WO2010020199A1 - Aircraft hybrid propulsion - Google Patents

Aircraft hybrid propulsion Download PDF

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Publication number
WO2010020199A1
WO2010020199A1 PCT/CZ2009/000102 CZ2009000102W WO2010020199A1 WO 2010020199 A1 WO2010020199 A1 WO 2010020199A1 CZ 2009000102 W CZ2009000102 W CZ 2009000102W WO 2010020199 A1 WO2010020199 A1 WO 2010020199A1
Authority
WO
WIPO (PCT)
Prior art keywords
propeller
propulsion
electric motor
aircraft
fuselage
Prior art date
Application number
PCT/CZ2009/000102
Other languages
French (fr)
Inventor
Jiri Vycital
Tomas Moravec
Original Assignee
Jiri Vycital
Tomas Moravec
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Jiri Vycital, Tomas Moravec filed Critical Jiri Vycital
Publication of WO2010020199A1 publication Critical patent/WO2010020199A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/04—Aircraft characterised by the type or position of power plants of piston type
    • B64D27/08—Aircraft characterised by the type or position of power plants of piston type within, or attached to, fuselages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to an aircraft propulsion system, applying the electric motor and internal combustion engine principles.
  • propulsion units ' creating the propulsion by converting the chemical energy contained in the fuel to the thermal energy and then by the expansion to the mechanical energy, this energy is used for accelerating the air flow by the propeller and based on -the momentum conservation principle the thrust necessary for the aircraft motion ' is-; generated.
  • this basic principle of the energy conversion used for the propulsion, attempts to utilize for the propulsion the electrical energy by its conversion to the mechanical energy in the electric motor are emerging recently.
  • These electric motors are able, because of the limited capacity of the batteries, .to power only lighter aircraft, mostly aircraft models.
  • hybrid propulsion simply combines two independent propeller propulsion units, comprising an internal combustion engine with a propeller and an electric motor with a propeller.
  • the basis of the conceptual arrangement according to the invention is ⁇ the push ⁇ piill configuration of both kinds of propeller propulsion units on the aircraft fuselage.
  • One propeller propulsion unit is installed in the forward fuselage in the tractor configuration and the other propeller propulsion unit is located in the rear fuselage in the pusher configuration.
  • This propulsion units arrangement has no internal mechanical coupling and allows either a combined operation of both propulsion units, when both units generate maximum propulsive effect or, coincidentally, thjs arrangement allows independent operation of one of the propulsion units only, e.g. during the cruise flight, when the energy of the second propulsion unit is saved.
  • propulsion units / propeller axes may be located either in the proximity of the main aircraft/ fuselage axis or may be identical with the main aircraft / fuselage axis a ⁇ d this way is eliminated the yawing moment, which is otherwise important during the one engine inoperative flight of the aircraft with a conventional configuration of; engines installed on the wings.
  • Another advantage of the independent configuration of the propulsion ' units presents the possibility of a recuperation charging of batteries during flight using the electric motor in a generator mode, driven by the propeller.
  • This system of charging during flight may be also combined with charging of the batteries from the generator on the internal combustion engine as well as from the ground source and tjie electricity distribution grid.
  • the aircraft hybrid propulsion consists of two propeller . propulsion units, independent of each other, in a push-pull configuration.
  • the forward tractor propeller propulsion unit 1 may be either electric motor or internal combustion propulsion unit.
  • the rear pusher propeller propulsion unit 2 is located on the rear of the fuselage and may be either electric or internal combustion; propulsion unit depending on what kind of propeller propulsion unit is used as the , forward unit.
  • the propeller axes of both the propulsion units, the forward as well the rear, are arranged in parallel/ coaxial with the fuselage main longitudinal axis of symmetry.
  • the batteries supplying the electric motor 2 are rechargeable during flight by the, recuperation from the electric propeller with a propeller 2 and/or from the generator installed on the internal combustion propulsion engine 1

