公开(公告)号：EP1478569B1

公开(公告)日：2009-09-23

申请号：EP03707587.6

申请日：2003-01-30

申请人： Gulfstream Aerospace Corporation

发明人： HENNE, Preston ,  HOWE, Donald ,  WOLZ, Robert ,  HANCOCK, Jimmy, Jr.

IPC分类号： B64C23/04 ,  B64C30/00

CPC分类号： B64C23/04 ,  B64C30/00

摘要： Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region therebetween and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle.

公开(公告)号：EP1710156A2

公开(公告)日：2006-10-11

申请号：EP06425228.1

申请日：2006-04-03

申请人： Lockheed Martin Corporation

发明人： Miller, Daniel N. ,  Young, David D.

IPC分类号： B64C23/04 ,  F15D1/12

CPC分类号： F15D1/12 ,  B64C21/04 ,  B64C23/00 ,  B64C23/04 ,  B64C2230/18 ,  Y02T50/166

摘要： The present invention provides flow field control techniques that adapt the aft body region flow field to eliminate or mitigate the development of massive separated flow field zones and associated unsteady vortical flow field structures. Embodiments of the present invention use one or more distributed arrays of flow control devices (submerged in the boundary layer) to create disturbances in the flow field that inhibit the growth of larger vortical structures and/or to energize the aft body shear layer to keep the shear layer attached the aft body surface. These undesirable aerodynamic phenomena produce increased vehicle drag which harms vehicle range, persistence, and loiter capabilities. Additionally, the unsteady nature of the turbulent vortical structures shed in the aft body wake region may produce increased dynamic buffeting and aft body heating by entraining nozzle jet exhaust (a.k.a. jet wash) - requiring additional structural support, shielding, and vehicle weight.

摘要翻译： 本发明提供流场控制技术，其适应尾部本体区域流场以消除或减轻块状分离流场区域和相关联的不稳定涡流流场结构的发展。 本发明的实施例使用流控制装置的一个或多个分布式阵列（浸没在边界层中）以在流场中产生干扰，其抑制较大涡旋结构的生长和/或激励后体剪切层以保持 剪切层附接在尾部本体表面上。 这些不合要求的空气动力学现象会产生增加的车辆阻力，从而损害车辆的行驶范围，持久性和空闲能力。 此外，尾部尾部尾流区域中的湍流旋涡结构的不稳定性质可通过夹带喷嘴喷射排气（也称为喷射清洗）产生增加的动态抖振和尾部本体加热 - 需要额外的结构支撑，屏蔽和车辆重量。

公开(公告)号：EP1373066A1

公开(公告)日：2004-01-02

申请号：EP02718318.5

申请日：2002-03-26

申请人： BAE Systems PLC

发明人： SCOTT, Simon, JosephBae Systems (Operations) Ltd ,  JOHNSON, Graham, A.Bae Systems (Operations) Ltd ,  THORNTON, Edward

IPC分类号： B64C21/00 ,  B64C23/04 ,  B64C21/10 ,  F15D1/12

CPC分类号： B64C23/005 ,  B64C23/04 ,  B64C2230/02 ,  B64C2230/12 ,  F05D2270/172 ,  F15D1/12 ,  Y02T50/166

摘要： The present invention relates to apparatus (3) for influencing fluid flow over a surface (1), and more particularly, but not exclusively, to turbulent boundary layer flow drag reduction for an aircraft. The present invention provides such apparatus including a plasma generator (7) comprising first (7) and second (9) spaced-apart independently controllable electrodes operable to cause a change in direction of the flow of the fluid over the surface.

公开(公告)号：EP0681544A4

公开(公告)日：1996-05-08

申请号：EP93918117

申请日：1993-05-25

申请人： TRACY RICHARD RIPLEY

发明人： TRACY RICHARD RIPLEY

IPC分类号： B64C3/14 ,  B64C23/04 ,  B64C30/00 ,  B64C3/10

CPC分类号： B64C3/14 ,  B64C23/04 ,  B64C30/00 ,  Y02T50/12

摘要： A supersonic flight aircraft having a longitudinally forwardly extending axis in the direction of flight, and a wing (11, 12) comprising a wing (11, 12) extending generally laterally relative to the axis, and having a leading edge (13, 14) angled forward or rearwardly relative to a normal to the axis at an angle (Μ), and the wing (11, 12) having a maximum thickness (t); the angle (Μ) and thickness (t) characterized in that in supersonic flight conditions, the forwardmost shock wave produced in association with the wing (11, 12) extends generally along or rearwardly of the leading edge (13, 14) whereby laminar airflow conditions are maintained over the leading edge (13, 14) and adjacent the surface of the wing (11, 12).

