3073 results about "Aerodynamic force" patented technology

The invention relates to an air-powered engine assembly, which comprises an air tank, an air valve, an air distributor, an intake pipe, camshafts, an intake duct, an exhaust control device, air cylinders, pistons, crankshafts, couplers, clutches, automatic gearboxes and differentials connected with the outside. The assembly is characterized in that the air valve, a constant pressure chamber and a pressure controller are arranged between the air tank and the air distributor; the air distributor is connected with a plurality of air cylinders on an air cylinder gasket; each air cylinder is connected with an exhaust chamber through an exhaust manifold; the exhaust chamber is provided with a turbine generator which is connected with a storage batter; the air cylinders are provided with the camshafts for controlling the air intake and exhaust of the air cylinders; the air cylinders are provided inside with the pistons for driving the crankshafts to rotate; the camshafts and the crankshafts are connected by chains; and the crankshafts are connected with the differentials through the couplers, the clutches and the gearboxes in turn. Therefore, doing work through air compression rather than fuel, the air-powered engine assembly has the advantages of avoiding waste gas discharge and air pollution, along with reliable operation, convenient operation, economical efficiency, practicality and so on. In addition, due to recycle of the waste gas for power generation, the air-powered engine assembly saves energy and reduces costs.

An aerodynamic golf club head incorporating a trip step feature located on the crown section. The benefits associated with the reduction in aerodynamic drag force associated with the trip step may be applied to drivers, fairway woods, and hybrid type golf club heads. The trip step is located between a crown apex and the back of the club head and may be continuous or discontinuous. The trip step enables a significant reduction in the aerodynamic drag force exerted on the golf club head by forcing the air passing over the club head from laminar flow to turbulent flow just before the natural separation point of the airstream from the crown. This selectively engineered transition from laminar to turbulent flow over the crown section slightly increases the skin friction but results in less aerodynamic drag than if the air were to detach from the crown section at the natural separation point.

An advanced aerodynamic control system for a wind turbine including a drive shaft and blade. The control system includes an air control system coupled to a duct that extends from a first end toward a second end of the blade. A slot extends along a portion of a surface of the blade and is in communication with the duct. An instrument measures operating data of the wind turbine. A controller collects the operating data and compares the operating data to predetermined operating norms. The controller actuates the air control system to urge pressurized air into the duct and out of the slot at a specific air flow rate based upon the comparison between the operating data and predetermined operating norms. Control of the flow rate aids in capture of power from the wind flowing through a swept area of the wind turbine.

A single dielectric barrier aerodynamic plasma actuator apparatus based on the dielectric barrier discharge phenomenon is disclosed and suggested for application to aerodynamic uses for drag reduction, stall elimination and airfoil efficiency improvement. In the plasma actuator apparatus non-uniform in time and space, partially ionized gasses are generated by one or more electrode pairs each having one electrically encapsulated electrode and one air stream exposed electrode and energization by a high-voltage alternating current waveform. The influence of electrical waveform variation, electrode polarity, electrode size and electrode shape on the achieved plasma are considered along with theoretical verification of achieved results. Light output, generated thrust, ionizing current waveform and magnitude and other variables are considered. Misconceptions prevailing in the present day plasma generation art are addressed and are believed-to-be corrected. The influence of electrostatic shielding effects of the developed plasma on the applied electric field are also considered.

A device for reducing vehicle aerodynamic resistance for vehicles having a generally rectangular flat front face comprising a plurality of load bearing struts of a predetermined size attached to the flat front face adjacent the sides and top thereof, a pair of pliable opposing flat sheets having an outside edge portion attached to the flat front face adjacent the sides thereof and an upper edge with a predetermined curve; the opposing flat sheets being bent and attached to the struts to form effective curved airfoil shapes, and a top pliable flat sheet disposed adjacent the top of the flat front face and having predetermined curved side edges, which, when the top sheet is bent and attached to the struts to form an effective curved airfoil shape, mate with the curved upper edges of the opposing sheets to complete the aerodynamic device.

A camera thrown or projected into an airborne trajectory, and an image capture system with network devices collaborating for the purpose of generating panoramic images and video sourced from network cameras thrown or projected in independent trajectories, and cameras capable of capturing stable image and video from spinning, spiraling and precessing apertures, and a throwable cameras streamlined in response to aerodynamic forces acting on respective housings.

The invention provides homogeneous small spherical particles of low molecular weight organic molecules, said small spherical particles having a uniform shape, a narrow size distribution and average diameter of 0.01-200 μm. The invention further provides methods of preparation and methods of use of the small spherical particles. These small spherical particles are suitable for applications that require delivery of micron-size or nanosized particles with uniform size and good aerodynamic or flow characteristics. Pulmonary, intravenous, and other means of administration are among the delivery routes that may benefit from these small spherical particles.

A metalwood type golf clubhead, including a clubhead body having a toe, heel, top crown surface, bottom sole surface, side surfaces, rear surface and ball-striking clubface, having an inwardly disposed lower surface located between the bottom sole surface and the top crown surface. The inwardly disposed lower structure provides improved weight distribution for better balance, additional strength and stability to clubhead and considerably decreases the overall cc displacement and overall weight/mass at the bottom of the clubhead without decreasing the size of the ball striking face and/or the upper top crown surface.

