CN110877738A - 混合电力推进系统以及操作方法 - Google Patents

混合电力推进系统以及操作方法 Download PDF

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Publication number
CN110877738A
CN110877738A CN201910842879.7A CN201910842879A CN110877738A CN 110877738 A CN110877738 A CN 110877738A CN 201910842879 A CN201910842879 A CN 201910842879A CN 110877738 A CN110877738 A CN 110877738A
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CN
China
Prior art keywords
motor
generator
electric
aircraft
stator
Prior art date
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Pending
Application number
CN201910842879.7A
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English (en)
Inventor
E.拉图利佩
R.弗里尔
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Pratt and Whitney Canada Corp
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Pratt and Whitney Canada Corp
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Publication date
Priority claimed from US16/411,267 external-priority patent/US11233470B2/en
Priority claimed from US16/411,484 external-priority patent/US11283376B2/en
Application filed by Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Publication of CN110877738A publication Critical patent/CN110877738A/zh
Pending legal-status Critical Current

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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
    • H02P6/00—Arrangements for controlling synchronous motors or other dynamo-electric motors using electronic commutation dependent on the rotor position; Electronic commutators therefor
    • H02P6/12—Monitoring commutation; Providing indication of commutation failure
    • 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
    • B60L50/00—Electric propulsion with power supplied within the vehicle
    • B60L50/10—Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines
    • B60L50/13—Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines using AC generators and AC motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • 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
    • B60L50/00—Electric propulsion with power supplied within the vehicle
    • B60L50/50—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells
