CN105408207B - 用于飞行器的电力推进组件 - Google Patents
用于飞行器的电力推进组件 Download PDFInfo
- Publication number
- CN105408207B CN105408207B CN201480033923.5A CN201480033923A CN105408207B CN 105408207 B CN105408207 B CN 105408207B CN 201480033923 A CN201480033923 A CN 201480033923A CN 105408207 B CN105408207 B CN 105408207B
- Authority
- CN
- China
- Prior art keywords
- power electronic
- electric
- electronic system
- aircraft
- electric propulsion
- Prior art date
- Legal status (The legal status 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 status listed.)
- Active
Links
- 238000001816 cooling Methods 0.000 claims abstract description 34
- 239000012530 fluid Substances 0.000 claims abstract description 7
- 230000005540 biological transmission Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 claims description 3
- 230000005611 electricity Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 208000035126 Facies Diseases 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000005431 greenhouse gas Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 239000003507 refrigerant Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/5813—Cooling the control unit
-
- 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
- B64D33/10—Radiator arrangement
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
- F04D25/068—Mechanical details of the pump control unit
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
- F04D25/0693—Details or arrangements of the wiring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/08—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/08—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation
- F04D25/082—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation the unit having provision for cooling the motor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/08—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation
- F04D25/12—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation the unit being adapted for mounting in apertures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/5806—Cooling the drive system
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
- F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
-
- 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
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/024—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising cooling means
-
- 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
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
-
- 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
- Y02T50/40—Weight reduction
