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1. 发明授权

US08840058B2 Airfoil shaped tail boom 有权
标题翻译：翼型尾巴
公开(公告)号：US08840058B2
公开(公告)日：2014-09-23
申请号：US13554309
申请日：2012-07-20
申请人： Albert G. Brand , Jimmy Narramore , James H. Harse , Brendan P. Lanigan
发明人： Albert G. Brand , Jimmy Narramore , James H. Harse , Brendan P. Lanigan
IPC分类号： B64C27/82
CPC分类号： B64C27/82 , B64C2027/8245
摘要： A system and method to control fuselage torque of an aircraft. The system includes a tail boom having a first surface that creates a high-pressure region in a downward rotorwash and a second surface that creates a low-pressure region in the downward rotorwash. The difference in pressure regions creates a lateral force that opposes the fuselage torque.
摘要翻译：一种控制飞机机身扭矩的系统和方法。该系统包括具有在向下的转子洗涤物中产生高压区域的第一表面和在向下的转子清洗器中产生低压区域的第二表面的尾斗。压力区域的差异产生与机身扭矩相反的横向力。

2. 发明申请

US20060239824A1 Proprotor blade with leading edge slot 有权
标题翻译： Proprotor刀片带前缘槽
公开(公告)号：US20060239824A1
公开(公告)日：2006-10-26
申请号：US10543222
申请日：2003-01-23
申请人： Daniel Robertson , Dudley Smith , Charles Hollimon , Jimmy Narramore , B. Mullins
发明人： Daniel Robertson , Dudley Smith , Charles Hollimon , Jimmy Narramore , B. Mullins
IPC分类号： A23L3/18
CPC分类号： B64C11/16 , B64C27/467 , B64C29/0033
摘要： A proprotor blade (27a, 27b, 127a, 127b) having a fixed, spanwise, leading edge slot (215) located in at least the inboard portion of the proprotor is disclosed. The slot (215) is formed by a selectively shaped slat (217) disposed in a selectively shaped recessed area (219) located at the leading edge (202) of the main portion of the proprotor blade. The slot (215) is selectively shaped so the a portion of the airflow over the lower airfoil surface of the proprotor blade is diverted between the main portion of the proprotor blade and the slat (217) and exits at the upper airfoil surface of the proprotor blade. The present invention may be used on both military-type tiltrotor aircraft (11) and civilian-type tiltrotor aircraft (111) with only minor variations to accommodate the different shapes of the proprotor blades.
摘要翻译：公开了一种具有固定的，翼展方向的前缘槽（215）的推进器叶片（27a，27b，127a，127b），其位于至少在推进器的内侧部分中。狭槽215由位于驱动器叶片的主要部分的前缘（202）上的选择性形状的凹入区域（219）中的选择性地成形的板条（217）形成。狭槽215被选择成形，使得在推进器叶片的下翼面表面上的气流的一部分在推进器叶片的主要部分和板条（217）之间转向并在推进器的上部翼型表面处离开刀。本发明可以用于军用型倾转旋翼飞机（11）和民用型倾转旋翼飞机（111），只有微小的变化来适应不同形状的推进器叶片。

3. 发明授权

US08814078B2 Airfoil shaped tail boom 有权
标题翻译：翼型尾巴
公开(公告)号：US08814078B2
公开(公告)日：2014-08-26
申请号：US13703667
申请日：2010-09-20
申请人： Albert G. Brand , Jimmy Narramore , James H. Harse , Brendan P. Lanigan
发明人： Albert G. Brand , Jimmy Narramore , James H. Harse , Brendan P. Lanigan
IPC分类号： B64C27/00 , B64C27/82
CPC分类号： B64C27/82 , B64C2001/0045 , B64C2027/8245 , Y02T50/12
摘要： A tail boom adapted for counteracting a fuselage torque created by an engine carried by a fuselage of a rotary aircraft. The tail boom is positioned within the rotorwash from the rotary and includes a first side surface contoured to create a low-pressure region of an airfoil and a second opposing side surface contoured to create a high-pressure region of an airfoil. The pressure difference between the high-pressure region and the low-pressure region causes the tail boom to move towards the low-pressure region, resulting in a lateral force opposing the torque on the fuselage.
摘要翻译：适用于抵消由旋转飞机的机身承载的发动机产生的机身扭矩的尾部吊杆。尾杆位于旋转器内的转子洗涤器内，并且包括成形为翼型的低压区域的第一侧表面和成形为翼型的高压区域的第二相对侧表面。高压区域和低压区域之间的压力差导致尾臂朝向低压区域移动，导致与机身上的扭矩相反的横向力。

