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1. 发明授权

US07556223B2 Vent system for an aerospace vehicle 有权
标题翻译：航空航天器通风系统
公开(公告)号：US07556223B2
公开(公告)日：2009-07-07
申请号：US11566504
申请日：2006-12-04
申请人： Kurt E. Acheson , David S. Chambers , Brian S. Kornegay
发明人： Kurt E. Acheson , David S. Chambers , Brian S. Kornegay
IPC分类号： B64D37/00
CPC分类号： B64D37/10 , B64C1/1453 , B64D37/005 , Y02T50/44
摘要： An improved vent system for venting an internal cavity of an aerospace vehicle to an exterior surface of the aerospace vehicle generally includes a substantially concave vent inlet surface recessed with respect the exterior surface, and a duct opening formed therein. The vent inlet surface has a major axis substantially parallel to the local external flow direction. The upstream surface contour and the downstream surface contour of the vent inlet surface are substantially oblique to the local external flow direction. The placement and orientation of the duct opening, as well as the geometry of the vent inlet surface, may be selected to achieve a particular pressurization of the internal cavity with respect to the external environment under a variety of conditions.
摘要翻译：用于将航空航天车辆的内部空腔排放到航空航天车辆的外表面的改进的排气系统通常包括相对于外表面凹陷的基本上凹入的通气口入口表面和形成在其中的管道开口。排气入口表面具有基本上平行于局部外部流动方向的长轴。排气入口表面的上游表面轮廓和下游表面轮廓基本上与局部外部流动方向倾斜。可以选择管道开口的布置和取向以及排气入口表面的几何形状，以在各种条件下实现内腔相对于外部环境的特定加压。

2. 发明申请

US20080128557A1 VENT SYSTEM FOR AN AEROSPACE VEHICLE 有权
标题翻译：航空汽车的通风系统
公开(公告)号：US20080128557A1
公开(公告)日：2008-06-05
申请号：US11566504
申请日：2006-12-04
申请人： Kurt E. Acheson , David S. Chambers , Brian S. Kornegay
发明人： Kurt E. Acheson , David S. Chambers , Brian S. Kornegay
IPC分类号： B64D37/10
CPC分类号： B64D37/10 , B64C1/1453 , B64D37/005 , Y02T50/44
摘要： An improved vent system for venting an internal cavity of an aerospace vehicle to an exterior surface of the aerospace vehicle generally includes a substantially concave vent inlet surface recessed with respect the exterior surface, and a duct opening formed therein. The vent inlet surface has a major axis substantially parallel to the local external flow direction. The upstream surface contour and the downstream surface contour of the vent inlet surface are substantially oblique to the local external flow direction. The placement and orientation of the duct opening, as well as the geometry of the vent inlet surface, may be selected to achieve a particular pressurization of the internal cavity with respect to the external environment under a variety of conditions.
摘要翻译：用于将航空航天车辆的内部空腔排放到航空航天车辆的外表面的改进的排气系统通常包括相对于外表面凹陷的基本上凹入的通气口入口表面和形成在其中的管道开口。排气入口表面具有基本上平行于局部外部流动方向的长轴。排气入口表面的上游表面轮廓和下游表面轮廓基本上与局部外部流动方向倾斜。可以选择管道开口的布置和取向以及排气入口表面的几何形状，以在各种条件下实现内腔相对于外部环境的特定加压。

3. 发明授权

US07611093B2 Dual flow APU inlet and associated systems and methods 有权
标题翻译：双流APU入口及相关系统和方法
公开(公告)号：US07611093B2
公开(公告)日：2009-11-03
申请号：US11829497
申请日：2007-07-27
申请人： Thomas A. Campbell , David S. Chambers , Robert H. Willie , Charles W. Rust
发明人： Thomas A. Campbell , David S. Chambers , Robert H. Willie , Charles W. Rust
IPC分类号： B64D41/00
CPC分类号： F02C7/04 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F02C6/06 , F02C7/042 , Y02T50/44 , Y02T50/671 , Y10T137/0536
摘要： Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.
摘要翻译：公开了双流辅助动力单元（APU）入口及相关系统和方法。根据本发明的一个实施例的入口包括入口孔和分隔件，其定位在入口中并且定位成将入口的第一部分与入口的第二部分分开。第一部分可以被配置成联接到APU的发动机进气口，并且第二部分可被配置成将空气引导离开进气口。分隔器可以定位成将具有第一总压力水平和第一失真水平的空气引导到入口的第一部分，并且具有第二总压力水平和第二失真水平的直接空气到入口的第二部分。第一总压力水平可以大致等于或高于第二总压力水平，或者第二失真水平可以大致等于或高于第一失真水平，或两者。

