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1.发明公开公开(公告)号：US20240270404A1
公开(公告)日：2024-08-15
申请号：US18440997
申请日：2024-02-14
CPC分类号： B64D41/007 , G06F30/15 , G06F30/28 , B64F5/00 , F03D1/0633 , F03D9/322 , F05D2220/76 , F05D2260/81
摘要： A method of modeling a turbine mounted behind an aircraft wing for providing a specified proportion of a propulsive force in the aircraft flight direction to an amount of power generated by the turbine when driven by the airflow trailing the wings. The turbine converts a portion of the otherwise wasted energy in the rotational vortices trailing the aircraft wings into thrust that reduces aircraft drag while also providing electricity to power electrical systems on the aircraft. The method is also capable of modeling a turbine construction that will use the energy in the wake solely to generate electricity without increasing drag on the aircraft or solely to reduce drag without generating electricity. In one embodiment, the method saves computation time by using a recursive routine to define a preliminary turbine configuration based on an idealized vortex model and then matches it to the flow trailing an actual aircraft wing.
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2.发明公开公开(公告)号：US20240199229A1
公开(公告)日：2024-06-20
申请号：US17908895
申请日：2021-09-07
申请人： BEIHANG UNIVERSITY
发明人： Chongwen JIANG , Zhihao LI , Shuyao HU , Chenhao XU , Zhenxun GAO , Chunxuan LI
IPC分类号： B64F5/00
CPC分类号： B64F5/00
摘要： A direct design method for generating an osculating curved waverider based on a complex leading edge, includes obtaining a leading edgeleading edge through determining a leading edge of a waverider according to a spread length, a front-to-rear length, and a sweep angle at each position of an aircraft, and arranging leading-edge discrete points on the leading edgeleading edge; drawing a small shock cone corresponding to each leading-edge discrete point by starting from each leading-edge discrete point, taking a local shock angle as a half cone angle and taking a free streamline direction as an axis; finding envelope surfaces of all small shock cones, namely, a shock curved surface corresponding to the leading edgeleading edge; generating a waverider by using the osculating curved waverider design method.
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公开(公告)号：US11975837B2
公开(公告)日：2024-05-07
申请号：US17619201
申请日：2021-03-26
发明人： Alexander Weng , Felix Helfrich , Holger Warner , Benedikt Kircher , Johanna Roestel , Efe Kolcak
CPC分类号： B64D11/003 , B64F5/00
摘要： A vehicle region with a roof section of a primary structure and with two luggage compartments. One of the luggage compartments comprises a detachable luggage compartment flap and a luggage compartment top, which forms the upper boundary of a part of a luggage space. A detachable fastening device can rotatably fasten the luggage compartment flap on the luggage compartment. A front edge of the luggage compartment top is at a distance from an end point in an intermediate space above a luggage compartment, to which end point a side of a ceiling panel is movable, the distance being greater than or equal to a width of the ceiling panel. Methods for installing and removing a ceiling panel above two luggage compartments are provided, wherein the ceiling panel is guided at least partially through a luggage space of a luggage compartment when the luggage compartment flap has been removed.
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公开(公告)号：US20240010333A1
公开(公告)日：2024-01-11
申请号：US18216068
申请日：2023-06-29
申请人： Karem Aircraft, Inc.
发明人： Abraham Karem , John Paul Parcell
CPC分类号： B64C29/0033 , B64F5/00 , B64C27/463 , B64C1/063
摘要： A tiltrotor aircraft is designed to accommodate rotors of different diameters, as well as corresponding wings and fuselages with different span and length, while maintaining very high parts commonality, especially with respect to drive train and power source. This enables design and operation of a fleet of such aircraft with significantly different rotor diameters, which are nevertheless optimized for different missions. In preferred embodiments the rotors are configured to have high stiffness and low weight to reduce aero-structural dynamic issues across the fleet. Also in preferred embodiments drive systems are designed for a full range of speed, torque, and power associated with all intended rotors. Turboshaft engine speeds are restricted to a narrow RPM range, so that a single gearset can be replaced to achieve the desired rotor RPM. Also in preferred embodiments, aircraft in a fleet can differ in folded length, empty weight, payload length by up 50%.
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5.发明公开公开(公告)号：US20230373609A1
公开(公告)日：2023-11-23
申请号：US18200128
申请日：2023-05-22
发明人： Kenji TOGAMI , Minoru YOSHIMOTO , Makoto HIROTA , Yuji HATTORI , Yuki IDE
CPC分类号： B64C3/14 , B64F5/00 , B64C2003/148
摘要： The ridge structure has ridge elements provided on a top face of a leading edge region directly downstream of a leading edge, which is a laminar flow region of a wing having a swept-back angle relative to a mainstream and provided with a leading edge, and extending in parallel toward downstream of the mainstream. When an angle of a ridgeline connecting vertexes of the ridge elements in an extending direction of the ridge elements relative to x direction is OR, an angle of a flow line of a boundary layer external edge of the mainstream relative to the x direction is θe, and an angle of a wavefront of stationary cross-flow instability, which is a mode in which a stationary disturbance amplifies inside a boundary layer of the surface and appears as a stationary vortex row, relative to the x direction is θcf, θR is between θe and θcf.
