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Month in the Patent Office

Month in the Patent Office These abstracts of British Patent Specifications are taken, by permission, from the officially prepared abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies of the full specification are obtainable at the same address, price 1s. each. Except where otherwise stated, the specification is unaccompanied by drawings if none is reproduced. GROUP XXXIII 600,759. Aircraft Undercarriages. Soc. Anon de Usines Chausson. April 10, 1945, No. 8861. Conven­ 600,371. Controlling Aircraft. Helliwells Ltd. and tion date, Feb. 25, 1944. (Class 4.) (Also in Group S. H. Pickrell. Sept. 28, 1946, No. 25,167/45. (CIass4.) XXXII.) A control member for aeroplanes comprises a uni­ An auxiliary wheel 48 is amounted alongside an versally mounted hand lever 1 carried by an arch or aircraft landing wheel 49 and is carried at the lower bridge-shaped member 5, one extremity of which end of a plunger 47 telescopically mounted within a moves in a slot 4 in a stationary member 3, the other cylinder 45 secured alongside the shock-absorber of extremity being connected to a control rod 8, and a the landing wheel. The wheel 48 is arranged to strike lateral extension 11 carrying a further control rod 12, the ground at the same instant as the landing wheel the lever being capable of rotation on its axis and and drive the plunger 47 into the cylinder 45 and thus being connected by a second universal joint 13 to a force oil contained in the cylinder through an orifice flexible cable 14. FIG. 4 shows a dual control arrange­ 51 into a reservoir 52. The pressure developed by flow ment, fore-and-aft movement of the levers 1 operating through the orifice 51 is proportional to the square of bell cranks 8a connected to a link 8b. The latter is con­ the vertical landing speed, and is applied by a conduit nected to a lever 8c operating the micro-switches 8e 44 to a pressure regulating chamber in the shock- of an electric motor 20, which moves the elevators absorber. through worm gearing 21, 22 and cables 32. Lateral movement of either lever 1 operates, through bell cranks 12a a link 126, a second lever 12c controlling the micro-switches of an electric motor 28 which con­ trols the joint movement of the ailerons and rudder through cables 25, 29a. Trimming may be effected by rotating the hand lever 1 in a bearing 6 to effect rela­ tive movement of the levers 26, 29 to which the aileron and rubber cables 25, 29a are respectively connected. Hydraulic or pneumatic actuation may be employed instead of electric actuation. (For Drawings see column 3) 600,374. Aircraft; variable-pitch Propellers. L. H. Leonard, Oct. 1, 1945, No. 25,455. Convention date Jan. 25, 1941. (Classes 4 and 114.) An aircraft which can take off in a vertical attitude and then travel horizontally is provided with a variable pitch propeller so positioned with respect to the centre of gravity, and of such blade area in proportion to the area of the sustaining surfaces, that the aerodynamic centre of the aircraft, i.e., the point at which the transverse aerodynamic force intersects the longi­ tudinal axis, during vertical flight with fine pitch is longitudinally forward of the centre of gravity, and during horizontal flight with coarse pitch is behind the centre of gravity. As shown in FIGS. 1, 2, and 5 contra- rotating propellers 7, 8, are mounted in the rear of the pilot's cockpit 1, between front and rear supporting and control surfaces 13 and 14, and 12 respectively. The tail portion of the fuselage is divided into four 600,963. Controlling Aircraft. General Motors, pivoted segments 5 which open outwardly to form an Corporation. Oct. 6, 1945, No. 26,062. Convention undercarriage for supporting the machine in a vertical date Oct. 20, 1944. (Class 4.) (Also in Groups XXVII position upon alighting and when taking off. and XXIX.) The figure shows a pilot's throttle control lever 62 which when moved into a high engine induction pipe 600,498. Screw Propellers. United Aircraft Cor­ pressure position operates a solenoid 176 which con­ poration. Oct. 10, 1945, No. 26,419. Convention date trols an intake liquid injection apparatus (not shown). Jan. 24. (Class 114.) (Also in Group XXXII.) In the high induction pipe pressure position lever 62 To damp out vibrations a blade is provided with a moves a lever 221 to depress a plunger 230 and close conical shell 32 fitting the base 30 of the blade, this contacts 1791, 1801 and 1851, 1861, 1871 in the sole­ containing a ball 36 contacting a seal of larger radius. The ball space is closed by a plug 34 to which balance noid circuit. Contacts 1851, 1861 1871 are opened weights 44 can be attached. Specifications 416,255 automatically after a short interval by a thermally and 437,631 are referred to. sensitive strip 24a and heater oil 250. October 1950 315 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 22 (10): 1 – Oct 1, 1950
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb031960
Publisher site
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Abstract

