公开(公告)号：US20250051015A1

公开(公告)日：2025-02-13

申请号：US18799067

申请日：2024-08-09

Applicant: B/E Aerospace Fischer GmbH

Inventor： Melanie Wieland ,  Sinan Akdeniz ,  Herbert Hacker

IPC: B64D11/06 ,  B64C1/18 ,  B64C27/04

Abstract: An aircraft seat connector for mounting an aircraft seat to a mounting rail provided at a floor of an aircraft cabin is provided. The aircraft seat connector comprises a base portion for being introduced into the mounting rail and a seat connection portion. The seat connection portion extends from the base portion and is configured for being releasably coupled to an aircraft seat. The seat connection portion allows for coupling the aircraft seat to the seat connection portion in at least two different spatial orientations.

公开(公告)号：US20240409231A1

公开(公告)日：2024-12-12

申请号：US18808856

申请日：2024-08-19

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Marcello BARRETO DE PINHO

IPC: B64D37/32 ,  B64C27/04 ,  B64D37/00 ,  B64D37/04

Abstract: An aircraft with a fuselage that accommodates a floor panel and a fuel storage system, wherein the fuel storage system comprises a tank system with at least one main tank 5a that is arranged underneath the floor panel; a cross ventilation system with a plurality of ventilation lines for venting the tank system, wherein the plurality of ventilation lines comprises at least one crossing ventilation line 11a that is routed from a first lateral side of the tank system to an opposite second lateral side of the tank system; and wherein the at least one crossing ventilation line is routed underneath or in the floor panel from the first lateral side of the tank system to the second lateral side of the tank system.

公开(公告)号：US20240404424A1

公开(公告)日：2024-12-05

申请号：US18608145

申请日：2024-03-18

Applicant: AIRBUS HELICOPTERS ,  AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Guillaume DUMUR ,  Ivan CHASSAGNE ,  Carl OCKIER

IPC: G09B9/46 ,  B64C27/04

Abstract: A rotorcraft flight training method for a rotorcraft comprising at least two engines and at least one rotor providing lift helping to keep the rotorcraft in the air. The method comprises at least the following steps: flying the rotorcraft in a mode wherein each engine supplies driving power to the rotor; and activating a first command to start a training phase simulating asymmetric flight, the training phase comprising a first flight phase comprising a first control operation, with a controller, controlling the at least two engines and a first display operation for displaying, with a display, information carrying at least two simulated powers.

公开(公告)号：US12100872B2

公开(公告)日：2024-09-24

申请号：US18314757

申请日：2023-05-09

Applicant: Textron Innovations Inc.

Inventor： Joseph Dean Rainville

IPC: B64D27/24 ,  B64C27/04 ,  B64D41/00 ,  H01M8/04537 ,  H01M8/04858

CPC classification number: H01M8/04552 ,  B64C27/04 ,  B64D27/24 ,  B64D41/00 ,  H01M8/04567 ,  H01M8/04873 ,  B64D2041/005 ,  B64D2221/00 ,  H01M2250/20

Abstract: A fuel-cell system for powering an electrical load, the system having first and second fuel cells, each having a positive node and a negative node. The positive node of the second fuel cell is electrically coupled to the negative node of the first fuel cell, and the positive node of the first fuel cell and the negative node of the second fuel cell are electrically coupled to the electrical load. Each fuel cell is electrically coupled to the electrical load without a power converter.

公开(公告)号：US20240246660A1

公开(公告)日：2024-07-25

申请号：US18566023

申请日：2022-06-03

Applicant: Safran Electronics & Defense

Inventor： Remi-Louis Lawniczak ,  Christophe Bastide

IPC: B64C13/50 ,  B64C27/04

CPC classification number: B64C13/507 ,  B64C27/04

Abstract: This aircraft flight compensator control system comprises a motor (3) and a variable-friction actuator (6) coupled with the motor and with an output shaft (8).
The variable-friction actuator comprises a variable-friction-torque magnetic clutch connected to the output shaft

公开(公告)号：US12043370B2

公开(公告)日：2024-07-23

申请号：US17818863

申请日：2022-08-10

Applicant: TEXTRON INNOVATIONS INC.

Inventor： Cody Fegely ,  Kenneth Stephen Wittmer

IPC: B64C13/00 ,  B64C13/50 ,  B64C27/04 ,  B64C27/57 ,  B64C27/82

CPC classification number: B64C13/503 ,  B64C27/04 ,  B64C27/57 ,  B64C2027/8209

Abstract: There is disclosed in one example a flight control computer for a rotary aircraft, including: a first interface to communicatively couple to a flight control input; a second interface to communicatively couple to flight geometry actuators; a data source; a multi-dimensional lookup table including a data structure to correlate flight control inputs to flight geometry actuator outputs according to a third-factor; and circuitry and logic instructions to: receive an input via the first interface; query the data source for the third-factor; query the multi-dimensional lookup table for a control input modifier according to the flight control input and the third-factor; and compute and send via a third interface a flight geometry output according to the control input modifier.

