CN106143926A - 用于飞行器推进和升高的电直接驱动器 - Google Patents

用于飞行器推进和升高的电直接驱动器 Download PDF

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CN106143926A
CN106143926A CN201610416391.4A CN201610416391A CN106143926A CN 106143926 A CN106143926 A CN 106143926A CN 201610416391 A CN201610416391 A CN 201610416391A CN 106143926 A CN106143926 A CN 106143926A
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motor
multiphase
energy storage
electromotor
storage devices
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W·L·西格尔
R·J·罗德里格斯
M·J·布莱克韦尔德
J·T·阿尔特
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ROOLS-ROYCE
Rolls Royce North American Technologies Inc
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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
    • B64D41/00—Power installations for auxiliary purposes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K21/00—Synchronous motors having permanent magnets; Synchronous generators having permanent magnets
    • 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
    • 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
    • B64D41/00—Power installations for auxiliary purposes
    • B64D2041/002—Mounting arrangements for auxiliary power units (APU's)
    • 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
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/60—Other road transportation technologies with climate change mitigation effect
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    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/60—Other road transportation technologies with climate change mitigation effect
    • Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
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Abstract

本公开提供了一种装置，该装置具有耦接到发电机的原动机，所述发电机直接电耦接到电动机。螺旋桨或风扇可耦接到电动机并由其驱动。双向电力转换器可耦接到所述发电机，并进一步耦接到能量储存设备。能量储存设备可选择性地耦接到电动机。还提供了使用该装置的方法。

