Patents Assigned to Learjet Inc.
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Patent number: 10515491Abstract: Methods and apparatus disclosed herein may facilitate the evaluation of time-correlated operational data associated with a mobile platform more effectively by presenting the relevant data in ways that are relatively straightforward to interpret and more favorable to the identification of potential root causes. In some aspects, the methods and apparatus disclosed herein may facilitate the evaluation of multiple systems simultaneously at different points in time to study the initiation and evolution of one or more faults across one or more systems. In various embodiments, the methods and apparatus disclosed herein make use of graphic user interfaces containing synchronized elements such as two-dimensional plots, fault timelines, alert timelines and status information to facilitate diagnostics of mobile platforms.Type: GrantFiled: September 9, 2015Date of Patent: December 24, 2019Assignee: LEARJET INC.Inventor: Peter Fleming Levy
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Patent number: 10252818Abstract: A viewing device for an aircraft includes an image receiver adapted to receive an image of a predetermined spatial area of an exterior of an aircraft, an image projector adapted to display the image of the predetermined spatial area, and an image conduit connecting the image receiver to the image projector. The image receiver is adapted to be positioned on an exterior side of the aircraft below a lateral width of a fuselage of the aircraft while the image projector is adapted to be positioned on an interior side of the aircraft above the lateral width of the fuselage of the aircraft. The image projector is adapted to be positioned at a first predetermined height above a floor on the interior side of the aircraft, consistent with a person's eye level. The image projector is separated from the image receiver by a first predetermined distance.Type: GrantFiled: November 14, 2013Date of Patent: April 9, 2019Assignee: LEARJET INC.Inventors: Harris K. Butler, III, Kris Rustman
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Patent number: 10220593Abstract: A composite material includes a honeycomb layer with top and bottom sides. The honeycomb layer includes a plurality of walls defining a plurality of cells therein. A first adhesive layer is disposed adjacent to the top side of the honeycomb layer. A second adhesive layer is disposed adjacent to the bottom side of the honeycomb layer. A third adhesive layer is disposed adjacent to the first adhesive layer on the top side of the honeycomb layer. A first composite layer is disposed adjacent to the third adhesive layer on the top side of the honeycomb layer. A second composite layer is disposed adjacent to the second adhesive layer on the bottom side of the honey comb layer. At least the third adhesive layer comprises viscous properties that discourage the creation of channels within the first composite layer when co-cured.Type: GrantFiled: July 1, 2014Date of Patent: March 5, 2019Assignee: LEARJET INC.Inventors: Khassan Mourtazov, Pierre Drolet, Pierre Harter, David Wilson
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Patent number: 9981732Abstract: A door for an aircraft includes a first panel divisible into at least two first slats that are releasably connected to one another, a first tensioning cable attached between the at least two first slats, and a first tensioner connected to the first tensioning cable and being operative to apply a first tension thereto, thereby permitting the first tensioning cable to hold the at least two first slats together to form the first panel and to release the first tension in the first tensioning cable upon occurrence of a release action, thereby permitting the at least two first slats to dissociate from one another so that the first panel fragments.Type: GrantFiled: July 11, 2014Date of Patent: May 29, 2018Assignees: LEARJET INC., C&D ZODIAC, INC.Inventors: William A. Goings, Eric Long
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Patent number: 9873501Abstract: A system and method for fabricating a composite material assembly. The components of the assembly originate from more than one mold while providing curing or solidifying under heat and vacuum in one step only, preferably with a composite material in a pre-preg form which does not require autoclave treatment. A removable insert is removed from a second mold prior to assembly of a first mold to the second mold. A section of a laminate extending over the removable insert overlaps over an adjacent laminate after closing and assembly of the first mold onto the second mold.Type: GrantFiled: July 13, 2010Date of Patent: January 23, 2018Assignee: LEARJET INC.Inventors: Alain Landry, Germain Belanger
