 1955

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Jun 1, 1955

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