JP2022549856A - 車両機室熱管理システムおよび方法 - Google Patents
車両機室熱管理システムおよび方法 Download PDFInfo
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
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- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/61—Types of temperature control
- H01M10/613—Cooling or keeping cold
-
- 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
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
-
- 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
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
-
- 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
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/62—Heating or cooling; Temperature control specially adapted for specific applications
- H01M10/625—Vehicles
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/65—Means for temperature control structurally associated with the cells
- H01M10/656—Means for temperature control structurally associated with the cells characterised by the type of heat-exchange fluid
- H01M10/6567—Liquids
- H01M10/6568—Liquids characterised by flow circuits, e.g. loops, located externally to the cells or cell casings
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
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- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0674—Environmental Control Systems comprising liquid subsystems
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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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
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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
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- 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
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
Description
本願は、参照することによってその全体として本明細書に組み込まれる、2019年9月25日に出願された、米国仮出願第62/905,810号の利益を主張する。
1.概要
2.利益
3.システム
4.方法
Claims (23)
- システムであって、
電気航空機であって、
内部を画定する機室と、
前記内部内の機室空気と
を備える、電気航空機と、
前記電気航空機に車載の複数のバッテリセルと、
冷蔵システム内の冷媒と、
第1の流体ループであって、
前記第1の流体ループ内の作業流体と、
前記電気航空機に車載の第1の熱交換器、前記機室空気に流動的に接続される第1の熱交換器と、
前記作業流体を前記冷媒に熱的に結合し、熱エネルギーを前記冷媒から前記作業流体に伝達するように構成される凝縮器であって、前記凝縮器は、前記第1の熱交換器に選択的に流動的に結合される、凝縮器と、
前記複数のバッテリセルに熱的に結合される第2の熱交換器と、
前記作業流体を前記冷媒に熱的に結合し、熱エネルギーを前記作業流体から前記冷媒に伝達するように構成される蒸発器であって、前記蒸発器は、前記第2の熱交換器に選択的に流動的に結合される、蒸発器と、
前記第1の流体ループ内の作業流体を循環させるように構成される第1のポンプと
を備える、第1の流体ループと
を備える、システム。 - 冷却モードでは、前記第2の熱交換器を前記第1の熱交換器から流動的に結合解除する弁のセットをさらに備える、請求項1に記載のシステム。
- 前記第1および第2の熱交換器はそれぞれ、入口ポートと、出口ポートとを備え、前記入口ポートおよび出口ポートは、前記第1の流体ループ内の作業流体に流動的に結合され、前記弁のセットは、
機室加熱モードであって、前記弁のセットが、前記第2の熱交換器の出口を前記第1の熱交換器の入口に接続し、前記第1の熱交換器の出口を第2の熱交換器の入口に接続する機室加熱モードと、
機室冷却モードであって、前記弁のセットが、前記第2の熱交換器の出口を前記第2の熱交換器の入口に接続し、前記第1の熱交換器の出口を前記第2の熱交換器の入口に接続する機室冷却モードと
