69results about "Boundary layer controls" patented technology

An aircraft may comprise propulsors. The propulsors may be integrated into an array of propulsors. An array of propulsors may be integrated in an airfoil of the aircraft. The aircraft may include a flow turning control system. The flow turning control system may include an end wall and one or more movable flaps. The flow turning control system may enable selective flow turning of the flow of propelled by the array of propulsors. The selective flow turning may include actuating the one or more movable flaps. The selective flow turning may achieve flow turning of over a trailing edge of a movable flap.

An aircraft may comprise propulsors. The propulsors may be integrated into an array of propulsors. An array of propulsors may be integrated in an airfoil of the aircraft. The aircraft may include a flow turning control system. The flow turning control system may include an end wall and one or more movable flaps. The flow turning control system may enable selective flow turning of the flow of propelled by the array of propulsors. The selective flow turning may include actuating the one or more movable flaps. The selective flow turning may achieve flow turning of over a trailing edge of a movable flap.

An intentional fluid manipulation apparatus (IFMA) assembly that includes an upstream intentional momentum shedding apparatus (IMSA) configured to impart a first induced velocity to a local free stream flow during a nominal operation requirement. The upstream IMSA creates a streamtube. The IFMA includes a downstream IMSA, with some or all of the downstream IMSA being located in a downstream portion of the streamtube. The downstream IMSA imparts a second induced velocity to the local free stream flow within the streamtube. The second induced velocity at the location of the downstream IMSA has a component in a direction opposite to the direction of the first induced velocity at the location of the downstream IMSA.

A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.

Propulsion assembly for an aircraft, comprising a turbomachine (1), an attachment strut (40) and a structural element (10) carrying the turbomachine (1) by the attachment strut (40), the turbomachine having at least one rotating part (30) rotating about an axis of rotation (A), the rotating part (30) being arranged upstream of the structural element (10) and of the attachment strut (40) so that the air jet exiting from the rotating part (30) impacts the structural element (10) and the attachment strut (40) in the wake thereof, the leading edge of the structural element (10) and / or of the attachment strut (40) locally comprising at least one acoustic attenuation device (50, 60, 70, 80) arranged at least partially in the wake of the rotating part (30), the acoustic attenuation device being a partial modification of the structure and / or of the profile of the leading edge (11).

The present application belongs to the technical field of aircraft skin, and relates to an aircraft elastic porous medium skin, a plurality of hole bodies are prefabricated on the skin, an organ pipe type nozzle is installed in the hole body, the organ pipe type nozzle is connected with a jet control system for providing a heat medium for the organ pipe type nozzle; the organ pipe type nozzle comprises an inlet section, a resonance section, an intermediate section and an outlet section connected in sequence; the inlet section is provided with an incidence hole, the resonance section is provided with a resonance hole, the intermediate section is provided with an intermediate hole, and the outlet section is provided with an emission hole which is a diverging hole; the incidence hole, the resonance hole and the intermediate hole are all cylindrical holes, and the diameters of the incidence hole, the resonance hole and the intermediate hole gradually decrease. The elastic porous medium skin is used to induce the slip and micro-cavitation effect of unsteady boundary layer fluid, and the geometric parameters of the control hole are controlled, so that the self-adaptive boundary layer flow state is greatly reduced, the frictional resistance is reduced, and the outer lining has the characteristics of noise reduction, and has the scattering and absorption effect on sound waves.

Multilayer rib ornaments and methods of producing the same are described herein. One disclosed example method includes applying a first high elongation polymeric material to a web tool, where the web tool is provided from a first roller; and heating the first high elongation polymer material via a first heating process. The disclosed example method further includes applying a second high elongation polymeric material to the first high elongation polymeric material; and heating the second high elongation polymer material via a second heating process. The disclosed example method also includes applying a support layer to the second high elongation polymeric material via a lamination roller.

A laser processing device comprising: an optical arrangement; wherein the optical arrangement comprises an input for receiving a laser beam; wherein the optical arrangement comprises a beam splitter that splits the laser beam into at least two partial beams; wherein the optical arrangement recombines the partial beams into a laser spot for generating an interference pattern in the laser spot; wherein a first state of the laser beam at the input generates a first interference pattern and a second state of the laser beam generates a second interference pattern; wherein the first state and the second state differ in at least one of (i) a position of the laser beam at the input and (ii) an angle of incidence of the laser beam with respect to the input; and wherein the optical arrangement is configured such that the second interference pattern continues the first interference pattern in phase.

