| 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 | Temperature Sensitive Self Actuated Heat Boundary Layer Control Device | US15404810 | 2017-01-12 | US20180194456A1 | 2018-07-12 | Gene Arthur Quandt; Matthew James Hemsath; Tracy L. Duvall; David Brian Christman; Frederick T. Calkins |
| A method and apparatus for a boundary layer control device located relative to an aircraft structure. The boundary layer control device has a stowed position and a deployed position. The boundary layer control device moves from the stowed position to the deployed position. A thickness of a boundary layer for the aircraft structure increases in a manner that increases a distance of a heat flow field from the aircraft structure during operation of the aircraft. | ||||||
| 162 | Virtual aerodynamic surface systems | US14083077 | 2013-11-18 | US09994301B2 | 2018-06-12 | Teresa M. Kruckenberg; Vijay V. Pujar; Robert L. Braden |
| A method of generating a pressure wave proximate an airflow surface and altering airflow to promote a localized lowering of skin friction over the airflow surface is described herein. A series of pressure waves may be configured to create a virtual riblet to control turbulent vortices in a boundary layer adjacent to the airflow surface creating a virtual riblet. The pressure waves may be configured to prevent disruption of the flow of air relative to at least one of a step or a gap associated with the airflow surface. The pressure wave generating system may be comprised of at least one of a thermoacoustic material, a piezoelectric material and a semiconductor material, and a microelectric circuit. | ||||||
| 163 | AIRCRAFT HAVING A DRAG COMPENSATION DEVICE BASED ON A BOUNDARY LAYER INGESTING FAN | US15820593 | 2017-11-22 | US20180148162A1 | 2018-05-31 | Bernd Trahmer |
| An aircraft includes a fuselage having a tapered rear shape, a landing gear for moving the aircraft on a runway, a wing attached to the fuselage, at least a main engine for providing a main thrust and a rear fan, wherein the rear fan is attached to a tail section of the fuselage, wherein the aircraft is designed for conducting a take-off rotation around the landing gear during take-off from the runway, such that the tail section of the fuselage approaches the runway, wherein the rear fan is an open fan having fan blades extending in a radial direction to a longitudinal axis of the fuselage, wherein the fan blades are dimensioned to equal at least a boundary layer thickness of the flow along the fuselage and to be smaller than the gap between the runway and the tail section of the fuselage during the take-off rotation. | ||||||
| 164 | Spin resistant aircraft configuration | US15090945 | 2016-04-05 | US09926071B2 | 2018-03-27 | Matthew Gionta; Jon Karkow; John Roncz; Dieter Koehler; David Lednicer |
| A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft. | ||||||
| 165 | AIRCRAFT HAVING AN AFT ENGINE | US15271776 | 2016-09-21 | US20180079514A1 | 2018-03-22 | Kishore Ramakrishnan; Jixian Yao; Nikolai N. Pastouchenko; Ivan Malcevic |
| An aircraft is provided including a fuselage that extends along a longitudinal direction between a forward end and an aft end. A boundary layer ingestion fan is mounted to the fuselage at the aft end and is configured for ingesting boundary layer airflow off the surface of the fuselage. The fuselage defines a profile proximate the boundary layer ingestion fan that is optimized for ingesting a maximum amount of boundary layer air and improving propulsive efficiency of the aircraft. More specifically, the fuselage defines a cross sectional profile upstream of the boundary layer ingestion fan that has more cross sectional area in a top half relative to a bottom half as defined relative to a centerline of the boundary layer ingestion fan. | ||||||
| 166 | BIOMIMETIC AIRFOIL BODIES AND METHODS OF DESIGNING AND MAKING SAME | US15689831 | 2017-08-29 | US20180057141A1 | 2018-03-01 | David E. Shormann |
| An airfoil body may include a plurality of tubercles along a leading edge of the airfoil body and a plurality of crenulations along a trailing edge of the airfoil body, wherein at least one of a position, a size, and a shape of the plurality of tubercles and the plurality of crenulations varies in a non-periodic fashion. The non-periodic fashion may be according to a Fibonacci function and may mimic the configuration of a pectoral fin of a humpback whale. The tubercles and crenulations may be defined with respect to a pivot point. The spanwise profile, including the max chord trailing edge curvature, may closely follow divine spirals and related Fibonacci proportions. The spanwise chord thickness may vary in a nonlinear pattern. Related methods are also described. | ||||||
| 167 | STABILIZER ASSEMBLY FOR AN AIRCRAFT AFT ENGINE | US15191586 | 2016-06-24 | US20170369152A1 | 2017-12-28 | Jixian Yao; Andrew Breeze-Stringfellow |
