公开(公告)号：US12017800B2

公开(公告)日：2024-06-25

申请号：US17042720

申请日：2019-02-21

申请人： JAPAN AEROSPACE EXPLORATION AGENCY

发明人： Tatsunori Yuhara

IPC分类号： B64F5/10 ,  B64C23/04 ,  B64C30/00 ,  G06F30/15 ,  G06F111/10 ,  G06F113/28

CPC分类号： B64F5/10 ,  B64C30/00 ,  G06F30/15 ,  B64C23/04 ,  G06F2111/10 ,  G06F2113/28

摘要： [Object] To realize an improvement in design accuracy and a reduction in design time in a process of matching an equivalent cross-sectional area of a design shape of a supersonic aircraft to a target equivalent cross-sectional area in a sonic boom reduction method based on an equivalent cross-sectional area.
[Solving Means] The technique includes: setting an initial shape of the airframe and a target equivalent cross-sectional area of the airframe; estimating a near field pressure waveform for the initial shape of the airframe assuming that the supersonic aircraft flies at a cruising speed; evaluating an equivalent cross-sectional area from the estimated near field pressure waveform for the initial shape of the airframe; and setting a Mach plane corresponding to the cruising speed, and setting a design curve on the Mach plane, the design curve corresponding to an initial curve at which the initial shape of the airframe and the Mach plane intersect so that the equivalent cross-sectional area approaches the target equivalent cross-sectional area. Then, the shape of the airframe is designed based on the design curve.

公开(公告)号：US11473500B2

公开(公告)日：2022-10-18

申请号：US17242394

申请日：2021-04-28

申请人： Raytheon Company

发明人： Nicholas P. Cicchini

IPC分类号： F02C7/04 ,  F02K7/10 ,  B64D33/02 ,  B64D27/20 ,  F02K7/08 ,  F42B10/38 ,  F42B10/42 ,  F42B15/10 ,  F02K7/00 ,  B64C30/00 ,  B64C23/04

摘要： A method of reducing low-energy flow in a flight vehicle engine includes an isolator of the engine having a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where the isolator has sufficient back pressure. The swept-back wedge may also create swept oblique shocks along its length. Boundary layer flow streamlines are diverted running parallel to or parallel but moving outward conically to the swept-wedge leading edge moving outboard and upward. The non-viscous flow outside the boundary layer is processed through the swept-back ramp shock and diverted outboard and upward as well. The outboard aft portion of the wedge at the sidewall intersection may also induce shocks and divert flow near the walls closer toward the walls and upward, and/or improve flow mixing.

公开(公告)号：US20220274697A1

公开(公告)日：2022-09-01

申请号：US17614364

申请日：2019-07-01

申请人： chuanrui zhang

发明人： chuanrui zhang

IPC分类号： B64C30/00 ,  B64C23/04 ,  B64C1/00

摘要： This invention is focus on how to make a quieter supersonic flight. Several techniques and methods have been crafted to solve the noise problem of the sonic boom. Sonic boom is propagated from aircraft to the ground, so add interference media between them to block the noise wave could reduce the sonic boom level. Using special designed wings could also reduce noise wave. Part of the special wings design is inspired from the bird flock's flight. Using active shock wave to blow away the air at the windward front of the aircraft or using holes at the fuselage bottom to flow away the air underneath the fuselage could reduce the noise wave propagated to travel to the ground.

公开(公告)号：US11267552B2

公开(公告)日：2022-03-08

申请号：US16261486

申请日：2019-01-29

申请人： DASSAULT AVIATION

发明人： Aurélien Merlet ,  Zdenek Johan ,  Ximun Loyatho ,  Gilbert Roge

IPC分类号： B64C3/14 ,  B64C7/00 ,  B64C23/04 ,  B64C1/26 ,  B64C3/32

摘要： An aircraft portion includes a fuselage oriented in a longitudinal direction, an airfoil made up of at least one pair of wings arranged on either side of the fuselage in a transverse direction orthogonal to the longitudinal direction, and an airfoil-fuselage junction fairing at the interface between the airfoil and the fuselage. The junction fairing has, in a vertical plane, a lower profile and, in a horizontal plane, a horizontal profile at the junction of the outer surface of the junction fairing with the convex side of each wing. The horizontal profile and/or the lower profile successively has, in the longitudinal direction, a convex front segment, a concave intermediate segment, and a convex rear segment.

公开(公告)号：US10810886B2

公开(公告)日：2020-10-20

申请号：US15825916

申请日：2017-11-29

申请人： HONEYWELL INTERNATIONAL INC.

发明人： John G. Suddreth ,  Jerry Ball

IPC分类号： G01C23/00 ,  G08G5/00 ,  B64D43/00 ,  B64D45/00 ,  G06F30/15 ,  B64C23/04 ,  B64C30/00 ,  G06F119/10

摘要： Avionic display systems and methods are provided for generating avionic displays including symbology decreasing the likelihood of boom tolerance threshold exceedance (an overpressure events) due to potential constructive interference between pressure waves occurring during supersonic flight. In various embodiments, the avionic display system includes a display device on which an avionic display is generated. A controller architecture is operably coupled to the display device and configured to determine when there exists a possibility for an overpressure event to occur in a future timeframe due to constructive interference between colliding pressure waves, which are forecast to occur during the impending supersonic flight of one or more A/C. When determining that there exists a possibility for an overpressure event to occur in the future timeframe due to constructive interference between pressure waves, the controller architecture further generates symbology or other graphics on the avionic display indicative of the potential occurrence of the overpressure event.