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
本发明涉及用于飞行器的电力推进组件,包括引擎舱(10)、电动马达组件(12)以及控制系统,引擎舱(10)包括引擎舱(10)罩,引擎舱罩限定了其内布置有所述飞行器的包括风机(13)的电力推进单元的内部空间,电动马达组件(12)放置在所述推进单元后面并且连接至所述推进单元以在所述马达组件操作时向所述推进单元供给电能,控制系统包括电力电子系统,限定在所述马达组件与所述引擎舱(10)罩之间的空间限定了由在风机操作以向所述飞行器提供推力时所述风机(13)产生的空气流流动通过的管道。根据本发明,所述电力电子系统包括能够使热能从所述系统传递至工作流体以冷却所述系统的至少一个换热器,并且所述至少一个换热器放置成至少部分地突入所述管道,从而使工作流体包括在风机操作期间由所述风机(13)产生的所述空气流。
Description
技术领域
本发明涉及用于飞行器的电力推进组件,该电力推进组件具有用于冷却其电力电子系统的新型设计。
本发明还涉及设置有该电力推进组件的飞行器。
背景技术
航空工业是不断发展并且一直追寻技术进步的技术领域。试图减小空气运输的环境影响、降低明显的噪声和温室气体的排放的当前研究工作在该背景下。
在该背景下,机械/电子混合驱动或全电子驱动的概念是非常有前途的。因此,已知小型飞机如两座私人飞机的所有推动力通过电力提供。
大型飞机对获得更高推动力的需要导致由用于管理和控制输送至电力传动装置的电能的电力电子系统所散发的热量的显著增加。
当前,存在许多冷却电力电子系统的技术解决方案。
因此,已知电力电子系统包含使用水或甚至使用两相型制冷剂的冷却系统。
然而,现有技术的所有这些解决方案在增加至电力电子系统的附加重量(流体、循环系统等)方面是不利的。
使用一个或更多个风机来除去由电力电子系统产生的热也是已知的实施方案。
然而,由于借助于这样的解决方案除去由大型飞行器的推进单元的电力电子系统散发的热会显著增加重量,因此该解决方案不适用至航空领域。
另外,用于供给电力或用于传输电控制信号的各种布线的重量例如是推进单元的总重量的重要因素,该重量不利于飞机的有效载荷。
因此,有益的是限定一种如下的推进单元:其具有用于冷却推进单元的电力电子系统的新型结构并且还总体限制布线的重量并且特别地限制电力供给布线的重量。
本发明试图通过提出一种推进单元来减轻上文陈述的各种不足,所述推进单元的设计和操作模式特别简单并且允许其电力电子系统的有效冷却。
本发明的另一目的是减小与推进单元的布线相关联的重量。
发明内容
为此,本发明涉及用于飞行器的推进组件,该推进组件包括引擎舱、电动马达组件以及控制系统,其中,引擎舱包括引擎舱罩,引擎舱罩界定了其内放置飞行器的包括风扇的电力推进单元的内部容积,电动马达组件放置在所述推进单元后面并且连接至推进单元以在电动马达组件操作时向所述推进单元供给电能,控制系统包括电力电子系统,界定在所述马达组件与所述引擎舱罩之间的空间限定了如下涵道:在所述风扇操作以向所述飞行器提供推力时由所述风扇产生的空气流流动通过该涵道。
根据本发明,
–所述电力电子系统包括允许热能从所述系统传递至工作流体以冷却所述系统的至少一个换热器,并且,
–所述至少一个换热器定位成使得所述至少一个换热器至少部分突入所述涵道,从而使所述工作流体在所述风扇操作时由所述风扇产生的所述空气流组成。
由于电力电子系统容置在引擎舱中,因此能够充分利用由风扇产生的强制空气流。进入引擎舱的空气事实上通过风扇加速从而产生了有助于飞行器推动的空气流,该空气流增加了放置在空气流路径上的换热器的效率。这形成了该换热器的质量和体积方面的可能的最优化,从而导致换热器的质量的减小。
基于将电子系统容置在引擎舱中的另一技术优点在于系统尽可能靠近电动马达组件定位,由此减小了与推进组件的布线相关联的重量。
在该组件的各种特定实施方式中,每个实施方式具有其自身特定优点并且可以以多种技术上可行的方式结合:
–所述电力电子系统包括电力电子模块和电子控制板,电力电子模块和电子控制板连接至所述至少一个换热器以除去这些元件通过焦耳效应耗散的功率,由所述模块和所述板形成的该组件容置在所述引擎舱罩中。
通过所述模块和所述板形成的该组件容置在限定于所述引擎舱罩的内壁与外壁之间的壳体中。
–在所述引擎舱限定纵向轴线并且所述马达组件通过相对于所述纵向轴线沿径向或大致沿径向定向的一组或更多组臂连接至所述引擎舱的情况下,至少用于电气连接和/或传输命令信号的线缆穿过所述臂中的至少一些臂,
–在所述引擎舱限定纵向轴线并且所述马达组件通过相对于所述纵向轴线沿径向或大致沿径向定向的一组或更多组臂连接至所述引擎舱的情况下,所述臂中的至少一些臂具有至少一个冷却勺状部,所述至少一个冷却勺状部用于使由所述风扇产生的空气流中的一些空气流朝向所述马达组件偏转以冷却所述马达组件。
每个勺状部有利地具有朝向空气流定向的正面,所述空气流来自风扇并朝向对应臂流动,以使一些空气流朝向所述马达组件偏转从而冷却马达组件。该正面例如部分成圆顶状以限定朝向所述马达组件定向的斜面。
–所述换热器包括散热片,所述散热片布置成使得所述散热片沿由所述风扇产生的空气流流动的方向而定位以不扰乱所述流动,
–所述风扇包括能够旋转的叶片,每个所述叶片具有可调节螺距,所述电力推进单元包括允许每个所述风扇叶片的螺距调节的调节装置以保持可能的最佳效率,
–所述电力电子系统包括用于冷却所述电力电子系统的附加冷却装置。
该附加冷却装置例如是电连接至所述马达组件的风机。
本发明还涉及配备有至少一个电力推进组件的飞行器。
根据本发明,该电力推进组件是如上文所描述的推进组件。
附图说明
本发明的其他优点、目的和特定特征将通过参照附图以完全非限制的方式说明得到的描述变得明显,在附图中:
–图1是根据本发明的一个特定实施方式的推进组件的立体图,
–图2是图1的组件的纵向截面图。
具体实施方式
首先应指出的是附图并未按比例绘制。
图1和图2示出了根据本发明的优选实施方式的用于飞机的混合电力推进组件。
该推进组件包括引擎舱10,借助于机械连接件11如挂架将引擎舱10装配至飞行器的结构元件。仅以示例的方式,该结构元件可以是飞行器的机翼结构的一部分,组件例如定位在该机翼结构的翼稍。然而,该组件可以附接至该飞行器的机翼结构的一些其他点。
