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1. 发明授权

US07568660B2 Auxiliary fuel tank systems for aircraft and methods for their manufacture and use 有权
标题翻译：用于飞机的辅助燃料箱系统及其制造和使用方法
公开(公告)号：US07568660B2
公开(公告)日：2009-08-04
申请号：US11441492
申请日：2006-05-26
申请人： Mark E. Howe
发明人： Mark E. Howe
IPC分类号： B64D37/14
CPC分类号： B64D39/00 , B64D37/04 , Y10T137/4807 , Y10T137/86187
摘要： Auxiliary fuel tank systems for aircraft and methods for their manufacture and use. In one embodiment, an aircraft can include a fuselage, at least one engine, and a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold. The aircraft can further include an auxiliary fuel tank system operably coupled to the fuel system. The auxiliary fuel tank system can include a master tank assembly and at least one slave tank assembly. The master tank assembly can be removably installed in the fuselage, and can include a master tank body configured to hold fuel. The master tank body can be configured to pass through a door in the fuselage without disassembly. The slave tank assembly can be removably installed in the fuselage at least proximate to the master tank assembly, and can include a slave tank body configured to hold fuel.
摘要翻译：用于飞机的辅助燃料箱系统及其制造和使用方法。在一个实施例中，飞行器可以包括机身，至少一个发动机和配置成将燃料分配到发动机和空中加油歧管中的至少一个的燃料系统。飞机还可以包括可操作地连接到燃料系统的辅助燃料箱系统。辅助燃料箱系统可以包括主油箱组件和至少一个从油箱组件。主油箱组件可以可拆卸地安装在机身中，并且可以包括构造成保持燃料的主箱体。主罐体可以配置成通过机身的门而不拆卸。副油箱组件可以至少靠近主油箱组件可拆卸地安装在机身中，并且可以包括构造成保持燃料的副罐体。

2. 发明授权

US07083144B2 Apparatus and methods for support of propulsion systems interconnect members 有权
公开(公告)号：US07083144B2
公开(公告)日：2006-08-01
申请号：US10920802
申请日：2004-08-18
申请人： Mark E. Howe , George L. Huggins
发明人： Mark E. Howe , George L. Huggins
IPC分类号： B64D33/00
CPC分类号： B64D27/26 , B64D29/00
摘要： An apparatus for supporting an aircraft system interconnect member between a strut and an engine of the aircraft. The apparatus includes a disconnect panel near the engine through which the interconnect member is connected with the engine, and a support structure movably attached to the strut and that supports the interconnect member near the strut.

3. 发明授权

US07051979B2 Auxiliary fuel tank systems for aircraft and methods for their manufacture and use 有权
公开(公告)号：US07051979B2
公开(公告)日：2006-05-30
申请号：US10768267
申请日：2004-01-29
申请人： Mark E. Howe
发明人： Mark E. Howe
IPC分类号： B64C1/22 , B64D1/00
CPC分类号： B64D39/00 , B64D37/04 , Y10T137/4807 , Y10T137/86187
摘要： Auxiliary fuel tank systems for aircraft and methods for their manufacture and use. In one embodiment, an aircraft can include a fuselage, at least one engine, and a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold. The aircraft can further include an auxiliary fuel tank system operably coupled to the fuel system. The auxiliary fuel tank system can include a master tank assembly and at least one slave tank assembly. The master tank assembly can be removably installed in the fuselage, and can include a master tank body configured to hold fuel. The master tank body can be configured to pass through a door in the fuselage without disassembly. The slave tank assembly can be removably installed in the fuselage at least proximate to the master tank assembly, and can include a slave tank body configured to hold fuel.

4. 发明授权

US06889940B1 Auxiliary fuel tank systems for aircraft and methods for their manufacture and use 有权
标题翻译：用于飞机的辅助燃料箱系统及其制造和使用方法
公开(公告)号：US06889940B1
公开(公告)日：2005-05-10
申请号：US10768269
申请日：2004-01-29
申请人： Mark E. Howe
发明人： Mark E. Howe
IPC分类号： B64D37/04 , B64D39/00 , B64D37/00
CPC分类号： B64D37/04 , B64D39/00 , Y10T137/86228
摘要： Auxiliary fuel tank systems for aircraft and methods for their manufacture and use. In one embodiment, an aircraft can include a fuselage, at least one engine, and a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold. The aircraft can further include an auxiliary fuel tank system operably coupled to the fuel system. The auxiliary fuel tank system can include a master tank assembly and at least one slave tank assembly. The master tank assembly can be removably installed in the fuselage, and can include a master tank body configured to hold fuel. The master tank body can be configured to pass through a door in the fuselage without disassembly. The slave tank assembly can be removably installed in the fuselage at least proximate to the master tank assembly, and can include a slave tank body configured to hold fuel.
摘要翻译：用于飞机的辅助燃料箱系统及其制造和使用方法。在一个实施例中，飞行器可以包括机身，至少一个发动机和配置成将燃料分配到发动机和空中加油歧管中的至少一个的燃料系统。飞机还可以包括可操作地连接到燃料系统的辅助燃料箱系统。辅助燃料箱系统可以包括主油箱组件和至少一个从油箱组件。主油箱组件可以可拆卸地安装在机身中，并且可以包括构造成保持燃料的主箱体。主罐体可以配置成通过机身的门而不拆卸。副油箱组件可以至少靠近主油箱组件可拆卸地安装在机身中，并且可以包括构造成保持燃料的副罐体。

