| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | METHOD AND APPARATUS FOR CONTROLLING FLOW ABOUT A TURRET | US12842534 | 2010-07-23 | US20120018004A1 | 2012-01-26 | Alan Z. Ullman |
| Methods and apparatus are provided to control flow separation of an ambient flow along a surface and about a turret, such as by reducing flow separation aft of the turret. By reducing flow separation, the resulting turbulence may be similarly reduced such that the performance of a system, such as a laser system, housed by the turret may be improved. To reduce flow separation, a motive flow may be provided by ejector nozzles that open through the surface and are positioned proximate to and aft of the turret relative to the ambient flow. The motive flow has a greater velocity than the ambient flow to thereby create a region aft of the turret of reduced pressure relative to an ambient pressure. Within this region of reduced pressure aft of the turret, a portion of the ambient flow mixes with the motive flow, thereby reducing or eliminating flow separation. | ||||||
| 162 | Supersonic aircraft for reducing sonic boom effects at ground level | US11754276 | 2007-05-26 | US08083171B2 | 2011-12-27 | Preston A. Henne; Donald C. Howe; Robert R. Wolz; Jimmy L. Hancock, Jr. |
| Method for configuring and operating an aircraft for minimizing sonic boom effects at ground level during supersonic flight of the aircraft. The method includes configuring an aircraft and flying the aircraft at supersonic speed so that in the supersonic flight, a lower profile of the aircraft is presented and generally groundwardly directed; and generating multiple different magnitude pressure disturbances below the aircraft, and radiating therebelow, and controlling the different magnitude pressure disturbances generated below the aircraft so that differentials thereamong are sufficiently minimized that ground level sonic boom effects are minimized during the supersonic flight. | ||||||
| 163 | Shock wave modification method and system | US12656029 | 2010-01-13 | US08079544B2 | 2011-12-20 | Kevin Kremeyer |
| 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 laser pulses 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 a timer 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. | ||||||
| 164 | AIRCRAFT FAIRING | US13127606 | 2008-11-05 | US20110204185A1 | 2011-08-25 | Neil John Lyons |
| A shock control fairing for mounting a junction between adjoining aircraft surfaces. The fairing has a cross-sectional profile which varies along the length of the fairing. The cross-sectional profile of the fairing has a maximum area at a location which, when mounted to an aircraft, is substantially proximal to a location on the surface of the aircraft at which a shock would be expected to develop without the fairing. | ||||||
| 165 | Shock wave modification method and system | US12656029 | 2010-01-13 | US20110148717A1 | 2011-06-23 | Kevin Kremeyer |
| 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 laser pulses 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 a timer 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. | ||||||
| 166 | Supersonic aircraft footprint spreading control system and method | US11403253 | 2006-04-12 | US07861966B2 | 2011-01-04 | Scott Rethorst |
| A method and system to optimize the process a spreading the weight of supersonic aircraft downstream over a large area to reduce the pressure and intensity on the ground as function of air flow velocity, temperature, and/or pressure is provided. | ||||||
| 167 | AERODYNAMIC STRUCTURE WITH SERIES OF SHOCK BUMPS | US12735535 | 2009-02-17 | US20100301172A1 | 2010-12-02 | Norman Wood |
| 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. | ||||||
| 168 | SHOCK BUMP ARRAY | US12735534 | 2009-02-17 | US20100301171A1 | 2010-12-02 | Norman Wood |
| An aerodynamic structure comprising an array shock bumps (3, 10) extending from its surface, the array comprising: a first series of shock bumps; and one or more shock bumps positioned aft of the first series. Preferably at least one of the one or more shock bumps positioned aft of the first series is offset so that it is not positioned directly aft of any of the shock bumps in the first series. By providing an array of shock bumps instead of a single line, the first series of shock bumps and the one or more shock bumps positioned aft of the first series can be positioned to modify the structure of a shock which forms under a different respective condition. | ||||||
| 169 | Shock wave modification method and system | US11288425 | 2005-11-29 | US07648100B2 | 2010-01-19 | Kevin Kremeyer |
| 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; mechanism for transferring the information to or from the body; and device 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. | ||||||
| 170 | Supersonic aircraft footprint spreading control system and method | US11403253 | 2006-04-12 | US20090206207A1 | 2009-08-20 | Scott Rethorst |
| A method and system to optimize the process a spreading the weight of supersonic aircraft downstream over a large area to reduce the pressure and intensity on the ground as function of air flow velocity, temperature, and/or pressure is provided. | ||||||
| 171 | Supersonic flight vehicle | US06252230 | 1981-03-31 | US07392963B1 | 2008-07-01 | Stanley Leek; Hugh R. Joiner; Brian R. Caro |
| A supersonic guided weapon has radiation sensitive apparatus carried behind a radiation transparent window the window being formed within an open recess in the weapon nose, the recess being such that at supersonic speeds it forms shock waves which trap air within the recess to provide a measure of kinetic heat insulation for the window and also a minimum of supersonic drag. An elongate nose region can be provided ahead of the recess to house further radiation sensitive or radiation emitting apparatus. | ||||||
| 172 | Shock wave modification method and system | US11288425 | 2005-11-29 | US20070040726A1 | 2007-02-22 | Kevin Kremeyer |
| 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 means 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; means for transferring the information to or from the body; and means 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. | ||||||
