专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20170057618A1 SYNERGETIC NOISE ABSORPTION AND ANTI-ICING FOR AIRCRAFTS 审中-公开
标题翻译：用于航空器的协同噪声吸收和防御
公开(公告)号：US20170057618A1
公开(公告)日：2017-03-02
申请号：US14835659
申请日：2015-08-25
申请人： The Boeing Company
发明人： Vyacheslav Khozikov , Jesse I. Follet , Justin H. Lan , Eric H. Nesbitt
IPC分类号： B64C7/02 , B64D33/02 , B64D15/12 , H05B6/10 , H05B6/40
CPC分类号： B64C7/02 , B64D15/12 , B64D29/00 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , B64D2033/0286 , H05B6/101 , H05B6/40
摘要： Systems and methods are provided for an inductive coil anti-icing and noise absorption system. In certain versions, the inductive coil anti-icing and noise absorption system may include an inductive coil and a skin. The inductive coil may generate electromagnetic fields and may electromagnetically couple with the skin. The skin, upon electromagnetically coupling with the inductive coil, may increase in temperature and the increase in temperature may melt or prevent the formation of ice on the skin. The skin or a portion of the skin may be porous and may allow incorporation of a sound absorbing liner. The sound absorbing liner may attenuate noise generated by the aircraft (e.g., noise generated by the aircraft engine). Certain versions may include a plurality of inductive coils and a plurality of skins.
摘要翻译：为感应线圈防冰和噪声吸收系统提供了系统和方法。在某些版本中，感应线圈防冰和噪声吸收系统可以包括感应线圈和皮肤。感应线圈可以产生电磁场并且可以与皮肤电磁耦合。皮肤在与感应线圈电磁耦合时可能会增加温度，并且温度的升高可能会熔化或防止皮肤上形成冰。皮肤或皮肤的一部分可以是多孔的，并且可以允许结合吸音衬垫。吸音衬垫可以衰减飞行器产生的噪音（例如，飞机发动机产生的噪音）。某些版本可以包括多个感应线圈和多个皮肤。

2. 发明授权

US11964752B2 Acoustically treated landing gear door and method for reducing noise from landing gear of an aircraft 有权
公开(公告)号：US11964752B2
公开(公告)日：2024-04-23
申请号：US17726491
申请日：2022-04-21
申请人： The Boeing Company
发明人： Navid Daneshvaran , Justin H. Lan , Takao Suzuki , Deric A. Babcock , Jordan R. Kreitzman , Eric H. Nesbitt
IPC分类号： B64C25/00 , B64C25/16 , G10K11/168 , G10K11/20
CPC分类号： B64C25/001 , B64C25/16 , G10K11/168 , G10K11/20 , B64C2025/003
摘要： There is provided an acoustically treated landing gear door for reducing noise from a landing gear of an aircraft. The acoustically treated landing gear door includes a landing gear door for attachment to the aircraft. The landing gear door includes an acoustic treatment assembly integrated on an inner mold line of an interior side, and extending within an interior cavity of the landing gear door. The acoustic treatment assembly includes a core structure having a first side and a second side, a plurality of core cells extending between the first side and the second side, and a drainage system. The acoustic treatment assembly further includes an acoustic facesheet and a nonporous backsheet. The acoustically treated landing gear door reduces the noise from the landing gear, when the landing gear is in a deployed position, by attenuating acoustic waves emanating from the landing gear and reflected off the acoustic treatment assembly.

3. 发明授权

US10442523B2 Synergetic noise absorption and anti-icing for aircrafts 有权
公开(公告)号：US10442523B2
公开(公告)日：2019-10-15
申请号：US14835659
申请日：2015-08-25
申请人： The Boeing Company
发明人： Vyacheslav Khozikov , Jesse I. Follet , Justin H. Lan , Eric H. Nesbitt
IPC分类号： B64C7/02 , B64D15/12 , B64D29/00 , B64D33/02 , H05B6/10 , H05B6/40
摘要： Systems and methods are provided for an inductive coil anti-icing and noise absorption system. In certain versions, the inductive coil anti-icing and noise absorption system may include an inductive coil and a skin. The inductive coil may generate electromagnetic fields and may electromagnetically couple with the skin. The skin, upon electromagnetically coupling with the inductive coil, may increase in temperature and the increase in temperature may melt or prevent the formation of ice on the skin. The skin or a portion of the skin may be porous and may allow incorporation of a sound absorbing liner. The sound absorbing liner may attenuate noise generated by the aircraft (e.g., noise generated by the aircraft engine). Certain versions may include a plurality of inductive coils and a plurality of skins.