An aircraft includes a fuselage and at least one primary wing having an upper surface, at least one recess in the upper surface and at least one conduit in fluid communication with the at least one recess. At least one ejector is disposed within the at least one recess and is configured to receive compressed air via the at least one conduit.

An aircraft structure (10) having a fuselage (20), an engine (70) and an air inlet (100) for receiving air for the engine is specified. The air inlet has a cowl which surrounds an inlet opening. The air inlet furthermore has a compression surface (102) and a transition shoulder (104). The air inlet (100) additionally has a flow guide surface (110), which is arranged as a local elevation in a region of the transition shoulder (104) and extends into the inlet opening. This flow guide surface designed as a local elevation contributes to improving the displacement of the boundary layer of a fluid flowing along the aircraft structure at the air inlet.

A hybrid electric gas turbine propulsion system (100) may comprise: a first propulsion system (401), a second propulsion system (402), and a third propulsion system (403). The first propulsion system (401) may comprise a first fan (212), a first turbine (252), a first compressor (232), and a first electric motor (190), the first fan (212) operably coupled to the first turbine (252) and the first compressor (232) by a first shaft (126), the first shaft (126) coupled to the first electric motor (190), the first shaft (126) configured to be disposed radially inward of a fuselage (12) of an aircraft (10). The second propulsion system (402) and the third propulsion system (403) may be in accordance with the first propulsion system (401). The hybrid electric gas turbine propulsion system (100) may be symmetric about a vertical plane extending through a neutral aerodynamic axis (104).

An air injection assembly for an aircraft is provided. The aircraft includes a fuselage extending between a forward end and an aft end along a longitudinal direction and a boundary layer ingestion fan mounted to the fuselage at the aft end of the fuselage. The air injection assembly includes at least one injection port defined on a surface of the fuselage at a location upstream of the boundary layer ingestion fan. A supplemental airflow is provided through a fluid passageway to the injection port where it is ejected to displace at least a portion of relatively higher velocity boundary layer airflow. In this manner, the airflow entering boundary layer ingestion fan is more uniform, has less swirl distortion, and has a lower average velocity.

The embodiment of the present application discloses a vortex generator, an aircraft and a control method of the aircraft, wherein the vortex generator comprises a flow guide, a driver, a detector and a controller. The flow guide is arranged on the fuselage of the aircraft and is used to form a vortex in the airflow flowing on the surface of the fuselage. The driver is used to drive the flow guide to move relative to the fuselage, so as to adjust the height of the flow guide protruding from the surface of the fuselage. The detector is used to obtain a predetermined parameter, and the predetermined parameter represents the thickness of the boundary layer formed by the airflow on the surface of the fuselage. The controller is used to obtain the thickness of the boundary layer according to the predetermined parameter, so as to control the driver to adjust the protruding height of the flow guide to match the thickness of the boundary layer. The embodiment of the present application can improve the effect of the vortex generator.

A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.

A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.

A hybrid electric gas turbine propulsion system (100) may comprise: a first propulsion system (401), a second propulsion system (402), and a third propulsion system (403). The first propulsion system (401) may comprise a first fan (212), a first turbine (252), a first compressor (232), and a first electric motor (190), the first fan (212) operably coupled to the first turbine (252) and the first compressor (232) by a first shaft (126), the first shaft (126) coupled to the first electric motor (190), the first shaft (126) configured to be disposed radially inward of a fuselage (12) of an aircraft (10). The second propulsion system (402) and the third propulsion system (403) may be in accordance with the first propulsion system (401). The hybrid electric gas turbine propulsion system (100) may be symmetric about a vertical plane extending through a neutral aerodynamic axis (104).

Methods for forming microstructures in photocurable material are described. At least one image of light or radiation for curing the photocurable material is applied in a pattern corresponding to the image. The image is formed by near-field diffraction of the light or radiation and comprises areas of higher intensity adjacent to areas of lower intensity.

A composite part for a vehicle is provided. The composite part has a first surface (22a) and an opposing second surface (22b), wherein at least part of the first surface forms an outer aerodynamic surface of a vehicle. A region of the part has a curvature in two orthogonal directions. The part has an undulation (40) defining a channel (60) in one of the first surface or the second surface, and a corresponding ridge (50) in the other of the first surface and the second surface.

