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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, 07 Feb 2012 08:00:00 EST</lastBuildDate>
        <item>
            <title><![CDATA[Guidance system for an aircraft]]></title>
            <link>http://www.freepatentsonline.com/8112224.html</link>
            <description><![CDATA[The guidance system (1) comprises a first means (2) for guiding the aircraft while maintaining a spacing with another aircraft, a second means (3) for making the aircraft pass through a particular waypoint at a required passing time, and means (5) for selecting automatically one of said first and second means (2, 3).]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Mechanical stepper motors for gun-fired projectiles, mortars and missiles]]></title>
            <link>http://www.freepatentsonline.com/8110785.html</link>
            <description><![CDATA[A projectile including: a body having an internal space; and a mechanical stepper motor disposed in the body. The mechanical stepper motor including: a shuttle having one of a plurality of pockets and movable pins offset from each other with a first spacing; a body portion having the other of the plurality of pockets and movable pins offset from each other with a second spacing, where the first spacing is different from the first spacing; and actuation means for engaging at least one of the movable pins into a corresponding pocket to step one of the shuttle and body portion a predetermined linear and/or rotary displacement.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Projectile having one or more windows for transmitting power and/or data into/from the projectile interior]]></title>
            <link>http://www.freepatentsonline.com/8110784.html</link>
            <description><![CDATA[A projectile including: a casing; first and second windows provided on the casing for at least one of transmitting a first optical signal into an interior of the casing and transmitting a second optical signal from the interior of the casing; a receiving element disposed on the interior of the casing and in optical communication with one or more of the first and second windows for at least one of converting the first optical signal into electrical energy and storing data provided in the first optical signal; and a transmitting element disposed on the interior of the casing and in optical communication with one or more of the first and second windows for transmitting data provided in the second optical signal to outside the casing.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Article formed from a composite material]]></title>
            <link>http://www.freepatentsonline.com/8109734.html</link>
            <description><![CDATA[An article such as a fan blade of a turbofan engine comprises a core made up of components at least some of which comprise packs of rods embedded in a resin matrix material. The rods extend in the span-wise direction of the blade to resist centrifugal forces imposed on the blade during operation. The core is encased in a skin formed from preforms which may comprise fabric reinforcements.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Slotted high lift aerofoils]]></title>
            <link>http://www.freepatentsonline.com/8109473.html</link>
            <description><![CDATA[A slotted aerofoil configuration is provided in which the leading element thereof is contoured to provide mild stall characteristics. A wing based partially or fully on such an aerofoil, an air vehicle including such wings, and a method for designing an aerofoil are also disclosed.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Collapsible structures with adjustable forms]]></title>
            <link>http://www.freepatentsonline.com/8109472.html</link>
            <description><![CDATA[Structures and methods are disclosed regarding deployable structures with expandable longerons adjustably coupled with supporting structures such that an angle between the supporting structures can be adjusted. Such structures can include and/or be used for solar arrays, bridges, support structures, and more. These structures can be easily transported to a new location and deployed from the stowed configuration into a larger functional structure. In some embodiments these structures can use one or more longerons that can have two resting states: deployed and rolled.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Tubular shaped interstellar space craft]]></title>
            <link>http://www.freepatentsonline.com/8109471.html</link>
            <description><![CDATA[The invention relates to a plasma based aircraft possessing a magnetic field, and a plasma vortex. The craft is tubular in shape. The craft has a vast array of capacitors. The craft also has a proton accelerator, plasma guns, and diversion devices. The craft will approach the speed of light, over time. The craft obtains fuel direct from an atmosphere or a radiation induced atmosphere in space, at no cost, similar to our Moon's radiation induced atmosphere of the noble gases. The craft can travel to a gk star, for only the cost of construction of craft. The craft has three on-board escape, exploratory craft. The craft produces plasma vortices within an electromagnetic field. The field is an inhomogeneous, diamagnetic, orbiting plasma field, with a magnetohydrodynamic electrically conducting plasma current.The craft possesses approximately seven uninsulated, tungsten bands, encircling craft.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Overpressure protector]]></title>
            <link>http://www.freepatentsonline.com/8109470.html</link>
            <description><![CDATA[An aircraft fuel tank assembly comprises a first fuel tank, a second fuel tank and a tank-to-tank overpressure protector therebetween. The overpressure protector has a closed state and an open state. The fuel tank assembly further comprises an indicator for indicating whether the overpressure protector is in the open or closed state, the indication of the indicator being able to be sensed at a location outside of the fuel tanks. The fuel tank assembly may comprise a test mechanism arranged to effect movement of the overpressure valve from the closed state to the open state, the test mechanism being operable from a location outside a fuel tank. The fuel tank assembly may comprise an overpressure valve re-set mechanism, the re-set mechanism being operable from a location outside the fuel tanks.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Combined staircase and lavatory module for an aircraft]]></title>
            <link>http://www.freepatentsonline.com/8109469.html</link>
            <description><![CDATA[A module for an aircraft for accessing an upper region of the aircraft includes both an ascent region and an accommodation region, with the regions being divided from each other by a divider element. The accommodation region may, for example, be designed as an on-board lavatory. In this way it may be possible to do without the provision of an additional lavatory monument.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Nacelle for aircraft comprising means of reversing thrust and aircraft comprising at least one such nacelle]]></title>
            <link>http://www.freepatentsonline.com/8109468.html</link>