引擎舱10包括引擎舱10罩,引擎舱10罩界定了其内定位有电动马达12的内部容积,其中,电动马达12驱动安装在该电动马达12前方的风扇13。引擎舱10围绕电动马达12关于纵向轴线14同轴布置。
简单地说,该推进组件使用具有涵道式推进器的风扇13在引擎舱10的空气入口15处吸进外部空气,该风扇13包括前弹状物16。通过风扇13吸进并且加速的空气流朝向喷嘴被输送通过环形空间17,环形空间17限定在电动马达12的外表面与引擎舱10罩的内壁之间。
引擎舱10使用已知技术直接连接至机翼的翼稍,从而允许载荷沿所有方向起作用。引擎舱10通过相对于纵向轴线14大致沿径向定向的一组或更多组臂18机械连接至电动马达12。
引擎舱10还具有连续的外表面,这也就是说引擎舱10的长度的在空气流动方向上的至少前半部分中不存在不连续部,从而使空气围绕引擎舱10形成层流。
推进组件还包括控制系统,该控制系统包括电力电子系统,电力电子系统包括电力电子模块19和电子控制板20,电力电子模块19和电子控制板20连接至换热器21以除去这些元件通过焦耳效应耗散的功率。
尽管电力电子模块19和电子控制板20容置在引擎舱10罩中,然而,换热器21定位成使得其突出至环形空间17中,使电动马达12的外表面与引擎舱10罩的内表面分开。
因此,能够充分利用由风扇13产生的强制空气流来有效冷却换热器21,由此能够在质量和体积方面优化该换热器21使得换热器的重量尽可能被限制。
Claims (10)
1.一种用于飞行器的电力推进组件,包括引擎舱(10)、电动马达组件(12)以及控制系统,其中,所述引擎舱(10)包括引擎舱罩,所述引擎舱罩界定了其内放置所述飞行器的包括风扇(13)的电力推进单元的内部容积,所述电动马达组件(12)放置在所述电力推进单元后面并且连接至所述电力推进单元以在其操作时向所述电力推进单元供给电能,所述控制系统包括电力电子系统,界定在所述电动马达组件与所述引擎舱罩之间的空间限定了如下涵道:在所述风扇操作以向所述飞行器提供推力时,由所述风扇(13)产生的空气流流动通过所述涵道,其特征在于,
所述电力电子系统包括电力电子模块、电子控制板以及允许热能从所述电力电子系统传递至工作流体以冷却所述电力电子系统的至少一个换热器,
所述电力电子模块和所述电子控制板容置在限定于所述引擎舱罩的内壁与外壁之间的壳体中,
所述至少一个换热器定位成使得所述至少一个换热器至少部分地突入所述涵道中,从而使所述工作流体包括在所述风扇(13)操作时由所述风扇(13)产生的所述空气流,并且
在所述引擎舱(10)限定纵向轴线(14)并且所述电动马达组件通过相对于所述纵向轴线沿径向或大致沿径向定向的一组或更多组臂连接至所述引擎舱(10)的情况下,至少用于电气连接和/或传输命令信号的线缆穿过所述臂中的至少一些臂。
2.根据权利要求1所述的电力推进组件,其特征在于,所述电力电子模块和所述电子控制板连接至所述至少一个换热器以除去这些元件通过焦耳效应耗散的功率。
3.根据权利要求1或2所述的电力推进组件,其特征在于,在所述引擎舱(10)限定纵向轴线并且所述电动马达组件通过相对于所述纵向轴线沿径向或大致沿径向定向的一组或更多组臂连接至所述引擎舱(10)的情况下,所述臂中的至少一些臂具有至少一个冷却勺状部,所述至少一个冷却勺状部用于使由所述风扇(13)产生的空气流中的一些空气流朝向所述电动马达组件偏转以冷却所述电动马达组件。
4.根据权利要求1或2所述的电力推进组件,其特征在于,所述换热器包括散热片,所述散热片布置成使得所述散热片沿由所述风扇(13)产生的空气流流动的方向而定位以不扰乱所述流动。
5.根据权利要求3所述的电力推进组件,其特征在于,所述换热器包括散热片,所述散热片布置成使得所述散热片沿由所述风扇(13)产生的空气流流动的方向而定位以不扰乱所述流动。
6.根据权利要求1或2所述的电力推进组件,其特征在于,所述电力电子系统包括用于冷却所述电力电子系统的附加冷却装置。
7.根据权利要求3所述的电力推进组件,其特征在于,所述电力电子系统包括用于冷却所述电力电子系统的附加冷却装置。
8.根据权利要求4所述的电力推进组件,其特征在于,所述电力电子系统包括用于冷却所述电力电子系统的附加冷却装置。
9.根据权利要求5所述的电力推进组件,其特征在于,所述电力电子系统包括用于冷却所述电力电子系统的附加冷却装置。
10.一种飞行器,所述飞行器配备有至少一个如权利要求1至9中的任一项所述的电力推进组件。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1355557 | 2013-06-14 | ||
FR1355557A FR3006996B1 (fr) | 2013-06-14 | 2013-06-14 | Ensemble de propulsion electrique pour aeronef |
PCT/EP2014/062426 WO2014198923A1 (fr) | 2013-06-14 | 2014-06-13 | Ensemble de propulsion électrique pour aéronef |
Publications (2)
Publication Number | Publication Date |
---|---|
CN105408207A CN105408207A (zh) | 2016-03-16 |
CN105408207B true CN105408207B (zh) | 2018-12-18 |
Family
ID=48874407
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201480033923.5A Active CN105408207B (zh) | 2013-06-14 | 2014-06-13 | 用于飞行器的电力推进组件 |
Country Status (6)
Country | Link |
---|---|
