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Month in the Patent Office

Month in the Patent Office latter's centre of area, so that the door is insensitive to overall pressure differences between the spaces on Month in the Patent Office either side of the outer skin. Members 17, 18 located respectively on the forward edge of the door opening These abstracts of British Patent Specifications are condensed, by permission, from the official and on the door leading edge are so shaped as to form a semi-aerofoil shaped projection and to ensure specifications. Copies of the full specifications are obtainable from the Patent Office, 25 Southampton that the airflow causes a pressure rise on the leading Buildings, W.C.2, price 2s. 8d. each. portion 17 and a pressure fall on the trailing portion 18, thus ensuring closing of the door under all condi­ 707,731. Undercarriages. Electro-Hydraulics Ltd. tions of flight. In an alternative construction the door for a portion only of the span, and made of spruce- Application July 14, 1949. is formed as a sheet-metal pressing, the leading edge wood laminations, the remaining portion 23 of the blade being made of a light material such as balsa portion being shaped to constitute the aerofoil trailing An undercarriage bogie 29 with tandem landing wood arranged with its grain extending chordwise. portion 18. wheels 7,8 is biassed into a tail-down attitude so A steel plate 12 embedded in the leading edge portion that on touching down the rear wheels 8 make contact 708,231. High-speed wind tunnels. Aktiengesell- 10 is provided with an eye 15 for the reception of a with the ground before the front wheels 7, thus reduc­ schaft Für Technische Studien. Application Novem­ pin by which the blade is secured to the rotor head. ing the initial drag on the undercarriage. As shown in ber 4, 1952. The construction results in the centre of gravity being no . 1 the bogie is biassed by the shock-absorber disposed close to the leading edge, and the portion 20 forms a beam structure with spaced flange portions resisting chordwise bending. A sheet metal strip 36 covers the leading edge, the remainder of the blade being covered with glass thread fabric 35. 707,881. Cooling aircraft structures. Rolls-Royce Ltd. Application October 12, 1950. In order to allow the development of convection air currents through a nacelle to prevent heat damage to the aircraft structure, apertures are formed in the walls of the nacelle, each being provided with a pivoted door 10 which is held closed by the pressure of the airstream when the machine is airborne and opened by a spring 41 when the machine ceases to be airborne. The door pivot 35, which carries the closing spring 41, is so located that the orthogonal projection of its axis on the plane of the door passes through the A high-speed wind tunnel 7 is operated by a closed- cycle gas-turbine plant comprising a compressor 1, heat exchanger 2, heater 3, turbine 4, and coolers 5, 6, the tunnel inlet and outlet being connected at 8, 9 to the compressor outlet and inlet respectively. The pressure of the working fluid may be raised by an auxiliary compressor 27 or lowered by a discharge valve 28. In an alternative arrangement an auxiliary compressor coupled to the main compressor 1 and fitted with a bye-pass valve is connected between the tunnel outlet and the point 9 to make up any pressure losses, especially those due to shocks at the diffuser. 708,086. Thrust spoilers. Power Jets (Research and Development) Ltd. Application December 7, 1951. To prevent dangerous conditions arising from the operation of thrust spoilers 4 when the aircraft is alighting, movement of the pilot-operated control mechanism 8 is opposed or prevented automatically under certain conditions of operation; for example the amount of spoiling may be reduced gradually as the speed falls below the value at which the diverted jet unduly heats the aircraft or tends to enter the engine air intake. Control devices associated with the mecha­ nism 8 may be operated when the speed falls to the predetermined value by the air speed indicator 10, a spring-loaded vane 11 on the fuselage, or by the rotational speed of the landing wheels through a connexion 13. Temperature-responsive controls may be operated by thermostats 14, 15 in the engine air inlet and on the fuselage outside the crew or passenger compartment, respectively. In addition a connexion 16 may be provided between the mechanism 8 and the throttle 17 to reduce the jet thrust under such condi­ tions. August 1954 269 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 26 (8): 1 – Aug 1, 1954
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032463
Publisher site
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Abstract