の間で動作可能である、請求項2に記載のシステム。 - 第2のポンプをさらに備え、前記冷却モードでは、前記作業流体の第1の部分は、前記第1の熱交換器を備える第1のサブループ内に配列され、前記作業流体の第2の部分は、前記第2の熱交換器を備える第2のサブループ内に配列され、前記第1および第2のポンプは、それぞれ、前記第1および第2のサブループ内に配列される、請求項3に記載のシステム。
- 前記弁のセットは、
前記第1の熱交換器の入口と関連付けられる第1の端部と、
前記第1の熱交換器の出口と関連付けられる第2の端部と、
前記第2の熱交換器の入口と関連付けられる第3の端部と、
前記第2の熱交換器の出口と関連付けられる第4の端部と
を画定する4方向切替弁を備える、請求項3に記載のシステム。 - 前記冷蔵システムは、外部気流から隔離される、請求項1に記載のシステム。
- 流体継手をさらに備え、前記流体継手は、前記第1の流体ループを、前記作業流体を備える地上ベースのインフラストラクチャに選択的に接続するように構成される、請求項1に記載のシステム。
- 充電機構は、前記流体継手を前記地上ベースのインフラストラクチャに流動的に接続し、前記複数のバッテリセルを前記地上ベースのインフラストラクチャに電気的に接続するように構成される、請求項7に記載のシステム。
- 航空機外部から前記機室内部への吸気経路を画定する第1のオリフィスと、
前記機室内部から前記航空機外部への排気経路を画定するノズルと、
前記排気経路に沿って配列される空気コンプレッサであって、前記空気コンプレッサは、前記ノズルにおける圧力を増加させるように構成される、空気コンプレッサと
をさらに備える、請求項1に記載のシステム。 - 前記排気経路は、航空電子工学機器にわたって通過する、請求項9に記載のシステム。
- 第2の流体ループ内の第2の作業流体と、
前記複数のバッテリセルに熱的に接続される熱交換器であって、前記第2の流体ループは、前記熱交換器の内部を通して延在する、熱交換器と、
前記第2の流体ループを前記第1の流体ループに熱的に接続する第2の熱交換器と、
前記第2の作業流体を前記第2の流体ループを通して循環させるように構成される第2のポンプと
をさらに備える、請求項1に記載のシステム。 - 方法であって、
前記電気航空機を飛行させることであって、前記電気航空機は、機室、前記機室内の機室空気、およびバッテリパックを備える、ことと、
前記電気航空機を飛行させる間、前記機室を冷却することであって、
第1の熱交換器において、熱エネルギーの第1の部分を機室空気から第1の作業流体に伝達することと、
第2の熱交換器において、前記熱エネルギーの第1の部分を前記第1の作業流体から第2の作業流体に伝達することであって、前記第2の作業流体は、前記バッテリパックと熱連通する、ことと、
前記熱エネルギーの第1の部分を前記バッテリパックの熱質量内に貯蔵することと
を含む、ことと
を含む、方法。 - 前記電気航空機が着地されている間、前記第2の作業流体の第1の部分と地上インフラストラクチャからの前記第2の作業流体の第2の部分を置換することを含む、前記航空機を事前に調整することをさらに含む、請求項12に記載の方法。
- 前記第1の作業流体は、第1の流体ループ内にあり、前記機室を冷却することはさらに、
機室温度閾値の充足を決定することに応答して、前記第1の流体ループを第1のサブループおよび第2のサブループに分割することであって、前記第1の作業流体の第1の部分は、前記第1のサブループ内に含有され、前記作業流体の第2の部分は、前記第2のサブループ内に含有され、前記第1のサブループは、前記第1の熱交換器を備え、前記第2のサブループは、前記第2の熱交換器を備える、ことと、
ヒートポンプを使用して、熱エネルギーを前記第1のサブループから前記第2のサブループに伝達することと
を含む、請求項12に記載の方法。 - 前記バッテリパックと、前記第1の作業流体と、前記第2の作業流体と、前記機室空気とを備える熱システムの総熱エネルギーは、飛行の間、持続的に増加する、請求項14に記載の方法。
- 飛行の間、外部空気の前記機室の中への流動を調整することをさらに含み、
タービンを使用して、前記バッテリパックを回生充電し、同時に、前記流動の熱エネルギーを低減させること
を含む、請求項12に記載の方法。 - 前記電気航空機を飛行させる間、前記機室空気の圧力と周囲圧力を均衡させることをさらに含む、請求項16に記載の方法。
- 飛行の間、機室空気の一部を排気ノズルを通して通気することをさらに含み、
ファンを使用して、前記排気オリフィスにおける機室空気圧力または前記排気オリフィスにおける機室空気速度のうちの1つを増加させること
を含む、請求項12に記載の方法。 - 機室空気の一部を通気することに先立って、前記機室空気の一部を航空電子工学機器を横断して送風することをさらに含む、請求項18に記載の方法。
- 前記バッテリパックは、第1のセルと、第2のセルとを備え、前記機室を冷却することはさらに、第3の熱交換器を使用して、前記第1のセルと第2のセルとの間の熱エネルギーを対流平衡させることを含む、請求項12に記載の方法。
- システムであって、
航空機の機室内部に流動的に接続される機室熱交換器と、
前記航空機のバッテリセルに熱的に接続されるバッテリ熱交換器と、
凝縮器であって、
作業流体によって、前記バッテリ熱交換器に流動的に接続される凝縮器入口と、
凝縮器出口と
を備える、凝縮器と、
蒸発器であって、
前記作業流体によって、前記機室熱交換器に流動的に接続される蒸発器入口と、
蒸発器出口と
を備える、蒸発器と、
弁であって、
加熱モードであって、前記弁が、前記凝縮器出口を前記機室熱交換器に流動的に接続し、前記蒸発器出口を前記バッテリ熱交換器に流動的に接続する加熱モードと、
冷却モードであって、前記弁が、前記凝縮器出口を前記バッテリ熱交換器に流動的に接続し、前記蒸発器出口を前記機室熱交換器に流動的に接続する冷却モードと
の間で選択的に動作可能である、弁と
を備える、システム。 - 前記バッテリセルのための別個の車載能動的冷却システムを欠いている、請求項21に記載のシステム。
- 請求項12-20のいずれかに記載の方法を実施するように構成される、システム。
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