公开(公告)号：US09896193B2

公开(公告)日：2018-02-20

申请号：US12735536

申请日：2009-02-17

申请人： Norman Wood

发明人： Norman Wood

IPC分类号： B64C23/04 ,  B64C23/00 ,  B64C3/14

CPC分类号： B64C23/04 ,  B64C23/00 ,  B64C2003/148 ,  B64C2003/149

摘要： An aerodynamic structure comprising a shock bump (3) extending from its surface. The shock bump is asymmetrical about a plane of asymmetry, and the plane of asymmetry: passes through a centre (6) of the shock bump, is parallel with a principal direction of air flow over the structure, and extends at a right angle to the surface of the structure.

公开(公告)号：US20170313413A1

公开(公告)日：2017-11-02

申请号：US15378861

申请日：2016-12-14

申请人： Kevin Kremeyer

发明人： Kevin Kremeyer

IPC分类号： B64C23/04 ,  B64G1/62

CPC分类号： B64C23/04 ,  B64G1/62 ,  Y10T137/0391

摘要： A system for modifying a shock wave formed in a fluid by a body to modify effects of the shock wave on information transferred to or from the body. The system includes an element for heating fluid along a path to form a volume of heated fluid expanding outwardly from the path, the path extending from the body and through the shock wave; an element for transferring the information to or from the body; and an element for timing the transferring of the information relative to the heating of the fluid along the path to modify certain effects of the shock wave on the information.

公开(公告)号：US09463870B2

公开(公告)日：2016-10-11

申请号：US12735535

申请日：2009-02-17

申请人： Norman Wood

发明人： Norman Wood

IPC分类号： B64C23/04 ,  B64C3/14

CPC分类号： B64C23/04 ,  B64C2003/148 ,  B64C2003/149 ,  Y02T50/12

摘要： An aerodynamic structure (1) comprising a series of shock bumps (3a, 3b, 3c) extending from its surface. The shock bumps are distributed along a line (7) with a smaller mean angle of sweep than an unperturbed shock (4) which would form adjacent to the surface during transonic movement of the structure in the absence of the shock bumps. Instead of being distributed along the line of the unperturbed shock, the shock bumps are distributed along a line which is less swept than the mean angle of sweep of the unperturbed shock. When the structure is moved at a transonic speed; a shock forms adjacent to its surface and the shock bumps perturb the shock (9) so as to reduce its angle of sweep.

摘要翻译： 包括从其表面延伸的一系列冲击凸起（3a，3b，3c）的气动结构（1）。 冲击突起沿着具有较小的平均扫掠角度的线（7）分布，而不受无扰动冲击（4）的影响，在不存在冲击突起的情况下，该结构在跨音速运动期间将与表面相邻。 沿着不受扰动的冲击线的分布而不是沿着不受干扰的冲击的平均扫掠角度的扫描线的分布。 当结构以跨音速移动时; 在其表面附近形成冲击，并且冲击震荡扰乱冲击（9），以减小其扫掠角度。

公开(公告)号：US08979018B2

公开(公告)日：2015-03-17

申请号：US13687483

申请日：2012-11-28

申请人： The Boeing Company

发明人： William Pflug ,  Brian J. Tillotson

IPC分类号： B64C23/04 ,  B64C3/10 ,  B64C5/00 ,  B64C30/00 ,  B64D1/02 ,  B64D7/00 ,  B64D27/16 ,  B64D29/00 ,  F42B10/04

CPC分类号： B64C23/04 ,  B64C3/10 ,  B64C5/00 ,  B64C30/00 ,  B64D1/02 ,  B64D7/00 ,  B64D27/16 ,  B64D29/00 ,  F42B10/04

摘要： An air vehicle having a bilaterally asymmetric configuration for reducing wave drag may include a body having a longitudinal axis. The air vehicle may further include longitudinally offset engine nacelles, asymmetrically lengthened engine nacelles, and/or longitudinally offset protruding aerodynamic surfaces for reducing wave drag.

摘要翻译： 具有用于减少波浪阻力的双向不对称构造的空中车辆可以包括具有纵向轴线的主体。 空中飞行器还可以包括纵向偏移的发动机机舱，不对称延长的发动机舱和/或纵向偏移的突出的空气动力学表面，用于减少波浪阻力。

公开(公告)号：US08727286B2

公开(公告)日：2014-05-20

申请号：US13523761

申请日：2012-06-14

申请人： Joseph S. Silkey ,  Philip Smereczniak

发明人： Joseph S. Silkey ,  Philip Smereczniak

IPC分类号： B64C23/04

CPC分类号： B64C23/005 ,  B64C2230/04 ,  B64C2230/12 ,  F15D1/12 ,  Y02T50/166

摘要： Systems and methods for controlling air vehicle boundary layer airflow are disclosed. Representative methods can include applying electrical energy bursts and/or other energy bursts in nanosecond pulses in the boundary layer along a surface of an air vehicle. In a particular embodiment, electrical energy is discharged into the boundary layer to reduce the tendency for the boundary layer to separate and/or to reduce the tendency for the boundary layer to transition from laminar flow to turbulent flow. Representative actuators discharging the energy can be arranged in a two-dimensional array of individually addressable actuators.

摘要翻译： 公开了用于控制飞行器边界层气流的系统和方法。 代表性的方法可以包括沿着空中交通工具的表面在边界层中以纳秒脉冲施加电能脉冲串和/或其他能量脉冲串。 在特定实施例中，电能被排放到边界层中以减少边界层分离和/或降低边界层从层流向湍流转变的趋势。 排出能量的代表性执行器可以被布置成可独立寻址的致动器的二维阵列。