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Patent abstracts

Patent abstracts such as 127mm. The structural panels of connections is stress-critical to rigidize Method of producing larger members of the set are elongated the structure in the installed position propulsion tanks in the longitudinal direction, to provide and so that, under crash impact In UK patent 2270028 General Electric conditions, the intermediate panel more surface area for mounting payload, Co. describes a lightweight tank, useful section is able to follow the movement and to provide more heat rejection for holding fuels and the like in space- of the seat backs of the forward row of surface. The propellant tank(s), which deployed vessels. It is produced by passenger seats. This is so the heads of may be fuel and oxidizer tanks, are depositing a metal layer on the outer the passengers in the aft row do not spherical in the shortest members of the surface of a disposable pattern, forming collide with the intermediate panel set, and are increased in length by a lightweight tank shell thereon, section of the divider, so avoiding addition of cylindrical sections, to typically by wrapping with a polymer- unnecessary injuries. To permit the provide greater volume in larger impregnated reinforcing material and intermediate panel section further members thereby to provide longer then curing followed by removal of the freedom of forward movement, the operating life. Similarly, the solar pattern. The metal layer serves as a leak stress-critical interconnection, pre­ panels, heat pipes and the like may be barrier and protects the polymer from ferably between the intermediate panel elongated. corrosive damage that may be produced section and the upper panel section, by the propellant fuel or oxidant. includes an expandable friction hinge to enable the intermediate panel section to move away from the upper panel Spacecraft-to-launch-vehicle section to a maximum collapsed transition structure Producing metal-coated position determined by the expansion of In UK patent 2270665 General Electric the hinse. propulsion tanks Co. describes a support transition which In UK patent 2270089 General Electric is affixed to all spacecraft for supporting Co. describes a lightweight space- the spacecraft on a ring of a booster or deployed propulsion tank. It is made by launch vehicle. The transition is in the US patent depositing an adherent metal layer on general form of a ring defining a The US Patent Office recently granted the desired surfaces of a lightweight longitudinal axis parallel to the axis of Unison Industries Patent No. 5,343,154 tank shell produced by wrapping. It is the spacecraft and the booster. The directed to a diagnostic device for gas- then cured on a disposable pattern, transition has a circular end adapted to turbine ignition systems and Patent No. which may be coated with a polymeric mate with the booster support ring and a 5,347,422 directed to an apparatus and material, having a desired shape, and an polygonal end adapted to mate with the method for an ignition system. These array of reinforcing material, such as spacecraft, and makes a smooth patents contain claims which relate to carbon fibres, itself impregnated with a transition between ends. The built-in test (BIT) diagnostic features polymer material such as an epoxy resin. circumference of the transition, at any and "hybrid" solid-state circuitry in use The disposable pattern is removed in Unison ignition exciters with cross-section transverse to the before the metal layer is deposited. The applications on aircraft main propulsion longitudinal axis is constant. The metal layer serves as a leak barrier and and APU engines. The Unison ignition transition is advantageously made of a protects the underlying polymer system for the AlliedSignal TFE-731- composite material such as fibre- material from corrosive damage that 20 engine utilizes technology protected reinforced solidified liquid or carbon- may be produced by the propellant fuel by both of these patents. fibre reinforced resin. In a particular or oxidant. The desired surfaces may be embodiment, the polygonal end is a either on the inside or on the outside square rectangle, with four straight sides wall of the tank. The metal layer may be and rounded corners. formed of Ni, Au, Cu, Ti, Al or stainless Spark-sequencing technology steel and be deposited by electroless Unison has been allowed patent claims deposition, vacuum metallization or by the US Patent Office for use of spark chemical vapour deposition. A second sequencing in solid-state turbine metal layer of Ni, Au, or Cu may be Aircraft cabin divider ignition systems. These claims relate to electrolytically deposited on top of the In UK patent 2273088 Magerik Ltd variable spark-rate control to improve adherent metal layer. describes an aircraft cabin divider. It is combustion in a gas-turbine engine. A formed of pivotally interconnected new patent containing these claims will panel sections that can be between two be issued by the US Patent Office in the rows of passenger seats. The panel near future. The claims will cover Low cost, selectable sections comprise an upper panel Unison's proprietary "Burst-of-Sparks" section for mounting to the ceiling of an configuration spacecraft solid-state ignition exciters in use on aircraft cabin and a lower panel section In UK patent 2270666 General Electric many turbine applications today. for fixing to the floor of the cabin. The Co. describes a method to reduce the Further details are available from upper and lower panel sections are time and costs required to build Unison Industries, 7575 Baymeadows pivotally mounted to an intermediate spacecraft. The spacecraft are members Way, Jacksonville, Florida 32256 USA. panel section which, in the installed of a set. Each member has the same Tel: 904 739 4000; Fax: 904 739 4006; position, faces passengers sitting in the structural members, such as panels, but Telex: 523210. aft row of seats to one side of the different members of the set are divider. At least one of the pivotal inter­ elongated by multiples of an increment AEAT March/April 1995 37 http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Patent abstracts

