JP2021525673A - 電力システムアーキテクチャとこれを用いたフォールトトレラントvtol航空機 - Google Patents
電力システムアーキテクチャとこれを用いたフォールトトレラントvtol航空機 Download PDFInfo
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- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
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- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
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- 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
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- 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
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
- B64D31/02—Initiating means
- B64D31/06—Initiating means actuated automatically
- B64D31/09—Initiating means actuated automatically in response to power plant failure
- B64D31/10—Initiating means actuated automatically in response to power plant failure for preventing asymmetric thrust
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L2200/00—Type of vehicles
- B60L2200/10—Air crafts
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- 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
- B64D2221/00—Electric power distribution systems onboard aircraft
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- 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
- Y02T50/50—On board measures aiming to increase energy efficiency
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- 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
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Abstract
Description
[0002]本出願は、2018年5月31日にBevirtらに出願された米国仮特許出願番号62/678,275の優先権を主張するものであり、参照によりその全体が本明細書に組み込まれる。
[0029]航空機での使用に適合した電気モータ用のための信頼性を高めた電力システムアーキテクチャを備えた電力システムである。個々のバッテリは、例えば6つ以上のモータを有するシステムで2つ以上のモータのサブセットに電力を供給するために利用することができる。各モータは、2つ以上のバッテリサブセットから電力を供給できるため、モータの故障に対応可能である。各モータには2セット以上の巻線があり、各巻線は異なるバッテリで駆動される。前進飛行または垂直離着陸モードにおいて巻線の故障、バッテリの故障、またはモータの故障が生じると、電力経路が自動的に変更されて、適切な姿勢制御を継続し、十分な推力を提供し得る。モータの故障時に、故障したモータからオフセットされた第2のモータの電源を切り、姿勢制御を容易にすることができる。
[0031]いくつかの態様において、航空機は、離陸時に推力を提供するために、電気モータによって動力供給されるブレードプロペラを利用することがある。このプロペラ/モータユニットは、推進アセンブリと呼ばれることがある。いくつかの態様において、航空機の翼は、プロペラが離着陸のための垂直推力を提供するように、前縁を上向きにして回転することがある。いくつかの態様において、翼のモータ駆動プロペラユニットは、それ自体が固定翼に対して回動し、それによってプロペラは、離着陸のための垂直推力を提供することができる。モータ駆動プロペラユニットの回動により、プロペラと電気モータの両方を回転させることによって推力の方向転換が可能となり、したがって、回転ジョイントの周りまたは回転ジョイントを介したトルク駆動のジンバルまたは他の方法を必要としない。
Claims (16)
- 電動式の垂直離着陸航空機において、
複数の推進アセンブリであって、それぞれが1つの電気モータを具える推進アセンブリと、
複数のバッテリであって、それぞれが2つ以上の前記電気モータに連結されている複数のバッテリとを具え、
前記電気モータはそれぞれ複数のモータ巻線回路を具え、1つのモータの前記巻線回路のそれぞれが異なるバッテリに連結されていることを特徴とする航空機。 - 複数のインバータをさらに具え、前記バッテリのそれぞれが、1つのインバータを介して前記電気モータのそれぞれに連結されている、請求項1に記載の航空機。
- モータ故障時に所望の航空機の姿勢を維持するために、前記バッテリによって前記電気モータに供給される電力を自律的に調整するように適合されたフライト制御システムをさらに具える、請求項1に記載の航空機。
- モータ故障時に所望の航空機の姿勢を維持するために、前記バッテリによって前記電気モータに供給される電力を自律的に調整するように適合されたフライト制御システムをさらに具える、請求項2に記載の航空機。
- バッテリ故障時に所望の航空機の姿勢を維持するために、前記バッテリによって前記電気モータに供給される電力を自律的に調整するように適合されたフライト制御システムをさらに具える、請求項1に記載の航空機。
- バッテリ故障時に所望の航空機の姿勢を維持するために、前記バッテリによって前記電気モータに供給される電力を自律的に調整するように適合されたフライト制御システムをさらに具える、請求項2に記載の航空機。
- 前記電気モータのそれぞれが複数のモータ巻線回路を具え、1つのモータの前記複数のモータ巻線回路のうちの前記巻線回路のそれぞれが異なるバッテリに連結されている、請求項1に記載の航空機。
- 前記電気モータのそれぞれが複数のモータ巻線回路を具え、1つのモータの前記複数のモータ巻線回路のうちの前記巻線回路のそれぞれが異なるバッテリに連結されている、請求項2に記載の航空機。
- 前記電気モータのそれぞれが複数のモータ巻線回路を具え、1つのモータの前記複数のモータ巻線回路のうちの前記巻線回路のそれぞれが異なるバッテリに連結されている、請求項4に記載の航空機。
- 前記電気モータのそれぞれが複数のモータ巻線回路を具え、1つのモータの前記複数のモータ巻線回路のうちの前記巻線回路のそれぞれが異なるバッテリに連結されている、請求項6に記載の航空機。
- 前記複数のバッテリのそれぞれが、前記航空機の縦軸の左側にある1つまたは複数のモータに連結され、前記複数のバッテリのそれぞれが、前記航空機の縦軸の右側にある1つまたは複数のモータに連結されている、請求項1に記載の航空機。
- 前記複数のバッテリのそれぞれが、前記航空機の縦軸の左側にある1つまたは複数のモータに連結され、前記複数のバッテリのそれぞれが、前記航空機の縦軸の右側にある1つまたは複数のモータに連結されている、請求項2に記載の航空機。
- 前記複数のバッテリのそれぞれが、前記航空機の縦軸の左側にある1つまたは複数のモータに連結され、前記複数のバッテリのそれぞれが、前記航空機の縦軸の右側にある1つまたは複数のモータに連結されている、請求項7に記載の航空機。。
- 前記複数のバッテリのそれぞれが、前記航空機の縦軸の左側にある1つまたは複数のモータに連結され、前記複数のバッテリのそれぞれが、前記航空機の縦軸の右側にある1つまたは複数のモータに連結されている、請求項8に記載の航空機。。
- 垂直離着陸航空機の動力および推進システムにおける第1のモータのモータ故障に対応するための方法であって、前記航空機が、
それぞれが1つの電機モータを具える複数の推進アセンブリと、
それぞれが2つ以上の前記電気モータに連結されている複数のバッテリとを具え、
前記電気モータのそれぞれは複数のモータ巻線回路を具え、1つのモータの前記巻線回路のそれぞれは異なるバッテリに結合されており、
前記方法が、
第2のモータの電源を切るステップであって、前記第2のモータは、前記第1のモータに対して前記航空機の縦方向の中心線の反対側にある、ステップと、
必要な推力を維持するために、残りのモータの一部または前部に供給される電力を増大するステップと、を含むことを特徴とする方法。 - 前記複数のバッテリのそれぞれが、前記航空機の縦軸の左側にある1つまたは複数のモータに連結され、前記複数のバッテリのそれぞれが、前記航空機の縦軸の右側にある1つまたは複数のモータに連結されている、請求項15に記載の方法。
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EP3802322A1 (en) | 2021-04-14 |
JP2023134581A (ja) | 2023-09-27 |
US11827347B2 (en) | 2023-11-28 |
KR20240007689A (ko) | 2024-01-16 |
CN112368208A (zh) | 2021-02-12 |
KR20210006972A (ko) | 2021-01-19 |
EP3802322A4 (en) | 2022-02-23 |
US20200010187A1 (en) | 2020-01-09 |
US20240025543A1 (en) | 2024-01-25 |
WO2019232472A1 (en) | 2019-12-05 |
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