CESSNA AIRCRAFT COMPANY Patent applications |
Patent application number | Title | Published |
20160101876 | Aircraft Troubleshooting Network - A global network is described for accessing aircraft remotely via a wide area network. Aircraft flight and operational data stored on the aircraft may be directly accessed via remote workstation or downloaded by centralized automatic processes for later analysis and diagnosis. | 04-14-2016 |
20160101875 | Adjustable Interior Markup - A system and method for simulating a structure is disclosed. An adjustable interior mockup for simulating a structure has a base with a first elongated side and a second elongated side, the first elongated side being nonadjacent the second elongated side; and an adjustable frame secured to the base. The adjustable frame includes a plurality of girder members secured along the first and second elongated sides to form an arc; a plurality of brackets; a plurality of arms having a latch attached to one end; and a sheet of fabric. The girders are securely fastened along the first elongated side of the base at predetermined intervals; the brackets are secured to the girders; the arms are received by the brackets and adjustably anchored to the girders via a fastener; and the latches engage the sheet of fabric, thus pulling the fabric into a shape that resembles the structure. | 04-14-2016 |
20150289695 | System For Attachment Of Coat Rod And Cargo Net - A system for quickly attaching and detaching a coat rod or cargo restraint system to the interior surfaces of an aircraft to optimize the limited space aboard an aircraft. | 10-15-2015 |
20150288466 | Systems And Methods For Testing Susceptibility Of Aircraft Components To Radio Frequencies - An apparatus for testing for the susceptibility of an aircraft system to radio frequencies comprises a wireless module for generating radio signals that sweep each of the 2.4 GHz frequency band and the 5 GHz frequency band. A first amplifier is configured for amplifying signals in the 2.4 GHz band, and a second amplifier is configured for amplifying signals in the 5 GHz band. The apparatus comprises at least one dual band antenna for transmitting the signals in each of the 2.4 GHz and the 5 GHz bands. | 10-08-2015 |
20150261895 | Synthesis Of Radio Frequency Environment - A system and method for simulating the radio frequency environment of an aircraft is described. Simulated location data and navigational aid data is used to calculate a digital representation of the radio frequency environment of an airplane at the simulated location. The digital representation of the radio frequency environment is converted into an analog signal and provided to the navigational system of the aircraft. | 09-17-2015 |
20150239548 | Window Assembly Installation - A system and method for installing a window panel assembly into an aircraft is disclosed. In one embodiment, the system has a retaining device having an outside edge that is sealed against an inboard surface of the aircraft skin. A biasing member is mounted to an inboard edge of the retaining device, and a plurality of protrusions (which are secured onto the biasing member) press against the window panel. This pushes the window panel outward, maintaining a seal around the edge of the window. | 08-27-2015 |
20150147183 | Propeller With Lightening Strike Protection - A propeller blade assembly including a propeller blade having a leading edge, and a trailing edge extending between a tip and a hub, and an electrically conductive band extending longitudinally on either or both of the leading edge and trailing edge. The electrically conductive band secured to the leading edge of the propeller serves as an entry point on the aircraft and conductive channel into the airframe thereby avoiding the potentially damaging effect of the lightening on the carbon fiber composite propeller. | 05-28-2015 |
20150048210 | System And Method For Reduced Flammability Of An Aircraft Fuel System - Disclosed is a method for controlling the flammability of fuel vapors in an aircraft main fuel tank that is located in whole or in part in the fuselage contour. The method comprises a fuel system architecture and fuel consumption sequencing maintaining liquid fuel in said main tanks during all normal operations. Ceasing the withdrawal of fuel from the main tank when the fuel reaches a predetermined level thereby limiting the volume and flammability exposure time of the fuel vapor ullage. Once the predetermined level is met the fuel is supplied from wing tanks throughout the remainder of the mission. The predetermined main tank fuel level at which wing tank fuel begins to be consumed is determined by the aircraft flight reserves fuel volume stored in the main tank as well as the amount necessary to continuously submerge the main tank fuel pumps during the entire mission. | 02-19-2015 |
20140300146 | Tracking Table Assembly - Disclosed is a foldable tracking table assembly comprising a primary leaf, and a secondary leaf rotatably secured to the primary leaf and a table bracket secured to the opposite end of the primary leaf The table bracket in turn is secured to an adapter plate which is atop one or more pillow blocks. The pillow blocks are disposed atop linear rails upon which the pillow blocks are capable of longitudinally traversing. Adjacent the linear rail is a serrated track parallel to the at least one rail and a serrated pawl capable of locking engagement with the serrated track. A solenoid facilitates the locking engagement of the pawl with the serrated track wherein a user of the table assembly manually activates the solenoid withdrawing the serrated pawl from locking engagement with the serrated track thereby allowing the table assembly to traverse the linear rail to a position that accommodates the user. | 10-09-2014 |
20140263848 | REVERSIBLE FLIGHT CONTROL SYSTEMS - An improved flight control system is described, providing for increased or reduced pilot input forces necessary to cause desired control surface deflections. | 09-18-2014 |
20140191081 | Seat Base For Aircraft - A seat base for use in aircraft has a first cross member, a second cross member, a first leg, a second leg, and a base plate having a first bendable tab and a second bendable tab facing away from the first tab. The first cross member, the second cross member, and the base plate are each configured to be secured to the first and second legs in an extended position and a retracted position. The first and second legs are configured to be secured to seat feet and floor tracking rails. The first and second cross members are secured to the base plate so as to allow for selective rotation of the first and second cross members in response to relative vertical movement of the first leg with respect to the second leg. | 07-10-2014 |
20140131520 | Thermal Insulation Barrier For An Aircraft De-Icing Heater - A structure for use with an electrothermal heating element is disclosed comprising a heating element contained in a mat and heater supports attached to one surface of the mat. The heating element is disposed between the skin and internal structure of an aircraft with the heater supports disposed toward the internal structure thereof. The heater supports maintain an insulating layer of air between the mat and the internal structure of the aircraft. | 05-15-2014 |
