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        <title>Free Patents Online: Aeronautics</title>
        <link>http://www.freepatentsonline.com/rssfeed/rsspat244.xml</link>
        <description>USPTO Class 244 Aeronautics</description>
        <language>en-us</language>
        <lastBuildDate>Tue, 09 Feb 2010 08:00:00 EST</lastBuildDate>
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            <title><![CDATA[Laser target seeker device]]></title>
            <link>http://www.freepatentsonline.com/7659494.html</link>
            <description><![CDATA[A laser target seeker device arranged to receive a laser beam reflected from an object. Detector elements are arranged to detect the reflected laser beam. A processor is arranged to determine the received radiation on the respective detector element in order to determine the origin of the laser beam. A diffractor is arranged relative to the detector elements and configured to diffract the reflected laser beam into portions prior to being detected by the detector elements. The detector elements are arranged to detect the respective portion. A flyable body is for hitting a target by means of a laser beam. A system for hitting a target by means of a laser beam. A method for detecting a laser beam reflected from an object. Use of a kinoform member in a laser target seeker for diffracting a laser beam.]]></description>
            <pubDate>Tue, 09 Feb 2010 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Hose hinge assembly]]></title>
            <link>http://www.freepatentsonline.com/7658417.html</link>
            <description><![CDATA[A high-pressure hose hinge assembly provides a continuous fluid path between first and second components that move relative to each other. The hose hinge assembly includes a plurality of rotatable swivel fittings that couple a plurality rigid pipe sections. A first swivel fitting is fixedly coupled to the first component and another swivel fitting is coupled to the second component. At least one swivel fitting and two rigid pipe sections extend between the swivel fittings coupled to the first and second components to provide a continuous fluid path.]]></description>
            <pubDate>Tue, 09 Feb 2010 08:00:00 EST</pubDate>
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            <title><![CDATA[Pilot flight control stick haptic feedback system and method]]></title>
            <link>http://www.freepatentsonline.com/7658349.html</link>
            <description><![CDATA[A pilot flight control stick haptic feedback system includes a pilot user interface, a position sensor, a pilot motor, and a control circuit. The pilot user interface is movable to a position at a movement rate. The position sensor senses the position of the pilot user interface and supplies a pilot user interface position signal. The pilot motor is coupled to the pilot user interface, and receives pilot motor feedback signals. The pilot motor, in response to the pilot motor feedback signals, supplies feedback force to the pilot user interface. The control circuit determines one or more of the pilot user interface position, movement rate, aircraft control surface slew rate capacity, aircraft control surface load rate capacity, and aerodynamic stall risk and, based on at least a subset of these determinations, supplies pilot motor feedback signals to the pilot motor.]]></description>
            <pubDate>Tue, 09 Feb 2010 08:00:00 EST</pubDate>
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        <item>
            <title><![CDATA[Enhancement and extension of structural integrity of aircraft structure]]></title>
            <link>http://www.freepatentsonline.com/7658348.html</link>
            <description><![CDATA[A method and apparatus for modifying aircraft having a fuselage and center fuselage carry through structure that support wing structures, comprising placing a load transferring member to extend through the center fuselage carry through structure, and transferring the tension loads from the wing structures to the center fuselage carry through structure so as to provide a redundant load path that is resistant to the hazards of single point failures modes.]]></description>
            <pubDate>Tue, 09 Feb 2010 08:00:00 EST</pubDate>
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            <title><![CDATA[Micro air-vehicle transport container and launch system]]></title>
            <link>http://www.freepatentsonline.com/7658347.html</link>
            <description><![CDATA[A Micro Air-Vehicle (MAV) starting system that provides the combined functions of: packing protection of sensitive vehicle components, a mechanical starting assembly, and a launch pad. The preferred embodiment comprises a container and a container lid with the MAV clamped to the lid. Also disposed on the container lid is a starting assembly. The lid which doubles as a launching pad with the attached MAV is removed from the container, placed on the ground, the MAV is started with the starting mechanism and launched. The arrangement minimizes the physical risk to the operator, minimizes weight of the total MAV system, consumes minimum space in the operators transport system, and eliminates dependence on supply lines for battery replacement or charging.]]></description>
            <pubDate>Tue, 09 Feb 2010 08:00:00 EST</pubDate>
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            <title><![CDATA[Double ducted hovering air-vehicle]]></title>
            <link>http://www.freepatentsonline.com/7658346.html</link>
            <description><![CDATA[A dual ducted fan arrangement in which the duct components, engine, and avionics/payload pods are capable of being quickly disassembled to fit within common backpacking systems. Each duct is identical in fan, stator, and control vane design. Assembly connections between ducted fans and electronic modules are also identical. An engine or APU drives the dual ducted fans through a splined shaft to a differential or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms on each of the splined shafts between the differential and ducted fans. In the electric motor case relative speed is through electronic speed control. The fans are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.]]></description>
            <pubDate>Tue, 09 Feb 2010 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Gap covering for cabin panels]]></title>
            <link>http://www.freepatentsonline.com/7658044.html</link>
            <description><![CDATA[Currently, piping tapes are used as elastic masking elements of joints between lateral panels in an aircraft. According to one embodiment, a gap covering for cabin panels in an aircraft is provided, where the gap covering comprises a flexible cover region that is arranged between the cabin panels and finishes off so as to be substantially flush with surfaces of the panels. In this way, a lightweight economical gap covering which covers gaps in an effective and attractive manner and provides protection against injury is provided.]]></description>
            <pubDate>Tue, 09 Feb 2010 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Method and apparatus for manufacturing interchangeable and replaceable parts]]></title>
            <link>http://www.freepatentsonline.com/7657988.html</link>
            <description><![CDATA[A manufacturing method and apparatus is disclosed, whereby a specific production process is used in conjunction with a specific tooling methodology to provide a tooling process package that is capable of controlling tolerance stack-ups and process variations by accounting for them at each step in the process. One application particularly suited for the present invention is in the manufacturing of panels that are assembled to form the skins of a tiltrotor aircraft ( 11 ).]]></description>
            <pubDate>Tue, 09 Feb 2010 08:00:00 EST</pubDate>
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