4. 发明申请

US20130087653A1 AIRFOIL SHAPED TAIL BOOM 有权
标题翻译： AIRFOIL形状的尾巴
公开(公告)号：US20130087653A1
公开(公告)日：2013-04-11
申请号：US13703667
申请日：2010-09-20
申请人： Albert G. Brand , Jimmy Narramore , James H. Harse , Brendan P. Lanigan
发明人： Albert G. Brand , Jimmy Narramore , James H. Harse , Brendan P. Lanigan
IPC分类号： B64C27/82
CPC分类号： B64C27/82 , B64C2001/0045 , B64C2027/8245 , Y02T50/12
摘要： A tail boom adapted for counteracting a fuselage torque created by an engine carried by a fuselage of a rotary aircraft. The tail boom is positioned within the rotorwash from the rotary and includes a first side surface contoured to create a low-pressure region of an airfoil and a second opposing side surface contoured to create a high-pressure region of an airfoil. The pressure difference between the high-pressure region and the low-pressure region causes the tail boom to move towards the low-pressure region, resulting in a lateral force opposing the torque on the fuselage.
摘要翻译：适用于抵消由旋转飞机的机身承载的发动机产生的机身扭矩的尾部吊杆。尾杆位于旋转器内的转子洗涤器内，并且包括成形为翼型的低压区域的第一侧表面和成形为翼型的高压区域的第二相对侧表面。高压区域和低压区域之间的压力差导致尾臂朝向低压区域移动，导致与机身上的扭矩相反的横向力。

5. 发明申请

US20070018056A1 Retractable vortex generator 有权
标题翻译：可伸缩涡流发生器
公开(公告)号：US20070018056A1
公开(公告)日：2007-01-25
申请号：US11477806
申请日：2006-06-30
申请人： Jimmy Narramore
发明人： Jimmy Narramore
IPC分类号： B64C21/10
CPC分类号： B64C23/06 , Y02T50/162
摘要： A flow control device is disclosed including a flow control surface over which fluid is designed to flow in a predetermined direction. Vortex generators are associated with the flow control surface. Each respective vortex generator has a pivot axis that forms an acute angle with respect to the predetermined direction and is capable of being positioned in both of an extended state, in which the respective vortex generators function to create a swirling fluid flow, and a retracted state, in which the respective vortex generators are pivoted via the pivot axis so as to lie adjacent to the flow control surface. An actuator is associated with each of the vortex generators, each actuator adapted to position the associated vortex generator between the extended and retracted states. The flow control device is disclosed to be used in tiltrotor vehicles.
摘要翻译：公开了一种流量控制装置，其包括流动控制表面，流体被设计成沿预定方向流动。涡流发生器与流量控制表面相关联。每个相应的涡流发生器具有相对于预定方向形成锐角的枢转轴线，并且能够被定位在两个扩展状态中，其中相应的涡流发生器用于产生旋转流体流，并且缩回状态，其中相应的涡流发生器经由枢转轴线枢转，以便邻近流动控制表面。致动器与每个涡流发生器相关联，每个致动器适于将相关联的涡流发生器定位在延伸状态和缩回状态之间。流量控制装置被公开用于倾斜转向器车辆中。

6. 发明申请

US20120280079A1 Airfoil Shaped Tail Boom 有权
标题翻译：翼型形尾长臂
公开(公告)号：US20120280079A1
公开(公告)日：2012-11-08
申请号：US13554309
申请日：2012-07-20
申请人： Albert G. Brand , Jimmy Narramore , James H. Harse , Brendan P. Lanigan
发明人： Albert G. Brand , Jimmy Narramore , James H. Harse , Brendan P. Lanigan
IPC分类号： B64C9/00 , B64C27/82 , B64C27/04
CPC分类号： B64C27/82 , B64C2027/8245
摘要： A system and method to control fuselage torque of an aircraft. The system includes a tail boom having a first surface that creates a high-pressure region in a downward rotorwash and a second surface that creates a low-pressure region in the downward rotorwash. The difference in pressure regions creates a lateral force that opposes the fuselage torque.
摘要翻译：一种控制飞机机身扭矩的系统和方法。该系统包括具有在向下的转子洗涤物中产生高压区域的第一表面和在向下的转子清洗器中产生低压区域的第二表面的尾斗。压力区域的差异产生与机身扭矩相反的横向力。

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