Class / Patent application number | Description | Number of patent applications / Date published |
244204000 | By controlling boundary layer | 89 |
20080251647 | System For Reducing Aerodynamic Noise At A Supplementary Wing Of An Aircraft - A system for reducing aerodynamic noise of a supplementary wing of an aircraft is provided. The supplementary wing is hinged to a main wing and is extendable when a gap region between the main wing and the supplementary wing is opened. The system includes a separating surface which can be moved into the gap region when the supplementary wing is extended and which extends at least partially along a separation flow line between a vortex flow region and a gap flow for the air flowing in the gap region. The separating surface is an n-stable surface which through an actuator device can be moved between at least one of the stable states and at least one additional state. | 10-16-2008 |
20090001222 | CONTROL OF AERODYNAMIC FORCES BY VARIABLE WETTED SURFACE MORPHOLOGY - Systems and methods for providing dynamic control to a vehicle in a dynamic fluid. The systems and methods of the invention relate to one or more morphable surfaces that can be controlled by a controller and an actuator in an active manner to provide asperities that interact with a fluid moving across the morphable surfaces. By controlling the size, shape and location of the asperities, one can exert control authority over the motion of the vehicle relative to the fluid, including a speed, a direction and an attitude of the vehicle. Examples of materials that provide suitable morphable surfaces include ionic polymer metal composites and shape memory polymers, both of which types of material are commercially available. Useful morphable surface systems have been examined and are described. | 01-01-2009 |
20090008505 | AIRCRAFT WITH A FLUID-DUCT-SYSTEM - An aircraft with a fluid-duct system for extraction of the laminar layer and/or blowing out of fluid at vulnerable places of the outer skin, wherein the fluid-duct system ( | 01-08-2009 |
20090020652 | WING LEADING EDGE HAVING VORTEX GENERATORS - An arrangement of devices as well as a method for improving the aerodynamics of an aircraft wing are disclosed. In embodiments, a plurality of vortex generators are attached in span-wise alignment on an deice boot along the wing's leading edge. The vortex generators are, in embodiments, constructed of a flexible material such that they are able to be expanded along with the boot during inflation and deflation thus mechanically involving the aerodynamic devices in the ice-shedding process. | 01-22-2009 |
20090065649 | STEERING OF VEHICLES THROUGH BOUNDARY LAYER CONTROL - In aeronautical devices where a fluid such as air flows over a surface ( | 03-12-2009 |
20090065650 | DYNAMIC ROUGHNESS FOR AERODYNAMIC APPLICATIONS - Systems and methods for providing dynamic control to a surface immersed in a dynamic fluid. The systems and methods of the invention relate to one or more morphable surfaces that can be control in an active manner to provide asperities that interact with a fluid moving across the morphable surfaces. By controlling the size, shape and location of the asperities, one can exert control authority over the motion of the surface relative to the fluid. Examples of materials that provide suitable morphable surfaces include ionic polymer metal composites and shape memory polymers, both of which types of material are commercially available. Useful morphable surface systems have been examined and are described. | 03-12-2009 |
20090173836 | Laser-based flow modification to remotely conrol air vehicle flight path - Systems, equipment, and methods to deposit energy to modify and control air flow, lift, and drag, in relation to air vehicles, and methods for seeding flow instabilities at the leading edges of control surfaces, primarily through shockwave generation through deposition of laser energy at a distance. | 07-09-2009 |
20090189023 | AERODYNAMIC HIGH-PERFORMANCE PROFILE FOR AIRCRAFT - Aerodynamic high-performance profile ( | 07-30-2009 |
20100243818 | Flying Object for Transonic or Supersonic Velocities - The invention relates to a flying object which moves with a transonic or supersonic velocity. The inventive flying object comprises a main body, a streaming element and a holding element. The holding element holds the streaming element distant from the main body. The streaming element is permeable for the airstream. For one embodiment the streaming element is built with a porous material. The streaming element has an outer surface with the shape of a cone or a truncated cone. The holding element holds the streaming element in an orientation with the cone opening towards the airstream. | 09-30-2010 |
20100270433 | Method and System For Global Flow Field Management Using Distributed, Surface-Embedded, Nano-Scale Boundary Layer Actuation - Systems and methods to provide distributed flow control actuation to manage the behavior of a global flow field, are provided. An example of a system can include an aerodynamic structure having an outer surface, and an array of a plurality of effectors connected to the outer surface of the aerodynamic structure to be in fluid contact with a flowing fluid when operationally flowing, to induce controlled, globally distributed disturbances at a viscous wall sublayer of a turbulent boundary layer of the flowing fluid when operationally flowing and to manipulate fluid behavior of the flowing fluid to thereby substantially reduce pressure loss associated with incipient separation of the fluid flow from portions of the aerodynamic structure. | 10-28-2010 |
20120286101 | HIGH-LIFT DEVICE, WING, AND NOISE REDUCTION STRUCTURE FOR HIGH-LIFT DEVICE - A high-lift device suppresses the occurrence of aerodynamic noise while minimizing an increase in airframe weight. The device includes a slat main body disposed to be able to extend from and retract into a main wing, and a concave part formed on the slat main body at a location facing the main wing and able to accommodate at least a part of a leading edge of the main wing. The device also includes an airflow control part disposed at an area in the concave part facing an upper surface of the main wing, that is accommodated between the main wing and the concave part when the slat main body is retracted into the main wing, and that suppresses turbulence colliding against the area in the concave part facing the upper surface of the main wing when the slat main body is extended from the main wing. | 11-15-2012 |
