TEXTRON INNOVATIONS INC. Patent applications |
Patent application number | Title | Published |
20160131765 | Method of Developing Flight Infrastructure in Conjunction with a Sale of an Aircraft - A method for providing WAAS infrastructure in conjunction with the sale of a WAAS enabled aircraft includes developing a sales package for a customer. The price of the sales package preferably includes a WAAS enabled aircraft and a WAAS infrastructure. The method further includes assembling a WAAS enabled aircraft and developing the WAAS infrastructure using a computer. The method also includes providing the customer with the WAAS enabled aircraft and the WAAS infrastructure. | 05-12-2016 |
20160130007 | WINDOW MOUNTED RAFT SYSTEM - An inflatable life raft system for an aircraft includes a window coupled to a fuselage portion of the aircraft. A mechanism is used to selectively detach the window from the fuselage. An inflatable life raft is deployable to the exterior of the aircraft upon detachment of the window from the aircraft. | 05-12-2016 |
20160083086 | ROTOR YOKE AND METHOD OF MAKING THE SAME - A rotor yoke manufactured by a process comprising preparing a molded rotor yoke in a closed cavity tool and possibly machining at least one portion of the molded rotor yoke to form the rotor yoke. In the preferred embodiment, the preparing of the molded rotor yoke is accomplished by applying layers of uncured low-flow composite material and a layer of uncured high-flow adhesive; substantially enclosing the uncured molded rotor yoke in the closed cavity tool; and applying pressure so as to compress the uncured molded rotor yoke; and curing the uncured molded rotor yoke. During the curing process, the high-flow adhesive bleeds out of the molded rotor yoke, thereby preventing marcels from forming through movement of the low-flow composite material. | 03-24-2016 |
20150367936 | Optimized Core for a Structural Assembly - The present application relates a core member for a core-stiffened structural assembly. The core member includes a plurality of cell members oriented a direction to provide a tailored stiffness in a certain direction. The core member can further include one or more planar members that can aid in shear transfer between cell members. The cell members can be made from bonding a plurality of corrugated layers together. The core-stiffened structure can be a rotor blade for an aircraft. In such an embodiment, the torsional stiffness of the rotor blade can be tailored in at least one of the chordwise and spanwise directions to provide tailor a torsional stiffness at any give location in the rotor blade. | 12-24-2015 |
20150175274 | 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. | 06-25-2015 |
20140360830 | ROTOR HUB VIBRATION ATTENUATOR - A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe. A vibration attenuator having weights rotating about separate axes offset from each other. | 12-11-2014 |
20140288731 | Flight Control System - A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces. Further, through the present invention, force input signals received from the pilot are filtered to improve the operation of the computer-aided flight control surfaces. | 09-25-2014 |
20140286772 | ROTOR HUB VIBRATION ATTENUATOR - A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe. | 09-25-2014 |
20140239085 | On-Board Water Spray System For Aircraft - A system for simulating wet runway conditions by using a liquid container that is placed inside an aircraft. The liquid container is connected to a nozzle that sprays water in front of the wheels of the aircraft. A valve is used to control the flow of water from the nozzle. Systems, such as the braking system of the aircraft, can then be tested in wet runway conditions simulated by the system. The amount of water sprayed from the nozzle can also be electronically controlled in relation to the speed of the aircraft, such that the nozzle sprays a nearly uniform layer of liquid in front of the wheels. The system can also be modified to include two tanks to manipulate the center of gravity of the aircraft. | 08-28-2014 |
20140175842 | Aircraft Side-Ledge Console - A console for aircraft that is located between two seats which face each other. The console includes an open ledge with a cup holder arrangement. The cup holder arrangement includes two removable holder dividers which can be flipped up or down and held into position by a spring-loaded cam arrangement. The console also includes two inwardly facing surfaces which provide connectors for electronic devices resting on the ledge. A light-emitting face is provided on a back wall of the ledge so that any articles resting on the ledge can be seen in dark environments. | 06-26-2014 |
20140158463 | Accoustic 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 from the base to an apex that aligns with a center line of the base. The projection extends over the fan wheel and tapers from left and right sides of the outlet to a fan tangency point at a midpoint of the outlet and aligned with the apex, 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. | 06-12-2014 |
20140114505 | 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. | 04-24-2014 |
20130327892 | Aircraft Cabin Door Pressure Vent System - Disclosed is an aircraft door including a handle-activated pressure relief system that avoids potentially dangerous pressure differences between the cabin and the atmosphere outside the aircraft. A flow path is created between the inboard and outboard handles on the door. A pressure vent door is located in the flow path. The vent door being is opened when either of the inboard and outboard handle assemblies are activated. Once either handle is rotated beyond a particular point, a spring in the supporting mechanics becomes over-center. At the same time, the vent door comes under the influence of a magnet, snapping the vent open. After the door has been opened, it can be relatched by operating the handles in the reverse direction. The magnet and spring hold the vent door open until the aircraft door is fully latched, sealed, and secured. Only then does the vent door sealingly close. | 12-12-2013 |
20130327134 | Liquid Based Ice Protection Test Systems And Methods - A liquid based ice protection test system for testing an aircraft part having a first heating element comprises a tub configured for retaining a low temperature bath. The system also includes a first support member for suspending the aircraft part in the tub and a first temperature sensing device for sensing temperatures from one or more locations of a skin of the aircraft part. | 12-12-2013 |