| 173 | Canard position and dihedral for boom reduction and pitch/directional control | US11147636 | 2005-06-07 | US20060237580A1 | 2006-10-26 | Robert Cuccias; John Morgenstern; Alan Arslan; Howard Lee |
| A supersonic aircraft comprises a fuselage extending forward and aft, wings coupled to lateral sides of the fuselage, and canards coupled to lateral sides of the fuselage forward of the wings. The individual canards are configured to generate shocks that wrap around the fuselage and intersect with wing leading edges on opposing sides of the fuselage. | ||||||
| 174 | Methods and systems for controlling lower surface shocks | US10815147 | 2004-03-31 | US20060060720A1 | 2006-03-23 | David Bogue |
| Methods and systems for controlling shocks on airfoil lower surfaces are disclosed. An airfoil in accordance with one embodiment of the invention includes an upper surface portion having an upper surface positioned to face generally upwardly during the level flight, and a lower surface portion having a leading edge region, a trailing edge region and a lower surface positioned to face generally downwardly during level flight. A shock control protrusion extends away from the lower surface and is positioned to generate a shock extending away from the lower surface at a least one flight condition. | ||||||
| 175 | Shock wave modification method and system | US10705232 | 2003-11-12 | US20050061908A1 | 2005-03-24 | Kevin Kremeyer |
| A shock wave in a gas is modified by emitting energy to form an extended path in the gas; heating gas along the path to form a volume of heated gas expanding outwardly from the path; and directing a path. The volume of heated gas passes through the shock wave and modifies the shock wave. This eliminates or reduces a pressure difference between gas on opposite sides of the shock wave. Electromagnetic, microwaves and/or electric discharge can be used to heat the gas along the path. This application has uses in reducing the drag on a body passing through the gas, noise reduction, controlling amount of gas into a propulsion system, and steering a body through the gas. An apparatus is also disclosed. | ||||||
| 176 | Canard position and dihedral for boom reduction and pitch/directional control | US10652128 | 2003-08-29 | US20050045764A1 | 2005-03-03 | John Morgenstern; Alan Arslan; Howard Lee; Robert Cuccias |
| A supersonic aircraft comprises the fuselage extending forward and aft along a longitudinal axis, a wing coupled to the fuselage, and a canard. The canard is coupled onto the fuselage forward of the wing at an elevated position that enables stretching of the aircraft lifting length and forms an effective area distribution to attain a shaped sonic boom signature. | ||||||
| 177 | Supersonic aircraft with spike for controlling and reducing sonic boom | US10104403 | 2002-03-22 | US06698684B1 | 2004-03-02 | Preston A. Henne; Donald C. Howe; Robert R. Wolz; Jimmy L. Hancock, Jr. |
| An aircraft includes a spike projecting forward from the leading end of the fuselage and/or rearward from the trailing end of the fuselage. The spike can include a single section or two or more sections of varying cross-sectional area. Transition regions between sections of varying cross-sectional area are located and shaped to reduce coalescence of shock waves created thereby during supersonic flight. The spike can be collapsible and can be retracted into the fuselage. The spike can have a cross-sectional shape wherein the nose thereof lies on a line formed by the intersection of the bottom of the spike with a plane tangent to the bottom of the spike. A spike thus shaped causes an asymmetric pressure distribution during supersonic flight, wherein the ground-directed pressure contour is of lesser magnitude than the pressure contour propagating in other directions. | ||||||
| 178 | Shock ( Wave) Absorber | US10198369 | 2002-07-18 | US20030146341A1 | 2003-08-07 | Eric Thomas Schmidt |
| The Shock Wave Absorber is an inverted, rotated sinusoidal form inserted in the foremost tip of a vessel traveling in a fluid, with an opening to the nose, which provides orientation for turbulent air, water, etc . . . | ||||||
| 179 | Passive aerodynamic sonic boom suppression for supersonic aircraft | US09499654 | 2000-02-08 | US06588703B1 | 2003-07-08 | Tom Hartmann |
| Sonic boom suppression apparatus for an aircraft including a nose portion having convex upper surfaces and a flat underside, slotted portions on the fuselage or wings of the aircraft, shock cancellation surfaces incorporated in the engine portion of the aircraft, and area/lift distribution tailoring, all of which are preferably used concomitantly. | ||||||
| 180 | Jet actuators for aerodynamic surfaces | US09742489 | 2000-12-22 | US06471477B2 | 2002-10-29 | Ahmed A. Hassan; David B. Domzalski |
| A jet actuator positioned within a hollow space in an aerodynamic structure for controlling the flow over an aerodynamic surface thereof includes a movable member linearly displaced by a voice coil mechanism and a flexible diaphragm defining a compression chamber open to the exterior of the aerodynamic surface through an orifice. Reciprocal displacement of the movable member changes the shape of the flexible diaphragm to alternately expel fluid (e.g., air) from and pull fluid into the compression chamber through the orifice. The movable member includes a pair of pistons joined by a cross element, one of the pistons being attached to the flexible diaphragm. In one embodiment, the flexible diaphragm comprises a bladder sealed around the orifice. The movable member is desirably made of composite material to reduce its inertia, and at least the piston attached to the flexible diaphragm may be stiffened with a composite laminate structure. Fluid intake to the compression chamber may be increased through the use of a one-way valve located either in the aerodynamic surface, or in the piston. In this regard, multiple flapper valves may surround the orifice in the aerodynamic surface for increased fluid ingestion. | ||||||
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