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公开(公告)号：US20240343406A1
公开(公告)日：2024-10-17
申请号：US18637971
申请日：2024-04-17
摘要： An aircraft section comprising a fuel storage tank, a first strap, a second strap, at least one anchoring structure and at least one coupling portion; wherein: the first strap comprises two attachment portions anchored to the at least one anchoring structure; the second strap comprises two attachment portions anchored to the at least one anchoring structure; and the first strap and the second strap are arranged under tension such that the tank is maintained pressed against the at least one coupling portion by the first strap and the second strap. Also an aircraft with such a section.
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公开(公告)号：US12054238B2
公开(公告)日：2024-08-06
申请号：US17793745
申请日：2021-01-08
申请人： BAE Systems plc
IPC分类号： B64C1/14 , B29C70/54 , B32B37/18 , B32B38/00 , B32B38/10 , B32B38/18 , B64C1/06 , B64C39/00 , B64F5/10 , B64U20/70 , B32B37/26 , B32B38/04 , B64C1/00
CPC分类号： B64C1/1446 , B29C70/545 , B32B37/18 , B32B38/0004 , B32B38/10 , B32B38/1808 , B64C1/061 , B64C1/068 , B64C39/029 , B64F5/10 , B64U20/70 , B32B2037/268 , B32B2038/047 , B32B2605/18 , B64C2001/0045
摘要： An airframe or a part thereof 3, for example a skin assembly or a profile such as a structural profile, comprises: a wall W having an aperture A therethrough, wherein the wall W provides a frame F surrounding, at least in part, the aperture A; a panel P conforming with the aperture A; and wherein the airframe or the part 3 thereof is configurable in: a first configuration, wherein the panel P and the frame F are mutually spaced apart; and a second configuration, wherein the panel P is received in the frame F and wherein the frame F resists movement of the panel P in two or three mutually orthogonal directions.
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公开(公告)号：US12012206B2
公开(公告)日：2024-06-18
申请号：US18227310
申请日：2023-07-28
申请人： Joby Aero, Inc.
发明人： Gregor Veble Mikic , Alex Stoll , JoeBen Bevirt
摘要： The aircraft can include: an airframe, a tilt mechanism, a payload housing, and can optionally include an impact attenuator, a set of ground support members (e.g., struts), a set of power sources, and a set of control elements. The airframe can include: a set of rotors and a set of support members. By utilizing a larger rotor blade area (and/or larger rotor disc area) and adjusting the blade pitch and RPM, the rotors can augment the lift generated by the aerodynamic profile of the aircraft in the forward flight mode in addition to providing forward thrust. Variants generating lift with the rotors can reduce or eliminate additional control surfaces (e.g., wing flaps, ailerons, ruddervators, elevators, rudder, etc.) on the aircraft since the thrust and motor torque is controllable (thereby indirectly controlling lift) at each rotor, thereby enabling pitch, yaw, and/or roll control during forward flight.
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公开(公告)号：US12006019B2
公开(公告)日：2024-06-11
申请号：US17626735
申请日：2020-07-09
CPC分类号： B64C1/061 , B29D99/0014 , B64F5/10 , B64C2001/0072
摘要： An internal structural reinforcement element for fuselages, where the internal structural reinforcement element has a longitudinal direction adapted for its placement in the longitudinal direction of the fuselage and a transversal direction perpendicular to the longitudinal direction, comprising:
an external reinforcement element,
an internal reinforcement element, located internally to the external reinforcement element in the transversal direction of the structural element,
where both reinforcement elements are manufactured from resin-impregnated fibre, and
an intermediate element, located between the external reinforcement element and the internal reinforcement element in the transversal direction of the structural element, the intermediate element being manufactured from pre-impregnated composite material.-
公开(公告)号：US11975825B2
公开(公告)日：2024-05-07
申请号：US17101688
申请日：2020-11-23
申请人： Bell Textron Inc.
CPC分类号： B64C27/14 , B64C1/061 , B64D27/02 , F16C3/02 , F16C3/023 , F16D3/06 , F16C2223/30 , F16C2326/43 , F16D2001/103 , F16D2200/0052 , F16D2250/0046 , Y10T403/7032
摘要： A spline assembly, including a spline shaft having a first end and a second end, wherein the first end is splined to engage a spline receiver of a primary drive system and includes a substantially spherical alignment head, wherein the spherical alignment head comprises an expendable hydrocarbon material that is caused to melt by operation of the primary drive system over time.