    • B60L50/51—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells characterised by AC-motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • 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
    • B60L50/00—Electric propulsion with power supplied within the vehicle
    • B60L50/50—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells
    • B60L50/60—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
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    • B60L53/00—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles
    • B60L53/20—Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange of energy storage elements in electric vehicles characterised by converters located in the vehicle
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    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B64D27/402—Arrangements for mounting power plants in aircraft comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B64D31/02—Initiating means
    • B64D31/06—Initiating means actuated automatically
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
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    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
    • B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
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    • B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
    • B64D35/08—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10—Adaptations for driving, or combinations with, electric generators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
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    • H—ELECTRICITY
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    • H02P29/025—Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load the fault being a power interruption
    • H—ELECTRICITY
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    • H02P29/028—Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load the motor continuing operation despite the fault condition, e.g. eliminating, compensating for or remedying the fault
    • H—ELECTRICITY
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    • H02P5/46—Arrangements specially adapted for regulating or controlling the speed or torque of two or more electric motors for speed regulation of two or more dynamo-electric motors in relation to one another
    • H02P5/50—Arrangements specially adapted for regulating or controlling the speed or torque of two or more electric motors for speed regulation of two or more dynamo-electric motors in relation to one another by comparing electrical values representing the speeds
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    • H02P2101/00—Special adaptation of control arrangements for generators
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    • H02P27/00—Arrangements or methods for the control of AC motors characterised by the kind of supply voltage
    • H02P27/04—Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage
    • H02P27/06—Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using dc to ac converters or inverters
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
    • H02P3/00—Arrangements for stopping or slowing electric motors, generators, or dynamo-electric converters
    • H02P3/06—Arrangements for stopping or slowing electric motors, generators, or dynamo-electric converters for stopping or slowing an individual dynamo-electric motor or dynamo-electric converter
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Abstract

用于操作安装到飞行器的混合电力飞行器推进系统的方法和系统。所述方法包括：由第一电动机驱动第一旋转推进器，所述第一电动机可操作地连接到发电机；由第二电动机驱动第二旋转推进器，所述第二电动机可操作地连接到所述发电机；以及由热力发动机驱动第三旋转推进器，所述热力发动机可操作地连接到所述发电机并配置成驱动所述发电机。

Description

混合电力推进系统以及操作方法
技术领域
本公开大体涉及使用来自内燃发动机和电动机两者的功率的飞行器推进系统。
背景技术
混合电力飞行器推进系统组合内燃和电力推进技术。在电力推进系统中，电能通过电动机转换为旋转能以驱动推进风扇或螺旋桨。
使飞行器推进系统的功率的至少一部分来自电动机具有环境和成本益处。因此，需要改进现有架构。
发明内容
根据广泛的方面，提供了一种用于操作安装到飞行器的混合电力飞行器推进系统的方法。该方法包括：由第一电动机驱动第一旋转推进器，所述第一电动机可操作地连接到发电机；由第二电动机驱动第二旋转推进器，所述第二电动机可操作地连接到发电机；以及由热力发动机驱动第三旋转推进器，所述热力发动机可操作地连接到发电机并且配置成驱动所述发电机。
根据另一广泛的方面，提供了一种具有推进系统的混合电力飞行器，所述推进系统包括：第一旋转推进器；第一电动机，其联接到所述第一旋转推进器并配置成用于向第一旋转推进器施加旋转力；第二旋转推进器；第二电动机，其联接到所述第二旋转推进器并且配置成用于向所述第二旋转推进器施加旋转力；发电机，其联接到所述第一电动机和所述第二电动机并且配置成用于向所述第一电动机和所述第二电动机施加交流（AC）电功率；第三旋转推进器；以及热力发动机，其联接到所述发电机和所述第三旋转推进器并且被配置成用于驱动所述发电机和所述第三旋转推进器。
根据本文中所描述的实施例，可以以各种组合使用本文中所描述的系统、装置和方法的特征。
附图说明
现在参考附图，在附图中：
图1是根据说明性实施例的燃气涡轮发动机的示意性横截面视图；
图2是根据说明性实施例的混合电力飞行器推进系统的框图；
图3是根据说明性实施例的具有两个电动机的混合电力飞行器推进系统的框图；
图4是根据说明性实施例的具有双定子发电机的混合电力飞行器推进系统的框图的框图；
图5是根据说明性实施例的具有双定子电动机的混合电力飞行器推进系统的框图；
图6是根据说明性实施例的具有选择性连接的混合电力飞行器推进系统的框图；
图7是根据说明性实施例的具有额外推进功率的混合电力飞行器推进系统的框图；