公开(公告)号：US11851171B2

公开(公告)日：2023-12-26

申请号：US17264180

申请日：2019-07-26

Applicant: LEONARDO S.P.A.

Inventor： Paolo Pisani ,  Federico Montagna ,  Stefano Poggi

IPC: B64C27/04 ,  F02C7/14 ,  F28D9/00 ,  F28D21/00

CPC classification number: B64C27/04 ,  F02C7/14 ,  F28D9/0068 ,  F28D2021/0021 ,  F28D2021/0049 ,  F28D2021/0089

Abstract: A heat exchanger for a transmission unit of an aircraft is described that comprises: a first module defining a first feed path for a first fluid to be cooled; a second module defining a second feed path for a second cooling fluid; the first and second feed paths being thermally coupled to each other; each second module comprising: at least one cell formed by an inlet for a second cooling fluid; an outlet for the second cooling fluid, which is arrange on the opposite side to the inlet along a first direction; a first wall thermally coupled to the first path; a pair of second walls; and a plurality of fins projecting in a cantilever fashion from the first wall. The heat exchanger further comprises at least a first row of fins, which lie on a plane orthogonal to the first direction, the fins of the first row extending at progressively increasing distances from one of the second walls along a second direction orthogonal to the first direction.

公开(公告)号：US11820520B2

公开(公告)日：2023-11-21

申请号：US17695287

申请日：2022-03-15

Applicant: AIRBUS HELICOPTERS

Inventor： Sebastien Andral ,  Christophe Serr

IPC: B64D15/00 ,  B64C27/04 ,  B64C27/82

CPC classification number: B64D15/00 ,  B64C27/04 ,  B64C27/82 ,  B64C2027/8254

Abstract: A rotorcraft provided with a yaw motion control system comprising a fairing and a rotor provided with blades, the blades being arranged in the fairing and able to rotate about an axis of rotation of the rotor, the fairing comprising a casing defining an air stream, the air stream extending in a direction of flow of the air within the fairing from an intake section towards an outlet section. The rotorcraft comprises an ice protection system comprising at least one grille arranged upstream of the air stream in the air flow direction, the grille facing the intake section parallel to the axis of rotation and the casing, no grille facing at least one unprotected section of the intake section in a direction parallel to the axis of rotation.

公开(公告)号：US11794879B2

公开(公告)日：2023-10-24

申请号：US17515231

申请日：2021-10-29

Applicant: Alexander I. Poltorak

Inventor： Alexander I. Poltorak

IPC: B64C17/02 ,  B64C27/08 ,  B64C39/02 ,  B60W20/10 ,  B64C27/04 ,  B64U10/10 ,  B64U10/13 ,  B64U30/20 ,  B64U50/13 ,  B64U50/19 ,  B64U101/60

CPC classification number: B64C17/02 ,  B60W20/10 ,  B64C27/04 ,  B64C27/08 ,  B64C39/024 ,  B64U10/10 ,  B64U10/13 ,  B64U30/20 ,  B64U50/13 ,  B64U50/19 ,  B64U2101/60

Abstract: A hover-capable flying machine such as a drone includes a robotic arm extending from the body, and an instrumentality for balancing the machine in response to disturbances such as those caused by picking up and dropping of the payload by the extended robotic arm. In embodiments, the end of the arm is equipped with a balancing rotor assembly that may provide lift sufficient to counteract the weight of the payload and/or of the arm. In embodiments, the machine's power pack is shifted in response to the disturbances. The power pack may be moved, for example, on a rail within and/or extending beyond the machine in a direction generally opposite to the extended arm. The power pack may also be built into a bandolier-like device that can be rolled-in and rolled out, thus changing the center of gravity of the machine.

公开(公告)号：US11787531B2

公开(公告)日：2023-10-17

申请号：US17666260

申请日：2022-02-07

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Dominik Vogel ,  Alexandru Dinca

IPC: B64C27/04 ,  B64D1/08

CPC classification number: B64C27/04 ,  B64D1/08

Abstract: A modular load carrying apparatus for a rotary wing aircraft and to a rotary wing aircraft with such a modular load carrying apparatus. The modular load carrying apparatus may include a tube, first and second caps at first and second axial ends of the tube, a carrier star with docking devices that are adapted for rotatably receiving a seat or a carrier beam that may be folded against the tube in a stowed position or unfolded from the tube in a deployed position. A tension rod may be spanned between the first and second caps and transfer tension loads from the carrier star via the second cap towards the first cap.