20140116194 | SELF-CENTERING AIRCRAFT FLAP POSITION COMMAND APPARATUS - An apparatus for controlling positioning of flaps in an aircraft includes a shift lever movable to each of a plurality of shift lever positions to control positioning of the flaps of the aircraft to each of a respective plurality of associated flap positions. A shift lever indexing plate includes a plurality of engagement positions associated with the plurality of shift lever positions, respectively, the shift lever being coupled to an engagement member, the engagement member moving with the shift lever and being biased to selectively engage a selected one of the plurality of the engagement positions associated with a selected one of the shift lever positions to command the aircraft flaps to the flap position associated with the selected one of the shift lever positions. The shift lever indexing plate includes a web portion which separates the engagement positions of the shift lever indexing plate, the web portion and the shift lever being shaped and the shift lever being biased such that when the shift lever is at rest and only the shift lever bias is applied to the shift lever, the engagement member must be engaged with one of the plurality of engagement positions of the shift lever indexing plate. | 05-01-2014 |
20140053975 | Composite Panel With Fixed Void Content And Methods Of Making Same - A method for a composite panel having a desired void content is disclosed. The method comprises the step of laying on a surface a first ply of resin. A first filament is placed on the first ply, and a second ply of resin is laid on the first ply and the first filament to form a first intermediate composite panel. The first intermediate composite panel is cured in an autoclave to form a second intermediate composite panel. The second intermediate composite panel is submerged in a solution that dissolves the first filament. | 02-27-2014 |
20140049407 | Illuminated Sidestick Controller, Such As An Illuminated Sidestick Controller for Use In Aircraft - A system and method for illuminating one or more sidestick controllers within a cockpit of an aircraft is described. In some embodiments, the system includes a sidestick controller having lighting components that display lighting behaviors representing the movement and/or control of an aircraft. In some embodiments, the system illuminates various different lighting components on a sidestick controller based on information received from aircraft control systems, cockpit lighting systems, and other systems associated with an aircraft. | 02-20-2014 |
20130312432 | Water-Evacuator For Air Conditioner - A system and method for removing condensate from an air conditioning unit is disclosed. The system comprises a conduit including an outlet portion that is connected to a chamber of a housing of the unit at a first location. The conduit includes an inlet portion that is connected to the chamber at a second location where condensate accumulates. A gravitational separator portion which extends below the second location is connected to the outlet portion and the inlet portion. A draining portion having an orifice for allowing condensate to exit the conduit is connected to the gravitational separator portion below the second location. The first location is chosen such that during operation of the unit the pressure at the first location is less than the pressure at the second location. | 11-28-2013 |
20130256056 | Acoustic Baffle For Centrifugal Blowers - An acoustic baffle for reducing noise of a centrifugal fan includes a base for mounting with a fan outlet and a projection extending from the length of the base at a back side of the base and curving away from a top surface of the base. The projection continuously tapers along at least one side from an area proximate the base to an apex. The apex aligns with a fan tangency point, and the apex or a trough of the projection aligns with a midpoint of the outlet, when the acoustic baffle is installed in the outlet. The acoustic baffle effects a gradual variation in radial and tangential airflow at the blower outlet, to reduce fan blade passage tone. | 10-03-2013 |
20130245907 | Antilock Braking System With Directional Control - A system and method for adjusting a yaw of an aircraft having an antilock braking system is disclosed. The antilock braking system includes a controller configured to receive a directional input from a rudder. The controller is further configured to deliver a braking output to at least one of a left wheel brake and a right wheel brake. A position of the rudder indicates a pilot's desired steering response, and to allow for braking optimization by the antilock braking system, the pilot depresses fully the left wheel brake pedal and the right wheel brake pedal. The controller receives the directional input after both the right wheel brake pedal and the left wheel brake pedal have been fully depressed. The controller then delivers the braking output and a pressure on one of the left wheel brake and the right wheel brake is reduced in accordance with the directional input. | 09-19-2013 |
20130226374 | Yaw Damping System And Method For Aircraft - An alternative system for damping the dutch roll mode in an aircraft is provided using roll control surfaces. Classical yaw dampers for the dutch roll mode utilize the yaw control surfaces such as a rudder to dampen the dutch roll mode oscillations. An alternative damper is described that utilizes roll control surfaces such as spoilers or ailerons to dampen the dutch roll mode. | 08-29-2013 |
20130087655 | Precipitation Static Charge Drain System For An Aircraft Window - A static charge drain system for an aircraft window includes a resistive probe penetrating an outer ply of the aircraft window, a first end of the probe being exposed at an outer surface of the outer ply of the aircraft window. A second end of the probe penetrates an inner surface of the outer ply of the aircraft window. A conductive drain element is disposed between the outer ply of the aircraft window and an inner ply of the aircraft window and is electrically connected between the second end of the probe and a ground point of the aircraft window. | 04-11-2013 |
20130082502 | Motion Sensing Seat Lock - A lock for locking an object in a vehicle in place comprises a base comprising a side surface and a front surface. The side surface has at least one opening, and the front surface has a ballast retainer and a hub mounting portion. A hub is rotatably coupled to the hub mounting portion. A ballast, which is operatively coupled to the hub, is housed within the ballast retainer. At least one locking member is also operatively coupled to the hub. The ballast is configured to automatically reposition itself within the ballast retainer from an initial unlocked position to a final locked position in response to a change in velocity of the vehicle. This repositioning of the ballast actuates the hub, and causes the at least one locking member to extend past the at least one opening. | 04-04-2013 |