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公开(公告)号：WO2009132090A1
公开(公告)日：2009-10-29
申请号：PCT/US2009/041391
申请日：2009-04-22
Applicant: KAREM, Abe
Inventor： KAREM, Abe
IPC: B64C27/02
CPC classification number: B64C27/37 , B64C29/0033
Abstract: A rotorcraft is equipped with a rotor hub of large diameter in order to accommodate high loads from a hingeless rotor. In preferred embodiments, a rotorcraft has a rotor disposed on a mast with blades attached to a hub by means of a feather bearing that receives a shank of a blade. The hub is attached to non-rotating structure such as a tilting nacelle by means of a hub bearing. This facilitates the transfer of moments generated on the rotor to the airframe. The hub and feather bearings can be sized and arranged such that a feather bearing on a hub is disposed within an imaginary cylinder centered at a rotational axis of the hub and having a diameter no greater 1.2 times an inner diameter of the hub bearing. This can result in a large diameter hub and hub bearing capable of withstanding very large bending moments.
Abstract translation: 旋翼航空器配备有大直径的转子轮毂，以适应来自无铰链转子的高负载。 在优选实施例中，旋翼航空器具有设置在桅杆上的转子，其具有通过容纳叶片柄的羽毛轴承附接到轮毂的叶片。 轮毂通过轮毂轴承连接到诸如倾斜机舱的非旋转结构。 这有助于将转子上产生的力矩传递到机身。 轮毂轴承和羽毛轴承的尺寸和布置应使得毂上的羽毛轴承设置在以轮毂的旋转轴线为中心的假想圆柱体内，其直径不大于轮毂轴承的内径的1.2倍。 这可能导致能够承受非常大的弯矩的大直径轮毂和轮毂轴承。
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公开(公告)号：WO2009032195A1
公开(公告)日：2009-03-12
申请号：PCT/US2008/010251
申请日：2008-08-28
Applicant: KAREM, Abe
Inventor： KAREM, Abe
IPC: B64C11/24
CPC classification number: F01D5/147 , B29C33/505 , B29C70/342 , B29D99/0028 , B29L2031/08 , F03D1/0675 , F05B2230/40 , F05B2280/6003 , F05B2280/6013 , F05B2280/6015 , F05D2230/40 , F05D2300/44 , F05D2300/603 , F05D2300/614 , Y02E10/721 , Y02P70/523 , Y02T50/672 , Y10S264/57 , Y10S264/59
Abstract: Composite structures with internal cavities are constructed with relatively stiff walls that can support additional composite laminate layers, creating a self-tooling structure. The structure is subsequently simulcured, preferably in combination with elevated temperatures or pressures. Preferred structures are long and slender, and are constructed with one or more internal cells. Rotor blades are especially suited to the preferred construction methods. The walls can be advantageously constructed using composite sandwich panels, having an exterior laminate layer. In preferred embodiments, additional composite layers can be added before or after the simulcuring process.
Abstract translation: 具有内部空腔的复合结构被构造成具有相对刚硬的壁，其可以支撑附加的复合层压层，从而产生自动加工结构。 随后模拟该结构，优选结合升高的温度或压力。 优选的结构是长而细长的，并且由一个或多个内部电池构成。 转子叶片特别适用于优选的施工方法。 可以使用具有外部层压层的复合夹层板有利地构造壁。 在优选实施例中，可以在模拟过程之前或之后添加额外的复合层。
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公开(公告)号：WO2008091300A2
公开(公告)日：2008-07-31
申请号：PCT/US2007/018007
申请日：2007-08-13
Applicant: KAREM, Abe
Inventor： KAREM, Abe
IPC: B64C29/02
CPC classification number: B64C29/0033
Abstract: Tilt-rotor aircraft experience increased efficiency and fuel economy by including wing extensions outboard of the tilting nacelles. Stall and buffeting during conversion from rotor-born hover to wing-born forward flight are reduced to an acceptable level using wide chord flaps deflected upwards by at least 15-20°, preferably in combination with leading edge slats. The outboard wing or wing portion is preferably has a span at least 25-40% of a span of the inboard section, and a total surface area at least 10-20% the total surface area of the corresponding inboard section.
