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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/11/17/2009&amp;uspat=on</link>
<description>USPTO Class 244 Aeronautics</description>
<language>en-us</language>
<lastBuildDate>Thu, 19 Nov 2009 14:16:16 EST</lastBuildDate>

<item>
<title><![CDATA[Stealth bomber, transporter, air-to-air fueling tanker, and space plane]]></title>
<link>http://www.freepatentsonline.com/7618005.html</link>
<description><![CDATA[A stealth transporter aircraft having a rhomboid airframe with a dihedral bottom surface and a top surface designed as an airfoil. The rhomboid cross-sectional configuration of the airframe gives it increased lift, stealth characteristics, and enhanced load bearing capacity. The aircraft does not have conventional wing structure and its dihedral bottom surface allows it to make wheels-up emergency landings on water and hard runway surfaces with greater pilot survivability. A rigid central tubular area extending nearly the full length of the airframe is configured for passengers, luggage, munitions, and/or equipment and provides a backbone for the aircraft. The aircraft further has rear engines, a large fuel carrying capability, and may also undergo primarily interior modifications for function as a space plane or air-to-air fueling tanker. A vortex spoiler on the side edges of the airframe is also preferred, which eliminates trails while in high altitude flight.]]></description>
<pubDate>Tue, 17 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Force balancing actuator]]></title>
<link>http://www.freepatentsonline.com/7618007.html</link>
<description><![CDATA[There is provided a force balancing actuator for mounting a pressure vessel, containing an engine, to aircraft structure. The force balancing actuator includes a cylinder and piston that is mechanically connected between the pressure vessel and aircraft structure. This piston and cylinder adjustably provides force there between in response to variations in differential pressure between the pressurized cabin and ambient pressure. The cylinder and piston thereby relieves excessive load on engine isolators allowing the isolators to absorb engine vibrations.]]></description>
<pubDate>Tue, 17 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Apparatus for attachment of a unit to attachment devices in a vehicle]]></title>
<link>http://www.freepatentsonline.com/7618009.html</link>
<description><![CDATA[An apparatus for attachment of a unit to attachment devices in a vehicle, in particular an aircraft, has attachment elements which are provided for connection to the attachment devices. In this case, at least one attachment adapter is provided, and can be connected on the one hand to the unit to be attached and on the other hand by means of the attachment elements to at least one attachment device.]]></description>
<pubDate>Tue, 17 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Air supply for an aircraft]]></title>
<link>http://www.freepatentsonline.com/7618008.html</link>
<description><![CDATA[Nowadays in aircraft on-board inert gas generation systems (OBIGGS) are used to generate inert gases. Cooled bleed air of engines or auxiliary turbines is fed to said OBIGGS systems. According to an embodiment of the present invention, an air supply device for an OBIGGS system in an aircraft is proposed that comprises a bleed position ( 1,2 ). By way of the bleed position ( 1,2 ), air from an air conditioning unit ( 4,5 ) on board the aircraft can be bled and can be fed to the OBIGGS system. There is thus no need for an additional heat exchanger and an additional ram-air channel. Maintenance expenditure and air resistance are thus reduced.]]></description>
<pubDate>Tue, 17 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Ram air inlets for use with aircraft environmental control systems and other aircraft and non-aircraft systems]]></title>
<link>http://www.freepatentsonline.com/7618006.html</link>
<description><![CDATA[Ram air inlets for use with aircraft environmental control systems and other aircraft and non-aircraft systems are described herein. In one embodiment, a ram air inlet configured in accordance with the present invention includes an inlet lip spaced apart from an inlet housing. An inlet door is moveably attached to the inlet housing, and includes a first surface portion, a second surface portion, and a transition region extending between the first and second surface portions. The first surface portion is moveably positioned at least approximately forward of the inlet lip. The second surface portion is fixed at an angle relative to the first surface portion, and is moveably positioned at least approximately aft of the inlet lip. The transition region is positioned at least approximately adjacent to the inlet lip to form an inlet opening therebetween. Movement of the inlet door in a first direction reduces the size of the inlet opening to thereby decrease the flow of ram air through the inlet. Conversely, movement of the inlet door in a second direction enlarges the inlet opening to increase the flow of ram air through the inlet.]]></description>
<pubDate>Tue, 17 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Artificial satellite equipment panel]]></title>
<link>http://www.freepatentsonline.com/7619326.html</link>
<description><![CDATA[A satellite equipment panel on which may be mounted an installation equipment of a predetermined function, connectable by an interface, constitutes an artificial satellite. The satellite equipment panel includes a panel body, at least two interfaces for an interconnection to another satellite equipment panel, a line transfer switch disposed within the panel body for line transferring of the interconnection between the interfaces, wiring disposed within the panel body and connected at one end to one of the interfaces and at the other end to the line transfer switch for interconnecting the interfaces on that panel body. The interfaces and the wiring, in cooperation with a support structure, constitute a wiring module disposed within the panel body. The interface may comprise at least one of interfaces of electric communication, optical communication, and optical sensor.]]></description>
<pubDate>Tue, 17 Nov 2009 08:00:00 EST</pubDate>
</item>

<item>
<title><![CDATA[Flow control redistribution to mitigate high cycle fatigue]]></title>
<link>http://www.freepatentsonline.com/7617670.html</link>
<description><![CDATA[A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow, The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and/or distortion of the inlet when the particular engine conditions.]]></description>
<pubDate>Tue, 17 Nov 2009 08:00:00 EST</pubDate>
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