Description

用于飞行器推进和升高的电直接驱动器
相关申请的交叉引用
本申请是要求于2015年5月5日提交的美国临时申请No.62/157,050的优先权的非临时申请，其通过引用整体上并入在此。
技术领域
本公开一般涉及电动飞行器推进和升高，并且更特别而非排他性地涉及用于飞行器推进和升高的电直接驱动器。
背景技术
减轻在电动飞行器推进和升高中遇到的困难仍是感兴趣的领域。对于该困难的现有方法遭受到相对于特定应用的各种限制和缺点。例如，该领域中的当前应用会是沉重的且占用飞行器内大容量的空间，使得其应用被禁止。因此，需要对该技术进一步的贡献。
发明内容
本公开的一个实施例是用于飞行器推进和升高的独特的电直接驱动器。其它实施例包括装置、系统、设备、硬件及其使用方法。本申请的进一步的实施例、形式、特征、方面、益处和优点由在此提供的描述和附图而变得显而易见。
附图说明
图1是用于飞行器推进和升高的电直接驱动器的示意图；及
图2是在此公开的用于飞行器推进和升高的电直接驱动器的实施例的示意图。
具体实施方式
为了促进对本公开的原理的理解，现在将参考附图中所示的实施例，并且将使用特定语言来描述相同内容。但应理解，并非旨在借以限定本公开的范围。设想所述实施例中的任何变化和进一步的修改，及在此所述的本公开的原理的任何进一步的应用，如同本公开所属领域的技术人员通常会想到的一样。
参考图1，提供了具有电推进/升高驱动器的系统100的示意图。系统100的这个实施例可以利用体积大、沉重、复杂且昂贵的功率电子器件来调节从发电机104到为机载平台提供推进或升高能力的电动机110a、110b的功率流。功率电子设备将发电机104的输出(例如电压、电流和频率)转换为电动机110a、110b的特定需要(例如电压、电流和频率)。功率电子器件“现有技术水平”度量显示功率密度范围为3-5kW/kg且比重范围为5-7kW/liter。用于传统机载平台的实施例的升高和推进功率要求可能非常高，因而使得在这种概念下对于功率电子器件所需的重量和体积是被禁止的。
如图1所示，可以是发动机的原动机102耦接到发电机104。发电机104电耦接到AC/DC转换器106，这样的整流器。驱动风扇/螺旋桨112a、112b的每一个电动机110a、110b通过DC/AC转换器108a、108b连接到AC/DC转换器106。也可将能量储存设备114提供给系统100。系统100可包括原动机102、发电机104、AC/DC转换器功率电子器件106、转换器108a、108b、电动机110a、110b、风扇/螺旋桨112a、112b、能量储存114和连接件116。连接件116可以包括在系统100的各部件之间的连接件116a-i。
现在参考图2，提供了具有本公开的电推进/升高驱动器的系统200的示例实施例的示意图。系统200可去掉以前在传统系统中使用的许多功率电子器件。例如，这通过直接从发电机104为电动机110a、110b(例如推进/升高风扇电动机)供电来实现。
系统200可包括原动机202(例如，诸如燃气涡轮发动机的发动机)、发电机204(例如多相发电机)、转换器208(例如，DC/AC转换器功率电子器件)、电动机210a、210b(例如，诸如多相同步电动机的电动机)、风扇/螺旋桨212a、212b、和能量储存214(例如，一个或多个电池)、以及一个或多个连接件216。连接件216可包括可操作地并且电耦接或连接系统200的部件的直接或间接连接件。连接件216a、216b可连接原动机202与发电机204。连接件216c可连接发电机204与转换器208。连接件216d可连接转换器208与能量储存214。连接件216e、216f可连接发电机204与电动机210a、210b。连接件216g、216h可连接电动机210a、210b与能量储存214。
如所示的，在发电机204(例如，多相发电机)与电动机210a、210b(例如，多相同步电动机)之间提供直接连接件216e、216f。多相发电机204例如可以是同步或异步永磁体或绕线磁场式(wound field)同步发电机。多相同步电动机210a、210b例如可以是永磁体或绕线磁场式同步电动机。例如，诸如燃气涡轮发动机或往复活塞式内燃发动机的原动机202驱动发电机。电动机210a、210b驱动风扇/螺旋桨212a、212b用于升高和/或水平推进。
可通过改变耦接到发电机204的原动机202的速度来控制电动机210a、210b的电机速度从而控制风扇/螺旋桨212a、212b的风扇/螺旋桨速度。发电机204的速度直接确定输出电压、电流和频率，其确定驱动风扇/螺旋桨212a、212b的电动机210a、210b的速度。在绕线磁场式发电机或电动机的情况下，可以通过改变励磁来控制速度。
对于紧急情况用途，系统200可包括具有双向电力转换器208的小能量储存设备/部件214。能量储存设备/部件214可以是发动机发电机(engine generator)、一个或多个电池、或其组合。双向电力转换器208例如可以是DC/AC转换器。双向电力转换器208可将来自发电机204的AC电力整流为DC电力以向能量储存设备214充电。随后当需要应急电力时，双向电力转换器208会将来自能量储存设备214的DC电力逆变为用于电动机210a、210b的AC电力。仅需要能量储存设备/部件214携带足够的能量以将机载平台从工作高度安全地传送到地面。
系统200可包括装置。系统200可包括耦接到发电机204的原动机202，直接电耦接到发电机204的一个或多个电动机210a、210b，耦接到一个或多个电动机210a、210b并由其驱动的一个或多个螺旋桨212a、212b，耦接到发电机204并进一步耦接到能量储存设备214的转换器208(例如，双向电力转换器)。能量储存设备214可选择性地耦接到一个或多个电动机210a、210b。电动机210a、210b可包括多相同步电动机、绕线磁场式同步电动机或其组合。发电机204可包括绕线磁场式同步多相发电机、永磁体多相发电机，或其组合。能量储存设备214可包括一个或多个电池、发动机发电机，或其组合。
系统200可包括飞行器推进或升高系统。系统200可包括飞行器，该飞行器容纳耦接到一个或多个发电机204(例如，多相发电机)的一个或多个原动机202，直接电耦接到发电机204的一个或多个电动机210a、210b(例如，多相电动机)，耦接到相应的电动机210a、210b并由其驱动的螺旋桨212a、212b，以及耦接到发电机204并进一步耦接到能量储存设备214的电力转换器208(例如双向电力转换器)。能量储存设备214可选择性地耦接到电动机210a、210b。
还设想了使用系统200的方法。方法可包括将容纳在飞行器中的原动机202耦接到发电机204，该发电机204直接耦接到电动机210a、210b。方法可进一步包括通过原动机202的速度和励磁中的至少一个的变化来改变电动机210a、210b的速度。
尽管在附图和前述说明中详细说明并描述了本公开，但应将其认为在文字上是说明性而非限制性的，应理解，仅示出并描述了优选实施例，并且希望保护在本公开的精神内的所有变化和修改。应理解，尽管在以上说明中使用的诸如更优的、优选地、优选的或更优选的词语的使用指示如此描述的特征是更希望的，但其不是必须的，并且可将缺乏该特征的实施例设想为在本公开的范围内，该范围由以下的权利要求限定。在阅读权利要求时，其旨在当使用诸如“一”、“一个”、“至少一个”、或“至少一部分”的词语时，并非旨在将权利要求局限于仅仅一项，除非在权利要求中具体地做出相反表述。当使用语言“至少一部分”和/或“一部分”时，该项可包括一部分和/或整个项，除非具体地做出相反表述。
除非另有规定或限定，宽泛地使用了术语“安装”、“连接”、“支撑”和“耦接”及其变型，并且包含直接或间接安装、连接、支撑和耦接。此外，“连接”和“耦接”并非局限于物理或机械连接或耦接。