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Electric Propulsion And Braking For Vehicles (AREA)
  • Hybrid Electric Vehicles (AREA)

Abstract

The invention relates to the aircraft hybrid propulsion, consisting of two propeller propulsion units, one of which is based on the principle of an internal combustion engine (1). with a propeller and the second one on the principle of an electric motor (2) with a propeller characterized in that the propulsion units are installed without an interdependent mechanical coupling in the push-pull configuration in the direction of flight on the aircraft fuselage, so that one of the propulsion units (1, 2) is located in the forward fuselage and generates a propulsion effect using a tractor propeller and the second one of the propulsion units (1, 2) is located in the rear fuselage and generates a propulsion effect using a pusher propeller and the batteries supplying the energy to the electric motor are rechargeable by recuperation during flight. From the electric motor with a propeller (2) and/or from a generator installed on the internal combustion engine (1).

Description

Aircraft Hybrid Propulsion
Technical Field
The invention relates to an aircraft propulsion system, applying the electric motor and internal combustion engine principles.
Background Art
At present, most of the practically usable aircraft are powered by propulsion units', creating the propulsion by converting the chemical energy contained in the fuel to the thermal energy and then by the expansion to the mechanical energy, this energy is used for accelerating the air flow by the propeller and based on -the momentum conservation principle the thrust necessary for the aircraft motion ' is-; generated. Besides this basic principle of the energy conversion ;used for the propulsion, attempts to utilize for the propulsion the electrical energy by its conversion to the mechanical energy in the electric motor are emerging recently. These electric motors are able, because of the limited capacity of the batteries, .to power only lighter aircraft, mostly aircraft models. There appear also experirfigήts* attempting to overcome the limitations of the capacity of the batteries by /thφ application of a hybrid propulsion (a combination of an internal combustion engine and an electric motor), which are conceived as an analogy to the hybrid automobiles drive systems. In the frame of the this concept, there exists either a mechanical coupling between the combustion engine and the electric motpjv constituting a coupled drive train to a single propeller only and this way both propulsion units are interdependent, or the combustion engine is only a source of energy for the battery charging. These designs have disadvantages, from the point of view of the aircraft applications, mainly with regard to their complexity, weight ■
Figure imgf000002_0001
the hydrocarbon fossil fuels on the crude oil bases, the trend of the electrical energy utilization for the aircraft propulsion gains increasing importance. Disclosure of the Invention
The disadvantages and limited capabilities of a purely electrically powered aircraft are eliminated by the proposed hybrid propulsion, which simply combines two independent propeller propulsion units, comprising an internal combustion engine with a propeller and an electric motor with a propeller.
The basis of the conceptual arrangement according to the invention is^the push^piill configuration of both kinds of propeller propulsion units on the aircraft fuselage. One propeller propulsion unit is installed in the forward fuselage in the tractor configuration and the other propeller propulsion unit is located in the rear fuselage in the pusher configuration. This propulsion units arrangement has no internal mechanical coupling and allows either a combined operation of both propulsion units, when both units generate maximum propulsive effect or, coincidentally, thjs arrangement allows independent operation of one of the propulsion units only, e.g. during the cruise flight, when the energy of the second propulsion unit is saved. At the same time, another advantage of this concept presents the alignment of both propulsion units / propeller axes with the main longitudinal fuselage / aircraft axis jso. that the propulsion units axes may be located either in the proximity of the main aircraft/ fuselage axis or may be identical with the main aircraft / fuselage axis aηd this way is eliminated the yawing moment, which is otherwise important during the one engine inoperative flight of the aircraft with a conventional configuration of; engines installed on the wings.
Another advantage of the independent configuration of the propulsion ' units presents the possibility of a recuperation charging of batteries during flight using the electric motor in a generator mode, driven by the propeller. This system of charging during flight may be also combined with charging of the batteries from the generator on the internal combustion engine as well as from the ground source and tjie electricity distribution grid.
Brief Description of Drawings
The invention will be further explained by the Figure 1 , showing a side schematic view of the propeller propulsion units' installation in the aircraft fuselage. Best Mode for carrying out the Invention
The aircraft hybrid propulsion, according to the Figure 1 , consists of two propeller . propulsion units, independent of each other, in a push-pull configuration. The forward tractor propeller propulsion unit 1 may be either electric motor or internal combustion propulsion unit. The rear pusher propeller propulsion unit 2 is located on the rear of the fuselage and may be either electric or internal combustion; propulsion unit depending on what kind of propeller propulsion unit is used as the, forward unit. The propeller axes of both the propulsion units, the forward as well the rear, are arranged in parallel/ coaxial with the fuselage main longitudinal axis of symmetry.
The batteries supplying the electric motor 2 are rechargeable during flight by the, recuperation from the electric propeller with a propeller 2 and/or from the generator installed on the internal combustion propulsion engine 1