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Patent number: 9873503Abstract: Tailplanes and empennages for aircraft are disclosed. An exemplary tailplane disclosed includes a stabilizer having a fixed shape and an elevator movably secured to the stabilizer. The elevator is movable from a neutral position relative to the stabilizer. The stabilizer and the elevator define an airfoil cross-sectional shape having a positive camber when the elevator is in the neutral position. The positive camber of the airfoil cross-sectional shape may facilitate movement of the elevator during some flight conditions. Also disclosed are tailplanes having camber distributions that vary along the spans of the tailplanes.Type: GrantFiled: July 21, 2014Date of Patent: January 23, 2018Assignee: LEARJET INC.Inventors: Reuben Chandrasekharan, Nick Iarocci, Shermineh Vafa, Iyad Akel
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Patent number: 9561846Abstract: A bias gain system for aircraft rudder comprises a pair of connector ends receiving an actuation force from a bias actuator. A rudder bar interface is positioned between the connector ends. The interface rotates about the rudder bar as a function of the actuation forces from the bias actuators. A mechanism comprises links and joints between the connector ends and the rudder bar is actuatable between a contracted configuration, in which first moment arms are defined between the connector ends and the rudder bar interface, and an expanded gain configuration, in which second moment arms have a greater dimension than the first moment arms. An actuator is connected to the mechanism to actuate the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators, to move the mechanism between configurations. An aircraft and a method for controlling a torque on a rudder bar of an aircraft are also provided.Type: GrantFiled: July 26, 2011Date of Patent: February 7, 2017Assignee: LEARJET INC.Inventors: Harris K. Butler, III, Mihalis Veletas
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Patent number: 9359066Abstract: A cable support apparatus for an aircraft cable control system comprises at least one cable support unit. The cable support unit includes a pulley adapted to carry a cable of the aircraft cable control system, a support link with a first joint between the pulley and the support link and a second joint between the support link and the structure of the aircraft, and a compensation link connected with the structure of the aircraft. The thermal expansion of the compensation link causes a displacement of the support link. An aircraft and a method for maintaining a tension of a cable of a cable control system of an aircraft are also provided.Type: GrantFiled: May 19, 2011Date of Patent: June 7, 2016Assignee: LEARJET INC.Inventor: Harris Butler
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Publication number: 20140145029Abstract: A bias gain system for aircraft rudder comprises a pair of connector ends receiving an actuation force from a bias actuator. A rudder bar interface is positioned between the connector ends. The interface rotates about the rudder bar as a function of the actuation forces from the bias actuators. A mechanism comprises links and joints between the connector ends and the rudder bar is actuatable between a contracted configuration, in which first moment arms are defined between the connector ends and the rudder bar interface, and an expanded gain configuration, in which second moment arms have a greater dimension than the first moment arms. An actuator is connected to the mechanism to actuate the mechanism to actuate the mechanism independently from the actuation forces from the bias actuators, to move the mechanism between configurations. An aircraft and a method for controlling a torque on a rudder bar of an aircraft are also provided.Type: ApplicationFiled: July 26, 2011Publication date: May 29, 2014Applicant: LEARJET INC.Inventors: Harris K. Butler, III, Mihalis Veletas
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Publication number: 20130011586Abstract: A system and method for fabricating a composite material assembly. The components of the assembly originate from more than one mold while providing curing or solidifying under heat and vacuum in one step only, preferably with a composite material in a pre-preg form which does not require autoclave treatment. A removable insert is removed from a second mold prior to assembly of a first mold to the second mold. A section of a laminate extending over the removable insert overlaps over an adjacent laminate after closing and assembly of the first mold onto the second mold.Type: ApplicationFiled: July 13, 2010Publication date: January 10, 2013Applicants: SHORT BROTHERS PLC, LEARJET INC.Inventors: Alain Landry, Germain Belanger
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Patent number: 5238207Abstract: The invention is a proportional rudder boost system for manually controlled aircraft which also have a yaw dampening system. The boost system includes four sensors in the pilot's and copilot's pedals including a summation means which adds the manual inputs from both pilots to provide a combined output signal to the power boost computer. Once the combined output signal exceeds a minimum force level, the boost computer signals the yaw servo to increase its torque applied to the rudder from zero in proportion to the increase in manual force applied to the rudder pedals up to a maximum power assist force level.Type: GrantFiled: April 16, 1991Date of Patent: August 24, 1993Assignee: Learjet Inc.Inventors: Frederick R. Wallace, Joseph N. Hein