图8是根据说明性实施例的电机逆变器的示例；
图9是根据说明性实施例的示例性控制器的框图。
应注意，在所有附图中，相似特征用相似附图标记标识。
具体实施方式
本文中描述了一种混合电力飞行器推进系统和方法。所述飞行器推进系统使用由热力发动机生成的功率以及由发电机生成的功率。图1示出了优选地被提供用于亚音速飞行中的类型的示例性热力发动机，即燃气涡轮发动机10。燃气涡轮发动机10通常以串联流动连通方式包括：风扇12，通过所述风扇推进环境空气；压缩机区段14，其用于对空气加压；燃烧器16，压缩空气在所述燃烧器中与燃料混合并且被点燃，以用于生成热燃烧气体的环形流；以及涡轮机区段18，其用于从燃烧气体提取能量。涡轮机区段18的高压转子20通过高压轴24驱动地接合到压缩机区段14的高压转子22。涡轮机区段18的低压转子26通过在高压轴24内延伸并且独立于高压轴旋转的低压轴28驱动地接合到风扇转子12并且驱动地接合到压缩机区段14的其他低压转子（未示出）。
虽然示出为涡轮风扇发动机，但是燃气涡轮发动机10可以替代地为另一类型的发动机，例如涡轮轴发动机，还通常以串联流动连通方式包括压缩机区段、燃烧器和涡轮机区段。还可以应用涡轮螺旋桨发动机。在一些实施例中，所述热力发动机可以是除燃烧发动机以外的类型，诸如活塞发动机或旋转发动机。另外，虽然本文中针对飞行应用描述发动机10，但是应理解，还可以应用其他用途，诸如工业等等。应注意，还可以使用除活塞或旋转发动机以外的恒定容积式燃烧热机。
现在参考图2，示出了混合电力飞行器推进系统200的示例性实施例。系统200呈现AC-AC架构，由此交流（AC）电功率生成并且被直接施加到电动机。在AC-DC-AC架构中，AC电功率被转换为直流电（DC），并且然后被重新转换为AC电功率以驱动电动机。AC-AC架构比AC-DC-AC架构更有效，因为在从AC到DC和从DC到AC的转换阶段期间发生损耗。
热力发动机201可操作地联接到发电机202。发电机202从热力发动机201接收原动力（motive power）（或机械能）并且将所述原动力转换成电功率。发电机202输出交流（AC）电功率。然后将所述AC电功率直接提供给电动机204。电动机204将所述AC电功率转换成呈旋转力形式的机械能。所述旋转力被施加到旋转结构206（即，旋转推进器），诸如飞行器的螺旋桨或推进风扇。
电动机204还从电机逆变器208接收AC电功率。电机逆变器208可操作地联接到蓄电池210（或飞行器电气系统）。蓄电池210可以是为混合电力飞行器推进系统200提供的专用蓄电池。替代地，供应到逆变器208的电功率可以来自：辅助功率单元、补充功率单元、备用发电机系统或者并不包括蓄电池或电容器的飞行器电气系统。因此，电机逆变器208可以经由飞行器上的蓄电池总线或者经由专用布线和/或连接器连接到蓄电池210。包含将化学能直接转换成电能的一个或多个电池（cell）的任何类型的装置可以用作蓄电池（battery）210。在一些实施例中，蓄电池210基于非化学原理，诸如使用处于能量存储模式下的超级电容器的电力。
电机逆变器208从蓄电池210（或另一直流源）接收直流（DC）电功率并且将DC电压转换为AC电压，调节AC电压的频率和相位以使得电机204能够生成机械功率。当电动机204由外部机器力驱动时，电机逆变器208还可以以相反意义用于对蓄电池210充电，从而使其充当发电机，在此情况下，逆变器可以将AC电压转换回DC电压。在一些实施例中，电机逆变器208还可以以反向模式使用，由此将AC电功率转换为DC电功率。
因此，电动机204具有第一输入，其可操作地联接到发电机202以接收第一AC电功率源。电动机204还具有第二输入，其可操作地联接到电机逆变器208以接收第二AC电功率源。应注意，电动机204无需具有两个独立输入（即，一个来自发电机202，并且一个来自逆变器208）。发电机202的输出以及逆变器208的输出可以在电机输入接口之前并行组合或连接。响应于接收第一AC电功率源以及第二AC电功率源中的任一者（或者同时接收两者），电动机204将生成用于驱动旋转结构206的旋转输出。
控制器212被配置成用于通过使用来自发电机202的第一AC电功率源、来自电机逆变器208的第二AC电功率源或其组合来选择性地驱动电动机204。当从发电机202和电机逆变器208两者同时接收AC电功率时，电动机204可获得更大量的功率。这又允许将更大的旋转力施加到旋转结构206。
在一些实施例中，由发电机202提供的第一AC电功率源是电动机204的主要推进功率源。例如，在低功率操作条件下，诸如在巡航模式下，旋转结构206的所有推进功率可以由发电机202提供。在高功率操作条件下，诸如在爬升模式或起飞模式下，可以由蓄电池210通过电机逆变器208来提供推进功率的增强。因此，电动机204可通过电机逆变器208获得二次或额外电功率源以便补充由发电机202提供的电功率。
在一些实施例中，电机逆变器208被定尺寸成匹配电动机204的二次功率需求，即，电机逆变器208无需是全尺寸电机逆变器，以便独自驱动电动机204。另外，不需要发电机转换器来将电压从AC转换为DC，因为由发电机202生成的电功率被无转换地馈送到电动机204。因此，此架构避免在低功率操作条件期间需要两个转换阶段。在一些实施例中，蓄电池210直接从电机逆变器208再充电。