| The present disclosure is directed to an aerodynamic stabilizer assembly for stabilizing an aft fan mounted to a fuselage of an aircraft. For example, the stabilizer assembly includes one or more generally horizontal stabilizers for mounting to a nacelle of the aft fan and the fuselage so as to stabilize the aft fan. Each of the generally horizontal stabilizers includes an inner portion and an outer portion. As such, the inner portions are mounted to a nacelle of the aft fan and the fuselage at a predetermined downward angle with respect to a central axis of the aft fan so as to direct airflow upwards and into the aft fan, the outer portion being mounted to the inner portion. | ||||||
| 168 | Protective finish for wing tip devices | US13887211 | 2013-05-03 | US09845162B2 | 2017-12-19 | Darrell D. Campbell, Jr. |
| The present disclosure provides a system, method, and apparatus for a protective finish for an airfoil. In one or more embodiments, the disclosed method involves providing a sheath, and applying the sheath to the surface of the airfoil. In one or more embodiments, the sheath wraps around the surface of the airfoil from the leading edge of the airfoil towards the trailing edge of the airfoil. In at least one embodiment, the sheath covers approximately 50 percent to approximately 70 percent of the chord length of the airfoil. In some embodiments, the sheath is manufactured from at least one polymer, such as a polyurethane and/or a floropolymer. In one or more embodiments, the airfoil is a winglet, a raked wing tip, and/or a wing. | ||||||
| 169 | SYNCHRONIZATION OF FLUIDIC ACTUATORS | US15653557 | 2017-07-19 | US20170313411A1 | 2017-11-02 | Avraham SEIFERT; Isaac DAYAN; Tom SHTENDEL |
| A fluidic system is disclosed. The system comprises a plurality of fluidic oscillatory actuators, and at least one synchronization conduit connecting two or more of the actuators such as to effect synchronization between oscillations in the two or more connected actuators. | ||||||
| 170 | Mitigating shock using plasma | US14936953 | 2015-11-10 | US09725159B2 | 2017-08-08 | Mark Joseph Clemen, Jr.; Donald V. Drouin, Jr.; Alan F. Stewart |
| A method, apparatus, and system for mitigating undesired effects of a vehicle traveling at a speed greater than a critical Mach number for the vehicle. Ultraviolet energy is generated using a plurality of ultraviolet energy sources associated with an interior structure of the vehicle that travels at the speed greater than the critical Mach number for the vehicle. The ultraviolet energy is transported from the plurality of ultraviolet energy sources past an exterior of the vehicle around a selected location of the vehicle. A plasma is created around the selected location to mitigate the undesired effects of the vehicle traveling at the speed greater than the critical Mach number for the vehicle. | ||||||
| 171 | Synchronization of fluidic actuators | US14354579 | 2012-10-25 | US09718538B2 | 2017-08-01 | Avraham Seifert; Isaac Dayan; Tom Shtendel |
| A fluidic system is disclosed. The system comprises a plurality of fluidic oscillatory actuators, and at least one synchronization conduit connecting two or more of the actuators such as to effect synchronization between oscillations in the two or more connected actuators. | ||||||
| 172 | Devices, systems and methods for passive control of flow | US14199899 | 2014-03-06 | US09567056B2 | 2017-02-14 | Siegfried Hermann Zerweckh; Michael Rudolf Ruith; Steven James Ruther; Pritesh Chetan Mody |
| Systems, devices and methods are disclosed for controlling the flow of a fluid over the window of an optical instrument housing in a freestream flow field. For example, the flow upstream of the housing may be split to create a flow region over the window that is conducive to successful operation of the instrument. The flow region may be maintained for various rotations of the housing about yaw, pitch, and roll axes. The disclosed features in some embodiments induce flow regions with reduced spatial and temporal density gradients of the flow over the window. | ||||||
| 173 | Plasma optimized aerostructures for efficient flow control | US11710750 | 2007-02-26 | US09541106B1 | 2017-01-10 | Mehul Patel; Thomas Corke; Alan B. Cain |
| The present invention relates to a method of designing or optimizing a control surface for use with plasma actuators for controlling an aircraft, missile, munition or automobile, and more particularly to controlling fluid flow across their surfaces or other surfaces using plasma actuators, which would benefit from such a method. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and automobiles. The method of flow control also provides a means for reducing aircraft, missile's, munition's and automobile's power requirements. These methods also provide alternate means for aerodynamic control using low-power hingeless plasma actuator devices. | ||||||
| 174 | AIRCRAFT | US15135040 | 2016-04-21 | US20160332741A1 | 2016-11-17 | Matthew MOXON |