Aircraft Engineering and Aerospace Technology , Volume 67 (2): 1 – Feb 1, 1995

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb037556
Publisher site
See Article on Publisher Site

Abstract

such as 127mm. The structural panels of connections is stress-critical to rigidize Method of producing larger members of the set are elongated the structure in the installed position propulsion tanks in the longitudinal direction, to provide and so that, under crash impact In UK patent 2270028 General Electric conditions, the intermediate panel more surface area for mounting payload, Co. describes a lightweight tank, useful section is able to follow the movement and to provide more heat rejection for holding fuels and the like in space- of the seat backs of the forward row of surface. The propellant tank(s), which deployed vessels. It is produced by passenger seats. This is so the heads of may be fuel and oxidizer tanks, are depositing a metal layer on the outer the passengers in the aft row do not spherical in the shortest members of the surface of a disposable pattern, forming collide with the intermediate panel set, and are increased in length by a lightweight tank shell thereon, section of the divider, so avoiding addition of cylindrical sections, to typically by wrapping with a polymer- unnecessary injuries. To permit the provide greater volume in larger impregnated reinforcing material and intermediate panel section further members thereby to provide longer then curing followed by removal of the freedom of forward movement, the operating life. Similarly, the solar pattern. The metal layer serves as a leak stress-critical interconnection, pre­ panels, heat pipes and the like may be barrier and protects the polymer from ferably between the intermediate panel elongated. corrosive damage that may be produced section and the upper panel section, by the propellant fuel or oxidant. includes an expandable friction hinge to enable the intermediate panel section to move away from the upper panel Spacecraft-to-launch-vehicle section to a maximum collapsed transition structure Producing metal-coated position determined by the expansion of In UK patent 2270665 General Electric the hinse. propulsion tanks Co. describes a support transition which In UK patent 2270089 General Electric is affixed to all spacecraft for supporting Co. describes a lightweight space- the spacecraft on a ring of a booster or deployed propulsion tank. It is made by launch vehicle. The transition is in the US patent depositing an adherent metal layer on general form of a ring defining a The US Patent Office recently granted the desired surfaces of a lightweight longitudinal axis parallel to the axis of Unison Industries Patent No. 5,343,154 tank shell produced by wrapping. It is the spacecraft and the booster. The directed to a diagnostic device for gas- then cured on a disposable pattern, transition has a circular end adapted to turbine ignition systems and Patent No. which may be coated with a polymeric mate with the booster support ring and a 5,347,422 directed to an apparatus and material, having a desired shape, and an polygonal end adapted to mate with the method for an ignition system. These array of reinforcing material, such as spacecraft, and makes a smooth patents contain claims which relate to carbon fibres, itself impregnated with a transition between ends. The built-in test (BIT) diagnostic features polymer material such as an epoxy resin. circumference of the transition, at any and "hybrid" solid-state circuitry in use The disposable pattern is removed in Unison ignition exciters with cross-section transverse to the before the metal layer is deposited. The applications on aircraft main propulsion longitudinal axis is constant. The metal layer serves as a leak barrier and and APU engines. The Unison ignition transition is advantageously made of a protects the underlying polymer system for the AlliedSignal TFE-731- composite material such as fibre- material from corrosive damage that 20 engine utilizes technology protected reinforced solidified liquid or carbon- may be produced by the propellant fuel by both of these patents. fibre reinforced resin. In a particular or oxidant. The desired surfaces may be embodiment, the polygonal end is a either on the inside or on the outside square rectangle, with four straight sides wall of the tank. The metal layer may be and rounded corners. formed of Ni, Au, Cu, Ti, Al or stainless Spark-sequencing technology steel and be deposited by electroless Unison has been allowed patent claims deposition, vacuum metallization or by the US Patent Office for use of spark chemical vapour deposition. A second sequencing in solid-state turbine metal layer of Ni, Au, or Cu may be Aircraft cabin divider ignition systems. These claims relate to electrolytically deposited on top of the In UK patent 2273088 Magerik Ltd variable spark-rate control to improve adherent metal layer. describes an aircraft cabin divider. It is combustion in a gas-turbine engine. A formed of pivotally interconnected new patent containing these claims will panel sections that can be between two be issued by the US Patent Office in the rows of passenger seats. The panel near future. The claims will cover Low cost, selectable sections comprise an upper panel Unison's proprietary "Burst-of-Sparks" section for mounting to the ceiling of an configuration spacecraft solid-state ignition exciters in use on aircraft cabin and a lower panel section In UK patent 2270666 General Electric many turbine applications today. for fixing to the floor of the cabin. The Co. describes a method to reduce the Further details are available from upper and lower panel sections are time and costs required to build Unison Industries, 7575 Baymeadows pivotally mounted to an intermediate spacecraft. The spacecraft are members Way, Jacksonville, Florida 32256 USA. panel section which, in the installed of a set. Each member has the same Tel: 904 739 4000; Fax: 904 739 4006; position, faces passengers sitting in the structural members, such as panels, but Telex: 523210. aft row of seats to one side of the different members of the set are divider. At least one of the pivotal inter­ elongated by multiples of an increment AEAT March/April 1995 37

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Feb 1, 1995

There are no references for this article.