20150307184 | Laser-Based Flow Modification to Remotely Control Air Vehicle Flight Path - Systems, equipment, and methods to deposit energy to modify and control air flow, lift, and drag, in relation to air vehicles, and methods for seeding flow instabilities at the leading edges of control surfaces, primarily through shockwave generation through deposition of laser energy at a distance. | 10-29-2015 |
20160068257 | BOUNDARY LAYER CONTROL FOR THICKNESS AND CAMBER MORPHING OF AERODYNAMIC SURFACES - An aerodynamic structure and a method of boundary layer control for thickness and camber morphing of aerodynamic surfaces in the aerodynamic structure are disclosed. In one embodiment, smart material controlled slots are provided along chord length and span length of the aerodynamic surfaces and leading edges of moveable control surfaces. Further, fluid is distributed on the aerodynamic surfaces and the leading edges of moveable control surfaces through the provided smart material controlled slots to vary fluid thickness of a boundary layer such that free stream fluid paths are modified around the aerodynamic surfaces to achieve an apparent change in a camber and thickness. | 03-10-2016 |
244204100 | Actively controlled vortex generator | 6 |
20080217485 | Smart Vortex Generator, and Aircraft, Vessel, and Rotary Machine Being Equipped with the Same - A smart vortex generator including a main body, disposed on a body surface, such as a main wing of aircraft, making a boundary to a flow of fluid, and at least a part of which includes a shape memory alloy. A form of the main body, depending on a temperature increment/decrement of the fluid, changes between (1) a first form capable of suppressing a flow separation by a vortex generation and (2) a second form capable of suppressing a turbulent flow, by a phenomenon that the shape memory alloy undergoes a phase transformation between a high-temperature-side stable phase and a low-temperature-side stable phase. The smart vortex generator demonstrates a multi-directional characteristic depending on a temperature change, such that no energy supply from the outside is required. The structure is simple, and repairs and maintenance as well as installation to existing wings are easy. | 09-11-2008 |
20110101173 | Aircraft with Aerodynamic Lift Generating Device - An aircraft ( | 05-05-2011 |
20120256056 | OSCILLATORY VORTICITY GENERATOR AND APPLICATIONS THEREOF - An oscillatory vorticity generator device for controlling the flow on an aero- or hydrodynamic surface of an element, the oscillatory vorticity generator device comprising:
| 10-11-2012 |
20130009016 | RETRACTABLE VORTEX GENERATOR FOR REDUCING STALL SPEED - A device and methods for low speed performance improvement of a lifting surface assembly are disclosed. At least one vortex generator is coupled to the lifting surface assembly, and the vortex generator is extended through the lifting surface assembly by drooping a hinged leading coupled to the lifting surface assembly to increase lift. The vortex generator is retracted inside the lifting surface assembly to decrease drag. | 01-10-2013 |
20130037657 | VORTEX GENERATORS - A vortex generator, or an array of vortex generators, for attenuating flow separation during flow of fluid over a surface. Vortex generators include a base with a forward end and a leading edge extending outward and rearward from the forward end to an outward end. The leading edge includes a first angular discontinuity at a height H | 02-14-2013 |
20140284430 | SYNCHRONIZATION OF FLUIDIC ACTUATORS - 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. | 09-25-2014 |
244205000 | With ionic or electrostatic surface | 13 |
20090127401 | ION FIELD FLOW CONTROL DEVICE - Disclosed is a boundary layer control apparatus, and method, for controlling and adjusting the boundary layer of a fluid flowing over a surface. The apparatus and method operate by using ionic wind to propel the fluid within the boundary layer in a specified direction thereby either increasing or decreasing the boundary layer thickness. | 05-21-2009 |
20090159754 | ROTARY WING SYSTEM WITH ION FIELD FLOW CONTROL - A rotary-wing system which generates a directed ion field to propel a fluid along a rotary-wing to control at least one boundary layer characteristic. | 06-25-2009 |
20090173837 | SYSTEMS AND METHODS FOR CONTROLLING FLOWS WITH PULSED DISCHARGES - 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. In other embodiments, energy can be discharged via pulses having a pulse width of about 100 nanoseconds or less, and an amplitude of about 10,000 volts or more. Actuators discharging the energy can be arranged in a two-dimensional ray of individually addressable actuators. Energy can be delivered to the boundary layer via a laser emitter, and energy can be received in a receiver after having transited over at least a portion of the airflow surface. In another embodiment, high energy electrons can be injected into the boundary layer using a hollow cathode array at the airflow surface. In still another embodiment, energy can be introduced at the surface of the air vehicle at a rate sufficient to heat the flow and cause shock waves to propagate into the flow. | 07-09-2009 |
20090212164 | AIRFOIL TRAILING EDGE PLASMA FLOW CONTROL APPARATUS AND METHOD - A flow control system and method especially well adapted for use on a Coanda surface. In one embodiment a plurality of plasma actuators are disposed over a Coanda surface of a wing of an aircraft. The actuators are selectively energized to either delay the onset of boundary layer flow separation from the Coanda surface, or to promote flow separation. One embodiment discloses using dual mode plasma actuators on a Coanda surface. The system and method is applicable to a wide variety of aerodynamic surfaces where control over the separation of a boundary layer flow over a trailing edge surface is desired. | 08-27-2009 |
20100108821 | METHOD, APPARATUS, AND SYSTEM FOR DEFLECTING AIR APPROACHING A WING - Fluid having a velocity approaching a surface having a leading edge may be deflected. An electric field may be projected ahead of the leading edge of the surface to ionize at least some molecules of the fluid approaching the wing. The strength of the electric field may vary between a maximum level and a minimum level periodically over time. A magnetic field may be projected from the surface to deflect the ionized molecules of the fluid such that some or all of the deflection is normal to the velocity of the approaching fluid and normal to the leading edge of the surface while the electric field is below its maximum level. | 05-06-2010 |
