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1.发明申请AEROFOIL ACCESSORIES AND METHOD FOR MODIFYING THE GEOMETRY OF A WING ELEMENT 审中-公开AEROFOIL附件和修改元件几何的方法公开(公告)号：US20110163205A1
公开(公告)日：2011-07-07
申请号：US13119315
申请日：2009-09-16
申请人： Michael Shepshelovich , Alex Nagel , Danny Abramov
发明人： Michael Shepshelovich , Alex Nagel , Danny Abramov
IPC分类号： B64C3/44
CPC分类号： B64C3/48 , B64C3/14 , B64C3/44 , B64C2003/142 , B64C2003/148 , Y02T50/12 , Y02T50/14
摘要： Aerofoil accessories are provided, configured for selective attachment to a wing element, the wing element having an outer facing aerofoil surface and being based on at least one datum aerofoil section. Each accessory provides a modified geometric profile to a datum profile of the at least one aerofoil section when attached to the wing element. The accessories are each configured for having a substantially fixed geometric profile with respect to the at least one datum aerofoil section at least whenever said wing element is airborne with the respective accessory attached to the wing element. The modified geometric profile is such as to provide said wing element with the accessory attached thereto with a desired change in performance relative to a datum performance provided by the wing element absent the accessory. A kit is also provided for enhancing performance of a wing element in off-design conditions. A method is also provided for enhancing performance of a wing element in adverse conditions.
摘要翻译： 翼型件附件被设置成用于选择性地附接到翼元件，翼元件具有外表面的翼面，并且基于至少一个基准翼型部分。 当附接到翼元件时，每个附件提供至少一个机翼部分的基准轮廓的改进的几何轮廓。 至少每当所述机翼元件与相应的附件附接到机翼元件上空时，附件被配置为相对于至少一个基准翼型部具有基本上固定的几何轮廓。 改进的几何轮廓是为了使所述翼元件具有附接到其上的附件，其具有相对于没有附件的机翼元件提供的基准性能的期望性能变化。 还提供了一个套件，用于在非设计条件下增强机翼元件的性能。 还提供了用于在不利条件下增强机翼元件的性能的方法。
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公开(公告)号：US10144499B2
公开(公告)日：2018-12-04
申请号：US13119315
申请日：2009-09-16
申请人： Michael Shepshelovich , Alex Nagel , Danny Abramov
发明人： Michael Shepshelovich , Alex Nagel , Danny Abramov
摘要： Aerofoil accessories are provided, configured for selective attachment to a wing element, the wing element having an outer facing aerofoil surface and being based on at least one datum aerofoil section. Each accessory provides a modified geometric profile to a datum profile of the at least one aerofoil section when attached to the wing element. The accessories are each configured for having a substantially fixed geometric profile with respect to the at least one datum aerofoil section at least whenever said wing element is airborne with the respective accessory attached to the wing element. The modified geometric profile is such as to provide said wing element with the accessory attached thereto with a desired change in performance relative to a datum performance provided by the wing element absent the accessory. A kit is also provided for enhancing performance of a wing element in off-design conditions. A method is also provided for enhancing performance of a wing element in adverse conditions.
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公开(公告)号：US09561844B2
公开(公告)日：2017-02-07
申请号：US13552263
申请日：2012-07-18
摘要： A method for providing a controllable side force to an air vehicle having a vertical stabilizer arrangement includes (a) selectively causing the vertical stabilizer arrangement to generate a first side force in a first side direction to provide the controllable side force, the first side force inducing a corresponding first yaw moment in a first yaw direction; and (b) selectively providing to the air vehicle a second yaw moment in a second yaw direction, the second yaw moment being induced by a force component of an auxiliary force applied to the air vehicle, the force component being in a force direction that is non-parallel with respect to the first side direction and the force component being spaced from a center of gravity of the air vehicle; wherein the second yaw direction is opposed to the first yaw direction. Also disclosed is a corresponding auxiliary yaw generating system.
