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公开(公告)号：US20210284328A1
公开(公告)日：2021-09-16
申请号：US16816577
申请日：2020-03-12
摘要： An aircraft includes a wing positioned below a vertical rotor, the wing extending in a transverse direction to a wingtip having an outboard face, and a turbulence feature located on the wingtip and oriented to induce turbulence in the rotor downwash flowing across the outboard face in a direction from a top surface of the wing to a bottom surface of the wing.
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公开(公告)号：US20090229694A1
公开(公告)日：2009-09-17
申请号：US12045924
申请日：2008-03-11
申请人： Carlos A. Fenny , Marc W. Kinard , John Lauffer
发明人： Carlos A. Fenny , Marc W. Kinard , John Lauffer
CPC分类号： H03C1/34 , B64C13/42 , F15B2211/20576 , F15B2211/31535 , F15B2211/324 , F15B2211/7054 , F15B2211/7055 , F15B2211/7056 , F15B2211/7107 , F15B2211/8757 , H03C7/00 , Y02T50/44 , Y10T137/86606
摘要： A hydraulic actuator is configured to provide redundant boost control to an aircraft within approximately the same space required by a single hydraulic cylinder. The hydraulic actuator includes a housing and a piston assembly disposed within the housing. The piston assembly includes a ram, a first piston secured to the ram, and second and third pistons disposed on the ram such that the second and third pistons are translatable relative to the longitudinal axis of the ram. The pistons form two hydraulically separate actuator cylinders within the space required by a single cylinder which results in a reduction in the weight and size of the hydraulic actuator.
摘要翻译： 液压致动器被配置为在单个液压缸所需的大致相同的空间内为飞机提供冗余升压控制。 液压致动器包括壳体和设置在壳体内的活塞组件。 活塞组件包括柱塞，固定到冲头的第一活塞，以及设置在冲头上的第二和第三活塞，使得第二和第三活塞可相对于压头的纵向轴线平移。 活塞在单个气缸所需的空间内形成两个液压分离的致动器气缸，这导致液压致动器的重量和尺寸的减小。
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公开(公告)号：US4517535A
公开(公告)日：1985-05-14
申请号：US402622
申请日：1982-07-28
申请人： Chuck Y. Pon
发明人： Chuck Y. Pon
CPC分类号： H01P1/227
摘要： A high power, high frequency attenuator which provides attenuation steps ch are switchable at very high speed, the attenuator implementing a method by which the input signal is split into two separate signals which are then subjected to impedance mismatches in the signal path, so that a portion of the split signals are reflected back to the signal splitter for dissipation there and the remaining portions of the split signal are transmitted to a summing circuit for recombination and output. The value of mismatch imposed determines the degree of attenuation obtained. The splitting of the signal reduces the stress upon the mismatched components as well as permits high switching speeds of the mismatches in and out of the circuit. In one embodiment of the invention directional couplers are used to provide the signal splitting and recombination functions, with the result that high isolation is achieved between the input port and the reflected signal caused by the mismatches.
摘要翻译： 一种高功率高频衰减器，其提供可以以非常高的速度切换的衰减步骤，该衰减器实现一种方法，通过该方法将输入信号分成两个分离的信号，然后在信号路径中经受阻抗失配，使得 分离信号的一部分被反射回到信号分离器以便在那里消散，并且分离信号的剩余部分被发送到求和电路用于复合和输出。 不匹配的值决定了所获得的衰减程度。 信号的分离减少了不匹配组件上的应力，并允许电路中和外部不匹配的高开关速度。 在本发明的一个实施例中，定向耦合器用于提供信号分离和复合功能，结果是在由错配引起的输入端口和反射信号之间实现了高隔离度。
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公开(公告)号：US20240199215A1
公开(公告)日：2024-06-20
申请号：US18537746
申请日：2023-12-12
IPC分类号： B64D15/16
CPC分类号： B64D15/16
摘要： A de-icing system for an airfoil includes a flexible skin having one or more stiffening elements embedded therein and one or more actuators positioned within the airfoil and configured to engage an impact area of the flexible skin with a displacement force. The stiffening elements extend substantially parallel to the leading edge of an airfoil and are placed in a chordwise succession proceeding away from the leading edge of the airfoil. The one or more stiffening elements are configured to transmit the displacement force to a non-impact area of the flexible skin adjacent to or near the one or more stiffening elements. The displacement force causes an outer surface of the flexible skin adjacent to the impact area to be distorted and an outer surface of the flexible skin of the non-impact area to be distorted.
