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公开(公告)号：US06663047B1
公开(公告)日：2003-12-16
申请号：US10251596
申请日：2002-09-20
申请人： Allen A. Arata
发明人： Allen A. Arata
IPC分类号： B64D106
摘要： There is provided an aircraft which can minimize its radar signature emission. Such aircraft comprises a fuselage having a lower fuselage portion. An internal fuselage cavity is defined within the lower fuselage portion and contains all landing gears and bombs therein. Moreover, a cavity-enclosing door is engaged to the lower fuselage portion. This specific cavity-enclosing door may form a closed position relative to the internal fuselage cavity to enclose all of the landing gears and bombs therein. In this respect, enclosure of all of the landing gears and bombs solely through the cavity-enclosing door may minimize the radar signature emission from the fuselage.
摘要翻译： 提供了可以最小化其雷达签名发射的飞机。 这种飞机包括具有较低机身部分的机身。 内部机身腔体定义在下部机身部分内，并包含所有起落架和炸弹。 此外，空腔封闭的门与下部机身部分接合。 该特定的空腔封闭门可以相对于内部机身腔形成闭合位置，以将所有起落架和炸弹封闭在其中。 在这方面，所有起落架和炸弹的封闭只能通过空腔封闭的门，可以最大程度地减少机身的雷达签名发射。
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公开(公告)号：US09975623B2
公开(公告)日：2018-05-22
申请号：US15064366
申请日：2016-03-08
申请人： Allen A. Arata
发明人： Allen A. Arata
CPC分类号： B64C9/02 , B64C3/48 , B64C7/00 , B64C2003/445
摘要： An elastomeric transition for spanning a gap between first and second surfaces on an aircraft includes an elastomeric skin. A first skin edge is configured for attachment to the first surface and a second skin edge is configured for attachment to the second surface. The elastomeric skin has a longitudinal dimension, coincident with the gap, which is significantly longer than a distance between laterally corresponding points on the first and second skin edges. At least one continuous rod is coupled at one end to a selected first point on the first surface and at another end to a selected second point, spaced apart from the first point, on the second surface. The at least one continuous rod is configured in the elastomeric transition to run along the gap such that the rod extends at an acute angle in relation to both the first and second skin edges.
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公开(公告)号：US07216835B2
公开(公告)日：2007-05-15
申请号：US11066341
申请日：2005-02-25
申请人： Allen A. Arata
发明人： Allen A. Arata
IPC分类号： B64C3/50
摘要： An extendable leading edge for the fuselage and wings of an aircraft is disclosed. The leading edge may be extended from a retracted position adjacent to the fuselage and wings to an extended position. In the extended position, the leading edge increases lift of the aircraft at low speeds. In the retracted position, gaps associated with the leading edge are avoided.
摘要翻译： 公开了用于飞机机身和机翼的可延伸前缘。 前缘可以从与机身和机翼相邻的缩回位置延伸到延伸位置。 在延伸位置，前缘在低速下增加了飞机的升力。 在缩回位置，避免了与前缘相关联的间隙。
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公开(公告)号：US10604233B2
公开(公告)日：2020-03-31
申请号：US15804773
申请日：2017-11-06
申请人： Allen A. Arata
发明人： Allen A. Arata
摘要： A propeller for an aircraft having a fuselage and a pair of fixed wings includes a mounting member secured to at least one wing. At least one blade is rotatably connected to each mounting member and has an airfoil shape. The at least one blade is in a locked condition during take-off and landing of the aircraft extending parallel to a leading edge of the wing and in an unlocked, rotating condition during flight for propelling the aircraft.
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5.发明授权Rechargeable compressed air system and method for supplemental aircraft thrust 有权充气压缩空气系统及补充飞机推力的方法公开(公告)号：US07104499B1
公开(公告)日：2006-09-12
申请号：US10255766
申请日：2002-09-25
申请人： Allen A. Arata
发明人： Allen A. Arata
IPC分类号： B64D41/00
CPC分类号： B64D27/02 , B64C9/38 , B64C15/02 , B64C15/14 , B64C2027/8245
摘要： A system for providing aircraft thrust includes a compressor, operable to take in a quantity of air, reduce the volume of the air to generate compressed air, and to deliver the compressed air to a tank. The tank is coupled to the compressor and is operable to receive the compressed air, store the compressed air, and deliver the compressed air to a nozzle mounted externally to the aircraft. The nozzle is operable to receive the compressed air and discharge the compressed air to provide thrust for the aircraft.