A method of assembling a riblet panel (200, 300a-d, 400a-d, 500, 600a-c, 700a-d, 800) for attaching riblets (202, 302a-d, 402a-d, 502, 602a-d, 702a-d) to a surface over which a fluid flows, the method comprising: preparing a plurality of riblet films, each riblet film comprising one or more riblets (202, 302a-d, 402a-d, 502, 602a-d, 702a-d); and attaching the plurality of riblet films to a common laminate film in a predetermined arrangement, wherein the riblet panel (200, 300a-d, 400a-d, 500, 600a-c, 700a-d, 800) is configured to adhere to the surface; and wherein the predetermined arrangement is configured such that, when the riblet panel (200, 300a-d, 400a-d, 500, 600a-c, 700a-d, 800) is adhered to the surface, the one or more riblets (202, 302a-d, 402a-d, 502, 602a-d, 702a-d) of the plurality of riblet films are configured to reduce the skin friction of the surface when the fluid flows over them.

The invention relates to a blade (7) made of composite material for a turbine engine (10), in particular of an aircraft, the blade (7) comprising an airfoil (70) formed by a fibrous preform embedded in a resin and extending along an axis (A) of elongation, the airfoil (70) comprising a leading edge (73), a trailing edge (74), a pressure side (71) and a suction side (72) connected to the pressure side (71) by the leading edge (73) and the trailing edge (74), the airfoil (70) further comprising at least one serrated element (9) formed by a plurality of teeth (92) and covering at least part of the leading edge (73) and / or the trailing edge (74), wherein the at least one serrated element (9) is made of a thermosetting or thermoplastic material.

A sheet member 1 includes: a front surface 111 including a first area 130 and a second area 140; a back surface 122; and a through-hole 15 formed between the front surface and the back surface, the first area 130 is a surface of a convex structure 13 that is formed as at least a part of the riblet structure RB and that protrudes from the second area, and an opening 151 of the through-hole 15 is formed in the second area 140.

The application relates to a high-speed boundary layer transition control device and a control method based on micro-nano gas film, wherein the high-speed boundary layer transition control device comprises a gas seepage wall, a gas chamber, a gas supply device and a control device; the gas chamber surrounds the gas seepage wall, and a cavity for gas residence is formed between the gas seepage wall and the gas chamber; the gas chamber is connected with the gas supply device; the control device comprises a first sensor, a second sensor and a control unit; the control unit is connected with the first sensor, the second sensor and the gas supply device respectively; the first sensor is used for collecting cavity pressure in the cavity; along the direction of external airflow, the second sensor is used for collecting wall surface pressure of the high-speed boundary layer upstream of the gas seepage wall; the control unit adjusts the output flow of the gas in the gas supply device based on the cavity pressure, the wall surface pressure and a pressure matching relationship, and the gas seeps out through the gas seepage wall and forms a micro-nano gas film.

A device to reduce turbulent flow skin friction uses carbon dioxide, riblets, and suction holes to reduce the overall drag of a body moving in a fluid. A deflector (2) pushes up the boundary layer of the incoming flow on a surface (1). Carbon dioxide is injected into a plenum (3) and ejected through an exhaust slot (4). Riblets of specific dimensions (5) are placed to interact with the carbon dioxide flow that is now the sublayer viscous flow. After passing the riblets, the flow is sucked partly through suction holes (6), preventing flow separation that could increase the form and wave drag.

An aerial vehicle is provided including rotor units connected to the aerial vehicle, and a control system configured to operate at least one of the rotor units. The rotor unit includes rotor blades, wherein each rotor blade includes a surface area, and wherein an asymmetric parameter is defined, at least in part, by the relationship between the surface areas of the rotor blades. The value of the asymmetric parameter is selected such that the operation of the rotor unit: (i) moves the rotor blades such that each rotor blade produces a respective vortex and (ii) the respective vortices cause the rotor unit to produce a sound output having an energy distribution defined, at least in part, by a set of frequencies, wherein the set of frequencies includes a fundamental frequency, one or more harmonic frequencies, and one or more non- harmonic frequencies having a respective strength greater than a threshold strength.

A hollow structure (10) includes a hollow plate (11) made of thermoplastic resin in which cells are arranged and a mounting member (30) configured to be securely mounted to an inner wall (4) of a jet engine for an aircraft. The hollow plate (11) includes a core layer (20) having side walls to define cells, a first skin layer (24) laminated on a first main surface of the core layer (20), and a second skin layer (25) laminated on a second main surface of the core layer (20). The mounting member (30) includes a columnar body (31) extending in the thickness direction of the hollow plate (11). A side surface of the body (31) is welded to the side wall of the core layer (20). The body (31) is not exposed from an outer surface of the first skin layer (24).

The present invention relates to a body (2); a cavity (3) located on the body (2) capable of holding ammunition and similar payloads; a rear wall (4) being a surface on which an airflow (AF) generated as the body (2) moves leaves the cavity (3); and a base plate (5) above which the airflow (AF) moves along the cavity (3).