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公开(公告)号：US20230327292A1
公开(公告)日：2023-10-12
申请号：US18206610
申请日：2023-06-06
发明人： Michael Raymond Hull , Steven Loveland , Yue Fan
IPC分类号： H01M50/512 , B64D27/24 , B60L50/64 , B64C29/00 , B60L58/10 , H01M10/42 , H01M50/249 , H01M50/209
CPC分类号： H01M50/512 , B64D27/24 , B60L50/64 , B64C29/00 , B60L58/10 , H01M10/425 , H01M50/249 , H01M10/4207 , H01M50/209 , H01M2010/4271 , B64D2221/00 , B60L2200/10 , H01M2220/20
摘要： A modular battery system includes an array of battery modules arranged in at least one stack. Each battery module includes a plurality of battery cells, a first side having positive and negative receptacles and a second side, that is opposite of the first side, having positive and negative plugs. The receptacles and plugs are configured such that adjacent battery modules in a side-by-side relationship are electrically coupled together via plug and receptacle connections and such that the battery modules are electrically coupled together in parallel. An interconnection electrically couples each stack of battery modules together via plug and receptacle connections with one of the battery modules in each stack such that the stacks of battery modules are electrically coupled together in parallel. Each of the battery modules includes a thermal conditioning system configured to thermally isolate the battery module from the other battery modules.
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公开(公告)号：US20240017823A1
公开(公告)日：2024-01-18
申请号：US17867231
申请日：2022-07-18
摘要： In an embodiment, an aircraft includes a drive system, a main engine coupled to the drive system to provide first power, and a supplemental engine coupled to the drive system to provide second power additive to the first power. The aircraft also includes a control system to control the main engine and the supplemental engine to optimize usage of the supplemental engine. The control system is operable to maintain the supplemental engine in a reduced power state at least until a determination is made that supplemental power is needed to satisfy a total power demand of the drive system. The control system is also operable to determine that supplemental power is needed to satisfy the total power demand of the drive system. The control system is further operable to increase a power level of the supplemental engine in response to the determination that supplemental power is needed.
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公开(公告)号：US12132180B2
公开(公告)日：2024-10-29
申请号：US17250729
申请日：2019-08-27
发明人： Georg Enkirch , Felix Haas , Moritz Lipperheide
IPC分类号： H01M10/613 , H01M10/04 , H01M10/647 , H01M10/653 , H01M10/6557 , H01M50/204 , H01M50/227 , H01M50/271
CPC分类号： H01M10/613 , H01M10/0481 , H01M10/647 , H01M10/653 , H01M10/6557 , H01M50/204 , H01M50/227 , H01M50/271
摘要： The invention relates to a battery cooling element having: an outer surface for resting at least in regions against a battery cell and/or for resting at least in regions against a battery module comprising at least two battery cells; an inner chamber for receiving a cooling medium, which inner chamber is surrounded at least in regions by the outer surface; and a cooling medium inlet connected to the inner chamber and a cooling medium outlet connected to the inner chamber, wherein the outer surface is made, at least in regions, of a thermally conductive, flexible film which can be shaped by a fluid pressure of the cooling medium.
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公开(公告)号：US12130617B2
公开(公告)日：2024-10-29
申请号：US18397371
申请日：2023-12-27
CPC分类号： G05D1/0011 , G05D1/0094 , G05D1/102 , G05D1/223 , G05D1/652 , G05D1/689 , G06T7/292 , G06V20/13 , G06V20/17 , G08G5/0047
摘要： One embodiment is a navigation system for an aircraft including a positioning system to generate information related to a position of the aircraft, a group of cameras mounted to a body of the aircraft, each camera of the group of cameras to simultaneously capture images of a portion of an environment that surrounds the aircraft, and a processing component coupled to the positioning system and the group of cameras, the processing component to determine a current position of the aircraft based on the information related to the position of the aircraft and the images.
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公开(公告)号：US12130199B2
公开(公告)日：2024-10-29
申请号：US17369470
申请日：2021-07-07
申请人： Bell Textron Inc.
IPC分类号： G01M13/04 , B64C13/50 , B64C27/605
CPC分类号： G01M13/04 , B64C27/605 , B64C13/503
摘要： Embodiments are directed to systems and methods for estimating wear in aircraft rotor systems. Data associated with loads and motions of a swashplate actuator is collected. The swashplate actuator drives a swashplate and at least one control link is coupled to the swashplate. The loads and motions of the at least one control link is estimated based upon the loads and motions of the swashplate actuator. Using a wear model, the current wear of control link components is estimated due to the loads and motions of the at least one control link. Wear estimates for the components are aggregated across multiple flights and used to determine when maintenance actions should occur.
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公开(公告)号：US20240353867A1
公开(公告)日：2024-10-24
申请号：US18635198
申请日：2024-04-15
摘要： An aircraft emergency descent method includes setting a pre-set maximum collective blade pitch and a pre-set altitude as part of a failure procedure; monitoring rotor assemblies through an aircraft control system and a failure detection module; determining when a rotor assembly has failed; and activating the failure procedure. The failure procedure includes commanding a maximum torque to a motor of each rotor assembly such that the rotational velocity of functioning rotors increases; detecting the increase in rotational velocity; adjusting either motor torque or a collective blade pitch to regulate rotational velocity; monitoring altitude of the aircraft; and upon determining when the aircraft reaches the pre-set altitude, adjusting the collective blade pitch to the pre-set maximum collective blade pitch via the at least one governor such that momentum is conserved, causing a descent rate of the aircraft to decrease as the aircraft approaches a ground surface.
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