US (1) | US10138899B2 (zh) |
EP (1) | EP3007977B1 (zh) |
CN (1) | CN105408207B (zh) |
ES (1) | ES2638778T3 (zh) |
FR (1) | FR3006996B1 (zh) |
WO (1) | WO2014198923A1 (zh) |
Families Citing this family (31)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105366060B (zh) * | 2015-12-03 | 2017-03-29 | 北京航空航天大学 | 一种轻质高效低噪声涵道式四级电动风扇推进器 |
CN105416573B (zh) * | 2015-12-03 | 2017-05-17 | 北京航空航天大学 | 一种轻质高效低噪声涵道式两级电动风扇推进器 |
CN106194498A (zh) * | 2016-08-11 | 2016-12-07 | 南昌航空大学 | 一种新型叠加组合式涵道风扇 |
US11105340B2 (en) * | 2016-08-19 | 2021-08-31 | General Electric Company | Thermal management system for an electric propulsion engine |
US10676205B2 (en) * | 2016-08-19 | 2020-06-09 | General Electric Company | Propulsion engine for an aircraft |
US10538337B2 (en) * | 2017-04-21 | 2020-01-21 | General Electric Company | Propulsion system for an aircraft |
US20180319288A1 (en) * | 2017-05-08 | 2018-11-08 | Bell Helicopter Textron Inc. | Ethanol-Fueled Fuel Cell Powered Aircraft |
CN108995818A (zh) * | 2017-06-07 | 2018-12-14 | 深圳光启合众科技有限公司 | 涵道风扇 |
FR3067860B1 (fr) * | 2017-06-15 | 2021-04-16 | Airbus Group Sas | Systeme de charge d'au moins une batterie d'accumulateurs d'un vehicule et procede de gestion de recharge de ladite au moins une batterie |
US11292604B2 (en) | 2017-10-23 | 2022-04-05 | Pratt & Whitney Canada Corp. | Integrated heat management for hybrid propulsion |
US10443620B2 (en) * | 2018-01-02 | 2019-10-15 | General Electric Company | Heat dissipation system for electric aircraft engine |
DE102018102525A1 (de) | 2018-02-05 | 2019-08-08 | Airbus Defence and Space GmbH | Antriebssystem für ein Luftfahrzeug und Verfahren zum Bereitstellen einer Antriebsleistung für ein Luftfahrzeug |
EP3522341A1 (de) * | 2018-02-06 | 2019-08-07 | Siemens Aktiengesellschaft | Elektrischer antrieb mit einer leistungselektronischen schaltung |
DE102018116144B4 (de) * | 2018-07-04 | 2022-08-11 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Luftfahrzeug |
US11926429B2 (en) * | 2018-07-04 | 2024-03-12 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Aircraft having cooling system for distributing heat transfer liquid to different regions of aircraft |
DE102018116157B4 (de) * | 2018-07-04 | 2022-02-24 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Luftfahrzeug |
GB201811040D0 (en) * | 2018-07-05 | 2018-08-22 | Rolls Royce Plc | Cooling |
CA3132274A1 (en) | 2019-03-01 | 2020-09-10 | Pratt & Whitney Canada Corp. | Circulating coolant fluid in hybrid electrical propulsion systems |
US11134585B2 (en) * | 2019-05-31 | 2021-09-28 | Hamilton Sundstrand Corporation | Aircraft power electronic unit and method of cooling |
