公开(公告)号：US11014684B2

公开(公告)日：2021-05-25

申请号：US15927228

申请日：2018-03-21

Applicant: Textron Aviation Inc.

Inventor： Vernon Weng-Yew Chang ,  Charles Bernard Beuning ,  Adam Blake Wolfe ,  Phuong Ngoc Ta ,  Mark Christopher Hansen

IPC: B64D41/00 ,  H02J1/00 ,  B64D13/06 ,  H02J7/00 ,  G05D1/00 ,  H02M7/44 ,  H02J7/14 ,  B64F5/40 ,  H02J1/10 ,  H01M50/20 ,  B64F5/60 ,  B64D45/00 ,  G01F9/00 ,  G07C5/00 ,  H01M10/42 ,  H01M50/50 ,  H01M50/543

Abstract: An expedited preflight readiness system for aircraft includes a power source having one or more battery modules for storing electrical power. An integrated controller is electrically and communicatively coupled with the power source for monitoring and controlling the power source to provide electrical power to aircraft subsystems. A mobile device is communicatively coupled with the integrated controller for communicating instructions to the integrated controller for initiating preflight readiness of the aircraft and for monitoring preflight readiness. A method for preconditioning an aircraft includes determining a state-of-charge of an APU and activating an environmental control subsystem for preconditioning the aircraft by adjusting a current temperature according to a preconditioning profile based on one or more of a target temperature, a target time, the current temperature, an outside air temperature, an amount of energy, and a state-of-charge of the APU.

公开(公告)号：USD915968S1

公开(公告)日：2021-04-13

申请号：US29623856

申请日：2017-10-27

Applicant: Textron Aviation Inc.

Designer： Michael Scott Robinson ,  Joshua Phillip DeDonder ,  Todd Alan Thisius

公开(公告)号：US10974843B2

公开(公告)日：2021-04-13

申请号：US15927248

申请日：2018-03-21

Applicant: Textron Aviation Inc.

Inventor： Vernon Weng-Yew Chang ,  Charles Bernard Beuning ,  August Bryce Ratzlaff ,  David Lee Swartzendruber

IPC: B64D41/00 ,  H02J1/00 ,  B64D13/06 ,  H02J7/00 ,  G05D1/00 ,  H01M2/10 ,  H02M7/44 ,  H02J7/14 ,  B64F5/40 ,  H02J1/10 ,  B64F5/60 ,  B64D45/00 ,  G01F9/00 ,  G07C5/00 ,  H01M10/42 ,  H01M2/30 ,  H01M2/20

Abstract: A distributed auxiliary-power-unit (APU) system for an aircraft includes one or more battery modules for storing electrical power, and a plurality of racks distributed throughout the aircraft for receiving the one or more battery modules to electrically connect with an electrical subsystem of the aircraft. A plurality of hot-swappable racks are adapted to receive the battery modules for electrically and communicatively coupling with the electrical subsystem and an integrated controller. A remote interface is communicatively coupled with the integrated controller for receiving user-input to direct electrical power from the battery modules to one or more subsystems of the aircraft. A number of battery modules installed is based on an amount of electrical power planned for a given flight of the aircraft.

公开(公告)号：US10940939B2

公开(公告)日：2021-03-09

申请号：US16213305

申请日：2018-12-07

Applicant: Textron Aviation Inc.

Inventor： Stephen M. Eddy ,  Scott Stallard ,  Richard John Scillia

IPC: B64C13/16 ,  B64C9/32 ,  B64C13/50

Abstract: A ground spoiler control architecture for aircraft includes a primary control architecture for providing a roll function, a speed-brake function and a ground spoiler function, and a secondary control architecture for providing the ground spoiler function in the event of a failure of the primary control architecture. The primary and secondary control architectures each include multiple actuators for actuating ground spoilers via independent and redundant signaling paths. Redundant hydraulic accumulators provide pressurized hydraulic fluid to the actuators. A ground spoiler control method includes determining whether the aircraft is on the ground based on the throttle-level-angle and whether any two wheels speeds are active or whether the main landing gear is weighted. Deployment of at least a portion of the ground spoiler panels occurs when and when the main landing gear is on the ground and the aircraft is in a landing configuration based on the throttle-level-angle.

公开(公告)号：US20210016891A1

公开(公告)日：2021-01-21

申请号：US16669847

申请日：2019-10-31

Applicant: Textron Aviation Inc.