Claims

1. The aircraft hybrid propulsion consisting of two propeller propulsion units, one of which is based on the principle of an internal combustion engine (1) with a . propeller and the second one on the principle of an electric motor (2) with a propeller, characterized in that the propulsion units are installed without an interdependent mechanical coupling in the push-pull configuration in the direction of flight on the aircraft fuselage, so that one of the propulsion units (1 , 2) is installed in the forward fuselage and generates a propulsion effect using a tractor propeller and the second one of the propulsion units (1 , 2) is installed in the rear fuselage and generates a propulsion effect using a pusher propeller and the batteries supplying the energy to the electric motor are rechargeable during flight.
2. The aircraft hybrid propulsion according to the claim 1 , characterized in that the batteries supplying the energy to the electric motor (2) are rechargeable during flight by recuperation using the electric motor with a propeller (2) and/or using a generator installed on the internal combustion engine (1).
PCT/CZ2009/000102 2008-08-20 2009-08-19 Aircraft hybrid propulsion WO2010020199A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CZ20080500A CZ2008500A3 (en) 2008-08-20 2008-08-20 Airplane hybrid drive
CZPV2008-500 2008-08-20

Publications (1)

Publication Number Publication Date
WO2010020199A1 true WO2010020199A1 (en) 2010-02-25

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WO (1) WO2010020199A1 (en)

Cited By (45)

