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  • Detection Of Rocket Body Through An Active Firing Plume | TechLink
    is arranged to detect thermal emission in a range that is characteristic of a firing rocket body The image detected by the sensor is applied to an analog to digital converter for digitization and application to a computer that includes a routine for separating the modulated photon energy of the detected image from the substantially unmodulated photon energy that characterizes rocket body emissions The unmodulated photon energy signature of the

    Original URL path: http://techlinkcenter.org/patents/8927915 (2016-02-10)
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  • Perpendicular Drive Mechanism For A Missile Control Actuation System | TechLink
    more about this patent and related research and licensing opportunities please contact any of our Tech Managers at http techlinkcenter org about staff Patent Identifier 8921749 Status Active Categories Aerospace A perpendicular drive mechanism for a missile control actuation system employs an electric motor and power shaft operatively coupled to a first spur gear A lead screw is coupled to a second spur gear The lead screw is oriented parallel to the motor and perpendicular to a central longitudinal axis The first and second spur gears meshingly engage such that the second spur gear rotates in the opposite direction as the first spur gear A lead nut threadingly engages with and is configured to move linearly along the central axis of the lead screw A crank arm is coupled on one end to the lead nut and on the other end to the canard shaft of a canard assembly As the lead nut moves linearly along the central axis of the lead screw the crank arm follows the lead nut and causes the canard assembly to actuate USPTO url http patft uspto gov netacgi nph Parser patentnumber 8921749 Facebook Twitter Google Plus LinkedIn Main menu Home Licensing Joint R D

    Original URL path: http://techlinkcenter.org/patents/8921749 (2016-02-10)
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  • Separation System And Burn Wire Release Mechanism For Tethered Spacecraft | TechLink
    more about this patent and related research and licensing opportunities please contact any of our Tech Managers at http techlinkcenter org about staff Patent Identifier 20150115106 Status Active Categories Aerospace A tethered spacecraft has a first endmass and a second endmass with a telescoping stacer spring and a tether arranged between the endmasses The spring is coiled around a center rod and initially contained within a housing the spring being biased to push the first endmass away from the second endmass The spring housing is affixed to the first endmass a first end of the spring being affixed to the spring housing and tether are affixed to spring at one end and to the second endmass at the other end A pretensioned loop holds the endmasses abuttingly together and a burnwire release mechanism cuts the loop to deploy the spring Upon deployment the spring extends to its full length to form a cylindrical boom and the endmasses continue to move outward along the spring centerline until stopped by the tether USPTO url http appft1 uspto gov netacgi nph Parser Sect1 PTO1 Sect2 HITOFF d PG01 p 1 u Facebook Twitter Google Plus LinkedIn Main menu Home Licensing Joint R D

    Original URL path: http://techlinkcenter.org/patents/20150115106 (2016-02-10)
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  • Burn Wire Release Mechanism For Spacecraft And Terrestrial Applications | TechLink
    release mechanism for a spacecraft or other system having two masses initially held together by a pretensioned loop with a spring configured to push the masses apart The burn wire release system includes at least one burn wire held in contact with the pretensioned loop material When an electrical current flows through the burn wire the wire heats up and severs the pretensioned loop and the masses are pushed apart

    Original URL path: http://techlinkcenter.org/patents/20150102172 (2016-02-10)
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  • Method For Low Power Non-Coking Liquid Hydrocarbon Fuel Vaporization And Supercritical Phase Change | TechLink
    this patent and related research and licensing opportunities please contact any of our Tech Managers at http techlinkcenter org about staff Patent Identifier 20140272732 Categories Aerospace Methods for vaporizing hydrocarbon fuel and delivering the hydrocarbon fuel in either a vaporized phase or a supercritical phase to for example a combustion chamber are provided herein A method of vaporizing a hydrocarbon fuel wherein the hydrocarbon fuel is in a liquid phase at a first temperature and a first pressure and wherein the first temperature of the liquid phase hydrocarbon fuel is less than its intrinsic oxidation or endothermic reaction temperature the method may include lowering a pressure of the liquid phase hydrocarbon fuel from the first pressure to a second pressure and heating the liquid phase hydrocarbon fuel from the first temperature to a second temperature wherein the hydrocarbon fuel at the second temperature and the second pressure is in a substantially completely vaporized phase substantially without thermally oxidizing the hydrocarbon fuel and wherein the hydrocarbon fuel in the substantially completely vaporized phase does not form carbonaceous contaminants USPTO url http appft1 uspto gov netacgi nph Parser Sect1 PTO1 Sect2 HITOFF d PG01 p 1 u Facebook Twitter Google Plus LinkedIn

    Original URL path: http://techlinkcenter.org/patents/20140272732 (2016-02-10)
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  • Ballistic Modification And Solventless Double Base Propellant, And Process Thereof | TechLink
    contact any of our Tech Managers at http techlinkcenter org about staff Patent Identifier 8828161 Categories Aerospace A double base propellant modifier uses a lead tin component with a defined amount of lead and a copper component with a defined surface area to effect super rate burning of double base propellants with defined plateau and mesa burning rate characteristics USPTO url http patft uspto gov netacgi nph Parser patentnumber 8828161

    Original URL path: http://techlinkcenter.org/patents/8828161 (2016-02-10)
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  • Parafoil Electronic Control Unit Having Wireless Connectivity | TechLink
    Identifier 8818581 Categories Aerospace A method is described that includes performing a b and c below with an electronic control unit of a parafoil a after being dropped from an airborne vehicle wirelessly receiving the parafoil s desired landing location b determining a flight path for the parafoil that lands at the desired landing location and c controlling the parafoil s flight path consistently with the determined flight path USPTO

    Original URL path: http://techlinkcenter.org/patents/8818581 (2016-02-10)
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  • Aerial Delivery System With High Accuracy Touchdown | TechLink
    terminal descent phase of aerial payload delivery In the first phase a small parafoil provides aerial delivery of a payload to within a close proximity of an intended touchdown point e g a target In the second phase a target designator acquires the target and a trajectory to the target is determined A harpoon launcher deploys a harpoon connected to the payload by an attachment line such as a rope

    Original URL path: http://techlinkcenter.org/patents/8800930 (2016-02-10)
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