EP3764523B1 (en) | 2019-07-10 | 2023-09-20 | Airbus Operations GmbH | Electric machine with integrated cooling system |
US11649064B2 (en) | 2019-08-02 | 2023-05-16 | Hamilton Sundstrand Corporation | Integrated motor drive cooling |
GB2587668A (en) * | 2019-10-02 | 2021-04-07 | Advanced Mobility Res And Development Ltd | Systems and methods for aircraft |
EP3825229A1 (en) | 2019-11-19 | 2021-05-26 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Propulsion system for an electrically driven aircraft, aircraft comprising a propulsion system and method of selectively adapting an energy supply within a propulsion system of an electrically driven aircraft |
DE102019219573A1 (de) | 2019-12-13 | 2021-06-17 | Rolls-Royce Deutschland Ltd & Co Kg | Stromrichterkühlung in der Luftfahrt |
CA3169650A1 (en) | 2020-02-10 | 2021-10-07 | Wisk Aero Llc | Aircraft with pusher propeller |
US11799364B2 (en) | 2020-04-30 | 2023-10-24 | Kaney Aerospace, Inc. | Electric propulsion system having integrated electrical and thermal architecture and related methods of operating and implementing same |
CA3144868A1 (en) | 2021-01-05 | 2022-07-05 | Pratt & Whitney Canada Corp. | Parallel hybrid power plant with hollow motor |
CN116981621B (zh) * | 2021-02-09 | 2024-07-02 | 杰欧比飞行有限公司 | 飞行器推进单元 |
EP4238872A3 (en) * | 2021-02-19 | 2023-11-22 | Lilium eAircraft GmbH | Aircraft engine |
GB2617597A (en) * | 2022-04-13 | 2023-10-18 | Greenjets Ltd | Electric propulsion systems |
US11613350B1 (en) | 2022-10-07 | 2023-03-28 | Archer Aviation, Inc. | Systems and methods for lifter motor cooling in eVTOL aircraft |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4685289A (en) * | 1981-06-12 | 1987-08-11 | Violett Robert S | Power plant for model jet aircraft |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3957230A (en) * | 1973-07-30 | 1976-05-18 | Boucher Roland A | Remotely controlled electric airplane |
US4608819A (en) * | 1983-12-27 | 1986-09-02 | General Electric Company | Gas turbine engine component cooling system |
GB2389174B (en) * | 2002-05-01 | 2005-10-26 | Rolls Royce Plc | Cooling systems |
GB0323993D0 (en) * | 2003-10-14 | 2003-11-19 | Rolls Royce Plc | Engine cooling |
JP2005256749A (ja) * | 2004-03-12 | 2005-09-22 | Nippon Densan Corp | ファン |
US8026644B2 (en) * | 2007-04-10 | 2011-09-27 | Violett Robert S | Electric propulsion system useful in jet-type model airplanes and UAVS |
FR2917714B1 (fr) * | 2007-06-25 | 2009-11-27 | Airbus France | Turboreacteur pour aeronef |
US9011106B2 (en) * | 2012-05-07 | 2015-04-21 | Hamilton Sundstrand Corporation | Fan motor controller |