在一些实施例中，使用电机逆变器208来从发电机202和电动机204的去同步化恢复或者防止发电机202和电动机204的去同步化。当用于去同步化的恢复时，电机逆变器208可以响应于从控制器212接收的命令或控制信号或者响应于在逆变器208中实现的逻辑来使电动机204的频率以及发电机202的频率再同步化，逆变器208监测并试图控制发电机202和电机204的频率和相位。在再同步化期间，控制器212可以暂时将发电机202与电动机204断开，例如通过打开发电机和电动机之间的继电器来实现。然后，电机逆变器208可以调节电动机204的功率，使得电动机204的速度被修改成使得电动机204的频率与发电机202的频率相匹配。然后可以使电动机204和发电机202回到彼此同相。一旦电动机204回到与发电机202同相，便还原发电机202和电动机204之间的连接。
当用于防止去同步化时，电机逆变器208可以主动监测电动机204的相位。在检测到发电机202和电动机204之间的相位不匹配时，例如在其中通过外力使电机减速的情况下，电机逆变器208可以发送与电动机204同相的电信号，以提供额外功率来使电动机204回到与发电机202同相。此特征可以由控制器212执行，或者其可以并入逆变器208中。
在一些实施例中，使用电机逆变器208来对蓄电池210再充电或者向连接到逆变器208的飞行器电气系统提供额外电功率。例如，电机逆变器208可以增加发电机202上的功率需求，使得由所述发电机产生的功率超过旋转结构206或载荷所需的功率，并且将多余功率馈送回到蓄电池210或飞行器电气系统。替代地，电机逆变器208可以通过将来自蓄电池210的能量馈送到电动机204来增加去往电动机204的功率。这又增加了旋转结构206可获得的功率。如果需要，电机逆变器208可以增加至旋转结构206的可获得的转矩（例如：对于可变桨距螺旋桨，可能需要额外转矩，这取决于螺旋桨的选定桨距），或者其可以充当发电机以通过将AC电压转换为高于DC总线电压的DC电压来从风转螺旋桨提取能量以便对蓄电池再充电或将电功率馈送回到飞行器电气系统。逆变器208具有控制DC总线上的电压的能力，从而控制去往DC总线的功率。
参考图3，示出了混合电力飞行器推进系统200的另一示例性实施例。在此示例中，两个电动机204a、204b由发电机202驱动。每一电动机204a、204b分别与其自己的旋转结构206a、206b相关联。还提供了两个电机逆变器208a、208b，一个电机逆变器分别用于馈送电动机204a、204b中的每一者。应理解，还可以使用单个电机逆变器308、而非两个单独的电机逆变器208a、208b。然后，将针对两个电动机204a、204b、而非电动机204a、204b中的仅一者的功率需求来使电机逆变器308定尺寸。另外，电机逆变器308将需要与电动机204a断开以便执行电动机204b的再同步化，并且与电动机204b断开以便执行电动机204a的再同步化。
在一些实施例中，在两个电机逆变器208a、208b中的一者发生故障的情况下，两个电机逆变器208a、208b互连。例如，如果一个电机逆变器208a发生故障，则另一个电机逆变器208b可以用于对蓄电池210充电或驱动与发生故障的电机逆变器208a相关联的电动机204a。这还可以通过使用电动机204a、204b和电机逆变器208a、208b之间的一系列连接来实现以允许电动机204a、204b到电机逆变器208a、208b的选择性连接和断开。
在一些实施例中，一个或多个继电器314a、314b分别提供在发电机202与电动机204a、204b中的每一者之间的互连路径中。继电器314a、314b是允许发电机202到电动机204a、204b中的任一者的选择性连接和断开的示例性实施例。还可以使用其他连接/断开方式。
电动机204a、204b可以提供在飞行器的单独机翼上。替代地，其可以提供在飞行器的相同机翼上。并且替代地，电动机204a、204b中的一者或两者可以提供在旋转推进装置（诸如螺旋桨、风扇、升力旋翼或助推器）的短舱或轮毂中，或反向旋转螺旋桨、风扇转子或助推器的轮毂中。
可以提供三个或更多个电动机，其中每一电动机204与电机逆变器208相关联。替代地，可以组合两个或更多个电机逆变器208以形成用于所有电动机204或其子设备（subset）的更大电机逆变器308。
图4示出了混合电力飞行器推进系统200的又另一实施例。在此示例中，发电机202是双定子发电机，其具有驱动一个电动机204a的第一发电机定子402a以及驱动另一个电动机204b的第二发电机定子402b。要注意此实施例还可以应用于三组或更多组发电机定子、电机和逆变器。可以组合逆变器208中的两者或更多者以形成用于所有电动机204或其子设备的更大电机逆变器308。在一些实施例中，电机逆变器208a、208b包括转换器，该转换器用于执行从AC到DC的转换以对蓄电池210再充电。彼此独立地驱动电动机204a、204b。在此实施例中，可以存在或可以不存在继电器314a、314b，以便允许发电机202和电动机204a、204b的选择性连接/断开。