20100133386 | PLASMA FLOW CONTROL ACTUATOR SYSTEM AND METHOD - A plasma actuator system and method especially well adapted for use on airborne mobile platforms, such as aircraft, for directional and/or attitude control. The system includes at least one plasma actuator having first and second electrodes mounted on a surface of an aircraft. The first and second electrodes are arranged parallel to a boundary layer flow path over the surface. A third electrode is mounted between the first and second electrodes and laterally offset from the first and second electrodes. A high AC voltage signal is applied across the first and third electrodes, which induces a fluid flow between the energized electrodes that helps to delay separation of the boundary layer. Applying the AC voltage across the second and third electrodes causes an induced fluid flow that creates the opposite effect of influencing the boundary layer flow to separate from the surface. A plurality of the actuators can be selectively placed at various locations on the aircraft, and selectively energized to provide directional control and/or attitude control over the aircraft. | 06-03-2010 |
20100224733 | Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft - An aircraft includes a surface over which an airflow passes. A plasma actuator is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma. | 09-09-2010 |
20100308177 | PLASMA ENHANCED RIBLET - An object moving through a fluid uses plasma to keep turbulent mixing vortices associated with turbulent air away from the majority of the surface of the object. The plasma may be used to enhance physical riblets, or the plasma may create a virtual riblet. | 12-09-2010 |
20110253842 | Laminated Plasma Actuator - A method and apparatus may comprise a first number of layers of a flexible material, a second number of layers of a dielectric material, a first electrode attached to a surface layer in the first number of layers, and a second electrode attached to a second layer in one of the first number of layers and the second number of layers. The first number of layers may be interspersed with the second number of layers. The first electrode may be configured to be exposed to air. The first electrode and the second electrode may be configured to form a plasma in response to a voltage. | 10-20-2011 |
20110272531 | DRAG REDUCTION THROUGH ION FIELD FLOW CONTROL - A boundary layer control system and method for controlling and adjusting the boundary layer of a fluid flowing over a surface. | 11-10-2011 |
20120074263 | Dynamically controlled cross flow instability inhibiting assembly - A cross flow instability inhibiting assembly generates periodic aerodynamic disturbances on a swept wing. The cross flow instability inhibiting assembly is dynamic in that it can be selectively turned on and off as needed. The cross flow instability inhibiting assembly is a strip of material separating a set of electrodes from a set of electrodes. When energized, the fields created between the electrodes and electrodes create plasma disturbances around the electrodes. The electric fields and plasma create heating and body force disturbances on the air or surrounding fluid. These plasma generated disturbances disrupt development of unstable voriticity due to cross flow, inhibiting transition to turbulent flow of the wing to which it is attached. The electrodes may be connected to electrical power in series or they may be connected to an alternating configuration. The system allows for various uses based on the design of the wing and the conditions in which the host aircraft is flying. | 03-29-2012 |
20120193483 | SYSTEM, APPARATUS, PROGRAM PRODUCT, AND RELATED METHODS FOR PROVIDING BOUNDARY LAYER FLOW CONTROL - Systems, apparatus, and program product and methods for controlling boundary layer flow across an aerodynamic structure which can produce separate regions of flow structures at different strengths by means of dielectric-barrier-discharge (DBD) type plasmas, are provided. An example of such apparatus provides plasma regions that are capable of being individually controlled by voltage and/or frequency, and modulated for the purposes of flow control. The apparatus includes an electrode assembly fitted with electrodes on either side of a dielectric such that different electrode geometries and arrangements create isolated regions of plasmas which results in separate regions of flow structures. These regions may be further controlled and modulated by the use of electronic-switching to produce irregularly shaped flow structures and strengths including those having a primarily vertical component. | 08-02-2012 |
20130001368 | SYSTEMS AND METHODS FOR CONTROLLING FLOWS WITH PULSED DISCHARGES - 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 it 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. | 01-03-2013 |
244206000 | With rotating member | 2 |
20110024574 | Aerodynamic Body And High-Lift System Comprising Such An Aerodynamic Body - An aerodynamic body with an outside with a top and bottom in relation to the direction of airflow, with lateral end parts that form the lateral ends of the aerodynamic body when viewed across the direction of airflow, where in the interior of the aerodynamic body a duct with an airflow drive with a drive motor and a compressor means that is driven by the aforesaid and that is arranged in the duct is arranged, with at least one inlet at the bottom and/or at at least one of the lateral end parts of the aerodynamic body and with at least one outlet at the top of the aerodynamic body for influencing the airflow at the aerodynamic body is arranged, where in the duct a sleeve is arranged which is rotatable by means of a drive motor, which sleeve includes at least one recess which at a particular rotational position of the sleeve can be made to at least in part coincide with the outlet at the top of the aerodynamic body so that the air that has been compressed by the compressor flows through the recess in the sleeve and through the outlet, as well as a high-lift system comprising such an aerodynamic body. | 02-03-2011 |
20160009364 | Fluid Boundary Layer Control | 01-14-2016 |
244207000 | With blowing | 37 |
20080272242 | Method for ensuring the safety of an aircraft flying horizontally at low speed - A method for ensuring the safety of an aircraft flying horizontally at low speed. | 11-06-2008 |
20090084905 | Aerodynamic Flap Of An Aircraft Having A Device Which Influences The Flap Vortex - A high-lift flap of an aircraft is provided having a device for influencing the flap vortex as well as a device for influencing the flap vortex at the lateral edge of the aerodynamic high-lift flap, which can be achieved effectively and at low cost. | 04-02-2009 |