Abstract translation: 倾斜转子飞机通过在机舱的外侧包括机翼延伸器来提高效率和燃油经济性。 从转子出生的悬停转向机翼向前飞行的转换期间的失速和缓冲减少到可接受的水平，使用向上偏转至少15-20°的宽弦襟翼，优选与前缘板条组合。 外侧翼或翼部优选具有内侧部分的跨度的至少25-40％的跨度，并且总表面积至少为相应内侧部分的总表面积的10-20％。
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公开(公告)号：WO2013022970A1
公开(公告)日：2013-02-14
申请号：PCT/US2012/049993
申请日：2012-08-08
Applicant: KAREM, Abe
Inventor： KAREM, Abe
IPC: B64C3/56
Abstract: An aircraft wing is equipped with asymmetric wing folding hinges to achieve a highly compact folded footprint. One or more of the hinges is advantageously placed at angle with respect to an aircraft centerplane such that the wing tips can fold over the centerplane without touching each other. Preferred aircraft have hinge angles that differ by several degrees such that one wing tip lies in front of the other in a folded configuration. Other asymmetries such as asymmetric hinge placement and asymmetric hinge seam length can be used concomitantly to enhance the compactness of the folded aircraft. Special application to wide span aircraft, high aspect ratio aircraft, and flying wing aircraft is contemplated.
Abstract translation: 飞机机翼配有不对称翼折叠铰链，以实现高度紧凑的折叠足迹。 铰链中的一个或多个有利地相对于飞机中心平面设置成角度，使得翼尖可以在中心平面上折叠而不彼此接触。 优选的飞机具有相差几度的铰链角度，使得一个翼尖处于折叠构型的另一个前端。 其他不对称性，例如不对称的铰链放置和不对称的铰接缝长度可以同时使用，以增强折叠的飞机的紧凑性。 考虑了对大跨度飞机，高纵横比飞机和飞翼飞机的特殊应用。
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公开(公告)号：WO2009111568A1
公开(公告)日：2009-09-11
申请号：PCT/US2009/036040
申请日：2009-03-04
Applicant: KAREM AIRCRAFT, INC. , GUPTA, Neil , KAREM, Abe
Inventor： GUPTA, Neil , KAREM, Abe
IPC: F03B3/12
CPC classification number: B64C11/20 , B64C27/473 , B64C2027/4736 , Y02T50/66
Abstract: A spar of a rotor blade having moderate depth transitions to a relatively much deeper shank over a relatively short distance. This rapid transition enables a low-weight blade root that is structurally efficient, offers a high moment capability, and enables high Mach number axial flow. A transition could advantageously reduce section depth by at least 15%, 20%, 30%, or even 40% over at most 5%, 6%, 10%, or 12% of a total length of the rotor blade. Such a transition could advantageously be accomplished using a cuff, which has interfaces with each of the spar and the shank. The rotor blade shank has a generally circular cross-section which allows for a rotary attachment to a hub, where the attachment may advantageously comprise a mechanical or elastomeric bearing. Preferred embodiments have a spar with a generally rectangular cross-section.
Abstract translation: 转子叶片的翼梁在相对较短的距离上具有适度的深度转变到相对较深的柄部。 这种快速过渡使得能够在结构上有效的低重量叶片根部提供高力矩能力，并实现高马赫数轴向流动。 在转子叶片的总长度的最多5％，6％，10％或12％的情况下，转变可以有利地减少截面深度至少15％，20％，30％，甚至40％。 这样的转变可以有利地使用具有与每个翼梁和柄部的接合的袖带来实现。 转子叶片柄具有大致圆形的横截面，其允许旋转连接到轮毂，其中附接可以有利地包括机械或弹性轴承。 优选实施例具有大致矩形横截面的翼梁。
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Patent Agency Ranking
公开(公告)号：WO2009048881A3
公开(公告)日：2009-04-16
申请号：PCT/US2008/079100
申请日：2008-10-07
Applicant: KAREM, Abe
Inventor： KAREM, Abe
Abstract: Aircraft fuselage structures have fuselage bulkheads in which the bulkhead outer caps are integrated with the skin, thereby reducing fastener count and weight. These outer caps and skin are preferably co-cured to form a strong structure. The outer caps can be advantageously constructed as continuous hoops of pultruded elements. The outer cap need not be interrupted by contours or cutouts for stringers, saving weight and reducing complexity. It is contemplated that by integrating the bulkhead outer caps into the skin, a bulkhead can still maintain equivalent stiffness and strength, while saving a significant number of rivets as compared to a comparable design without the outer cap.