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CH703260A1 (en) * 2010-06-03 2011-12-15 Eugen Gaehwiler Glider for motorized flight and gliding, comprises rechargeable direct current voltage source, and propeller fastened at shaft, where two electromotors are provided, which are coupled with shaft
WO2013186009A1 (en) * 2012-06-12 2013-12-19 Siemens Aktiengesellschaft Hybrid aircraft
GB2489311B (en) * 2011-03-21 2014-05-14 Tecniq S Ltd A method of operating a fixed wing aircraft
WO2014163688A1 (en) * 2013-03-09 2014-10-09 Rolls-Royce Corporation Aircraft power plant
FR3004699A1 (en) * 2013-04-19 2014-10-24 Airbus Operations Sas AIRCRAFT COMPRISING A HYBRID ENGINE
US9527597B1 (en) 2013-01-11 2016-12-27 Jaime Sada Unmanned aerial vehicle with twin-engine fore/AFT configuration and associated systems and methods
US9637217B2 (en) 2015-09-21 2017-05-02 General Electric Company Aircraft having an aft engine
US9764848B1 (en) 2016-03-07 2017-09-19 General Electric Company Propulsion system for an aircraft
US20170292523A1 (en) * 2016-04-11 2017-10-12 General Electric Company Electric propulsion engine for an aircraft
JP2017200816A (en) * 2016-04-11 2017-11-09 ゼネラル・エレクトリック・カンパニイ Electric propulsion engine for aircraft
US9815560B2 (en) 2015-09-21 2017-11-14 General Electric Company AFT engine nacelle shape for an aircraft
US9821917B2 (en) 2015-09-21 2017-11-21 General Electric Company Aft engine for an aircraft
US9884687B2 (en) 2015-09-21 2018-02-06 General Electric Company Non-axis symmetric aft engine
US9957055B2 (en) 2015-09-21 2018-05-01 General Electric Company Aft engine for an aircraft
US10000293B2 (en) 2015-01-23 2018-06-19 General Electric Company Gas-electric propulsion system for an aircraft
US10017270B2 (en) 2015-10-09 2018-07-10 General Electric Company Aft engine for an aircraft
US10071811B2 (en) 2016-08-22 2018-09-11 General Electric Company Embedded electric machine
US10093428B2 (en) 2016-08-22 2018-10-09 General Electric Company Electric propulsion system
US10124890B2 (en) 2014-04-11 2018-11-13 Dronetechuav Corporation Modular nacelles to provide vertical takeoff and landing (VTOL) capabilities to fixed wing aerial vehicles, and associated systems and methods
US10137981B2 (en) 2017-03-31 2018-11-27 General Electric Company Electric propulsion system for an aircraft
US10252810B2 (en) 2016-04-19 2019-04-09 General Electric Company Propulsion engine for an aircraft
US10308366B2 (en) 2016-08-22 2019-06-04 General Electric Company Embedded electric machine
US10392120B2 (en) 2016-04-19 2019-08-27 General Electric Company Propulsion engine for an aircraft
US10487839B2 (en) 2016-08-22 2019-11-26 General Electric Company Embedded electric machine
WO2020074304A1 (en) * 2018-10-07 2020-04-16 Martin Ziegler Recuperative drive system for jet-propelled vehicles around which there is a flow
US10676205B2 (en) 2016-08-19 2020-06-09 General Electric Company Propulsion engine for an aircraft
US10762726B2 (en) 2017-06-13 2020-09-01 General Electric Company Hybrid-electric propulsion system for an aircraft
US10793281B2 (en) 2017-02-10 2020-10-06 General Electric Company Propulsion system for an aircraft
US10800539B2 (en) 2016-08-19 2020-10-13 General Electric Company Propulsion engine for an aircraft
JP2020530423A (en) * 2017-08-10 2020-10-22 ネイサー、ポール Fluid Manipulation Assembly, Fluid Manipulation, and Aircraft
US10822103B2 (en) 2017-02-10 2020-11-03 General Electric Company Propulsor assembly for an aircraft
WO2021030888A1 (en) * 2019-08-16 2021-02-25 Embraer S.A. Unmanned aircraft having reduced acoustic signatures
GB2587674A (en) * 2019-10-02 2021-04-07 Advanced Mobility Res And Development Ltd Systems and methods for aircraft
US11097849B2 (en) 2018-09-10 2021-08-24 General Electric Company Aircraft having an aft engine
US11105340B2 (en) 2016-08-19 2021-08-31 General Electric Company Thermal management system for an electric propulsion engine
US11149578B2 (en) 2017-02-10 2021-10-19 General Electric Company Propulsion system for an aircraft
US11156128B2 (en) 2018-08-22 2021-10-26 General Electric Company Embedded electric machine
US11427344B2 (en) 2019-03-01 2022-08-30 Pratt & Whitney Canada Corp. Cooling system configurations for an aircraft having hybrid-electric propulsion system
US11574548B2 (en) 2019-04-25 2023-02-07 Pratt & Whitney Canada Corp. Aircraft degraded operation ceiling increase using electric power boost
US11639228B2 (en) 2019-03-01 2023-05-02 Pratt & Whitney Canada Corp. Engine layouts and associated compartmentalization for aircraft having hybrid-electric propulsion system
US11667391B2 (en) 2019-08-26 2023-06-06 Pratt & Whitney Canada Corp. Dual engine hybrid-electric aircraft
US11738881B2 (en) 2019-10-21 2023-08-29 Hamilton Sundstrand Corporation Auxiliary power unit systems
US11738874B2 (en) 2019-03-01 2023-08-29 Hamilton Sundstrand Corporation Aircraft having hybrid-electric propulsion system with electric storage located in fuselage
US11855301B2 (en) 2019-09-30 2023-12-26 Hamilton Sundstrand Corporation Systems and methods for battery ventilation
US12149154B2 (en) 2021-07-22 2024-11-19 General Electric Company Electric machine having a hybrid insulative-conductive manifold

