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<title>freepatentsonline.com</title>
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<title>freepatentsonline.com: Aeronautics</title>
<link>http://www.freepatentsonline.com/result.html?query_txt=ccl/244%20and%20isd/11/03/2009&amp;uspat=on</link>
<description>USPTO Class 244 Aeronautics</description>
<language>en-us</language>
<lastBuildDate>Thu, 05 Nov 2009 03:35:18 EST</lastBuildDate>

<item>
<title><![CDATA[Dual flow APU inlet and associated systems and methods]]></title>
<link>http://www.freepatentsonline.com/7611093.html</link>
<description><![CDATA[Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Unmanned aerial vehicle (UAV) deceleration system]]></title>
<link>http://www.freepatentsonline.com/7611094.html</link>
<description><![CDATA[A system for slowing an air vehicle, including an independently supported aerodynamic drag device designed so that, after contact is made between the flying air vehicle and the aerodynamic drag device, one or more parts of the aerodynamic drag device are carried along by the air vehicle thereby decelerating the air vehicle, so that a majority of a kinetic energy dissipation of a combination of the air vehicle and the aerodynamic drag device is due to an aerodynamic drag of the aerodynamic drag device.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Flight management process for an aircraft]]></title>
<link>http://www.freepatentsonline.com/7611098.html</link>
<description><![CDATA[A process wherein an aircraft starts from a cruising position by flying at a cruising speed to reach a position that intercepts the glide slope. The process can include the steps of decelerating from the begin descent speed and the begin descent altitude of the aircraft during a first descent phase with a first flight path angle until reaching a predetermined speed corresponding to an aircraft speed at which the aircraft flaps are extended for transitioning to a first intermediate position; following a second phase of descent at a considerably constant speed with a second flight path angle; and decelerating during a third phase of descent with a third flight path angle to reach the glide slope interception position. The aircraft slats and/or flaps adopt their first intermediate position considerably when transitioning from the second to the third phase of descent.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Internet linked environmental data collection system and method]]></title>
<link>http://www.freepatentsonline.com/7611092.html</link>
<description><![CDATA[An environmental data collection system and method is provided having an internet link for providing an additional level of security for a remotely controlled data collection platform having a security alarm for protecting the platform and the environmental subject of the study. A novel lighter-than-air platform having a novel snorkel for detachably securing, mooring and providing buoyancy control is provided for the collection of data in the form of real time audio and video linked to the internet and subscribers. The novel snorkel is flexible and retractable into the novel airship to provide remote buoyancy control of the airship together with silently operating electrical motors for allowing the novel airship to be remotely controlled and moved at will to track and monitor wildlife and make environmental measurements necessary for the protection of the environment, wildlife and the operation of the novel airship. Detachable securing means provide an anti-tethering feature of the novel airship and allow the collection of data from both, an aerial perspective and a ground perspective, while providing for the collection of data from either the surface of the earth or below the surface of the water while transmitting the data to scientists, environmentalists and subscribers through the internet.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Reaction-drive rotorcraft having an adjustable blade jet]]></title>
<link>http://www.freepatentsonline.com/7611090.html</link>
<description><![CDATA[Rotorcraft including an airframe having a fuselage extending between a forward and an aft end and a powerplant producing high-pressure fluid. The rotorcraft includes a rotor assembly rotatably mounted on the airframe and having a plurality of rotor blades extending from a hub. Each rotor blade has a base, a tip, a leading edge extending between the base and tip, and a trailing edge extending between the base and tip opposite the leading edge. Each rotor blade has a jet adjacent its trailing edge in fluid communication with the powerplant by way of a fluid path. Each jet is adjustable between an open position in which the jet allows the high-pressure fluid from the power plant to pass through the jet and out of the rotor blade and a closed position in which the jet prevents the high-pressure fluid from passing through the jet and out of the rotor blade.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[In orbit space transportation and recovery system]]></title>
<link>http://www.freepatentsonline.com/7611097.html</link>
<description><![CDATA[A preferred In Orbit Transportation & Recovery System (IOSTAR™) ( 10 ) includes a space tug powered by a nuclear reactor ( 19 ). The IOSTAR™ includes a collapsible boom ( 11 ) connected at one end to a propellant tank ( 13 ) which stores fuel for an electric propulsion system ( 12 ). This end of the boom ( 11 ) is equipped with docking hardware ( 14 ) that is able to grasp and hold a satellite ( 15 ) and as a means to refill the tank ( 13 ). Radiator panels ( 16 ) mounted on the boom ( 11 ) dissipate heat from the reactor ( 19 ). A radiation shield ( 20 ) is situated next to the reactor ( 19 ) to protect the satellite payload ( 15 ) at the far end of the boom ( 11 ). The IOSTAR™ ( 10 ) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Aerodynamic re-entry vehicle control with active and passive yaw flaps]]></title>
<link>http://www.freepatentsonline.com/7611095.html</link>
<description><![CDATA[A yaw control system is provided for use in a hypersonic airborne mobile platform, for example a re-entry vehicle. The system includes an active movable yaw control flap positioned between passive/fixed yaw ear surfaces that border or frame the active yaw flaps. The yaw control system includes an active yaw control flap embedded between passive/fixed yaw ear surfaces. The retracted active yaw control flap and passive/fixed yaw ear surfaces provide passive yaw damping during atmosphere reentry, bank-to-turn steering and midcourse fly-out/glide steering. The active yaw control flaps are preferably arranged on opposing sides of a re-entry vehicle, and may be independently extended to provide for steering the vehicle. The active yaw control flaps provide for active yaw control skid-to-turn terminal guidance to achieve a desired level of accuracy, such as needed when using the vehicle as a missile to strike a target.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[In orbit space transportation and recovery system]]></title>
<link>http://www.freepatentsonline.com/7611096.html</link>