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公开(公告)号：US20240109639A1
公开(公告)日：2024-04-04
申请号：US18532324
申请日：2023-12-07
发明人： John F. GUNDLACH , Jacob S. Allen
CPC分类号： B64C1/061 , B33Y80/00 , B64C3/24 , B64C2001/0054
摘要： An additive manufactured airframe structure includes a first additive manufactured fuselage segment including a first outer wall that extends in a normal direction from a first end to a second end, and also includes a plurality of reinforcement elements extending from the second end of, and away from, the first outer wall in the normal direction. The airframe structure also includes a second additive manufactured fuselage segment formed separately from the first additive manufactured fuselage segment and including a second outer wall that extends in the normal direction from a first end to a second end, and a plurality of receiving channels extending along the second outer wall. The plurality of reinforcement elements are received in the plurality of receiving channels and link together the first and second additive manufactured fuselage segments.
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公开(公告)号：US11939038B2
公开(公告)日：2024-03-26
申请号：US17625203
申请日：2020-06-25
发明人： Maarten Labordus
CPC分类号： B64C1/12 , B29C65/3636 , B29C65/3684 , B29D99/0014 , B64C1/061 , B64C1/064 , B64C1/069 , B29L2031/3082 , B64C2001/0072
摘要： A fuselage structure of an aircraft includes a fuselage skin, and a plurality of frame elements spaced apart from one another in a direction parallel to the aircraft longitudinal axis for supporting the fuselage skin. The fuselage skin includes a plurality of interconnected fiber-reinforced composite skin panels that extend between each pair of frame elements and are connected thereto. The composite skin panels further comprise a stiffener integrally formed in each composite skin panel. A method for manufacturing the fuselage skin. The composite skin panels may be interconnected and/or connected to a frame element through an induction welded connection.
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公开(公告)号：US11753141B2
公开(公告)日：2023-09-12
申请号：US16897890
申请日：2020-06-10
摘要： There is provided a method of mounting equipment to an aircraft. The method comprises attaching a mounting structure to the fuselage of the aircraft, the fuselage extending lengthwise along a longitudinal axis. This comprises irremovably attaching a plurality of substantially planar frames to the exterior of the fuselage, such that each frame is oriented orthogonal to the longitudinal axis and spaced apart from an adjacent frame; and irremovably attaching a plurality of intercostal ribs between pairs of adjacent frames of the plurality frames, such that each rib is oriented parallel to the longitudinal axis and attached to each of a pair of said adjacent frames. The method further comprises mounting equipment to or within the mounting structure; and covering the mounting structure and the equipment mounted thereon or therein with a cover. The method further comprises removably attaching the cover to the mounting structure or the fuselage. An assembly, structure, tailplane and aircraft are also provided.
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公开(公告)号：US20230242274A1
公开(公告)日：2023-08-03
申请号：US18114030
申请日：2023-02-24
申请人： Workhorse Group Inc.
发明人： Jay Ratajczak , Wei Wei , Haonan Zhang , Thaddeus Bort , Scott Wilson
IPC分类号： B64F1/36 , B66D1/48 , G08G5/00 , B64D1/22 , B64D1/12 , G05D1/10 , B60L53/80 , B60L53/14 , G05D1/00 , B64C1/06 , B64D27/24 , B64D31/00 , B60L5/36 , B64D41/00 , B64D1/10 , B64C39/02 , B64C25/00 , B64F1/32 , B64C1/30 , B60L50/60 , B64D45/00
CPC分类号： B64F1/364 , B60L5/36 , B60L50/66 , B60L53/14 , B60L53/80 , B64C1/30 , B64C1/061 , B64C25/001 , B64C39/024 , B64D1/10 , B64D1/12 , B64D1/22 , B64D27/24 , B64D31/00 , B64D41/00 , B64F1/32 , B64U20/70 , B66D1/48 , G05D1/0094 , G05D1/101 , G05D1/106 , G08G5/0069 , B60L2200/10 , B64D2045/0085 , B64U10/13 , B64U30/20 , B64U50/13 , B64U50/19 , B64U70/00 , B64U80/70 , B64U80/86 , B64U2101/60 , B64U2201/10
摘要： A method according to certain embodiments generally involves operating a system including an unmanned aerial vehicle (UAV) and a base station. The base station includes a nest including an upper opening having an upper opening diameter and a lower opening having a lower opening diameter less than the upper opening diameter. The lower opening is accessible from within the base station. The method generally includes landing the UAV within the nest such that a portion of the UAV is accessible via the lower opening, releasably attaching a load to the UAV, and operating the UAV to deliver the load to a destination.
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公开(公告)号：US11679858B2
公开(公告)日：2023-06-20
申请号：US16912195
申请日：2020-06-25
摘要： A method and apparatus for facilitating the attachment of an internal module in an internal space of an aircraft part is disclosed. The attachment device includes at least one attachment member comprising an attachment shank, a chamber for introducing the attachment member, the chamber including a first orifice through which the attachment shank passes in the installed configuration of the internal module, and a second orifice which serves for the introduction of the attachment member into the chamber from the outside.
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