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Cited By (63)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH703260A1 (en) * 2010-06-03 2011-12-15 Eugen Gaehwiler Glider for motorized flight and gliding, comprises rechargeable direct current voltage source, and propeller fastened at shaft, where two electromotors are provided, which are coupled with shaft
GB2489311B (en) * 2011-03-21 2014-05-14 Tecniq S Ltd A method of operating a fixed wing aircraft
WO2013186009A1 (en) * 2012-06-12 2013-12-19 Siemens Aktiengesellschaft Hybrid aircraft
US9527597B1 (en) 2013-01-11 2016-12-27 Jaime Sada Unmanned aerial vehicle with twin-engine fore/AFT configuration and associated systems and methods
US9581025B2 (en) 2013-03-09 2017-02-28 Rolls-Royce Corporation Aircraft power plant
WO2014163688A1 (en) * 2013-03-09 2014-10-09 Rolls-Royce Corporation Aircraft power plant
FR3004699A1 (en) * 2013-04-19 2014-10-24 Airbus Operations Sas AIRCRAFT COMPRISING A HYBRID ENGINE
US10124890B2 (en) 2014-04-11 2018-11-13 Dronetechuav Corporation Modular nacelles to provide vertical takeoff and landing (VTOL) capabilities to fixed wing aerial vehicles, and associated systems and methods
US10414508B2 (en) 2015-01-23 2019-09-17 General Electric Company Gas-electric propulsion system for an aircraft
US11312502B2 (en) 2015-01-23 2022-04-26 General Electric Company Gas-electric propulsion system for an aircraft
US11673678B2 (en) 2015-01-23 2023-06-13 General Electric Company Gas-electric propulsion system for an aircraft
US10000293B2 (en) 2015-01-23 2018-06-19 General Electric Company Gas-electric propulsion system for an aircraft
US9637217B2 (en) 2015-09-21 2017-05-02 General Electric Company Aircraft having an aft engine
US9815560B2 (en) 2015-09-21 2017-11-14 General Electric Company AFT engine nacelle shape for an aircraft
US9821917B2 (en) 2015-09-21 2017-11-21 General Electric Company Aft engine for an aircraft
US9884687B2 (en) 2015-09-21 2018-02-06 General Electric Company Non-axis symmetric aft engine
US9957055B2 (en) 2015-09-21 2018-05-01 General Electric Company Aft engine for an aircraft
US10017270B2 (en) 2015-10-09 2018-07-10 General Electric Company Aft engine for an aircraft
US9764848B1 (en) 2016-03-07 2017-09-19 General Electric Company Propulsion system for an aircraft
US20190322377A1 (en) * 2016-04-11 2019-10-24 General Electric Company Electric Propulsion Engine for an Aircraft
CN107444620A (en) * 2016-04-11 2017-12-08 通用电气公司 Engine is electric-only propulsion for aircraft
JP2017200816A (en) * 2016-04-11 2017-11-09 ゼネラル・エレクトリック・カンパニイ Electric propulsion engine for aircraft
JP2017190126A (en) * 2016-04-11 2017-10-19 ゼネラル・エレクトリック・カンパニイ Electric propulsion engine for aircraft
US10392119B2 (en) 2016-04-11 2019-08-27 General Electric Company Electric propulsion engine for an aircraft
US20170292523A1 (en) * 2016-04-11 2017-10-12 General Electric Company Electric propulsion engine for an aircraft
US11097850B2 (en) 2016-04-11 2021-08-24 General Electric Company Electric propulsion engine for an aircraft
US10252810B2 (en) 2016-04-19 2019-04-09 General Electric Company Propulsion engine for an aircraft
US10392120B2 (en) 2016-04-19 2019-08-27 General Electric Company Propulsion engine for an aircraft