4. 发明申请

US20220380026A1 ACOUSTICALLY TREATED LANDING GEAR DOOR AND METHOD FOR REDUCING NOISE FROM LANDING GEAR OF AN AIRCRAFT 有权
公开(公告)号：US20220380026A1
公开(公告)日：2022-12-01
申请号：US17726491
申请日：2022-04-21
申请人： The Boeing Company
发明人： Navid Daneshvaran , Justin H. Lan , Takao Suzuki , Deric A. Babcock , Jordan R. Kreitzman , Eric H. Nesbitt
IPC分类号： B64C25/00 , B64C25/16 , G10K11/20 , G10K11/168
摘要： There is provided an acoustically treated landing gear door for reducing noise from a landing gear of an aircraft. The acoustically treated landing gear door includes a landing gear door for attachment to the aircraft. The landing gear door includes an acoustic treatment assembly integrated on an inner mold line of an interior side, and extending within an interior cavity of the landing gear door. The acoustic treatment assembly includes a core structure having a first side and a second side, a plurality of core cells extending between the first side and the second side, and a drainage system. The acoustic treatment assembly further includes an acoustic facesheet and a nonporous backsheet. The acoustically treated landing gear door reduces the noise from the landing gear, when the landing gear is in a deployed position, by attenuating acoustic waves emanating from the landing gear and reflected off the acoustic treatment assembly.

5. 发明授权

US10364035B2 Synergetic noise absorption and anti-icing for aircrafts 有权
公开(公告)号：US10364035B2
公开(公告)日：2019-07-30
申请号：US14835611
申请日：2015-08-25
申请人： The Boeing Company
发明人： Vyacheslav Khozikov , Jesse I. Follet , Justin H. Lan , Eric H. Nesbitt
IPC分类号： B64D15/14 , B64D15/12 , B64D29/00 , B64C21/10 , B64D15/20 , B64D33/02
摘要： Systems and methods are provided for an inductive coil anti-icing and noise absorption system. In certain versions, the inductive coil anti-icing and noise absorption system may include an inductive coil and a skin. The inductive coil may generate electromagnetic fields and may electromagnetically couple with the skin. The skin, upon electromagnetically coupling with the inductive coil, may increase in temperature and the increase in temperature may melt or prevent the formation of ice on the skin. The skin or a portion of the skin may be porous and may allow incorporation of a sound absorbing liner. The sound absorbing liner may attenuate noise generated by the aircraft (e.g., noise generated by the aircraft engine). Certain versions may include a plurality of inductive coils and a plurality of skins.

6. 发明授权

US09587563B2 Sound attenuation apparatus and method 有权
标题翻译：声衰减装置及方法
公开(公告)号：US09587563B2
公开(公告)日：2017-03-07
申请号：US14804867
申请日：2015-07-21
申请人： THE BOEING COMPANY
发明人： Eric H. Nesbitt , Justin H. Lan , Thonse R. S. Bhat , Charles W. Rust
IPC分类号： F01N1/24 , F02C7/24 , F02K1/34 , B64D41/00
CPC分类号： B64D33/06 , B64D41/00 , B64D2041/002 , F01N1/24 , F02C7/045 , F02C7/24 , F02K1/82 , F05D2220/50 , F05D2250/283 , G10K11/161 , G10K11/168
摘要： An aircraft auxiliary power unit sound attenuation apparatus includes a perforated body having a center aperture through which exhaust fluid passes, a backing member outwardly offset from the perforated body, a plurality of connecting members coupling the perforated body to the backing member to form a locally reacting sound attenuation member having a plurality of channels spanning outwardly from the perforated body to the backing member, and a bulk absorber disposed in each of the plurality of channels where the bulk absorber is in fluid communication with the exhaust fluid, where the locally reacting sound attenuation member is in fluid communication with an auxiliary power unit of an aircraft so that the plurality of channels are oriented in a direction crossing a pressure drop direction of an exhaust fluid flow passing through the center aperture and each channel circumscribes the center aperture.
摘要翻译：飞机辅助动力单元声音衰减装置包括具有中心孔的穿孔体，废气通过该中心孔，从穿孔体向外偏移的背衬构件，多个连接构件，其将穿孔体联接到背衬构件，以形成局部反应声衰减构件具有从穿孔体向外延伸到背衬构件的多个通道，以及散装吸收器，其设置在多个通道中的每个通道中，其中散装吸收器与排气流体流体连通，其中局部反应的声音衰减构件与飞行器的辅助动力单元流体连通，使得多个通道在与穿过中心孔的排气流体的压降方向交叉的方向上定向，并且每个通道限定中心孔。