图5示出了混合电力飞行器推进系统200的另一示例性实施例。在此示例中，电动机204a、204b中的一者或多者具有双定子。所示出的示例示出了具有第一电机定子502a和第二电机定子504a的电动机204a，以及具有第一电机定子502b和第二电机定子504b的电动机204b。电机定子502a可操作地联接到发电机定子402a，并且电机定子502b可操作地联接到发电机定子402b。电机定子504a可操作地联接到电机逆变器208a，并且电机定子504b可操作地联接到电机逆变器208b。在此配置中，发电机202并不与电机逆变器208a、208b共享相同的电机定子，因此导致发电机功率和电机逆变器功率彼此独立。如果使用电机逆变器208a来对蓄电池210再充电，则定子504b将充当电机，而定子504a将充当发电机，需要从所述发电机进行从AC到DC的转换来对蓄电池210再充电。如果使用电机逆变器208b来对蓄电池210再充电，则定子504a将充当电机，而定子504b将充当发电机，从所述发电机需要从AC到DC的转换来对蓄电池210再充电。
参考图6，示出了混合电力飞行器推进系统200的另一实施例。在此示例中，在发电机202、电动机204a、204b和电机逆变器208a、208b之间提供额外连接。通过闭合继电器314a和314c并且打开继电器314d，发电机定子402a可以选择性地连接到电动机204a的两个定子502a、504a。通过闭合继电器314b和314e并且打开继电器314f，发电机定子402b可以选择性地连接到电动机204b的两个定子502b、504b。通过闭合继电器314d和314c并且打开继电器314a，电机逆变器208a可以选择性地连接到电动机204a的两个定子502a、502b。通过闭合继电器314f和314e并且打开继电器314b，电机逆变器208b可以选择性地连接到电动机204b的两个定子502b、504b。而且，如果需要，每一定子502a和/或502b可以同时连接到发电机定子402a和逆变器208A两者，而不打开继电器314a。这有助于能够使用逆变器来提供额外功率或提取功率以对蓄电池再充电，或者向飞行器DC总线提供功率，或者调节并维持电机和发电机彼此同相。对于其他电机和相关联发电机定子、逆变器、继电器等等也是同样的。此架构为发电机202提供驱动任一电动机204a、204b的两个定子502a、504a或502b、504b的能力，并且为电机逆变器208a、208b提供驱动任一电动机204a、204b的两个定子502a、504a或502b、504b的能力。
图6的架构还提供通过闭合继电器314a、314c、314d和/或314b、314e、314f来直接从发电机202对蓄电池210再充电的能力，从而分别在发电机202和电机逆变器208a、208b之间提供直接路径。在这种情况下，电机逆变器208a、208b中的一者或两者将需要设置有AC-DC转换器以将由发电机202接收的AC功率变换成用于蓄电池210的DC功率。如果需要，例如如果有助于启动热力发动机或在发动机启动之前驱动连接到发电机轴的辅助系统，诸如泵，则图6的架构还提供通过将定子402a或402b驱动为电动机而非发电机来使用蓄电池向热力发动机提供机械功率的能力。其他实施例也是如此。
转向图7，示出了混合电力飞行器推进系统200的又另一实施例。在此示例中，旋转结构206c可操作地联接到热力发动机201以便向飞行器提供额外推进力。事实上，由热力发动机201生成的原动力还可以直接施加到旋转结构206c（诸如飞行器的螺旋桨或推进风扇）以便补充由旋转结构206a、206b提供的推进力。
应注意，虽然结合图4的实施例示出了旋转结构206c，但是其还可以添加到图2、图3、图5和图6中所提供的其他实施例中的任一实施例以及其变型。其变型包括例如连接到三个电动机的三定子发电机。要理解，本实施例适用于任何数量的发电机定子和电机定子。本实施例的变型的另一示例是三定子电动机，每一定子连接到发电机定子、第一电机逆变器和第二电机逆变器中的一者。第一和第二电机逆变器可以连接到相同的蓄电池或者连接到单独的蓄电池。所属领域的技术人员将容易理解其他变型。
在一些实施例中，使用混合电力飞行器推进系统200的各种架构来解决系统200内的可能故障。下文描述故障模式的各种示例。
基于图2至图7的实施例，在热力发动机201发生故障的情况下，可经由蓄电池210获得旋转结构206的推进功率。然而，可获得的功率受到蓄电池210（或飞行器DC总线）的功率和能量容量以及电机逆变器208、208a、208b、308的额定功率的限制。类似地，在因短路所致的发电机故障的情况下，旋转结构206、206a、206b的推进功率可经由蓄电池210获得，但是受到蓄电池210的容量以及电机逆变器208、208a、208b、308的额定功率的限制。在蓄电池故障的情况下，推进功率是可获得的，但是受到发电机202的功率以及热力发动机201的可获得的燃料的限制。
基于其中存在至少两个电动机204a、204b的图3至图7的实施例，在一个电动机204a发生故障的情况下，另一个功能电动机204b可获得全功率。在一个电机逆变器208a发生故障的情况下，一个电动机204b可获得全功率，并且另一个电动机204a可获得部分功率，其受到发电机202的功率以及热力发动机201的可获得的燃料的限制。如果两个电机逆变器208a、208b连接在一起，则任一电动机204a、204b可以可获得全功率。