-
2013
- 2013-06-14 FR FR1355557A patent/FR3006996B1/fr active Active
-
2014
- 2014-06-13 US US14/898,127 patent/US10138899B2/en active Active
- 2014-06-13 WO PCT/EP2014/062426 patent/WO2014198923A1/fr active Application Filing
- 2014-06-13 CN CN201480033923.5A patent/CN105408207B/zh active Active
- 2014-06-13 EP EP14731219.3A patent/EP3007977B1/fr active Active
- 2014-06-13 ES ES14731219.3T patent/ES2638778T3/es active Active
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4685289A (en) * | 1981-06-12 | 1987-08-11 | Violett Robert S | Power plant for model jet aircraft |
Also Published As
Publication number | Publication date |
---|---|
US10138899B2 (en) | 2018-11-27 |
US20160137305A1 (en) | 2016-05-19 |
EP3007977B1 (fr) | 2017-05-31 |
FR3006996B1 (fr) | 2016-12-09 |
FR3006996A1 (fr) | 2014-12-19 |
EP3007977A1 (fr) | 2016-04-20 |
ES2638778T3 (es) | 2017-10-24 |
CN105408207A (zh) | 2016-03-16 |
WO2014198923A1 (fr) | 2014-12-18 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN105408207B (zh) | 用于飞行器的电力推进组件 | |
US8794571B2 (en) | Cooler for an aircraft cooling system, aircraft cooling system and method for operating an aircraft cooling system | |
US11092031B2 (en) | Drive system for an aircraft | |
CN107113997B (zh) | 散热机构及具有该散热机构的无人飞行器 | |
EP3505449B1 (en) | Heat dissipation system for electric aircraft engine | |
WO2021064382A2 (en) | Systems and methods for aircraft | |
US8678310B2 (en) | Ducted ram air generator assembly | |
EP2688801B1 (en) | Aircraft tail region with a cooling system installed in said aircraft tail region | |
US8310117B2 (en) | Electric propulsion system useful in jet-type model airplanes and UAVs | |
CN108290611B (zh) | 车辆减阻和发电系统 | |
CN102428004B (zh) | 用于飞机冷却系统的冷却器、飞机冷却系统和飞机冷却系统的操作方法 | |
CN111065539A (zh) | 车辆减阻及发电系统 | |
CN221214636U (zh) | 一种无人机机体总成及无人机 | |
WO2022138115A1 (ja) | 飛行体 | |
CN205022881U (zh) | 具有动平衡系统的无人直升机 | |
CN113335388B (zh) | 一种可快速散热的低风阻汽车机舱盖板 | |
ES2949800T3 (es) | Sección del extremo trasero de una aeronave | |
EP4199247A1 (en) | Thermoelectric cooling assembly and method for thermally insulating an aircraft fuselage exterior from an aircraft antennae array | |
KR20050016643A (ko) | 덕트형 공기 동력 장치 | |
CN207099523U (zh) | 一种用于无人机电路板的无动力散热装置 | |
CN105217045A (zh) | 具有隔热罩的无人直升机 | |
SK492021U1 (sk) | Chladiace ústrojenstvo motora s tlačnou vrtuľou | |
KR20240052012A (ko) | 발전기의 열관리를 위한 시스템 | |
SK1652023A3 (sk) | Chladiace ústrojenstvo motora s tlačnou vrtuľou | |
JP2021130340A (ja) | 無人飛行体 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
GR01 | Patent grant | ||
GR01 | Patent grant |