Inventor： Thomas Edward Dwier ,  Robert G. Wellemeyer

IPC: B64D37/34 ,  B64C3/14

Abstract: Disclosed are systems and methods for maintaining bulk fuel temperatures in an aircraft. In one aspect, a recirculation system causes fuel to be delivered from a relatively low point near the feed hopper of each tank on the aircraft to one or more outboard locations of the wings. Once there, the fuel, due to gravity, flows back over the lower skin of the wing in channels back towards the fuselage, thus cooling the fuel. In other aspects, control systems are disclosed that coordinate the recirculation based on fuel levels in the tanks and fuel temperatures. The control systems also utilize a fuel scavenge system to maintain acceptable temperatures in the tanks.

公开(公告)号：US10787262B2

公开(公告)日：2020-09-29

申请号：US16055339

申请日：2018-08-06

Applicant: Textron Aviation Inc.

Inventor： Barry John Ward

IPC: B64D11/06 ,  A47C17/17 ,  A47C1/124 ,  A47C11/00 ,  A47C17/16 ,  A47C17/34 ,  B60N2/34 ,  A47C17/175 ,  B64D11/00

Abstract: Disclosed is a modular seat for aircraft. The system has a frame that is able to be interconnected with other frames laterally. Since each lateral frame has the same pivot points (when viewed from the side), the linked seats rotate together. The seats also include buckle lugs which enable a particular seat to be used on either side of the aircraft.

公开(公告)号：US20200216179A1

公开(公告)日：2020-07-09

申请号：US16719525

申请日：2019-12-18

Applicant: Textron Aviation Inc.

Inventor： Brent William Last ,  Gregory Lynn Ellis ,  Brandon Riley Shannon

IPC: B64D11/06 ,  A47C7/50

Abstract: An upholstery-guided footrest includes a footrest mechanically coupled to a seat. The footrest is configured for moving between a stowed position and one or more deployed positions. A flexible member has a first end and a second end opposite the first end. The first end is fastened to the seat and the second end is fastened to the footrest such that the flexible member supports the footrest during stowing. The flexible member bends around a frontside of the seat and is configured to guide and support the footrest into a stowed position.

公开(公告)号：US10689120B2

公开(公告)日：2020-06-23

申请号：US15689301

申请日：2017-08-29

Applicant: Textron Aviation Inc.

Inventor： Thang Chien Phi

IPC: B64D11/06 ,  B60N2/14 ,  B60N2/30

Abstract: A stowable reversible seat for a vehicle includes a first member pivotally coupled to a floor for supporting a seat base, a second member releasably secured to the floor for supporting the seat base, and a seat back pivotally coupled to the first member. Components of the seat pivot between a folded configuration for stowing and a deployed configuration for seating. The orientation of the seat may be reversed for switching between a forward-facing direction and an aft-facing direction. A method of configuring a seat into an aircraft includes adapting a cabinet area to receive and conceal the seat, configuring a rail to make the seat slidable out from the cabinet area into an aisle, attaching a pivotable seat base on the seat, and pivotally mounting a supporting leg underneath a portion of the seat to secure the pivotable seat base in a substantially horizontal position.

公开(公告)号：US20200182177A1

公开(公告)日：2020-06-11

申请号：US16707567

申请日：2019-12-09

Applicant: Textron Aviation Inc.

Inventor： Mark Sheridan Hunter ,  Ronald J. Parker

IPC: F02D41/02 ,  F02D11/02 ,  F02D11/10 ,  F16H59/02 ,  B64D31/04 ,  B64D31/14 ,  F02D41/14

Abstract: Disclosed is a throttle quadrant arrangement utilizing a throttle lever mechanically connected to three Rotary Variable Differential Transformers (RVDTs). The signals from the RVDTs are monitored by a process where the processing component. More specifically, RVDT outputs are monitored by the engine control system to determine if they are outside a predetermined range of operability. If an RVDT is not operable, the engine control system establishes a thrust output using the signal from one of the functional two. If only one or none are within the range, the system moves on to a default mode.

公开(公告)号：US20190283861A1

公开(公告)日：2019-09-19

申请号：US16298009

申请日：2019-03-11

Applicant: Textron Aviation Inc.

Inventor： Raymond Charters Maple

IPC: B64C7/02 ,  B64C21/02

Abstract: A fluid diverting air inlet includes an intake opening through an outer surface of an enclosure for receiving air flowing outside the outer surface. The intake opening ramps downwardly below the outer surface to define an intake passageway. An air diversion device is formed by lateral sidewalls of the intake opening that extend vertically above the outer surface. The lateral sidewalls converge together at an upstream end of the air inlet, and the lateral sidewalls diverge apart towards a downstream end of the air inlet. Flanges extend outwardly from the tops of the lateral sidewalls such that divided air passageways for boundary layer fluids are formed on each side of the air diversion device. The sidewalls and flanges are integrated with the air inlet such that fluid moving immediately adjacent the outer surface of the enclosure is diverted around the air inlet to avoid ingestion into the intake opening.