Claims (20)

1.一种飞行器推进系统的装置，包括：
原动机，其耦接到发电机；
电动机，其直接电耦接到所述发电机；
螺旋桨，其耦接到所述电动机并由所述电动机驱动；以及
双向电力转换器，其耦接到所述发电机，并进一步耦接到能量储存设备；以及
其中，所述能量储存设备选择性地耦接到所述电动机。
2.根据权利要求1所述的装置，其中，所述电动机是多相同步电动机。
3.根据权利要求1所述的装置，其中，所述电动机是绕线磁场式同步电动机。
4.根据权利要求1所述的装置，其中，所述发电机是绕线磁场式同步多相发电机。
5.根据权利要求1所述的装置，其中，所述发电机是永磁体多相发电机。
6.根据权利要求1所述的装置，其中，所述能量储存设备包括一个或多个电池。
7.根据权利要求1所述的装置，其中，所述能量储存设备包括发动机发电机。
8.一种飞行器推进系统，包括：
一个或多个原动机，其耦接到一个或多个多相发电机；
一个或多个多相电动机，其直接电耦接到所述一个或多个多相发电机；
螺旋桨，其耦接到所述一个或多个多相电动机的每一个并由所述一个或多个多相电动机的每一个驱动；以及
双向电力转换器，其耦接到所述一个或多个多相发电机，并进一步耦接到能量储存设备；以及
其中，所述能量储存设备选择性地耦接到所述一个或多个多相电动机。
9.根据权利要求8所述的飞行器推进系统，其中，所述一个或多个原动机是燃气涡轮发动机。
10.根据权利要求8所述的飞行器推进系统，其中，所述一个或多个多相发电机是绕线磁场式同步发电机。
11.根据权利要求8所述的飞行器推进系统，其中，所述一个或多个多相电动机是绕线磁场式同步电动机。
12.根据权利要求8所述的飞行器推进系统，其中，所述能量储存设备包括一个或多个电池。
13.根据权利要求8所述的飞行器推进系统，其中，所述能量储存设备包括发动机发电机。
14.一种飞行器推进系统的方法，包括：
将容纳在飞行器中的原动机耦接到直接电耦接到电动机的发电机；以及
通过所述原动机的速度和励磁中的至少一个的变化来改变电动机的速度。
15.根据权利要求14所述的方法，其中，所述电动机包括绕线磁场式电动机中的至少一个。
16.根据权利要求14所述的方法，其中，所述电动机包括多相同步电动机和绕线磁场式同步电动机中的至少一个。
17.根据权利要求14所述的方法，其中，所述发电机是绕线磁场式同步多相发电机。
18.根据权利要求14所述的方法，其中，所述发电机是永磁体多相发电机。
19.根据权利要求14所述的方法，其中，所述能量储存设备包括一个或多个电池。
20.根据权利要求14所述的方法，其中，所述能量储存设备包括发动机发电机。
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