<description><![CDATA[A preferred In Orbit Transportation & Recovery System (IOSTAR™) ( 10 ) includes a space tug powered by a nuclear reactor ( 19 ). The IOSTAR™ includes a collapsible boom ( 11 ) connected at one end to a propellant tank ( 13 ) which stores fuel for an electric propulsion system ( 12 ). This end of the boom ( 11 ) is equipped with docking hardware ( 14 ) that is able to grasp and hold a satellite ( 15 ) and as a means to refill the tank ( 13 ). Radiator panels ( 16 ) mounted on the boom ( 11 ) dissipate heat from the reactor ( 19 ). A radiation shield ( 20 ) is situated next to the reactor ( 19 ) to protect the satellite payload ( 15 ) at the far end of the boom ( 11 ). The IOSTAR™ ( 10 ) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[High speed vertical take-off and land aircraft with active fan balancing system]]></title>
<link>http://www.freepatentsonline.com/7611091.html</link>
<description><![CDATA[A high-speed vertical take-off and land aircraft includes a body with an engine supported by the body. A fan assembly is also carried by the body. The fan assembly includes a hub and a plurality of blades to provide vertical lift for the aircraft. A plurality of frictionless air bearings vertically support the fan assembly while a plurality of idler wheels horizontally center the fan assembly. In addition the aircraft includes an active system for sensing vibration and balancing the fan assembly.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Seal assemblies for use with drooped spoilers and other control surfaces on aircraft]]></title>
<link>http://www.freepatentsonline.com/7611099.html</link>
<description><![CDATA[Aerodynamic seals for use with control surfaces on aircraft are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member and a second seal member. The first seal member has a first proximal portion configured to be attached to a fixed airfoil portion of the aircraft, and a first distal portion configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion to at least partially seal the gap between the fixed airfoil portion and the movable control surface as the control surface moves relative to the fixed airfoil portion.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Side thruster module]]></title>
<link>http://www.freepatentsonline.com/7610747.html</link>
<description><![CDATA[A side thruster module, comprises: a cavity-type body skin extending in a longitudinal direction; a first thruster arranged in the body skin and extending in a longitudinal direction; and a conversion nozzle arranged in the body skin and extending in a radial direction perpendicular to the longitudinal direction, for converting a direction of a thrust generated from the first thruster in the longitudinal direction into the radial direction. A large number of thrusters can be mounted at the side thruster module thus to generate a high thrust, and the side thruster module can be slim in the radial direction perpendicular to the longitudinal direction.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[System, method, and apparatus for metallic-composite joint with compliant, non-corrosive interface]]></title>
<link>http://www.freepatentsonline.com/7611595.html</link>
<description><![CDATA[A metallic-composite joint is formed by inserting a metallic member into a slot of a pi-shaped composite preform. The preform is formed from woven carbon fiber in a binder of resin and may or may not be cured prior to assembly. An inert compliant layer is located between the legs of the preform and the metallic member. The resin binder or an adhesive is used to bond the compliant layer to the preform. The compliant layer has a coefficient of thermal expansion that more closely matches that of the preform. The properties of the compliant layer also avoid galvanic corrosion between the carbon in the preform and the metallic member.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Roadway for decelerating a vehicle including an aircraft]]></title>
<link>http://www.freepatentsonline.com/7611305.html</link>
<description><![CDATA[A method for slowing a vehicle traveling over a movable surface in a direction of travel where the vehicle has a first wheel and at least a second wheel offset from the first wheel in a direction opposite to the direction of travel. The method including: deploying the movable surface to an open position; moving the movable surface to a closed position due to the weight exerted on the movable surface by the first wheel of the vehicle as it travels over the movable surface; locking the movable surface in the closed position to convert at least a portion of a kinetic energy of the vehicle into potential energy to slow the vehicle; and redeploying the movable surface to the open position such that at least the moving can be repeated due to the weight exerted on the movable surface by the second wheel of the vehicle.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[System and method for enhancing the payload capacity, carriage efficiency, and adaptive flexibility of external stores mounted on an aerial vehicle]]></title>
<link>http://www.freepatentsonline.com/7610841.html</link>
<description><![CDATA[A system and method for the conversion of fuel tanks, detachably mountable on the exterior of an aerial vehicle, into high volume, high capacity, diverse functionality and aerodynamically efficient airborne stores is disclosed. A conventional external fuel drop tank is modified such that the exterior shape of the tank is substantially retained while the interior of the tank is suitable restructured to allow for the introduction of diverse airborne stores, associated airborne store mounting means, control and monitoring means and support means therein, which replace the fuel store. The airborne store is suitably interfaced to the stores control and management system of the aerial vehicle. The airborne store is integrated into a new external stores configuration The enhanced airborne store will have aerodynamic characteristics substantially similar to the original external fuel tank while its payload capacity is substantially improved.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Flight control surface actuator assembly including a free trial mechanism]]></title>
<link>http://www.freepatentsonline.com/7610828.html</link>
<description><![CDATA[A flight control surface actuator includes a mechanism that enables the actuator translation member to be selectively decoupled from the actuator rotating member. The actuator includes an actuation member, a translation member, an extension member, and a locking member. The actuation member is adapted to receive a drive force and is configured, in response to the drive force, to rotate and cause the translation member to translate. The extension member surrounds at least a portion of the translation member and is configured to be selectively coupled to, and decoupled from, the translation member. The locking member surrounds at least a portion of the extension tube and is movable between a lock position, in which the locking member couples the extension member to the translation member, and a release position, in which the locking member decouples the extension member from the translation member.]]></description>
<pubDate>Tue, 03 Nov 2009 08:00:00 EST</pubDate>
</item>

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