基于其中发电机202具有双定子402、404的图4至图7的实施例，在因两个定子402、404中的一者上的开路（open circuit）所致的发电机故障的情况下，两个电动机204a、204b中的一者可获得全功率。两个电动机204a、204b中的另一者可获得部分功率，其受到蓄电池210的容量和与其相关联的电机逆变器208a、208b的额定功率的限制。另外，在蓄电池耗尽的情况下，来自运行发电机定子的能量可以通过两个电机逆变器传递到相对电机。
基于其中每一电动机204a、204b具有两个定子的图5的实施例，在一个定子502a或504a发生故障的情况下，仍然可以从电动机204a获得一些功率。如果定子502a发生故障，仍然可以从蓄电池210获得功率，并且该功率受到蓄电池210的容量和与其相关联的电机逆变器208a的额定功率以及剩余的电机定子504a的额定功率的限制。如果定子504a发生故障，则仍然可以从发电机202获得功率，并且该功率受到发电机202的功率以及热力发动机201的可获得的燃料以及剩余的电机定子502a的额定功率的限制。
基于图6的实施例，如果逆变器208a或208b发生故障，则借助适当继电器配置，相关联的电动机204a或204b仍然可以从发电机定子402a或402b获得全功率，其受到发电机额定值的限制。类似地，如果发电机定子402a或402b发生故障，则相关联的电动机204a或204b的两个电机定子可以由蓄电池210供电。然后，可获得的总功率将取决于逆变器208a或208b和蓄电池210的额定值。
基于图7的实施例，如果两个电动机204a、204b发生故障并且飞行器没有燃气了，则来自蓄电池的功率可以传递到热力发动机201的主轴以产生旋转结构206c的推进功率。电机逆变器208a、208b可以连接到发电机202以充当电机并且向旋转结构206C以及诸如泵的其他装置增加功率。如果所有电力系统都发生故障，则热力发动机201仍然可以为旋转结构206c提供推进功率。
图8是电机逆变器208的示例性实施例。示出了可以与本文中所描述的混合电力飞行器推进系统200一起使用的许多可能实施例中的一个实施例。线路V+和V-连接到蓄电池210的正端子和负端子。线路A、B、C连接到电动机204，并且表示提供给所述电动机204的AC电功率的三个相。
参考图9，示出了控制器212的示例性实施例，所述控制器212包括处理单元902和存储器904，存储器904中存储有计算机可执行的指令906。图9还可以表示嵌入逆变器208中的控制功能。处理单元902可以包括如下任何合适装置：其被配置成实现所述系统，使得指令906在由控制器212或其他可编程设备执行时可以导致执行如本文中所述的功能/动作/步骤。处理单元902可以包括例如任何类型的通用微处理器或微控制器、数字信号处理（DSP）处理器、中央处理单元（CPU）、集成电路、现场可编程门阵列（FPGA）、可重新配置的处理器、其他适当编程或可编程逻辑电路，或者其任何组合。
存储器904可以包括任何合适已知或其他机器可读存储介质。存储器904可以包括非暂时性计算机可读存储介质，例如，但不限于，电子的、磁性的、光学的、电磁的、红外的或半导体系统、设备或装置，或者前述的任何合适组合。存储器904可以包括位于控制器212内部或外部的任何类型的计算机存储器的合适组合，例如随机存取存储器（RAM）、只读存储器（ROM）、光盘只读存储器（CDROM）、电光存储器、磁光存储器、可擦除可编程只读存储器（EPROM）和电可擦除可编程只读存储器（EEPROM）、铁电RAM （FRAM）等等。存储器904可以包括适于可检索地存储可由处理单元902执行的机器可读指令906的任何存储器件（例如，装置）。要注意，控制器212可以被实现为全权数字发动机控制器（FADEC）或其他类似装置的一部分，其他类似装置包括电子发动机控制器（EEC）、发动机控制单元（EUC）等等。
本文中所描述的方法和系统可以用高级程序语言或面向对象编程语言或脚本语言或其组合实现，以与计算机系统（例如控制器212）通信或辅助计算机系统（例如控制器212）的操作。替代地，所述方法和系统可以用汇编或机器语言实现。所述语言可以是编译或解释语言。用于实现所述方法和系统的程序代码可以存储在存储介质或装置上，例如ROM、磁盘、光盘、闪存驱动器或任何其他合适存储介质或装置。所述程序代码可以由通用或专用可编程计算机读取，以用于在所述存储介质或装置由计算机读取以执行本文中所描述的程序时配置和操作计算机。所述方法和系统的实施例还可以视为通过其上存储有计算机程序的非暂时性计算机可读存储介质实现。所述计算机程序可以包括如下计算机可读指令：其致使计算机（或者在一些实施例中，控制器212的处理单元902）以特定和预先限定的方式操作以执行本文中所描述的功能。
计算机可执行指令可以呈由一个或多个计算机或其他装置执行的许多形式，包括程序模块。通常，程序模块包括执行特定任务或实现特定抽象数据类型的例程、程序、对象、组件、数据结构等等。通常，在各种实施例中可以根据需要组合或分配程序模块的功能。
以上描述仅旨在表示是示例性的，并且本领域技术人员将认识到，可以在不背离所公开的本发明的范围的情况下对所描述的实施例作出改变。鉴于对本公开的回顾，落入本发明的范围内的另外其他修改对本领域的技术人员将是显而易见的。