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公开(公告)号：WO2008024256A2
公开(公告)日：2008-02-28
申请号：PCT/US2007/018106
申请日：2007-08-14
Applicant: KAREM, Abe
Inventor： KAREM, Abe
CPC classification number: G08G5/0069 , G05D1/00 , G08G5/0021
Abstract: A new generation of simplified vehicle electronic systems can be operated by either an onboard (manned) or off-board (remote controlled) operator, or automatically from an on-board system without any human operator. In the latter case, preferred embodiments can provide security against operation by unauthorized personnel and/or operation in an unauthorized travel path, without a need for a flight crew operated panic button or for a remote guidance facility. In another aspect, the operating controls of an aircraft or other highly complex vehicle are sufficiently simplified that the vehicle can be operated by a flight controller interface that is located outside the flight crew station. In yet another aspect, the communications system of a vehicle is sufficiently simplified such that the vehicle can be operated using substantially only a single long-range frequency band, and a second, short-range frequency band.
Abstract translation: 新一代的简化车载电子系统可以由机载（有人）或非机载（遥控）操作员操作，也可以由机载系统自动操作，无需任何人工操作员。 在后一种情况下，优选实施例可以提供针对未经授权的人员的操作和/或在未经授权的行驶路径中的操作的安全性，而不需要机组人员操作的应急按钮或用于远程引导设施。 另一方面，飞机或其他高度复杂的车辆的操作控制装置被充分简化，使得车辆能够通过位于机组人员外部的飞行控制器接口来操作。 在又一方面，车辆的通信系统被充分简化，使得车辆可以基本上仅使用单个长程频带和第二短程频带来操作。
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公开(公告)号：WO2020097367A1
公开(公告)日：2020-05-14
申请号：PCT/US2019/060322
申请日：2019-11-07
Applicant: KAREM AIRCRAFT, INC. , KAREM, Abe
Inventor： KAREM, Abe
Abstract: Devices and systems of the inventive concept provide a durable, all-weather manned or unmanned aircraft that is capable of vertical flight and provides improved stability upon payload launch or delivery. The payload bay is positioned along the central axis of the aircraft and proximal to the aircrafts center of gravity. Control and fuel systems are positioned fore and aft of the payload bay, respectively. The payload bay is configured to store and deliver a wide variety of payload types. The aircraft also includes features that reduce vibration, prolong the interval between necessary maintenance, and permit all-weather operation.
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公开(公告)号：WO2019108517A1
公开(公告)日：2019-06-06
申请号：PCT/US2018/062570
申请日：2018-11-27
Applicant: KAREM, Abe
Inventor： KAREM, Abe
Abstract: Devices, systems, and methods are provided in which a wing of a tiltrotor aircraft is rotated during operational flight, for example from a position perpendicular to the aircraft's fuselage through an angle of 30 or more in the direction of flight. This effectively narrows the maximum width of the aircraft, and facilitates maneuvering through closely spaced obstacles.
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公开(公告)号：WO2019094804A1
公开(公告)日：2019-05-16
申请号：PCT/US2018/060141
申请日：2018-11-09
Applicant: KAREM, Abe
Inventor： KAREM, Abe
Abstract: Exhaust redirecting devices are described that are suitable for use in tilt rotor aircraft. Such devices are constructed of light weight material and permit redirection of exhaust gases from turbojet engines of tilt rotor aircraft as nacelles of the aircraft transition between vertical and horizontal flight. Use of a controller permits coordination between exhaust redirection and nacelle position.
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