20090108141 | METHOD AND APPARATUS FOR ENHANCING ENGINE-POWERED LIFT IN AN AIRCRAFT - Lift produced by an airfoil of an aircraft is increased by suppressing fluid detachment from the surface of the airfoil. An engine cowling extends outwardly from the surface of the airfoil that has an exit plane configured for directing exhaust gases toward a rear of the aircraft. Fences extending outwardly from the surface and proximate to the exit plane of the engine cowling are configured to guide the exhaust gases along at least a portion of the airfoil surface, thereby restricting spanwise movement of the gases and increasing the Coanda Effect exhibited by the gases, thereby increasing the amount of lift produced along the surface of the airfoil. Such techniques may be used in short take-off and landing (STOL) aircraft. | 04-30-2009 |
20090206207 | Supersonic aircraft footprint spreading control system and method - 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. | 08-20-2009 |
20090261206 | Method of using microjet actuators for the control of flow separation and distortion - A system for controlling unwanted flow separation. One or more microjets are placed to feed auxiliary fluid into a region of suspected flow separation. If the separation is intermittent, sensors can be employed to detect its onset. Once separation is developing, the microjets are activated to inject a stream of fluid into the separation region. This injected fluid affects the flow and serves to control the flow separation. A steady-state embodiment can be used to continuously fluid. On the other hand, sensors and a rapidly reactive control circuit can be used to inject fluid only when it is needed to inhibit flow separation. The sensors and control circuit can operate off of simple pressure gradient detection or predictive algorithms that anticipate when flow separation will occur. | 10-22-2009 |
20090289150 | BOUNDARY LAYER CONTROL SYSTEM AND METHODS THEREOF - An airfoil boundary layer control system may be provided. The airfoil boundary layer control system may include at least one airfoil that may include a first surface and a second surface coupled together at a leading edge and a trailing edge; at least one hollow chamber defined within the at least one airfoil; and an aperture defined in the airfoil and positioned substantially near the trailing edge, the aperture coupled in flow communication with the at least one hollow chamber; a pressure source coupled in flow communication with the at least one hollow chamber. | 11-26-2009 |
20090308980 | Method and system for fully fixed vehicle control surfaces - A fully fixed, non-articulating geometry vehicle that includes a number of virtual control surfaces operable to replicate a mechanical control surface's functionality. These virtual control surfaces further include a number of flow control devices on the non-articulating vehicle surface. The plurality of flow control surfaces is operable to induce secondary flow structure(s) within a boundary layer of a fluid flow over the non-articulating vehicle surface. A virtual control surface controller is operable to dynamically adjust a frequency and amplitude of the secondary flow structure(s) in order to reposition the virtual control surface. A vehicle control and stability system communicatively coupled to the plurality of virtual control surfaces is operable to direct positioning of the plurality of virtual control surfaces in response to vehicle control commands. | 12-17-2009 |
20100084514 | System and method to control flowfield vortices with micro-jet arrays - The present invention provides a system and method for actively manipulating and controlling aerodynamic or hydrodynamic flow field vortices within a fluid flow over a surface using micro-jet arrays. The system and method for actively manipulating and controlling the inception point, size and trajectory of flow field vortices within the fluid flow places micro-jet arrays on surfaces bounding the fluid flow. These micro-jet arrays are then actively manipulated to control the flow behavior of the ducted fluid flow, influence the inception point and trajectory of flow field vortices within the fluid flow, and reduce flow separation within the primary fluid flow. | 04-08-2010 |
20100243819 | DEVICE FOR DELAYING BOUNDARY LAYER SEPARATION - Device for delaying the separation of a boundary layer in flow of air ( | 09-30-2010 |
20100327120 | AIR OUTLET SYSTEM FOR AIRCRAFT LEADING EDGE - An aircraft leading edge is extended by an aerodynamic surface providing an aerodynamic flow and where air discharges are arranged preventing separation of the aerodynamic flow. The air discharges are arranged in at least two rows essentially parallel to the leading edge and in an offset manner for at least two consecutive rows. At least one block is inserted between two walls that form the aerodynamic surface. The block includes, on the one hand, an outside surface extending the aerodynamic surface, a first inclined surface contacting the first wall forming the aerodynamic surface, and a second inclined surface contacting the second wall that forms the aerodynamic surface, and, on the other hand, projecting and/or hollow shapes that are made at the inclined surfaces and that are arranged in an alternating fashion from one surface to the next, allowing air to pass on both sides of the aerodynamic surface. | 12-30-2010 |
20110031353 | DE-ICING SYSTEM FOR AN AIRCRAFT - The invention pertains to a de-icing system for an aircraft with at least one heat source and at least one air delivery means for delivering air into regions of the aircraft to be de-iced. In comparison with the prior art, the invention is characterized in that the air delivery means is connected to an air-conditioning system of the aircraft for discharging air from the cabin of the aircraft via an air heating device, wherein the air heating device is connected to at least one heat source in order to heat the air from the cabin of the aircraft. The de-icing system according to the invention is able to realize a wing de-icing that not only fulfills an anti-icing function, but also a de-icing function on the ground without additional expenditure of energy. The function of the de-icing system according to the invention could also be advantageously supplemented by utilizing the cabin waste air for increasing the flow energy on the upper side of the wing in order to delay a change-over or separation of the boundary layer and to generally increase the lift or lower the resistance. | 02-10-2011 |
20110049304 | AEROFOIL SLOT BLOWING - An aerofoil defining geometric upper and lower surfaces which together form a leading edge region and a trailing edge region, and comprising a blowing device having a slot in the lower geometric surface in the leading edge region for injecting fluid into the airflow over the aerofoil, wherein the slot is located forward of the leading edge stagnation point at the critical angle of incidence of the aerofoil, and wherein the blowing device is adapted to inject the fluid forwardly of the slot and substantially parallel to the lower surface. Also, a method of improving the performance of the aerofoil by injecting fluid into the airflow over the aerofoil from the slot. The upper surface of the aerofoil can be kept clean, giving the potential for laminar flow during cruise without significantly compromising the high lift performance of a blown leading edge at high incidence. | 03-03-2011 |