5. 发明申请

US20100126139A1 PIVOTING FAN NOZZLE NACELLE 有权
标题翻译：风扇喷嘴NACELLE
公开(公告)号：US20100126139A1
公开(公告)日：2010-05-27
申请号：US12323951
申请日：2008-11-26
申请人： Mark E. Howe
发明人： Mark E. Howe
IPC分类号： F02K3/02
CPC分类号： F02K3/04 , F02K1/1207 , F02K1/72 , F02K3/06 , Y02T50/671
摘要： A variable area nozzle system for a gas turbine engine includes a fan duct inner wall, a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall, and a fan nozzle. The fan nozzle defines at least a portion of the fan duct outer wall and includes a nozzle aft edge. The fan duct inner wall and the nozzle aft edge collectively define a fan duct nozzle throat area. The fan nozzle is configured to pivot about a pivot axis that may be oriented transversely relative to a longitudinal axis of the gas turbine engine. The fan nozzle may be pivoted from a stowed position to a deployed position in order to vary the fan duct nozzle throat area.
摘要翻译：用于燃气涡轮发动机的可变区域喷嘴系统包括风扇管道内壁，与风扇管道内壁以径向隔开的关系设置的风扇管道外壁和风扇喷嘴。风扇喷嘴限定了风扇管道外壁的至少一部分，并且包括喷嘴后边缘。风扇管道内壁和喷嘴后边缘共同定义了风扇管道喷嘴喉部区域。风扇喷嘴构造成围绕可相对于燃气涡轮发动机的纵向轴线横向定向的枢转轴线枢转。风扇喷嘴可以从收起位置枢转到展开位置，以便改变风扇管道喷嘴喉部区域。

6. 发明授权

US07357355B2 Auxiliary fuel tank systems for aircraft and methods for their manufacture and use 有权
公开(公告)号：US07357355B2
公开(公告)日：2008-04-15
申请号：US11429831
申请日：2006-05-08
申请人： Mark E. Howe
发明人： Mark E. Howe
IPC分类号： B64D37/04
CPC分类号： B64D37/04 , B64D39/00 , Y10T137/86228
摘要： Auxiliary fuel tank systems for aircraft and methods for their manufacture and use. In one embodiment, an aircraft can include a fuselage, at least one engine, and a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold. The aircraft can further include an auxiliary fuel tank system operably coupled to the fuel system. The auxiliary fuel tank system can include a master tank assembly and at least one slave tank assembly. The master tank assembly can be removably installed in the fuselage, and can include a master tank body configured to hold fuel. The master tank body can be configured to pass through a door in the fuselage without disassembly. The slave tank assembly can be removably installed in the fuselage at least proximate to the master tank assembly, and can include a slave tank body configured to hold fuel.

7. 发明授权

US08959889B2 Method of varying a fan duct nozzle throat area of a gas turbine engine 有权
标题翻译：改变燃气涡轮发动机的风扇管道喷嘴喉部区域的方法
公开(公告)号：US08959889B2
公开(公告)日：2015-02-24
申请号：US13360658
申请日：2012-01-27
申请人： Mark E. Howe
发明人： Mark E. Howe
IPC分类号： B63H11/00 , F02K3/02 , F02K1/00 , B63H11/10 , A63F13/30 , G07F17/32 , H04M1/725 , H04M1/02
CPC分类号： A63F13/12 , A63F2300/206 , A63F2300/406 , F02K1/09 , F02K1/11 , F02K1/1207 , F02K1/72 , F05D2260/96 , G07F17/32 , G07F17/3202 , G07F17/3218 , G07F17/3223 , G07F17/3232 , H04M1/0254 , H04M1/72527 , H04M1/72544 , Y02T50/671
摘要： A method of varying a fan duct nozzle throat area of a gas turbine engine includes pivoting a fan nozzle outwardly relative to a longitudinal axis of the gas turbine engine. The fan nozzle is configured to move axially non-contemporaneously with the pivoting of the fan nozzle.
摘要翻译：改变燃气涡轮发动机的风扇管道喷嘴喉部区域的方法包括相对于燃气涡轮发动机的纵向轴线向外转动风扇喷嘴。风扇喷嘴构造成与风扇喷嘴的枢转非同时轴向移动。

