Patent application number | Description | Published |
20120232722 | Automatic Configuration Control of a Device - Methods, systems, and devices for determining system/device configuration and setting a mode of operation based on the determined configuration. An air vehicle processor: (a) receives a component information | 09-13-2012 |
20130048242 | HEAT TRANSFER SYSTEM FOR AIRCRAFT STRUCTURES - A heat transfer system is provided by the present disclosure that includes, in one form, a structural member having an upper skin, a lower skin, and a foam core disposed between the upper skin and the lower skin. At least one heat conducting array extends through the foam core and between the upper skin and the lower skin, the heat conducting array defining at least one upper cap, at least one lower cap, and a wall portion extending between the upper cap and the lower cap, the upper cap being disposed proximate a heat source. A heat conducting spreader is disposed between the lower cap of the heat conducting array and the lower skin of the structural member. | 02-28-2013 |
20140061376 | Reconfigurable battery-operated vehicle system - A quadrotor UAV including ruggedized, integral-battery, load-bearing body, two arms on the load-bearing body, each arm having two rotors, a control module mounted on the load-bearing body, a payload module mounted on the control module, and skids configured as landing gear. The two arms are replaceable with arms having wheels for ground vehicle use, with arms having floats and props for water-surface use, and with arms having pitch-controlled props for underwater use. The control module is configured to operate as an unmanned aerial vehicle, an unmanned ground vehicle, an unmanned (water) surface vehicle, and an unmanned underwater vehicle, depending on the type of arms that are attached. | 03-06-2014 |
20140343752 | DEEP STALL AIRCRAFT LANDING - An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation. | 11-20-2014 |
20140350748 | INVERTED-LANDING AIRCRAFT - An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation. | 11-27-2014 |
20150266146 | METHOD OF MANUFACTURING A HEAT TRANSFER SYSTEM FOR AIRCRAFT STRUCTURES - A method of manufacturing a heat transfer system is provided that includes preparing a heat conducting array by perforating at least a portion of the heat conducting array, placing the heat conducting array around foam elements, and forming the structural assembly under heat and pressure. A material of the foam elements extends through the perforated portion of the heat conducting array during the forming step. | 09-24-2015 |
20150307180 | HEAT TRANSFER SYSTEM FOR AIRCRAFT STRUCTURES - A heat transfer system for use within an avionics bay of an aircraft is provided by the present disclosure that includes, in one form, an aircraft panel comprising an upper skin, a lower skin, and a foam core disposed between the upper skin and the lower skin. At least one heat conducting array extends through the foam core and between the upper skin and the lower skin, the heat conducting array defining at least one upper cap, at least one lower cap, and a wall portion extending between the upper cap and the lower cap, the upper cap being disposed proximate avionics within the avionics bay. A heat conducting spreader is disposed between the lower cap of the heat conducting array and the lower skin of the aircraft panel. | 10-29-2015 |