7. 发明申请

US20170057644A1 SYNERGETIC NOISE ABSORPTION AND ANTI-ICING FOR AIRCRAFTS 审中-公开
公开(公告)号：US20170057644A1
公开(公告)日：2017-03-02
申请号：US14835611
申请日：2015-08-25
申请人： The Boeing Company
发明人： Vyacheslav Khozikov , Jesse I. Follet , Justin H. Lan , Eric H. Nesbitt
IPC分类号： B64D15/14 , B64D15/20 , B64C21/10
CPC分类号： B64D15/14 , B64C21/10 , B64D15/12 , B64D15/20 , B64D29/00 , B64D2033/0206 , B64D2033/0233 , B64D2033/0286
摘要： Systems and methods are provided for an inductive coil anti-icing and noise absorption system. In certain versions, the inductive coil anti-icing and noise absorption system may include an inductive coil and a skin. The inductive coil may generate electromagnetic fields and may electromagnetically couple with the skin. The skin, upon electromagnetically coupling with the inductive coil, may increase in temperature and the increase in temperature may melt or prevent the formation of ice on the skin. The skin or a portion of the skin may be porous and may allow incorporation of a sound absorbing liner. The sound absorbing liner may attenuate noise generated by the aircraft (e.g., noise generated by the aircraft engine). Certain versions may include a plurality of inductive coils and a plurality of skins.

8. 发明授权

US09963238B2 Sound attenuation apparatus and method 有权
公开(公告)号：US09963238B2
公开(公告)日：2018-05-08
申请号：US15400576
申请日：2017-01-06
申请人： THE BOEING COMPANY
发明人： Eric H. Nesbitt , Justin H. Lan , Thonse R. S. Bhat , Charles W. Rust
IPC分类号： G10K11/168 , F02K1/34 , B64D41/00 , G10K11/16
CPC分类号： B64D33/06 , B64D41/00 , B64D2041/002 , F01N1/24 , F02C7/045 , F02C7/24 , F02K1/82 , F05D2220/50 , F05D2250/283 , G10K11/161 , G10K11/168
摘要： An aircraft auxiliary power unit sound attenuation apparatus includes a perforated body having a center aperture through which exhaust fluid passes, a backing member outwardly offset from the perforated body, a plurality of connecting members coupling the perforated body to the backing member to form a locally reacting sound attenuation member having a plurality of channels spanning outwardly from the perforated body to the backing member, and a bulk absorber disposed in each of the plurality of channels where the bulk absorber is in fluid communication with the exhaust fluid, where the locally reacting sound attenuation member is in fluid communication with an auxiliary power unit of an aircraft so that the plurality of channels are oriented in a direction crossing a pressure drop direction of an exhaust fluid flow passing through the center aperture and each channel circumscribes the center aperture.

9. 发明授权

US09771868B2 Sound attenuation apparatus and method 有权
公开(公告)号：US09771868B2
公开(公告)日：2017-09-26
申请号：US14804577
申请日：2015-07-21
申请人： THE BOEING COMPANY
发明人： Eric H. Nesbitt , Justin H. Lan , Thonse R. S. Bhat , Charles W. Rust
IPC分类号： F02C7/045 , F02C7/24 , F02K1/34 , F02K1/82 , B64C1/40 , B64D29/02 , F01D25/24 , F02C7/00 , B64D29/08
CPC分类号： F02C7/24 , B64C1/40 , B64D29/02 , B64D29/08 , B64D33/06 , F01D25/24 , F02C7/045 , F02K1/827 , F05D2220/323 , F05D2250/283 , F05D2250/313 , F05D2260/962 , G10K11/168
摘要： An aircraft engine sound attenuation apparatus includes a perforated face member, a backing member, a plurality of connecting members coupling the perforated face member to the backing member to form a plurality of channels spanning from the perforated face member to the backing member, and a bulk absorber disposed in each of the plurality of channels, wherein the plurality of channels are connected to an interior portion of an aircraft engine nacelle component so that the plurality of channels are oriented in a direction substantially normal to a direction of fluid flow pressure drop passing through the aircraft engine.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式