公开(公告)号：EP0120009A4

公开(公告)日：1986-01-20

申请号：EP83900088

申请日：1982-09-30

申请人： BOEING CO

发明人： VANDERHOEVEN ANTONIUS JOHANNES

IPC分类号： B64C7/02 ,  B64C23/04 ,  B64D27/00 ,  B64C1/38

CPC分类号： B64C23/04 ,  B64C7/02 ,  B64D27/00

摘要： A wing-mounted pod (30) for preventing an unstable increase in the pitching moment of a swept-wing aircraft due to increasing speed and angle of attack. This invention is for use on a swept-wing aircraft of the type having nonlinear, unstable increase in its pitching moment due to a loss of lift at the outboard wing (16) above a predetermined angle of attack at high Mach numbers. For an aircraft having a single, strut-mounted engine (26, 29) on each wing, the pod (30) is placed along the intersection of the upper surface of the wing (12) and the inboard side of the engine mounting strut (26). The pod (30) prevents an increase in the pitching moment by inducing the formation of a shock (S) in the air flowing over the upper surface of the inboard wing (14) at the same angle of attack at which the outboard wing (16) loses lift. The shock causes localized flow separation on the inboard wing, thereby preventing the increase in pitching moment otherwise experienced by the aircraft.

公开(公告)号：EP4190695B1

公开(公告)日：2024-05-08

申请号：EP22183853.5

申请日：2022-07-08

IPC分类号： B64C30/00 ,  B64C21/02 ,  B64C23/04 ,  B64C3/14

CPC分类号： B64C2003/14920130101 ,  B64C30/00 ,  B64C21/02 ,  B64C23/04 ,  B64C3/14 ,  Y02T50/10

公开(公告)号：EP3868650A1

公开(公告)日：2021-08-25

申请号：EP21153194.2

申请日：2021-01-25

申请人： Mitsubishi Heavy Industries, Ltd.

发明人： NAGASHIKI, Mayuko

IPC分类号： B64C3/30 ,  B64C3/46 ,  B64C23/04 ,  B64C3/44

摘要： Problem
A shock wave suppression device (10) and an aircraft (1) capable of suitably reducing drag on a blade surface are provided.
Solving Means
A shock wave suppression device (10) is configured to suppress a shock wave generated on a blade surface (3a) of a blade (3), the shock wave suppression device including a bump cover (13) provided to follow the blade surface and deformable to protrude outward from the blade surface, and a displacing unit (14) configured to displace the bump cover between a steady state to follow the blade surface and a deformed state to protrude outward from the blade surface. The bump cover has a curved shape in the deformed state configured to be a continuous surface from an upstream side to a downstream side in a flow direction of a fluid flowing through the blade surface.

公开(公告)号：EP3778389A1

公开(公告)日：2021-02-17

申请号：EP19775252.0

申请日：2019-02-21

申请人： Japan Aerospace Exploration Agency

发明人： YUHARA, Tatsunori

IPC分类号： B64C30/00 ,  B64C23/04

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：EP2250088B1

公开(公告)日：2016-01-06

申请号：EP09715682.2

申请日：2009-02-17

申请人： Airbus Operations Limited

发明人： WOOD, Norman

IPC分类号： B64C23/04

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

公开(公告)号：EP2873609A1

公开(公告)日：2015-05-20

申请号：EP14183188.3

申请日：2014-09-02

申请人： The Boeing Company

发明人： Griffin, Steven F.

IPC分类号： B64C23/04

CPC分类号： F01N1/02 ,  B64C23/04

摘要： A synthetic jet muffler (200) includes an exit end (210), a propagation path (215) for conducting a first sound wave (220) emitted by a synthetic jet generator (225) to the exit end (210), and a shroud (240) for conducting a second sound wave (245) emitted from the synthetic jet generator (225) in a direction opposite to the first sound wave (220) to the exit end (210), wherein the shroud (240) is disposed so that the first and second sound waves (220, 245) travel different distances to effect noise cancellation at the exit end (210).

摘要翻译： 合成射流消音器（200）包括出口端（210），用于将由合成射流发生器（225）发射的第一声波（220）传导到出射端（210）的传播路径（215） （240），用于将与所述合成射流发生器（225）相反的第二声波（245）沿与所述第一声波（220）相反的方向传导到所述出口端（210），其中所述护罩（240） 第一和第二声波（220,245）行进不同的距离以在出口端（210）处实现噪声消除。