20110108672 | Traversing Jet Actuator - An apparatus comprises a platform configured to move in a streamwise direction, an actuation unit associated with a control surface of the platform, a fluid source configured to supply an airflow to the actuation unit, and a control unit for moving an air jet across the control surface. The actuation unit is configured to form a traversing air jet pointing in the streamwise direction. | 05-12-2011 |
20110309201 | ACTIVE FLOW CONTROL FOR TRANSONIC FLIGHT - An air vehicle includes an airfoil designed for transonic flight. The airfoil has a region of supersonic flow during transonic flight. A surface of the airfoil has upstream and downstream orifices at or within the region. The air vehicle further includes an active flow control system for controlling air vehicle motion during transonic flight by controlling flow through the orifices to alter strength and location of a shock wave in the region. The system creates an aerodynamic imbalance to move the shock wave. | 12-22-2011 |
20120068020 | STOL AND/OR VTOL AIRCRAFT - An STOL and/or VTOL aircraft comprises (1) a fuselage having a front end, a rear end and two lateral sides, the fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (2) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage with movable surfaces for controlling the aircraft; and (3) a wing on each side of the fuselage having a front edge, a trailing edge and an upper surface extending from the front edge to the trailing edge. According to the invention, a device is provided for increasing the speed of an airstream flowing over the upper surfaces of the wings as compared to the speed of the airstream flowing over the lower surfaces thereof. Such means comprise openings in the upper surfaces of the wings for the egress of air from interior spaces within the wings and air pump apparatus for pressurizing such interior spaces. The openings are designed to direct airflow over the upper surfaces of the wings in a direction toward the trailing edges thereof. | 03-22-2012 |
20140091180 | Systems and Methods for Attenuation of Noise and Wakes Produced by Aircraft - Systems and methods for reducing the trailing vortices and lowering the noise produced by the side edges of aircraft flight control surfaces, tips of wings and winglets, and tips of rotor blades. A noise-reducing, wake-alleviating device is disclosed which incorporates an actuator and one or more air-ejecting slot-shaped openings coupled to that actuator and located on the upper and/or lower surfaces and/or the side edges of an aircraft flight control surface or the tip of a wing, winglet or blade. The actuation mechanism produces sets of small and fast-moving air jets that traverse the openings in the general streamwise direction. The actuation destabilizes the flap vortex structure, resulting in reduced intensity of trailing vortices and lower airplane noise. | 04-03-2014 |
20160375986 | METHOD AND APPARATUS FOR ROBUST LIFT GENERATION - A system and method for robust lift generation through flow separation suppression are presented. A fluid flow is ejected over a lifting surface from a fluid ejection orifice, and a flow direction of the fluid flow over the lifting surface is directed using a plurality of vanes configured in the fluid ejection orifice. The flow direction is rotated in a span-wise direction over the lifting surface by swiveling the vanes. | 12-29-2016 |
20160375987 | SYSTEM AND METHOD FOR ENHANCING THE HIGH-LIFT PERFORMANCE OF AN AIRCRAFT - A drag reduction system for an aircraft may include an air ejector having an ejection port located between an aft portion of an airfoil main element and a forward portion of a trailing edge device. The air ejector may be configured to discharge an air jet from the ejection port in such a manner that the air jet passes over the upper surface of the trailing edge device. | 12-29-2016 |
244208000 | And suction | 19 |
20080296439 | INTEGRAL SUCTION DEVICE WITH ACOUSTIC PANEL - An inlet flow control system disposed within a nacelle includes a panel on an inner surface of that nacelle. The panel includes a noise attenuation layer that dissipates noise energy. A vacuum source generates a pressure differential across the noise attenuation layer for drawing airflow through the panel and away from an inner surface of the nacelle. | 12-04-2008 |
20090084906 | Dynamic bumps for drag reduction at transonic-supersonic speeds - A system for reducing overall drag of a mobile platform includes a surface on which an airflow forms a boundary layer and a generally normal shockwave. The airflow is at a first velocity that is one of transonic and supersonic. An oscillating jet injects and extracts a jet flow through the surface. The jet flow is at a second velocity that is substantially less than the first velocity. A recirculation region is upstream of the normal shockwave and is disposed at least partially in the boundary layer. The recirculation region is established at least by the oscillating jet. A generally oblique wave is established by the recirculation region and weakens the normal shockwave to reduce the overall drag experienced by the surface. | 04-02-2009 |
20090321580 | VERNIER ACTIVE FLOW CONTROL EFFECTOR - Methods and apparatus for controlling the attitude of a mobile platform with a resolution suitable for vernier attitude control. In one embodiment a method includes flowing fluid through an orifice of an aerodynamic surface. The method also includes modifying a boundary layer of the aerodynamic surface with the flowing fluid. Another embodiment provides an aerodynamic member of a mobile platform. The aerodynamic member includes an aerodynamic surface, an orifice, an actuator, and a fluid moving member. The orifice is in the aerodynamic surface and the actuator is subject to friction and backlash. The fluid moving member communicates with the orifice and causes the fluid to flow through the orifice to modify the boundary layer of aerodynamic surface. | 12-31-2009 |
20100044520 | Establishment of laminar boundary layer flow on an aerofoil body - In order to establish laminar flow on the attachment line ( | 02-25-2010 |
