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公开(公告)号：US11834154B2
公开(公告)日：2023-12-05
申请号：US16813718
申请日：2020-03-09
申请人： NCTAR, LLC
摘要： A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume having a first average velocity from an engine, and expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave.
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公开(公告)号：US20230130658A1
公开(公告)日：2023-04-27
申请号：US17905311
申请日：2021-02-05
发明人： Atsushi UENO
摘要： A method of designing an aircraft shape of a supersonic aircraft according to an embodiment of the present invention includes: obtaining an equivalent cross-sectional area distribution of an initial shape at an off-track position of an aircraft; setting a target equivalent cross-sectional area distribution at the off-track position of the aircraft for reducing sonic booms on the basis of the obtained equivalent cross-sectional area distribution; and converting, on the basis of a required additional cross-sectional area distribution that is a difference between the equivalent cross-sectional area distribution and the target equivalent cross-sectional area distribution, a required additional cross-sectional area of a cross-section of the aircraft on an off-track Mach plane that extends through an arbitrary position in an airflow direction into a required additional cross-sectional area of a cross-section of the aircraft on an on-track Mach plane of the aircraft that is located near the off-track Mach plane and adding the required additional cross-sectional area of the cross-section of the aircraft on the on-track Mach plane.
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公开(公告)号：US20230002050A1
公开(公告)日：2023-01-05
申请号：US17654251
申请日：2022-03-10
申请人： THE BOEING COMPANY
摘要： A system and method for ejecting a store from an aircraft include a stowage tube configured to retain the store. The stowage tube includes an open rear end. A door panel is coupled to the stowage tube. An actuator driven linkage is coupled to the door panel. The actuator driven linkage is configured to rotate the door panel about a pivot axis at a forward edge opposite from an aft end between a closed position associated with a stowed position of the system and an open position associated with a deployed position of the system. The stowage tube is configured to rearwardly eject the store out of the open rear end when the system is in the deployed position.
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公开(公告)号：US11535355B2
公开(公告)日：2022-12-27
申请号：US16804304
申请日：2020-02-28
申请人： The Boeing Company
摘要： An aerodynamic body includes an upper surface and a lower surface. The upper surface includes a first portion of a first axisymmetric body. The lower surface is mated with the upper surface. The lower surface includes a waverider shape. The waverider shape is derived from the shockwave generated by a second axisymmetric body.
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5.发明申请公开(公告)号：US20220325678A1
公开(公告)日：2022-10-13
申请号：US17715450
申请日：2022-04-07
摘要： Lobed mixer nozzles for supersonic and subsonic aircraft, and associated systems and methods are disclosed herein. A representative lobe mixer nozzle includes a fan flow duct aligned along a longitudinal axis, and a core flow duct, also aligned along the longitudinal axis. At least one duct wall, for example, a splitter, forms, at least in part, a radially inner boundary of the fan flow duct, and a radially outer boundary of the core flow duct. The duct wall terminates at a reference exit plane, and has multiple first lobes extending radially inwardly, and multiple second lobes extending radially outwardly. At least one lobe is canted forward relative to the reference exit plane, and at least one lobe is canted aft relative to the reference exit plane.
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公开(公告)号：US11465766B2
公开(公告)日：2022-10-11
申请号：US16457418
申请日：2019-06-28
申请人： The Boeing Company
发明人： Michael F. Stoia , Garrett W. Ek , Arun Muley
摘要： Methods and apparatus for cooling a surface on a flight vehicle and/or generating power include advancing the flight vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A supercritical working fluid is circulated through a fluid loop that includes compressing the supercritical working fluid through a compressor, heating the supercritical working fluid through a heat intake that is thermally coupled to the surface, expanding the supercritical working fluid in a thermal engine to generate a work output, cooling the supercritical working fluid, and recirculating the supercritical working fluid to the compressor. The work output of the thermal engine is operably coupled to the compressor, and may optionally be coupled to a generator to produce power. The supercritical working fluid absorbs heat from the surface, eliminating hot spots and permitting use of lighter and/or less expensive materials.
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公开(公告)号：US20220291125A1
公开(公告)日：2022-09-15
申请号：US17199604
申请日：2021-03-12
申请人： Raytheon Company
发明人： Gary A. Frazier , John J. Coogan
摘要： A real-time ablation sensor uses an optical detector, such as a spectrometer or radiometer, to detect ablation of a material, for example by detecting a signal indicative of ablation of the material, which may be an engineered material. The optical detector may detect reflected light, either from the material being ablated, or from products of the ablation, such as in the vicinity of the material being ablated. A light source may be used to provide light that is reflected by the material and/or the ablation products, with the reflected light received by the detector. The light may be of a selected wavelength or wavelengths, with the selection made in combination with the selection/configuration of the material to be ablated, and/or the selection/configuration of the optical detector.
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公开(公告)号：US20220289360A1
公开(公告)日：2022-09-15
申请号：US17563125
申请日：2021-12-28
发明人： Tom Vice
摘要： A system that optimizes the shape or configuration of an aircraft to minimize ground overpressure shock strength while in supersonic flight over speed restricted terrain and to morph to an optimized configuration for drag minimization while over unrestricted terrain.
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公开(公告)号：US11441517B2
公开(公告)日：2022-09-13
申请号：US16658832
申请日：2019-10-21
申请人： ROLLS-ROYCE plc
摘要： A supersonic jet aircraft and a method of operating the same. The supersonic jet aircraft having at least three turbofan engines and an engine management computer. A first engine of the at least three turbofan engines is configured to be de-activatable during flight to move from an operational state in which it provides thrust to an operational state in which it stops providing thrust. Other engines of the at least three turbofan engines are configured to provide sufficient thrust to the supersonic jet aircraft when the first engine is de-activated such that the aircraft can perform a supersonic climb operation and/or a supersonic cruise operation.
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公开(公告)号：US11345457B2
公开(公告)日：2022-05-31
申请号：US16788636
申请日：2020-02-12
申请人： Andrew W. Sklar
发明人： Andrew W. Sklar
摘要： A supersonic aircraft fuselage includes a fuselage body having a first end, a second end, a length extending between the first end and second end, a surface, a first flat plane extending from the first end to a center of the fuselage body along the length on the surface, and a second flat plane extending from the second end to the center of the fuselage body along the length on the surface. The surface includes a curved portion conforming to a Sears-Haack body shape and abutting the first flat plane and second flat plane and extending between the first end and second end. A supersonic aircraft includes a first fuselage, a second fuselage, and a space between the first fuselage and second fuselage. The first fuselage and second fuselage form a Busemann biplane geometry within the space.
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