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  • Positive Locking Mechanism For Rotating Helicopter Mount | TechLink
    includes a locking mechanism having a generally arcuate outer surface with a plurality of deep and shallow notches formed therein The notches correspond to different positions of rotation of the first and second members One end of the second longitudinal member includes a yoke rotatably connected to the locking mechanism with a pivot pin A locking plunger in the second longitudinal member engages the notches in the locking mechanism and

    Original URL path: http://techlinkcenter.org/patents/8800421 (2016-02-10)
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  • System And Method For Maneuver Plan For Satellites Flying In Proximity Using Apocentral Coordinate System | TechLink
    in closed form for relative motion about a circular primary for solutions that are non drifting i e the orbital periods of the two vehicles are equal computes the impulsive maneuvers in the primary radial and cross track directions and parameterizes these maneuvers and obtain solutions that satisfy constraints for example collision avoidance or direction of coverage or optimize quantities such as time or fuel usage Apocentral coordinates and a

    Original URL path: http://techlinkcenter.org/patents/8768622 (2016-02-10)
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  • Shock Cancellation Mechanism For The Control Of Unsteady Interaction In Contra-Rotating High- And Low-Pressure Turbines | TechLink
    Low Pressure Turbines If you are interested in learning 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 8739508 Categories Aerospace In a high pressure turbine used in combination with a contra rotating low pressure turbine in which the geometry of the inlet guide vane of the low pressure turbine induces a reflection of the incident shock wave from the high pressure turbine airfoil that propagates back upstream to impact the blade thereby denigrating both the performance of the high pressure turbine and its durability The shock wave reflection is eliminated by fitting the downstream vanes with holes or indentations that allow jets of compressor bleed air to penetrate the boundary layer and induce a net velocity component across the main flow direction in the near wall region This induced flow component acts to cancel the net flow component created by the moving shock from the upstream blade row thereby obviating the reflection that occurs naturally to cancel the flow USPTO url http patft uspto gov netacgi nph Parser patentnumber 8739508 Facebook Twitter Google Plus LinkedIn Main menu Home Licensing Joint R D Technology

    Original URL path: http://techlinkcenter.org/patents/8739508 (2016-02-10)
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  • Wideband Aircraft Antenna With Extended Frequency Range | TechLink
    with no nulls over a wide 8 1 bandwidth from 225 MHz to 1 85 GHz The antenna has an aerodynamically streamlined shape with a rugged housing capable of withstanding velocities up to Mach 2 In addition to its usage on aircraft this antenna would be useful in a wide range of applications as a general purpose wide bandwidth omnidirectional antenna The antenna achieves its performance capabilities with the use

    Original URL path: http://techlinkcenter.org/patents/8736506 (2016-02-10)
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  • Extendable Stabilizer For Projectile | TechLink
    bore of a sliding tail boom The sliding tail boom may translate or extend rearward with respect to the fixed tail boom before the projectile exits a launch tube The through bore of the sliding tail boom may include a tapered portion A tail boom sleeve may be fixed to a rear portion of the fixed tail boom The tail boom sleeve may include a tapered portion that abuts the

    Original URL path: http://techlinkcenter.org/patents/8735789 (2016-02-10)
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  • Gas Turbine Engine With Dual Compression Rotor | TechLink
    Managers at http techlinkcenter org about staff Patent Identifier 8726635 Categories Aerospace The present invention provides a gas turbine engine having a combustion chamber section substantially forward of an axial compressor section An example embodiment uses a centrifugal compressor section behind the axial compressor section to help route compressed air exiting the axial compressor section forward to the combustion chamber section USPTO url http patft uspto gov netacgi nph Parser

    Original URL path: http://techlinkcenter.org/patents/8726635 (2016-02-10)
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  • Active Twist Hollow Beam 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 8721282 Categories Aerospace A system for actively controlling the span wise rotational twist of a hollow beam along its longitudinal axis including a hollow beam structure having a leading edge and a trailing edge region the beam being split along its length an actuator arranged between split surfaces of the beam the actuator adapted to move the split surfaces in a longitudinal direction relative to each other inducing a twist in the beam The hollow beam is affixed to an external structure at one or both ends with only the zero warping displacement points of the beam being attached to the external structure material or device In one embodiment the actuator is a plurality of solid blocks with high thermal expansion coefficients arranged between frames of the split surfaces of the beam with alternating blocks being heated by resistance heaters to cause expansion in the spanwise longitudinal direction USPTO url http patft uspto gov netacgi nph Parser patentnumber 8721282 Facebook Twitter Google Plus LinkedIn Main menu Home Licensing Joint R D Technology Summaries Patents SBIR

    Original URL path: http://techlinkcenter.org/patents/8721282 (2016-02-10)
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  • Micro-Unmanned Aerial Vehicle Deployment System | TechLink
    for a cruise missile having submunition compartments The system includes a vehicle launch module releasable from the cruise missile submunition compartment The vehicle launch system has a control circuit and at least one micro unmanned aerial vehicle contained therein Structure is provided in the launch module for deploying the micro unmanned aerial vehicle A separable tether can be joined between the cruise missile and the vehicle launch module that separates

    Original URL path: http://techlinkcenter.org/patents/8708285 (2016-02-10)
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