摘要翻译： 一种用于向具有垂直稳定器装置的机动车辆提供可控侧力的方法包括：（a）选择性地使垂直稳定器装置在第一侧方向上产生第一侧力以提供可控的侧向力，第一侧向力 在第一偏转方向上相应的第一横摆力矩; 以及（b）选择性地向所述空中交通工具提供在第二偏转方向上的第二横摆力矩，所述第二横摆力矩由施加到所述空中车辆的辅助力的力分量感应，所述力分量处于 相对于第一侧方向不平行，并且力分量与空中交通工具的重心间隔开; 其中所述第二偏转方向与所述第一偏转方向相对。 还公开了相应的辅助偏航产生系统。
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4.发明授权公开(公告)号：US08763959B2
公开(公告)日：2014-07-01
申请号：US13119319
申请日：2009-09-16
CPC分类号： B64C3/48 , B64C3/14 , B64C3/44 , B64C2003/142 , B64C2003/148 , Y02T50/12 , Y02T50/14
摘要： A two element aerofoil, and wing element based thereon, is provided, including a primary aerofoil element including a leading edge of the aerofoil and a secondary aerofoil element including a trailing edge of the aerofoil. A gap is provided between the primary aerofoil element and the secondary aerofoil element. The primary aerofoil element has at least one of a profile, orientation and location with respect to a respective at least one of a profile, orientation and location of the secondary aerofoil element that is configured for minimizing or avoiding accretion of contaminant on the secondary aerofoil element when subjected to an airflow that includes the contaminant, at least at one design set of conditions. A method for designing a two element aerofoil is also provided.
摘要翻译： 提供了一种两元件机翼和基于此的翼元件，其包括包括机翼的前缘的主要翼型元件和包括机翼后缘的次级机翼元件。 在主翼型元件和次级机翼元件之间提供间隙。 主翼面元件具有相对于次级翼型元件的轮廓，取向和位置中的相应的至少一个的轮廓，取向和位置中的至少一个，其被配置为最小化或避免在次级翼型元件上的污染物的增加 当受到包含污染物的气流时，至少在一个设计的条件下。 还提供了一种用于设计两元件机翼的方法。
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公开(公告)号：US20110168850A1
公开(公告)日：2011-07-14
申请号：US13119319
申请日：2009-09-16
CPC分类号： B64C3/48 , B64C3/14 , B64C3/44 , B64C2003/142 , B64C2003/148 , Y02T50/12 , Y02T50/14
摘要： A two element aerofoil, and wing element based thereon, is provided, including a primary aerofoil element including a leading edge of the aerofoil and a secondary aerofoil element including a trailing edge of the aerofoil. A gap is provided between the primary aerofoil element and the secondary aerofoil element. The primary aerofoil element has at least one of a profile, orientation and location with respect to a respective at least one of a profile, orientation and location of the secondary aerofoil element that is configured for minimizing or avoiding accretion of contaminant on the secondary aerofoil element when subjected to an airflow that includes the contaminant, at least at one design set of conditions. A method for designing a two element aerofoil is also provided.
摘要翻译： 提供了一种两元件机翼和基于此的翼元件，其包括包括机翼的前缘的主要翼型元件和包括机翼后缘的次级机翼元件。 在主翼型元件和次级机翼元件之间提供间隙。 主翼面元件具有相对于次级翼型元件的轮廓，取向和位置中的相应的至少一个的轮廓，取向和位置中的至少一个，其被配置为最小化或避免在次级翼型元件上的污染物的增加 当受到包含污染物的气流时，至少在一个设计的条件下。 还提供了一种用于设计两元件机翼的方法。
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公开(公告)号：US07992827B2
公开(公告)日：2011-08-09
申请号：US11802139
申请日：2007-05-21
申请人： Michael Shepshelovich , Alex Nagel
发明人： Michael Shepshelovich , Alex Nagel
摘要： A wing for an aircraft is provided, including at least a first wing portion configured for providing high-lift mild stall characteristics at least at Reynolds numbers in the range between about 0.3*106 and about 2.0*106, and at least a second wing portion comprising a substantially permanently slotted aerofoil arrangement. Also provided are an air vehicle including such wings, a method for operating an aircraft, and a method for designing an aircraft wing.