These abstracts of British Patent Specifications are taken, by permission, from the officially prepared abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies of the full specification are obtainable at the same address, price 1s. each. Except where otherwise stated, the specification is unaccompanied by drawings if none is reproduced. GROUP XXXIII 600,759. Aircraft Undercarriages. Soc. Anon de Usines Chausson. April 10, 1945, No. 8861. Conven­ 600,371. Controlling Aircraft. Helliwells Ltd. and tion date, Feb. 25, 1944. (Class 4.) (Also in Group S. H. Pickrell. Sept. 28, 1946, No. 25,167/45. (CIass4.) XXXII.) A control member for aeroplanes comprises a uni­ An auxiliary wheel 48 is amounted alongside an versally mounted hand lever 1 carried by an arch or aircraft landing wheel 49 and is carried at the lower bridge-shaped member 5, one extremity of which end of a plunger 47 telescopically mounted within a moves in a slot 4 in a stationary member 3, the other cylinder 45 secured alongside the shock-absorber of extremity being connected to a control rod 8, and a the landing wheel. The wheel 48 is arranged to strike lateral extension 11 carrying a further control rod 12, the ground at the same instant as the landing wheel the lever being capable of rotation on its axis and and drive the plunger 47 into the cylinder 45 and thus being connected by a second universal joint 13 to a force oil contained in the cylinder through an orifice flexible cable 14. FIG. 4 shows a dual control arrange­ 51 into a reservoir 52. The pressure developed by flow ment, fore-and-aft movement of the levers 1 operating through the orifice 51 is proportional to the square of bell cranks 8a connected to a link 8b. The latter is con­ the vertical landing speed, and is applied by a conduit nected to a lever 8c operating the micro-switches 8e 44 to a pressure regulating chamber in the shock- of an electric motor 20, which moves the elevators absorber. through worm gearing 21, 22 and cables 32. Lateral movement of either lever 1 operates, through bell cranks 12a a link 126, a second lever 12c controlling the micro-switches of an electric motor 28 which con­ trols the joint movement of the ailerons and rudder through cables 25, 29a. Trimming may be effected by rotating the hand lever 1 in a bearing 6 to effect rela­ tive movement of the levers 26, 29 to which the aileron and rubber cables 25, 29a are respectively connected. Hydraulic or pneumatic actuation may be employed instead of electric actuation. (For Drawings see column 3) 600,374. Aircraft; variable-pitch Propellers. L. H. Leonard, Oct. 1, 1945, No. 25,455. Convention date Jan. 25, 1941. (Classes 4 and 114.) An aircraft which can take off in a vertical attitude and then travel horizontally is provided with a variable pitch propeller so positioned with respect to the centre of gravity, and of such blade area in proportion to the area of the sustaining surfaces, that the aerodynamic centre of the aircraft, i.e., the point at which the transverse aerodynamic force intersects the longi­ tudinal axis, during vertical flight with fine pitch is longitudinally forward of the centre of gravity, and during horizontal flight with coarse pitch is behind the centre of gravity. As shown in FIGS. 1, 2, and 5 contra- rotating propellers 7, 8, are mounted in the rear of the pilot's cockpit 1, between front and rear supporting and control surfaces 13 and 14, and 12 respectively. The tail portion of the fuselage is divided into four 600,963. Controlling Aircraft. General Motors, pivoted segments 5 which open outwardly to form an Corporation. Oct. 6, 1945, No. 26,062. Convention undercarriage for supporting the machine in a vertical date Oct. 20, 1944. (Class 4.) (Also in Groups XXVII position upon alighting and when taking off. and XXIX.) The figure shows a pilot's throttle control lever 62 which when moved into a high engine induction pipe 600,498. Screw Propellers. United Aircraft Cor­ pressure position operates a solenoid 176 which con­ poration. Oct. 10, 1945, No. 26,419. Convention date trols an intake liquid injection apparatus (not shown). Jan. 24. (Class 114.) (Also in Group XXXII.) In the high induction pipe pressure position lever 62 To damp out vibrations a blade is provided with a moves a lever 221 to depress a plunger 230 and close conical shell 32 fitting the base 30 of the blade, this contacts 1791, 1801 and 1851, 1861, 1871 in the sole­ containing a ball 36 contacting a seal of larger radius. The ball space is closed by a plug 34 to which balance noid circuit. Contacts 1851, 1861 1871 are opened weights 44 can be attached. Specifications 416,255 automatically after a short interval by a thermally and 437,631 are referred to. sensitive strip 24a and heater oil 250. October 1950 315

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Oct 1, 1950

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