4. 发明申请

US20080179466A1 Dual Flow APU Inlet and Associated Systems and Methods 有权
标题翻译：双流APU入口及相关系统和方法
公开(公告)号：US20080179466A1
公开(公告)日：2008-07-31
申请号：US11829497
申请日：2007-07-27
申请人： Thomas A. Campbell , David S. Chambers , Robert H. Willie , Charles W. Rust
发明人： Thomas A. Campbell , David S. Chambers , Robert H. Willie , Charles W. Rust
IPC分类号： B64D33/02 , F02C7/04
CPC分类号： F02C7/04 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F02C6/06 , F02C7/042 , Y02T50/44 , Y02T50/671 , Y10T137/0536
摘要： Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.
摘要翻译：公开了双流辅助动力单元（APU）入口及相关系统和方法。根据本发明的一个实施例的入口包括入口孔和分隔件，其定位在入口中并且定位成将入口的第一部分与入口的第二部分分开。第一部分可以被配置成联接到APU的发动机进气口，并且第二部分可被配置成将空气引导离开进气口。分隔器可以定位成将具有第一总压力水平和第一失真水平的空气引导到入口的第一部分，并且具有第二总压力水平和第二失真水平的直接空气到入口的第二部分。第一总压力水平可以大致等于或高于第二总压力水平，或者第二失真水平可以大致等于或高于第一失真水平，或两者。

5. 发明授权

US07344107B2 Dual flow APU inlet and associated systems and methods 有权
标题翻译：双流APU入口及相关系统和方法
公开(公告)号：US07344107B2
公开(公告)日：2008-03-18
申请号：US10974167
申请日：2004-10-26
申请人： Thomas A. Campbell , David S. Chambers , Robert H. Willie , Charles W. Rust
发明人： Thomas A. Campbell , David S. Chambers , Robert H. Willie , Charles W. Rust
IPC分类号： B64D41/00
CPC分类号： F02C7/04 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F02C6/06 , F02C7/042 , Y02T50/44 , Y02T50/671 , Y10T137/0536
摘要： Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.
摘要翻译：公开了双流辅助动力单元（APU）入口及相关系统和方法。根据本发明的一个实施例的入口包括入口孔和分隔件，其定位在入口中并且定位成将入口的第一部分与入口的第二部分分开。第一部分可以被配置成联接到APU的发动机进气口，并且第二部分可被配置成将空气引导离开进气口。分隔器可以定位成将具有第一总压力水平和第一失真水平的空气引导到入口的第一部分，并且具有第二总压力水平和第二失真水平的直接空气到入口的第二部分。第一总压力水平可以大致等于或高于第二总压力水平，或者第二失真水平可以大致等于或高于第一失真水平，或两者。

6. 发明授权

US06845943B2 Apparatuses and methods for preventing foreign object damage to aircraft engines 失效
标题翻译：防止飞机发动机异物损坏的装置和方法
公开(公告)号：US06845943B2
公开(公告)日：2005-01-25
申请号：US10690739
申请日：2003-10-20
申请人： David S. Chambers , Justin D. Cottet , David W. Foutch , Mark N. Simpson
发明人： David S. Chambers , Justin D. Cottet , David W. Foutch , Mark N. Simpson
IPC分类号： B64C7/00 , B64C25/16 , B64C25/32
CPC分类号： B64C25/16 , B64C7/00 , B64C25/32 , B64C2025/345
摘要： Apparatuses and methods for preventing foreign object damage (FOD) to aircraft engines are disclosed. In one embodiment, a deployable blocker is coupled to a wing portion and/or a fuselage portion of the aircraft and is configured to prevent debris from travelling on a direct trajectory from a landing gear wheel to an engine air inlet. In other embodiments, the blocker can prevent debris from bouncing off the wing lower surface into the engine inlet, or sticking to the wing lower surface and falling into the engine inlet. The deployable blocker can cover at least a portion of the landing gear when the landing gear is retracted and the blocker assembly stowed. In another embodiment, the blocker can be mounted to the landing gear.
摘要翻译：公开了用于防止飞机发动机的异物损坏（FOD）的装置和方法。在一个实施例中，可展开的阻挡器联接到飞行器的翼部和/或机身部分，并且被构造成防止碎片在从起落架齿轮到发动机空气入口的直接轨迹上行进。在其他实施例中，阻挡器可以防止碎片从机翼下表面弹出到发动机入口中，或者粘附到机翼下表面并落入发动机入口。当起落架缩回并且阻塞组件收起时，可展开的阻挡器可以覆盖起落架的至少一部分。在另一个实施例中，阻挡器可以安装到起落架上。

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