Patents by Inventor Justin B. McAllister
Justin B. McAllister has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
-
Publication number: 20160163206Abstract: 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.Type: ApplicationFiled: November 9, 2015Publication date: June 9, 2016Applicant: AEROVIRONMENT INC.Inventors: Christopher E. Fisher, Thomas Robert Szarek, Justin B. McAllister, Pavel Belik
-
Patent number: 9208689Abstract: 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.Type: GrantFiled: August 16, 2012Date of Patent: December 8, 2015Assignee: AeroVironment Inc.Inventors: Christopher E. Fisher, Thomas Robert Szarek, Justin B. McAllister, Pavel Belik
-
Publication number: 20150307180Abstract: 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.Type: ApplicationFiled: February 25, 2015Publication date: October 29, 2015Inventors: Uchenna Ofoma, Bart Dean Hibbs, Ronald Olch, Justin B. McAllister
-
Publication number: 20150266146Abstract: 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.Type: ApplicationFiled: May 26, 2015Publication date: September 24, 2015Inventors: Uchenna Ofoma, Bart Dean Hibbs, Ronald Olch, Justin B. McAllister
-
Patent number: 9067287Abstract: A method of manufacturing a heat transfer system is provided that includes, in one form, preparing a heat conducting array by perforating at least a portion of the heat conducting array, placing the heat conducting array around foam elements, placing a heat conducting spreader along one surface area of the foam elements, placing a lower skin over the heat conducting spreader, placing an upper skin over an opposite surface area of the foam elements to create a structural assembly, and curing the structural assembly. A material of the foam elements flows through the perforated portion of the heat conducting array during the curing step.Type: GrantFiled: August 29, 2011Date of Patent: June 30, 2015Assignee: AEROVIRONMENT, INC.Inventors: Uchenna Ofoma, Bart Dean Hibbs, Ronald Olch, Justin B. McAllister
-
Patent number: 8995131Abstract: 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.Type: GrantFiled: August 29, 2011Date of Patent: March 31, 2015Assignee: AeroVironment, Inc.Inventors: Uchenna Ofoma, Bart Dean Hibbs, Ronald Olch, Justin B. McAllister
-
Publication number: 20140350748Abstract: 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.Type: ApplicationFiled: August 16, 2012Publication date: November 27, 2014Applicant: AeroVironment Inc.Inventors: Christopher E. Fisher, Thomas Robert Szarek, Justin B. McAllister, Pavel Belik
-
Publication number: 20140343752Abstract: 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.Type: ApplicationFiled: August 16, 2012Publication date: November 20, 2014Applicant: AEROVIRONMENT INC.Inventors: Christopher E. Fisher, Thomas Robert Szarek, Justin B. McAllister, Pavel Belik
-
Patent number: 8761967Abstract: 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 set of at least one external component; (b) determine a mode of operation, by the processor having a current mode of operation setting, based on the received component information and at least one of: an initial mode of operation setting and the current mode of operation setting; (c) determines whether all of the one or more received component information sets match a configuration requirement; (d) transitions to a flight-ready status if the determination is a conjunctive match; and (e) transition to a reset status if the determination is not a conjunctive match.Type: GrantFiled: May 23, 2012Date of Patent: June 24, 2014Assignee: Aerovironment, Inc.Inventors: Christopher E. Fisher, Marc L. Schmalzel, Steven Chambers, Justin B. McAllister
-
Publication number: 20130047435Abstract: A method of manufacturing a heat transfer system is provided that includes, in one form, preparing a heat conducting array by perforating at least a portion of the heat conducting array, wrapping the heat conducting array around foam elements, placing a heat conducting spreader along one surface area of the foam elements, placing a lower skin over the heat conducting spreader, placing an upper skin over an opposite surface area of the foam elements to create a structural assembly, and curing the structural assembly. A material of the foam elements flows through the perforated portion of the heat conducting array during the curing step.Type: ApplicationFiled: August 29, 2011Publication date: February 28, 2013Applicant: AeroVironment IncInventors: Uchenna Ofoma, Bart Dean Hibbs, Ronald Olch, Justin B. McAllister
-
Publication number: 20130048242Abstract: 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.Type: ApplicationFiled: August 29, 2011Publication date: February 28, 2013Applicant: AeroVironment IncInventors: Uchenna Ofoma, Bart Dean Hibbs, Ronald Olch, Justin B. McAllister
-
Publication number: 20120232722Abstract: 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 14 set of at least one external component; (b) determine a mode of operation, by the processor having a current mode of operation setting, based on the received component information and at least one of: an initial mode of operation setting and the current mode of operation setting; (c) determines whether all of the one or more received component information sets match a configuration requirement; (d) transitions to a flight-ready status if the determination is a conjunctive match; and (e) transition to a reset status if the determination is not a conjunctive match.Type: ApplicationFiled: May 23, 2012Publication date: September 13, 2012Inventors: Christopher E. Fisher, Marc L. Schmalzel, Steven Chambers, Justin B. McAllister