20100116943 | AIRCRAFT COMPONENT EXPOSED TO STREAMING SURROUNDING AIR - An aircraft component, such as a wing, has perforations through an outer wall for boundary layer suction. In the space between the outer wall and inner wall partition walls form pressure channels and suction channels that are adjacent to each other and alternate, which channels communicate with the perforations. For example, alternating channels may be formed by a corrugated structure having trapezoidal corrugations providing a larger area for the suction channels than for the pressure channels. The pressure channels may be coupled to a hot-air reservoir by a control device, lines and valves, and the suction channels may be coupled to a vacuum reservoir, unless a short-circuit valve is used to cross connect the lines. | 05-13-2010 |
20100127129 | High performance airfoil with co-flow jet flow control - An aerodynamic system providing an airfoil having a chord length, a leading edge, and a trailing edge. The airfoil further includes a first airfoil surface extending from the leading edge to the trailing edge, a second airfoil surface opposite the first airfoil surface, extending from the leading edge to the trailing edge, an injection opening in the first airfoil surface, and a recovery opening in the first airfoil surface located between the injection opening and the trailing edge. A pressurized fluid source is in fluid communication with the injection opening and a vacuum source is in fluid communication with the recovery opening. An exemplary use of the aerodynamic system of the present invention provides the ejection of a mass of fluid out of the injection opening along a surface of the airfoil and drawing a mass of fluid into the recovery opening. | 05-27-2010 |
20100181433 | METHOD FOR INCREASING THE LIFT OF AERODYNAMIC SURFACES AND FOR REDUCING THE DRAG - A jet of air is impelled on to the upper surface of a flap in order to increase its lift. Part of the air in this air jet is drawn, through air intakes, from the air stream flowing over an upper surface of the fixed part of the wing, located upstream of the flap. The air jet drawn in by suction by the air intakes is reinforced by a jet of compressed air blown through a passage which opens immediately downstream of the air intakes. This creates a combined jet of the air sucked in and the blown jet, which is ejected on to the upper surface of the flap through outlet apertures located on the rear edge of the fixed part of the wing. | 07-22-2010 |
20100270434 | CONTROLLING THE BOUNDARY LAYER OF AN AIRFOIL - This invention relates to a method and system ( | 10-28-2010 |
20110210211 | DISCRETE CO-FLOW JET (dCFJ) AIRFOIL - The present invention provides an aircraft having one or more fixed wings in a flying wing configuration, where the aircraft further includes a high performance co-flow jet (CFJ) circulating about at least a portion of an aircraft surface to produce both lift and thrust. | 09-01-2011 |
20110309202 | Wingtec Holding Limited - A control device ( | 12-22-2011 |
20120001028 | WING OF AN AIRCRAFT AND ASSEMBLY OF A WING COMPRISING A DEVICE FOR INFLUENCING A FLOW - A wing of an aircraft is described, having: a main wing, at least one high lift flap which can be moved between a retracted and an extended position, and a spoiler. The main wing has ejection openings, arranged side-by-side along the main wing spanwise direction, and in the main wing chordwise direction, and which are connected via an air conduit with the outlet device of a flow delivery driver device on the main wing or on the spoiler. The spoiler has inlet openings for the intake of air, which are connected via an air conduit with the inlet device of the flow delivery driver device. The flow delivery driver device has a receiver device for the reception of command signals for purposes of adjustment of the flow delivery driver device. An arrangement of a wing with a device for purposes of flow control with such a wing is also described. | 01-05-2012 |
20120043428 | HIGH-LIFT FLAP, ARRANGEMENT OF A HIGH-LIFT FLAP TOGETHER WITH A DEVICE FOR INFLUENCING THE FLOW ON THE SAME AND AIRCRAFT COMPRISING SAID ARRANGEMENT - An aerodynamic body of an aircraft with an air outlet opening and an air intake opening that communicates with the air outlet opening via an air conduit is described. A flow delivery driver device for influencing the flow within the air conduit is integrated into the air conduit. The surfaces of the aerodynamic body in the body chord direction include at least one air outlet opening in the front region of the aerodynamic body, and at least one air intake opening on the upper surface of the aerodynamic body and in the rear region of the aerodynamic body and/or on the upper surface of the aerodynamic body in the trailing edge region and/or on the lower surface of the aerodynamic body in the trailing edge region. Arrangements of a main wing and an adjustable flap, and an aircraft with such an aerodynamic body are also described. | 02-23-2012 |
20120223190 | AERODYNAMIC BODY, REGULATING FLAP OR MAIN WING OR FIN OF AN AIRCRAFT AS WELL AS A STRUCTURAL COMPONENT WITH SUCH AN AERODYNAMIC BODY - An aerodynamic body with an aerodynamic body surface that creates a contoured surface for a fluid to stream around, with a device to influence the flow of the fluid streaming around the aerodynamic surface. The flow-influencing device includes a passage to link the fluid streaming around the aerodynamic surface with an actuator space of an aspirating and purging device situated in the aerodynamic body, and an indentation that is situated next to the passage, which is formed by a recessed section of the aerodynamic surface on a flow-influencing region within the contoured surface of the aerodynamic surface, so that a boundary wall is configured as part of the recessed surface lying opposite the indentation. The aspirating and purging device can generate a swirl in the flow of the fluid streaming around the aerodynamic surface, the rotational axis of which is directed along the assumed aerodynamic body chord direction. | 09-06-2012 |
20120280088 | METHOD OF LAMINAR FLOW CONTROL USING A DOOR ASSEMBLY - A method of operating a door assembly may include pivoting a first door about a first pivot axis from a closed position to an open position such that the first door acts as an inlet. The method may further include pivoting the first door to the closed position, and pivoting a second door about a second pivot axis from a closed position to an open position when the first door is in the closed position such that the second door acts as an outlet facing in a direction opposite the first door. The method may additionally include pivoting the second pivot axis about the first pivot axis when pivoting the second door, the second door being of a smaller size than the first door and forming at least a portion of the first door. | 11-08-2012 |