US11105340B2 (en) 2016-08-19 2021-08-31 General Electric Company Thermal management system for an electric propulsion engine
US11685542B2 (en) 2016-08-19 2023-06-27 General Electric Company Propulsion engine for an aircraft
US10800539B2 (en) 2016-08-19 2020-10-13 General Electric Company Propulsion engine for an aircraft
US10676205B2 (en) 2016-08-19 2020-06-09 General Electric Company Propulsion engine for an aircraft
US10487839B2 (en) 2016-08-22 2019-11-26 General Electric Company Embedded electric machine
US10308366B2 (en) 2016-08-22 2019-06-04 General Electric Company Embedded electric machine
US11724814B2 (en) 2016-08-22 2023-08-15 General Electric Company Embedded electric machine
US10071811B2 (en) 2016-08-22 2018-09-11 General Electric Company Embedded electric machine
US10093428B2 (en) 2016-08-22 2018-10-09 General Electric Company Electric propulsion system
US11247779B2 (en) 2016-08-22 2022-02-15 General Electric Company Embedded electric machine
US10822103B2 (en) 2017-02-10 2020-11-03 General Electric Company Propulsor assembly for an aircraft
US10793281B2 (en) 2017-02-10 2020-10-06 General Electric Company Propulsion system for an aircraft
US11149578B2 (en) 2017-02-10 2021-10-19 General Electric Company Propulsion system for an aircraft
US10137981B2 (en) 2017-03-31 2018-11-27 General Electric Company Electric propulsion system for an aircraft
US10762726B2 (en) 2017-06-13 2020-09-01 General Electric Company Hybrid-electric propulsion system for an aircraft
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JP2020530423A (en) * 2017-08-10 2020-10-22 ネイサー、ポール Fluid Manipulation Assembly, Fluid Manipulation, and Aircraft
US11156128B2 (en) 2018-08-22 2021-10-26 General Electric Company Embedded electric machine
US11097849B2 (en) 2018-09-10 2021-08-24 General Electric Company Aircraft having an aft engine
WO2020074304A1 (en) * 2018-10-07 2020-04-16 Martin Ziegler Recuperative drive system for jet-propelled vehicles around which there is a flow
US11639228B2 (en) 2019-03-01 2023-05-02 Pratt & Whitney Canada Corp. Engine layouts and associated compartmentalization for aircraft having hybrid-electric propulsion system
US11738874B2 (en) 2019-03-01 2023-08-29 Hamilton Sundstrand Corporation Aircraft having hybrid-electric propulsion system with electric storage located in fuselage
US11427344B2 (en) 2019-03-01 2022-08-30 Pratt & Whitney Canada Corp. Cooling system configurations for an aircraft having hybrid-electric propulsion system
US11574548B2 (en) 2019-04-25 2023-02-07 Pratt & Whitney Canada Corp. Aircraft degraded operation ceiling increase using electric power boost
WO2021030888A1 (en) * 2019-08-16 2021-02-25 Embraer S.A. Unmanned aircraft having reduced acoustic signatures
CN114555467A (en) * 2019-08-16 2022-05-27 埃姆普里萨有限公司 Unmanned aerial vehicle with reduced acoustic signature
CN114555467B (en) * 2019-08-16 2024-05-03 埃姆普里萨有限公司 Unmanned aerial vehicle with reduced acoustic signature
EP4013681A4 (en) * 2019-08-16 2023-08-30 Embraer, S.A. Unmanned aircraft having reduced acoustic signatures
US11667391B2 (en) 2019-08-26 2023-06-06 Pratt & Whitney Canada Corp. Dual engine hybrid-electric aircraft
US11855301B2 (en) 2019-09-30 2023-12-26 Hamilton Sundstrand Corporation Systems and methods for battery ventilation
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