8. 发明申请

US20120124963A1 METHOD OF VARYING A FAN DUCT NOZZLE THROAT AREA OF A GAS TURBINE ENGINE 有权
标题翻译：改变燃气涡轮发动机风扇喷嘴的方法
公开(公告)号：US20120124963A1
公开(公告)日：2012-05-24
申请号：US13360658
申请日：2012-01-27
申请人： Mark E. Howe
发明人： Mark E. Howe
IPC分类号： F02K3/02
CPC分类号： A63F13/12 , A63F2300/206 , A63F2300/406 , F02K1/09 , F02K1/11 , F02K1/1207 , F02K1/72 , F05D2260/96 , G07F17/32 , G07F17/3202 , G07F17/3218 , G07F17/3223 , G07F17/3232 , H04M1/0254 , H04M1/72527 , H04M1/72544 , Y02T50/671
摘要： A method of varying a fan duct nozzle throat area of a gas turbine engine includes pivoting a fan nozzle outwardly relative to a longitudinal axis of the gas turbine engine. The fan nozzle is configured to move axially non-contemporaneously with the pivoting of the fan nozzle.
摘要翻译：改变燃气涡轮发动机的风扇管道喷嘴喉部区域的方法包括相对于燃气涡轮发动机的纵向轴线向外转动风扇喷嘴。风扇喷嘴构造成与风扇喷嘴的枢转非同时轴向移动。

9. 发明授权

US08127532B2 Pivoting fan nozzle nacelle 有权
标题翻译：旋转风扇喷嘴机舱
公开(公告)号：US08127532B2
公开(公告)日：2012-03-06
申请号：US12323951
申请日：2008-11-26
申请人： Mark E. Howe
发明人： Mark E. Howe
IPC分类号： F02K3/02
CPC分类号： F02K3/04 , F02K1/1207 , F02K1/72 , F02K3/06 , Y02T50/671
摘要： A variable area nozzle system for a gas turbine engine includes a fan duct inner wall, a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall, and a fan nozzle. The fan nozzle defines at least a portion of the fan duct outer wall and includes a nozzle aft edge. The fan duct inner wall and the nozzle aft edge collectively define a fan duct nozzle throat area. The fan nozzle is configured to pivot about a pivot axis that may be oriented transversely relative to a longitudinal axis of the gas turbine engine. The fan nozzle may be pivoted from a stowed position to a deployed position in order to vary the fan duct nozzle throat area.
摘要翻译：用于燃气涡轮发动机的可变区域喷嘴系统包括风扇管道内壁，与风扇管道内壁以径向隔开的关系设置的风扇管道外壁和风扇喷嘴。风扇喷嘴限定了风扇管道外壁的至少一部分，并且包括喷嘴后边缘。风扇管道内壁和喷嘴后边缘共同定义了风扇管道喷嘴喉部区域。风扇喷嘴构造成围绕可相对于燃气涡轮发动机的纵向轴线横向定向的枢转轴线枢转。风扇喷嘴可以从收起位置枢转到展开位置，以便改变风扇管道喷嘴喉部区域。

10. 发明授权

US07040579B2 Auxiliary fuel tank systems for aircraft and methods for their manufacture and use 失效
公开(公告)号：US07040579B2
公开(公告)日：2006-05-09
申请号：US11042731
申请日：2005-01-24
申请人： Mark E. Howe
发明人： Mark E. Howe
IPC分类号： B64D37/00
CPC分类号： B64D37/04 , B64D39/00 , Y10T137/86228
摘要： Auxiliary fuel tank systems for aircraft and methods for their manufacture and use. In one embodiment, an aircraft can include a fuselage, at least one engine, and a fuel system configured to distribute fuel to at least one of the engine and an aerial refueling manifold. The aircraft can further include an auxiliary fuel tank system operably coupled to the fuel system. The auxiliary fuel tank system can include a master tank assembly and at least one slave tank assembly. The master tank assembly can be removably installed in the fuselage, and can include a master tank body configured to hold fuel. The master tank body can be configured to pass through a door in the fuselage without disassembly. The slave tank assembly can be removably installed in the fuselage at least proximate to the master tank assembly, and can include a slave tank body configured to hold fuel.

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