20130062473 | FLOW BODY AND METHOD FOR TAKING IN AND/OR BLOWING OUT FLUID THROUGH A PLURALITY OF OPENINGS IN A FLOW SURFACE SECTION OF A FLOW BODY - The invention pertains to a flow body with a flow surface section that extends in a flow body wingspan direction and a flow body chord direction and with a plurality of fluid lines that lead into the flow surface section and respectively form an opening therein, as well as to a method for taking in and/or blowing out fluid through at least one fluid line that leads into a flow surface section of a flow body and respectively forms an opening therein. | 03-14-2013 |
20130240676 | HIGH LIFT SYSTEM FOR AN AIRCRAFT - A high lift system with a main wing and control flaps, wherein the respective guiding device are at least partially provided with a fairing, having a flow control device for purposes of controlling the flow around the high lift system with at least two inlet ducts running along the main wing chordwise direction with in each case at least one inlet, which device is located on or underneath the lower surface of the high lift system, wherein at least one outlet duct for air is furthermore provided, which is connected with the inlet ducts in a fluid-communicating manner, and has at least one outlet, which is located on the upper surface of at least one regulating flap and/or with respect to the main wing chordwise direction in the rear third of the main wing of the high lift system. | 09-19-2013 |
20130277502 | FLOW BODY HAVING A LEADING EDGE, A SURFACE AND AN ACTIVE FLOW CONTROL SYSTEM AND VEHICLE COMPRISING AT LEAST ONE SUCH FLOW BODY AND AN AIR SOURCE - A flow body having a surface, a leading edge has an active flow control system. The active flow control system includes a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an interaction chamber having an inlet connectable to an air source, at least two outlets and at least two control pressure ports. The openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through the surface. The control pressure varying device is connected to the at least two control pressure ports in a fluidic manner, wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets. Each of the outlets is connected to one individual opening of the plurality of openings. | 10-24-2013 |
20140061387 | SURFACE ELEMENT FOR AN AIRCRAFT, AIRCRAFT AND METHOD FOR IMPROVING HIGH-LIFT GENERATION ON A SURFACE ELEMENT - A surface element, e.g. a wing, of an aircraft includes a leading edge, a high lift device arrangement positioned along the leading edge and at least one add-on body positioned in a leading edge region, wherein the high lift device arrangement is interrupted in the region of at least one add-on body for preventing collision with the add-on body and wherein the surface element includes an arrangement of openings in a region covering the add-on body, which openings are connected to an air conveying device for conveying air through the openings. Thereby an additional flap for harmonizing the flow above a pylon or other add-on body can be eliminated. | 03-06-2014 |
20150083866 | APPARATUS AND METHODS TO OPERATE LAMINAR FLOW CONTROL DOORS - Apparatus and methods to operate laminar flow control system doors with improved reliability and serviceability are described herein. One described example apparatus includes a fin of an aircraft, a door assembly on a first side of the fin having a first door defining a first opening and second door defining a second opening. The example apparatus also includes a perforated surface proximate a leading edge of the fin and an actuator disposed in the aircraft. The actuator drives a linkage that couples the door to the actuator. The linkage is to operate the door in a first open mode in which the first opening faces in a first direction to create a suction airflow path between the perforated surface and the first opening, and a second open mode in which the second opening faces in a second direction to create a purge airflow path between the second opening and the perforated surface. | 03-26-2015 |
244209000 | With suction | 15 |
20090014593 | Cooling system on the basis of suction of a boundary layer - A cooling system on board an aircraft includes a device for removing by suction a boundary layer, and a heat exchanger through which flows the boundary layer air that has been removed by suction. Cooling by way of a ram air channel can be reduced or entirely stopped, depending on the flight phase, such that the air drag of the aircraft and thus the fuel consumption can be reduced. | 01-15-2009 |
20090020653 | METHOD AND DEVICE FOR SUCTIONING THE BOUNDARY LAYER - A method for suctioning the boundary layer at the surface ( | 01-22-2009 |
20090212165 | PASSIVE REMOVAL OF SUCTION AIR FOR LAMINAR FLOW CONTROL, AND ASSOCIATED SYSTEMS AND METHODS - Passive removal of suction air for producing a laminar flow, and associated systems and methods are disclosed. One such method includes forming a laminar flow region over an external surface of an aircraft by drawing air through the external surface and into a plenum. The method can further include passively directing the air from the plenum overboard the aircraft. For example, the air can be passively directed to a region external to the aircraft having a static pressure lower than a static pressure in the plenum, as a result of the motion of the aircraft. Flows from different sections of the external surface can be combined in a common plenum, and the corresponding massflow rates can be controlled by the local porosity of the external surface. | 08-27-2009 |
20090266937 | REDUCTION OF FRICTIONAL LOSSES IN THE REGION OF BOUNDARY LAYERS ON SURFACES, AROUND WHICH A FLUID FLOWS - An aerodynamic body with a plurality of nozzles for throttling a fluid flow to be removed by suction through the nozzles in a self-regulated fashion is disclosed. The aerodynamic body according to one example, includes a plurality of throttling nozzles with a throttle section that is defined by an inlet and an outlet. In one example, the interior wall of the throttle section may be designed such that an effective flow cross section is reduced in a self-regulated fashion due to the creation of turbulences on the interior wall of the throttle section as the pressure differential between the inlet and the outlet of the throttle section increases. | 10-29-2009 |
20100078522 | APPARATUS, SYSTEM AND METHOD FOR DRAG REDUCTION - An apparatus, method and system for combining aerodynamic design with engine power to increase synergy between the two and increase climb performance, engine-out performance, and fuel efficiency for a variety of aircraft or the like. | 04-01-2010 |