            <description><![CDATA[Aircraft nacelle including a cowling and an engine, the cowling including a fixed portion and a mobile portion able to slide in order to define a radial opening with the mobile portion, a thrust reverser system including a plurality of flaps intended to be deployed in order to seal at least partially an annular channel surrounding the engine, the mobile portion of the cowling including an annular housing extending longitudinally in order to receive the flaps in rest position. Each flap is linked to the fixed portion by a pivot joint and is linked to the mobile portion by a sliding-pivot joint, in such a way that a sliding of the mobile portion in separating from the fixed portion provokes a rotation of each flap around the axis of rotation of the joint with the fixed portion.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Thrust reverser assembly with shaped drag links]]></title>
            <link>http://www.freepatentsonline.com/8109467.html</link>
            <description><![CDATA[A thrust reverser blocker door assembly for use in turbofan engines includes an engine nacelle with an aft translating cowl that is movable from a stowed position to a deployed position. An engine case is disposed within the engine nacelle forming an airflow duct therebetween. A gap is uncovered when the translating cowl is moved into the deployed position, and a cascade vane set is positioned in the gap. A blocker door covers the cascade vane set while in the stowed position and blocks a portion of the airflow duct while in the deployed position. A geometrically shaped drag link is pivotally connected to the engine case at a first end and connected to the blocker door at a second end. While in the deployed position, the shape of the drag link provides clearance from the engine case.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Thrust reverser cascade assembly and AFT cascade ring with flow deflector portion]]></title>
            <link>http://www.freepatentsonline.com/8109466.html</link>
            <description><![CDATA[An aircraft engine thrust reverser cascade assembly includes a plurality of circumferentially spaced cascade segments, each cascade segment including a plurality of spaced vanes including an aft-most vane, and an aft end. The cascade assembly also includes an aft cascade ring removably attached to the aft ends of the cascade segments. The aft cascade ring includes a deflector portion that at least partially extends forward of the aft ends of the cascade segments. The deflector portion is configured to at least partially redirect at least a portion of a volume of air as the air outwardly passes between the aft-most vanes and the aft ends of the cascade segments.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Electro-magnetic up-lock for retractable landing gear]]></title>
            <link>http://www.freepatentsonline.com/8109465.html</link>
            <description><![CDATA[An electro-magnetic landing gear up-lock includes at least one electro-magnet mounted to the aircraft structure positioned adjacent the landing gear trunion. When the at least one electro-magnet is energized, magnetically responsive material in the landing gear positioned adjacent to the electro-magnet is attracted to the electro-magnet with sufficient force to hold the landing gear in a retracted. De-energizing the electro-magnet causes the electro-magnet to release the landing gear to allow the landing gear to extend.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Aircraft taxiing and secondary propulsion system]]></title>
            <link>http://www.freepatentsonline.com/8109464.html</link>
            <description><![CDATA[An on board secondary propulsion system for an aircraft provides the capability of taxiing the aircraft on the ground without using the main aircraft engine(s). The power system includes a small taxi engine mounted on or in the aircraft at a location suitable to provide a thrust sufficient only to taxi the aircraft. Such a suitable system may be provided as original equipment to an aircraft or retrofitted to existing aircraft. The on board secondary propulsion system, in addition to the taxiing function, can provide electrical power, an environmental control unit, power for the aircraft hydraulic system and an emergency power unit as desired. The system can also be used to supplement the main aircraft engines as necessary during takeoff and climb to further reduce fuel consumption, noise, engine emissions, maintenance costs and extend the life of the main aircraft engines, reduce the required takeoff distance of an aircraft when used in conjunction with the main engines and provide emergency glide support.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Self-propelled undercarriage wheel having a low profile tire]]></title>
            <link>http://www.freepatentsonline.com/8109463.html</link>
            <description><![CDATA[An undercarriage wheel is disclosed comprising an axle member that supports a drive member, for example but not limited to a compact high torque electric motor, a wheel member driven by said drive member, and a tire attached to the wheel member, wherein the tire bulges in the width dimension of the wheel, wherein the drive member protrudes from the wheel member and thus occupies at least some of the additional width made available by the bulge of the tire. A further aspect of the invention is an undercarriage wheel that comprises an axle member that supports a drive member, for example but not limited to a compact high torque electric motor, a wheel member driven by said drive member, and a low-profile tire attached to the wheel member. Since the profile of the tire is low, additional space is available inside the wheel for the drive member. Preferably, the drive member occupies at least some of this additional space, and has sufficient power to be able to propel an aircraft to which the undercarriage assembly is attached, either alone or in combination with other self-propelled undercarriage assemblies attached to the aircraft.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
        </item>
        <item>
            <title><![CDATA[Lenticular airship]]></title>
            <link>http://www.freepatentsonline.com/8109462.html</link>
            <description><![CDATA[An airship may include a hull substantially shaped as an oblate spheroid, one or more frame members defining a support structure, wherein the support structure forms at least a partial support for the hull, at least one horizontal stabilizing member operably coupled to a lower surface of the airship, and at least one horizontal stabilizing member having a first end and a second end. The at least one horizontal stabilizing member may define an anhedral configuration. The airship may also include a vertical stabilizing member having a first end pivotally coupled to the airship and a second end oriented to remain below an upper surface of the airship. The vertical stabilizing member may be configured to pivot within a vertical plane, and the first end of the vertical stabilizing member and the first end of the at least one horizontal stabilizing member may be operably coupled to one another.]]></description>
            <pubDate>Tue, 07 Feb 2012 08:00:00 EST</pubDate>
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