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公开(公告)号：US11801946B2
公开(公告)日：2023-10-31
申请号：US16394278
申请日：2019-04-25
申请人： The Boeing Company
发明人： John E. Rogers , Robert Alan Smith
IPC分类号： B64F5/00 , G05B19/4093 , G05B19/4099 , G01B7/14
CPC分类号： B64F5/00 , G01B7/14 , G05B19/4099 , G05B19/40931 , G05B2219/35062
摘要： Systems and methods for measuring air gaps between opposing surfaces of two structural components. In one application, such measurements are used to fabricate a shim that fills the air gap between two structural members, such as parts of an aircraft. The resonant inductive coupling-based sensing system has the capability to remotely measure an air gap using an on-board transmit system. Furthermore, the system has the capability to switch between multiple inductor-capacitor sets such as to simultaneously measure air gaps across an area so that a better profile of the air gap can be determined. The resonant inductive coupling-based gap sensor is configured as signal generating and signal sensing electronics printed or mounted on respective flexible substrates to provide a flexible and portable measurement solution.
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公开(公告)号：US11732487B2
公开(公告)日：2023-08-22
申请号：US16443544
申请日：2019-06-17
申请人： The Boeing Company
发明人： August West McKenna
CPC分类号： E04G1/15 , B64F5/00 , E04G2001/157 , E04G2001/242
摘要： Apparatus, devices, and methods relating to a mechanical proximity sensor for a slidable extension. An illustrative apparatus may comprise an elevated platform and an extension slidably extendable from the elevated platform toward a workpiece. The apparatus also may comprise a probe coupled movably to the extension. The apparatus further may comprise an indicator connected to the probe and configured to rotate from a first orientation to a second orientation in response to engagement between the probe and the workpiece as the extension approaches the workpiece. The indicator may be configured to complete rotation from the first orientation to the second orientation when a leading edge of the extension is located at a predetermined distance from the workpiece.
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公开(公告)号：US11661184B2
公开(公告)日：2023-05-30
申请号：US16785412
申请日：2020-02-07
发明人： Brandon Powell
摘要： A method of designing a morphable aerodynamic surface includes discretizing and parameterizing a model of a morphable surface to create a function to optimize; utilizing finite element analysis to solve for displacements and associated errors at an initialization point; and iteratively calculating a gradient cost function, define step size and search direction, step according to defined step size and search direction, and recalculate displacements and associated errors to converge on final thickness vector.
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公开(公告)号：US20190248479A1
公开(公告)日：2019-08-15
申请号：US15894888
申请日：2018-02-12
CPC分类号： B64C25/52 , B64C2025/325 , B64F5/00
摘要： An aspect provides a skid landing gear assembly including a cross member disposed between a first skid tube and a second skid tube, and a tension cable member configured to be disposed in the cross member; wherein the tension cable member resists outward deflection of at least a portion of the skid landing gear assembly when a downward load is applied to the skid landing gear assembly. In other aspects, there are methods of avoiding ground resonance in a skid landing gear assembly, methods of assembling a skid landing gear assembly, methods of operating a helicopter with a skid landing gear assembly, and methods of improving the service life of a skid landing gear assembly.
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公开(公告)号：US20180354651A1
公开(公告)日：2018-12-13
申请号：US16003433
申请日：2018-06-08
申请人： AIRBUS OPERATIONS SL
发明人： Carlos GARCIA NIETO , Jaime CABRERA VALOR , Rosario MOLINA MORENO , Sergio HERNANDEZ SANMARTIN , María Pilar GUILLÉN MORENO , Fernando ALVAREZ ALVAREZ
IPC分类号： B64F5/00
CPC分类号： B64F5/00 , B05B12/24 , B05B12/26 , B05B13/005 , B25J15/00
摘要： A method for masking an aeronautical structure with a frisket before painting such aeronautical structure, including the steps of: providing the aeronautical structure comprising at least one hole; providing the frisket; providing at least one jamming element, wherein said jamming element is configured to be inserted into the at least one hole; providing at least one C-shaped jamming element configured to be placed on a lateral of the first section; arranging the frisket partially over the at least one hole; inserting the at least one jamming element into the at least one hole, partially holding the frisket; wrapping the first section of the aeronautical structure with the frisket, said first section being masked to avoid its painting; and placing the at least one C-shaped jamming element laterally embracing the first section with the frisket, the frisket being clamped against said first section.
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