20100181434 | APPARATUS & METHOD FOR PASSIVE PURGING OF MICRO-PERFORATED AERODYNAMIC SURFACES - A purging system for a laminar flow control system comprises an air scoop and a diffuser fluidly connected thereto. The air scoop is disposable into an external flow of an external atmosphere. The diffuser is configured to fluidly connect the air scoop to a suction cavity of the laminar flow control system wherein the suction cavity may be disposed adjacent a porous skin of an airfoil such as adjacent a leading edge of the airfoil. The laminar flow control system may be configured to suction boundary layer flow passing over the porous skin by drawing a portion of the boundary layer flow through a plurality of pores formed in the porous skin. The diffuser ducts high pressure flow captured by the air scoop to the suction cavity for discharge through the pores to reduce the potential of blockage thereof. | 07-22-2010 |
20100181435 | DOOR ASSEMBLY FOR LAMINAR FLOW CONTROL SYSTEM - A door assembly has a first door integrated with a second door. The first door has a first door cowl. The second door is pivotably mounted to the first door and has a second door cowl forming at least a portion of the first door cowl. The door assembly includes at least one actuator coupled to the first and second doors. Each one of the first and second doors is pivotable between open and closed positions and defines an opening when moved to the open position. The openings of the first and second doors face in opposite directions. The actuator is operative to pivotably move at least one of the first and second doors between the open and closed positions. | 07-22-2010 |
20100294892 | DEVICE FOR REDUCING THE AERODYNAMIC DRAG OF A LEADING SURFACE OF AN AIRCRAFT - A device for reducing the aerodynamic drag of a leading surface of an aircraft includes at least one air permeable structure disposed in an area of the leading surface and a suction device configured to interact with the at least one air permeable structure. | 11-25-2010 |
20120037760 | LAMINAR FLOW PANEL - An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. At least one hollow member is coupled to the inner surface and is operable to suction air from the outer surface and through the perforated panel skin. The at least one hollow member is oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body. | 02-16-2012 |
20120187252 | DEVICE FOR BOUNDARY LAYER SUCTION AND COMPOSITE COMPONENT THEREFOR - The invention relates to a device for boundary layer suction on the outer skin of an aircraft, on which outer skin a surface where drawing off by suction can take place comprising openings is connected to a suction source by way of at least one suction line, wherein the surface where drawing off by suction can take place is formed by at least one panel-shaped composite component that comprises an extruded profile, made of light metal, as a base body, which extruded profile comprises several suction channels that are open towards the outer skin, onto which base body, for the purpose of forming the outer skin, a micro-perforated metal cover sheet has been applied in the region of the surface where drawing off by suction can take place. | 07-26-2012 |
20130175402 | AIR SUCKING VEHICLE FUSELAGE COMPONENT, METHOD FOR PRODUCING AN AIR SUCKING VEHICLE FUSELAGE COMPONENT AND A VEHICLE, ESPECIALLY AN AIRCRAFT, WITH AN AIR SUCKING VEHICLE FUSELAGE COMPONENT - An air-sucking vehicle fuselage component includes an outer delimitation part, and inner delimitation part, and connecting elements. The inner delimitation part is connected via the connecting elements to the outer delimitation part. The outer delimitation part includes a continuously curved shape. The inner delimitation part includes two or more flat delimitation part components, which are each connected to one another at one edge to form a connection edge, and the connection edge is configured to be attached to the outer delimitation part. A type of framework structure is thus provided, which causes increased stability and can split impacting objects in particular if two inner delimitation part components are used on the vehicle fuselage component. | 07-11-2013 |
20140326834 | Laminar Flow Panel - An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. At least one hollow member is coupled to the inner surface and is operable to suction air from the outer surface and through the perforated panel skin. The at least one hollow member is oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body. | 11-06-2014 |
20150307183 | AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM SELECTIVELY POWERED BY THREE BLEED REPORTS - An engine compressor bleed system of an engine for an aircraft is provided including a plurality of compressor pressure ports configured to supply bleed air to satisfy a cooling load for at least a first stage of a flight profile of an aircraft. A first pressure port of the plurality of compressor pressure ports is configured to provide bleed air having a pressure at least equal to a cabin pressure of an aircraft and a temperature that does not exceed a predetermined threshold. | 10-29-2015 |
20160159464 | AIRCRAFT WING RIB - There is disclosed an aircraft wing rib comprising a structural rib section to which a wing skin can be attached; and a suction conduit to which, in use, a negative pressure can be applied so as to cause air to be drawn through suction holes provided in the outer surface of the wing skin. There is also disclosed an aircraft wing including such a wing rib. | 06-09-2016 |
20160159465 | Laminar Flow Panel - An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. A micro-lattice support structure is coupled to the inner surface and defines airflow gaps allowing suctioning of air from the outer surface through the perforated panel skin and into a plenum of the aerodynamic body. Rows of main beams of the micro-lattice support structure are aligned along land lines oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body. | 06-09-2016 |
244210000 | With nose slot | 1 |
20100019095 | WING OF AN AIRCRAFT - Wing of an aircraft having a mainplane ( | 01-28-2010 |
244212000 | Having trailing edge flap | 2 |
20130134262 | Jam Protection and Alleviation for Control Surface Linkage Mechanisms - A flaperon mechanism that provides jam protection while preventing the component departing from the airplane or causing unacceptable collateral damage. The jam protection feature comprises a controlled failure (fused) mechanism that is associated with the flaperon and flaperon hinge panel and maintains functional movement of the devices. Additional features can be added to the mechanism to block, shield, allow runout and shed other obstruction avenues. | 05-30-2013 |
20160200422 | Multiple Controllable Airflow Modification Devices | 07-14-2016 |