摘要翻译： 用于提供飞机推力的系统包括可操作地吸入大量空气的压缩机，减少空气的体积以产生压缩空气，并将压缩空气输送到罐。 罐与压缩机相连，可操作以接收压缩空气，储存压缩空气，并将压缩空气输送到安装在飞机外部的喷嘴。 喷嘴可操作以接收压缩空气并排出压缩空气以为飞机提供推力。
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公开(公告)号：USD475340S1
公开(公告)日：2003-06-03
申请号：US29164504
申请日：2002-07-25
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公开(公告)号：US07887298B2
公开(公告)日：2011-02-15
申请号：US11165655
申请日：2005-06-24
申请人： Allen A. Arata
发明人： Allen A. Arata
摘要： A helicopter rotor assembly with vertically staggered blades is disclosed. Each blade travels in a rotational path which does not cross the rotational paths of the other blades. This arrangement reduces noise because each blade travels in a path which avoids turbulent or disturbed air from the preceding blades. In one embodiment, the blades are arranged from the lowermost blade to the uppermost blade such that each blade following the lowermost blade will be above the blade in front of it. Since each blade pushes air down to create lift, this vertically staggered arrangement allows the blades to travel through less disturbed air.
摘要翻译： 公开了一种具有垂直交错叶片的直升机转子组件。 每个叶片在不与其他叶片的旋转路径交叉的旋转路径中行进。 这种布置降低了噪音，因为每个叶片在避开前述叶片的湍流或干扰的空气的路径中行进。 在一个实施例中，叶片从最下面的叶片布置到最上面的叶片，使得跟随最低叶片的每个叶片将在其前面的叶片的上方。 由于每个叶片将空气向下推动以产生升力，所以这种垂直交错布置允许叶片通过较少扰动的空气行进。
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公开(公告)号：US07137589B2
公开(公告)日：2006-11-21
申请号：US11045700
申请日：2005-01-28
申请人： Allen A. Arata
发明人： Allen A. Arata
IPC分类号： B64C27/26
CPC分类号： B64C27/26 , B64C2025/325
摘要： The invention is a helicopter that includes a fuselage with a longitudinal axis, a main rotor and tail rotor; and right and left wings mounted to said fuselage. The right and left wings having at least a portion of which are rotatable from a horizontal position wherein they produce lift in forward flight, to an at least partially downward position wherein they act as landing struts.
摘要翻译： 本发明是一种直升机，其包括具有纵向轴线的机身，主转子和尾部转子; 右翼和左翼安装在机身上。 右翼和左翼具有至少一部分可从水平位置旋转，其中它们在向前飞行中产生升力，至少部分地向下位置，其中它们用作着陆支柱。
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公开(公告)号：US06227498B1
公开(公告)日：2001-05-08
申请号：US09311072
申请日：1999-05-13
申请人： Allen A. Arata
发明人： Allen A. Arata
IPC分类号： B64C344
摘要： In accordance with the present invention, there is provided an aerodynamic control device for integrated use with an aircraft having an inboard lifting member. The inboard lifting member having a leading edge, a pair of opposing distal edges and a trailing edge. The control device is provided with a movable outboard member which extends substantially about the leading, distal and trailing edges of the inboard lifting member and is spaced apart therefrom. The outboard member is provided with a leading edge portion, a pair of opposing distal edge portions, and a trailing edge portion. The leading, distal, and trailing edge portions are movable in relation to the inboard lifting member to form an airfoil surface extending about the inboard lifting member and the outboard member for achieving aerodynamic control of the aircraft. The trailing edge portion has at least one deflectable segment which is vertically movable in relation to the leading and distal edge portions for achieving further aerodynamic control of the aircraft.
摘要翻译： 根据本发明，提供了一种用于与具有内侧提升构件的飞机一体使用的空气动力学控制装置。 内侧提升构件具有前缘，一对相对的远侧边缘和后缘。 控制装置设置有可移动的外侧构件，其基本上围绕内侧提升构件的前端，远端和后缘延伸并与其间隔开。 外侧构件设置有前缘部分，一对相对的远侧边缘部分和后缘部分。 前缘，远端和后缘部分可相对于内侧提升构件移动，以形成围绕内侧提升构件和外侧构件延伸的翼型表面，以实现飞机的空气动力学控制。 后缘部分具有至少一个相对于前缘和远端边缘部分垂直移动的可偏转节段，用于实现飞行器的进一步的空气动力学控制。
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公开(公告)号：US6116540A
公开(公告)日：2000-09-12
申请号：US310405
申请日：1999-05-12
申请人： Allen A. Arata
发明人： Allen A. Arata
摘要： In accordance with the present invention, there is provided a low observable aerodynamic control system for integrated use with an aircraft fuselage. The control system is provided with a shadow structure having an inner sloping region and an outer sloping region. The inner sloping region defines a shadow structure concavity. The outer sloping region is attachable to the aircraft fuselage. The control system is further provided with an aerodynamic control device having a body portion and a base portion. The base portion is disposed within the shadow structure concavity. The body portion extends from the base portion beyond the shadow structure concavity.
摘要翻译： 根据本发明，提供了一种用于与飞行器机身一体使用的低可观察的空气动力学控制系统。 该控制系统设置有具有内倾斜区域和外倾斜区域的阴影结构。 内部倾斜区域限定阴影结构凹面。 外倾斜区域可附着在飞机机身上。 该控制系统还设置有具有主体部分和基部的空气动力学控制装置。 基部设置在阴影结构凹部内。 主体部分从基部延伸超过阴影结构凹部。
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