本文中所描述的系统和方法的各个方面可以单独使用、组合使用、或者以在前述中描述的实施例中未具体论述的多种布置结构使用，并且因此其应用于并不限于在前述描述中阐述或者在附图中示出的部件的细节和布置结构。例如，在一个实施例中描述的方面可以以任何方式与在其他实施例中描述的方面组合。虽然已经示出和描述了特定实施例，但是对本领域的技术人员将显而易见的是，可以在不脱离本发明的更广泛方面的情况下作出改变和修改。以下权利要求的范围不应受到在示例中阐述的实施例的限制，而是应该被给予与整个说明书一致的最广泛的合理解释。

Claims (16)

1.一种用于操作安装到飞行器的混合电力飞行器推进系统的方法，所述方法包括：
利用第一电动机驱动第一旋转推进器，所述第一电动机可操作地连接到发电机；
由第二电动机驱动第二旋转推进器，所述第二电动机可操作地连接到所述发电机；以及
由热力发动机驱动第三旋转推进器，所述热力发动机可操作地连接到所述发电机并且配置成用于驱动所述发电机。
2.根据权利要求1所述的方法，其中，所述发电机是双定子发电机，所述双定子发电机具有驱动所述第一电动机的第一发电机定子以及驱动所述第二电动机的第二发电机定子。
3.根据权利要求1或2所述的方法，其中，由第一电动机驱动第一旋转推进器包括将交流（AC）电功率选择性地施加到所述第一电动机：
所述AC电功率来自所述发电机；以及
所述AC电功率来自第一电机逆变器，所述第一电机逆变器连接到直流（DC）功率源并且配置成用于将DC电功率转换为AC电功率。
4.根据权利要求3所述的方法，其中，将AC电功率选择性地施加到所述第一电动机包括：将所述发电机和所述第一电机逆变器中的一者与所述第一电动机断开；并且将所述发电机和所述第一电机逆变器中的另一者连接到所述第一电动机。
5.根据权利要求3或4所述的方法，其中，所述第一电动机是双定子电机，并且其中将AC电功率选择性地施加到所述第一电动机包括：将来自所述发电机的AC电功率施加到第一电机定子并且将来自所述第一电机逆变器的AC电功率施加到第二电机定子。
6.根据权利要求3或4所述的方法，其中，所述第一电动机是双定子电机，并且其中将AC电功率选择性地施加到所述第一电动机包括：将来自所述发电机的AC电功率施加到第一电机定子和第二电机定子；或者将来自所述第一电机逆变器的AC电功率施加到所述第一电机定子和所述第二电机定子。
7.根据权利要求3至6中任一项所述的方法，还包括：
检测所述第一电动机或所述第二电动机的故障；
将来自所述DC功率源的功率传递到所述热力发动机，以产生用于第三旋转结构的额外推进功率。
8.根据权利要求1所述的方法，其中所述热力发动机安装到所述飞行器的尾部，所述第一电动机安装到所述飞行器的第一机翼或第二机翼，并且所述第二电动机安装到所述飞行器的所述第一机翼或第二机翼。
9.根据权利要求1至8中任一项所述的方法，其中，所述热力发动机安装到所述飞行器的机头，所述第一电动机安装到所述飞行器的第一机翼或第二机翼，并且所述第二电动机安装到所述飞行器的所述第一机翼或第二机翼。
10.一种具有推进系统的混合电力飞行器，其包括：
第一旋转推进器；
第一电动机，其联接到所述第一旋转推进器并配置成用于向所述第一旋转推进器施加旋转力；
第二旋转推进器；
第二电动机，其联接到所述第二旋转推进器并且配置成用于向所述第二旋转推进器施加旋转力；
发电机，其联接到所述第一电动机和所述第二电动机并且配置成用于向所述第一电动机和所述第二电动机施加交流（AC）电功率；
第三旋转推进器；以及
热力发动机，其联接到所述发电机和所述第三旋转推进器并且被配置成用于驱动所述发电机和所述第三旋转推进器。
11.根据权利要求10所述的飞行器，还包括：
第一电机逆变器，其联接在所述第一电动机和直流（DC）功率源之间并且配置成用于将来自所述DC功率源的DC电功率转换为AC电功率，并将所述AC电功率施加到所述第一电动机; 以及
第二电机逆变器，其联接在所述第二电动机和所述DC功率源之间并且配置成用于将来自所述DC功率源的DC电功率转换为AC电功率，并将所述AC电功率施加到所述第二电动机。
12.根据权利要求11所述的飞行器，其中，所述发电机是双定子发电机，所述双定子发电机具有驱动所述第一电动机的第一发电机定子以及驱动所述第二电动机的第二发电机定子。
13.根据权利要求11或12所述的飞行器，其中，所述第一电动机和所述第二电动机均包括第一电机定子和第二电机定子，其中所述发电机连接到所述第一电机定子，并且其中所述第一电机逆变器和第二电机逆变器连接到所述第二电机定子。
14.根据权利要求11或12所述的飞行器，其中，所述第一电动机和所述第二电动机均包括第一电机定子和第二电机定子，其中所述发电机能够选择性地连接到所述第一电机定子和所述第二电机定子，并且其中所述第一电机逆变器和第二电机逆变器能够选择性地连接到所述第一电机定子和所述第二电机定子。
15.根据权利要求10至14中任一项所述的飞行器，其中，所述热力发动机安装到所述飞行器的尾部，所述第一电动机安装到所述飞行器的第一机翼或第二机翼，并且所述第二电动机安装到所述飞行器的所述第一机翼或第二机翼。
16.根据权利要求10至14中任一项所述的飞行器，其中，所述热力发动机安装到所述飞行器的机头，所述第一电动机安装到所述飞行器的第一机翼或第二机翼，并且所述第二电动机安装到所述飞行器的所述第一机翼或第二机翼。
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