| An aircraft including trailing edge flaps, a wing mounted propulsor positioned such that the flaps are located in a slipstream of the first propulsor in use when deployed. The aircraft further including a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor includes a ducted fan configurable between a first mode, in which the fan provides net forward thrust to the aircraft, and a second mode in which the fan provides net drag to the aircraft. The fan is positioned to ingest a boundary layer airflow in use when operating in the first mode. | ||||||
| 175 | BOUNDARY LAYER CONTROL ASSEMBLY FOR AN AIRCRAFT AIRFOIL AND METHOD OF CONTROLLING A BOUNDARY LAYER | US14610547 | 2015-01-30 | US20160221664A1 | 2016-08-04 | Ray-Sing Lin; Thomas G. Tillman; Chad M. Henze |
| A boundary layer control assembly for an aircraft airfoil includes a leading edge and a trailing edge spaced from the leading edge to form a chord length. The boundary layer control assembly also includes a heating element disposed proximate the leading edge to heat a boundary layer formed along the surface of the aircraft airfoil. | ||||||
| 176 | OPTICAL WINDOW SYSTEM WITH AERO-OPTICAL CONDUCTIVE BLADES | US14330493 | 2014-07-14 | US20160009360A1 | 2016-01-14 | David A. Vasquez; Michael Ushinsky; Joseph J. Ichkhan |
| A method of improving optical characteristics of an optical window operating in a flow of fluid and having first and second panes of optically transmissive material—each having an edge adjacent to, parallel with, and at least partially coextensive with each other—is described herein. The method includes inserting a thermally conductive blade between two adjacent edges of the first and second panes of optically transmissive material; and lifting an adverse flow stagnation zone forward of the optical window by protruding the thermally conductive blade into the flow of fluid from an outer surface of the panes of the optical window. | ||||||
| 177 | DEVICES, SYSTEMS AND METHODS FOR PASSIVE CONTROL OF FLOW | US14199899 | 2014-03-06 | US20150251745A1 | 2015-09-10 | Siegfried Hermann Zerweckh; Michael Rudolf Ruith; Steven James Ruther; Pritesh Chetan Mody |
| Systems, devices and methods are disclosed for controlling the flow of a fluid over the window of an optical instrument housing in a freestream flow field. For example, the flow upstream of the housing may be split to create a flow region over the window that is conducive to successful operation of the instrument. The flow region may be maintained for various rotations of the housing about yaw, pitch, and roll axes. The disclosed features in some embodiments induce flow regions with reduced spatial and temporal density gradients of the flow over the window. | ||||||
| 178 | Active flow control on a vertical stabilizer and rudder | US12903720 | 2010-10-13 | US09090326B2 | 2015-07-28 | Edward A. Whalen; Mark I. Goldhammer |
| Systems and methods described herein provide for the control of airflow over a vertical control surface of an aircraft to enhance the forces produced by the surface. According to one aspect of the disclosure provided herein, the vertical control surface of the aircraft is engaged by active flow control actuators that interact with the ambient airflow to alter one or more characteristics of the airflow. An actuator control system detects a flow control event, and in response, activates the active flow control actuators to alter the airflow. According to various aspects, the flow control event is associated with a separation of the airflow, which is corrected through the activation of the appropriate active flow control actuators, increasing the forces produced by the vertical control surface of the aircraft. | ||||||
| 179 | Method and system for sensor-based intelligent sails | US13662633 | 2012-10-29 | US08869725B2 | 2014-10-28 | Mikko Brummer |
| Systems, methods and computer program products for sensor-based sailboat sails, including a device to detect whether a flow on a sail is attached or separated including a flow separation sensor; a device using data from the separation sensor to trim the sail; a wind history device for storing a history of wind conditions on the sail; a UV-exposure sensor for measuring UV-exposure on the sail; an acceleration sensor to measure an attitude of the sail; a stress or strain sensor to measure stretch and loading of the sail; an energy supply to provide energy to the sensors; and a data display to show data from the sensors to a user. | ||||||
| 180 | SYNCHRONIZATION OF FLUIDIC ACTUATORS | US14354579 | 2012-10-25 | US20140284430A1 | 2014-09-25 | Avraham Seifert; Isaac Dayan; Tom Shtendel |
| A fluidic system is disclosed. The system comprises a plurality of fluidic oscillatory actuators, and at least one synchronization conduit connecting two or more of the actuators such as to effect synchronization between oscillations in the two or more connected actuators. | ||||||
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