latter's centre of area, so that the door is insensitive to overall pressure differences between the spaces on Month in the Patent Office either side of the outer skin. Members 17, 18 located respectively on the forward edge of the door opening These abstracts of British Patent Specifications are condensed, by permission, from the official and on the door leading edge are so shaped as to form a semi-aerofoil shaped projection and to ensure specifications. Copies of the full specifications are obtainable from the Patent Office, 25 Southampton that the airflow causes a pressure rise on the leading Buildings, W.C.2, price 2s. 8d. each. portion 17 and a pressure fall on the trailing portion 18, thus ensuring closing of the door under all condi­ 707,731. Undercarriages. Electro-Hydraulics Ltd. tions of flight. In an alternative construction the door for a portion only of the span, and made of spruce- Application July 14, 1949. is formed as a sheet-metal pressing, the leading edge wood laminations, the remaining portion 23 of the blade being made of a light material such as balsa portion being shaped to constitute the aerofoil trailing An undercarriage bogie 29 with tandem landing wood arranged with its grain extending chordwise. portion 18. wheels 7,8 is biassed into a tail-down attitude so A steel plate 12 embedded in the leading edge portion that on touching down the rear wheels 8 make contact 708,231. High-speed wind tunnels. Aktiengesell- 10 is provided with an eye 15 for the reception of a with the ground before the front wheels 7, thus reduc­ schaft Für Technische Studien. Application Novem­ pin by which the blade is secured to the rotor head. ing the initial drag on the undercarriage. As shown in ber 4, 1952. The construction results in the centre of gravity being no . 1 the bogie is biassed by the shock-absorber disposed close to the leading edge, and the portion 20 forms a beam structure with spaced flange portions resisting chordwise bending. A sheet metal strip 36 covers the leading edge, the remainder of the blade being covered with glass thread fabric 35. 707,881. Cooling aircraft structures. Rolls-Royce Ltd. Application October 12, 1950. In order to allow the development of convection air currents through a nacelle to prevent heat damage to the aircraft structure, apertures are formed in the walls of the nacelle, each being provided with a pivoted door 10 which is held closed by the pressure of the airstream when the machine is airborne and opened by a spring 41 when the machine ceases to be airborne. The door pivot 35, which carries the closing spring 41, is so located that the orthogonal projection of its axis on the plane of the door passes through the A high-speed wind tunnel 7 is operated by a closed- cycle gas-turbine plant comprising a compressor 1, heat exchanger 2, heater 3, turbine 4, and coolers 5, 6, the tunnel inlet and outlet being connected at 8, 9 to the compressor outlet and inlet respectively. The pressure of the working fluid may be raised by an auxiliary compressor 27 or lowered by a discharge valve 28. In an alternative arrangement an auxiliary compressor coupled to the main compressor 1 and fitted with a bye-pass valve is connected between the tunnel outlet and the point 9 to make up any pressure losses, especially those due to shocks at the diffuser. 708,086. Thrust spoilers. Power Jets (Research and Development) Ltd. Application December 7, 1951. To prevent dangerous conditions arising from the operation of thrust spoilers 4 when the aircraft is alighting, movement of the pilot-operated control mechanism 8 is opposed or prevented automatically under certain conditions of operation; for example the amount of spoiling may be reduced gradually as the speed falls below the value at which the diverted jet unduly heats the aircraft or tends to enter the engine air intake. Control devices associated with the mecha­ nism 8 may be operated when the speed falls to the predetermined value by the air speed indicator 10, a spring-loaded vane 11 on the fuselage, or by the rotational speed of the landing wheels through a connexion 13. Temperature-responsive controls may be operated by thermostats 14, 15 in the engine air inlet and on the fuselage outside the crew or passenger compartment, respectively. In addition a connexion 16 may be provided between the mechanism 8 and the throttle 17 to reduce the jet thrust under such condi­ tions. August 1954 269

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Aug 1, 1954

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