摘要翻译： 提供了一种用于飞行器的机翼，包括至少第一翼部分，其构造成用于至少在大约0.3×10 -6和大约2.0×10 6之间的范围内提供高升力轻度失速特性，以及至少第二翼部分 包括基本上永久开槽的翼型装置。 还提供了包括这种翼的飞行器，用于操作飞行器的方法以及用于设计飞机机翼的方法。
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公开(公告)号：US20070029440A1
公开(公告)日：2007-02-08
申请号：US10573570
申请日：2004-07-22
CPC分类号： B64D15/163 , B64C39/028 , B64C2201/028 , B64C2201/104 , B64C2201/165
摘要： An aircraft arrangement for Mini or Micro UAV comprising a fore wing (14) and an aft wing (12) in tandem closed-coupled arrangement. The aft wing (12) has side panels (18) and control surfaces (19), and tapered planform with positive sweep, while the fore wing (14) has non-positive trailing edge sweep. The fore wing (14) and the aft wing (12) are disposed at different height, and the aircraft arrangement has no other wings or tail arrangements.
摘要翻译： 一种用于迷你或微型无人机的飞行器装置，其包括串联闭合联接装置的前翼（14）和后翼（12）。 后翼（12）具有侧板（18）和控制表面（19），并且具有正扫掠的锥形平面，而前翼（14）具有非正的后缘扫掠。 前翼（14）和后翼（12）设置在不同的高度，并且飞行器装置没有其他翼或尾翼装置。
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公开(公告)号：US08113462B2
公开(公告)日：2012-02-14
申请号：US12007079
申请日：2008-01-07
IPC分类号： B64C3/14
CPC分类号： B64C3/14 , B64C2003/146 , Y02T50/12
摘要： The invention relates to an aircraft, and a method for operating an aircraft, the aircraft having a longitudinally unstable configuration and swept wings, the swept wings being based on aerofoils having a leading edge and configured for preventing attachment line transition in conditions of laminar flow over the swept wing for at least a predetermined first range of lift coefficients at a second range of Reynolds numbers. The invention also relates to an aerofoil, and to a method for providing an aerofoil, the airfoil being configured for a thick-sectioned subsonic/transonic swept wing, having a curved leading edge, a trailing edge, a thickness dimension and a chord dimension, wherein the leading edge comprises a leading edge curvature associated with a leading edge radius that is configured for preventing attachment line transition in conditions of laminar flow over the swept wing.
摘要翻译： 本发明涉及一种飞行器以及一种用于操作飞行器的方法，该飞行器具有纵向不稳定的构型和扫掠翼，该扫掠翼基于具有前缘的机翼，并被构造用于防止在层流状态下的连接线转换 所述扫掠翼在雷诺数的第二范围处至少提供预定的升力系数的第一范围。 本发明还涉及一种机翼，以及一种用于提供机翼的方法，所述翼型件被配置用于具有弯曲前缘，后缘，厚度尺寸和弦弦尺寸的厚切片亚音速/跨音速扫掠翼， 其中所述前缘包括与前缘半径相关联的前缘曲率，所述前缘半径被构造成用于防止在所述扫掠翼上层流的条件下的附着线转换。
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公开(公告)号：US20070278353A1
公开(公告)日：2007-12-06
申请号：US11802139
申请日：2007-05-21
申请人： Michael Shepshelovich , Alex Nagel
发明人： Michael Shepshelovich , Alex Nagel
IPC分类号： B64C3/50
摘要： A wing for an aircraft is provided, including at least a first wing portion configured for providing high-lift mild stall characteristics at least at Reynolds numbers in the range between about 0.3*106 and about 2.0*106, and at least a second wing portion comprising a substantially permanently slotted aerofoil arrangement. Also provided are an air vehicle including such wings, a method for operating an aircraft, and a method for designing an aircraft wing.
摘要翻译： 提供了一种用于飞机的机翼，包括至少第一翼部分，其构造成用于提供至少在约0.3×10 -6至约2.0×10 10范围内的雷诺数处的高升力轻度失速特性 以及至少第二翼部分，其包括基本上永久开槽的翼型装置。 还提供了包括这种翼的飞行器，用于操作飞行器的方法以及用于设计飞机机翼的方法。
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公开(公告)号：US20060226283A1
公开(公告)日：2006-10-12
申请号：US11305345
申请日：2005-12-19
IPC分类号： B64C3/14
摘要： A hybrid transonic-subsonic airfoil is provided that combines subsonic and transonic features for achieving simultaneously acceptable aerodynamic characteristics at low subsonic and high transonic Mach numbers.
摘要翻译： 提供了混合的跨音速亚音速翼型，其组合亚音速和跨音速特征，以在低亚音速和高跨音速马赫数下实现同时可接受的空气动力特性。
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