公开(公告)号：US20240286750A1

公开(公告)日：2024-08-29

申请号：US18175851

申请日：2023-02-28

Applicant: Raytheon Technologies Corporation

Inventor： Martin Amari

IPC: B64D31/00 ,  B60L15/20 ,  B60L50/60 ,  B64D27/24 ,  H02J9/06

CPC classification number: B64D31/00 ,  B60L15/20 ,  B60L50/60 ,  B64D27/24 ,  H02J9/061 ,  B60L2200/10 ,  B64D27/026

Abstract: A hybrid electric propulsion (HEP) system included in an aircraft includes a generator configured to output a first power, an energy storage system configured to output a second power, a propulsion system configured to generate thrust based on at least one of the first power and the second power, and an HEP controller in signal communication with the generator, the battery, and the HEP system. The HEP controller is configured to detect loss of the first power output from the generator, to determine an altitude of the aircraft and to actively control delivery of the second power to the propulsion system based on the altitude during the loss of the first power.

公开(公告)号：US20240425189A1

公开(公告)日：2024-12-26

申请号：US18341350

申请日：2023-06-26

Applicant: Raytheon Technologies Corporation

Inventor： Zubair A. Baig ,  Martin Amari ,  Ninad Joshi

IPC: B64D31/12 ,  B64D27/16 ,  B64D27/24

Abstract: An aircraft hybrid electrical propulsion (HEP) propulsion and attitude control system includes a propulsion system, electrical system and HEP controller. The propulsion system includes at least one propulsor and at least one electric motor configured to drive the at least one propulsor to generate to generate one or both of thrust and lift. The electrical system delivers a first amount of power to the at least one electric motor and a second amount of power to a plurality of electrical loads. The HEP controller determines at least one attitude goal of the aircraft, and controls the electrical system to adjust at least one of the thrust or lift to achieve the at least one attitude goal.

公开(公告)号：US20240209798A1

公开(公告)日：2024-06-27

申请号：US18085680

申请日：2022-12-21

Applicant: Raytheon Technologies Corporation

Inventor： Milos Ilak ,  Edmund Emmett Rochford ,  Martin Amari ,  Abhijit Chakraborty ,  Jerry Ding ,  Daniel T. Pollock ,  Konda Reddy Chevva ,  Jeffrey Ernst ,  William S. Heglund

IPC: F02C9/28 ,  F02C9/26

CPC classification number: F02C9/28 ,  F02C9/263

Abstract: A system including a supervisory controller configured to receive one or more mission objectives for an aircraft mission, and condition data; a memory for storing program instructions; at least one local supervisory controller, operatively coupled to the memory, and in communication with the supervisory controller and operative to execute program instructions to: simulate execution of the aircraft mission to address at least one of the one or more mission objectives; receive data output from at least one subsystem, the data output including a measurement of an aircraft physical system; generate a mission plan executable to address at least one of the one or more mission objectives via manipulation of the at least one subsystem; receive the generated mission plan at a subsystem controller directly from the at least one local supervisory controller; and automatically execute the generated mission plan to operate an aircraft.

公开(公告)号：US20240425190A1

公开(公告)日：2024-12-26

申请号：US18340341

申请日：2023-06-23

Applicant: Raytheon Technologies Corporation

Inventor： Martin Amari ,  Matthew L. Wilhide ,  Kyle Ives

IPC: B64D31/16 ,  B64C11/50

Abstract: A propulsion system includes a propulsion unit including a multi-stage fan having a first fan stage including a first rotor and a second fan stage including a second rotor. At least one propulsion motor is operably coupled to the first rotor and to the second rotor to drive the first rotor and the second rotor about a fan axis. A controller is configured to determine a position of at least one of the first rotor and the second rotor in response to an electrical signature of the at least one propulsion motor and adjust one or more operating parameters of at least one of the first rotor and the second rotor to reduce a noise produced by rotation of the first rotor and the noise produced by rotation of the second rotor in combination.

公开(公告)号：US20240408979A1

公开(公告)日：2024-12-12

申请号：US18330567

申请日：2023-06-07

Applicant: Raytheon Technologies Corporation

Inventor： Zubair A. Baig ,  Martin Amari ,  Tyler W. Hayes

IPC: B60W20/13 ,  B60L50/16 ,  B60W10/06 ,  B60W10/08

Abstract: A distributed hybrid propulsion system is provided and includes an engine assembly that includes an engine, which is non-propulsive, an energy storage element, a motor-generator and a common bus to which the engine assembly, the energy storage element, the motor-generator and the controller are connected. The common bus includes bi-directional power flow control elements, which are controllable to manage bi-directional power flow between the engine assembly, the energy storage element and the motor-generator.

公开(公告)号：US20240343399A1

公开(公告)日：2024-10-17

申请号：US18298952

申请日：2023-04-11

Applicant: Raytheon Technologies Corporation

Inventor： Martin Amari ,  Xin Wu ,  Tyler W. Hayes

IPC: B64D27/24 ,  B60L3/12 ,  B60L50/60 ,  B64D27/10 ,  B64D31/00 ,  B64D45/00

CPC classification number: B64D27/24 ,  B60L3/12 ,  B60L50/60 ,  B64D27/10 ,  B64D31/00 ,  B64D45/00 ,  B60L2200/10 ,  B64D27/026 ,  B64D2045/0085

Abstract: A hybrid electric propulsion (HEP) system of an aircraft includes a gas turbine engine configured to generate rotational power, and an electric propulsion system configured to generate at least one of thrust or lift for operation of the aircraft. The propulsion system includes a propulsor and an electric motor configured to drive the propulsor. A controller is in signal communication with the gas turbine engine and the electric propulsion system. The controller operates the gas turbine engine based on an on-board engine model (OEM), monitors electrical parameters of the electric propulsion system, and updates the OEM in response to changes to the electrical parameters.

公开(公告)号：US20240300657A1

公开(公告)日：2024-09-12

申请号：US18179045

申请日：2023-03-06

Applicant: Raytheon Technologies Corporation

Inventor： Zubair A. Baig ,  Martin Amari

IPC: B64D27/24 ,  F01D15/10

CPC classification number: B64D27/24 ,  B60L1/08 ,  F01D15/10 ,  B64D27/026 ,  F05D2220/323 ,  F05D2270/05

Abstract: An aircraft hybrid electrical propulsion (HEP) system includes an electrical system configured to deliver power to a plurality of electrical loads, a propulsion system configured to generate thrust in response to an input power, and an HEP controller in signal communication with the electrical system and the propulsion system. The HEP controller is configured to monitor a load demand of at least one electrical load among the plurality of electrical loads and to actively control the input power to actively control the thrust in response to changes in the load demand.