Pressure equalization between upper and lower surfaces of PV modules of an array of PV modules can be enhanced in several ways. Air gaps opening into the air volume, defined between the PV modules and the support surface, should be provided between adjacent PV modules and along the periphery of the array. The ratio of this air volume to the total area of the air gaps should be minimized. Peripheral wind deflectors should be used to minimize aerodynamic drag forces on the PV modules. The time to equalize pressure between the upper and lower surfaces of the PV modules should be maintained below, for example, 10-20 milliseconds. The displacement created by wind gusts should be limited to, for example, 2-5 millimeters or less. For inclined PV modules, rear air deflectors are advised for each PV module and side air deflectors are advised for the periphery of the array.

Continuous process for the production of carbon-based nanotubes, nanofibres and nanostructures, comprising the following steps: generating a plasma with electrical energy, introducing a carbon precursor and/or one or more catalysers and/or carrier plasma gas in a reaction zone of an airtight high temperature resistant vessel optionally having a thermal insulation lining, vaporizing the carbon precursor in the reaction zone at a very high temperature, preferably 4000° C. and higher, guiding the carrier plasma gas, the carbon precursor vaporized and the catalyser through a nozzle, whose diameter is narrowing in the direction of the plasma gas flow, guiding the carrier plasma gas, the carbon precursor vaporized and the catalyses into a quenching zone for nucleation, growing and quenching operating with flow conditions generated by aerodynamic and electromagnetic forces, so that no significant recirculation of feedstocks or products from the quenching zone into the reaction zone occurs, controlling the gas temperature in the quenching zone between about 4000° C. in the upper part of this zone and about 50° C. in the lower part of this zone and controlling the quenching velocity between 103 K/s and 106 K/s quenching and extracting carbon-based nanotubes, nanofibres and other nanostructures from the quenching zone, separating carbon-based nanotubes, nanofibres and nanostructures from other reaction products.

A resilient skirt assembly is provided, the assembly comprising a skirt panel adapted to connect to a trailer to direct at least a portion of the amount of air on the side of the trailer; and a skirt support adapted to connect the skirt to a trailer, the skirt support having a resilient strut providing lateral support to the skirt panel, the resilient strut allowing substantial lateral pivotal movement of the skirt panel between a skirt panel unloaded position and a skirt panel loaded position. A method of assembling a skirt assembly and a skirt kit are also provided.

Morphing an aerodynamic body's geometry in situ can optimize its aerodynamic properties, increasing range, reducing fuel consumption, and improving many performance parameters. The aerodynamic load exerted on the body by the flow is one such parameter, typically characterized as lift or drag. It is the aim of the present disclosure to teach the use of passive adaptive morphing structures to manage these aerodynamic loads.

The present invention relates to a method of controlling the aerodynamic load of a wind turbine's blades individually in such a way that the dynamic aerodynamic loads on the turbine are reduced and power production is optimised. In general the present invention will improve the overall stability of the turbine leading to reduce fatigue loads, reduced extreme loads during operation and reduced risk of blade-tower interaction. In particular preferred embodiment of the invention, flow properties are measured locally on the different blades or in front of the blades and from these measurements the pitch angle settings are changed, in other ways changing the aerodynamic properties, for the blades through a control unit.

Morphing an aerodynamic body's geometry in situ can optimize its aerodynamic properties, increasing range, reducing fuel consumption, and improving many performance parameters. The aerodynamic load exerted on the body by the flow is one such parameter, typically characterized as lift or drag. It is the aim of the present disclosure to teach the use of passive adaptive morphing structures to manage these aerodynamic loads.

A compound aircraft features variable incidence wings, a thruster, a rotor and a clutch connecting the engines to the rotor. Upon reaching a suitable forward speed, the control system of the compound aircraft unloads the rotor and disengages the clutch, disconnecting the rotor from the engines. The control system configures the cyclic and collective pitch effectors to cause the rotor to autorotate. The control system selects an autorotation rotational speed that is adequately rapid to prevent excessive deformation of the rotor blades due to aerodynamic forces acting on the blade and that is adequately slow to prevent excessive compressibility effects.

The invention discloses a CFD (computational fluid dynamics)/CSD (circuit switch data) coupled solving nonlinear aeroelasticity simulation method, comprising: firstly, carrying out calculation initialization; then solving the CFD of unsteady aerodynamic force; converting boundary load information; solving the CSD of nonlinear structure dynamic response; judging whether to exist computation or notby taking the response of structural finite-element mesh point displacement as a convergence criteria; if not exiting, carrying out the dynamic mesh deformation of a flow field after the surface displacement information of a computation model is converted; and then, continuing to compute until the convergence criteria is satisfied, thus finishing computation. By means of the simulation method disclosed by the invention, the problem of pneumatic nonlinearity and structural nonlinearity coupling and the problem of geometric large deformation dynamic mesh can be solved; and the simulation methoddisclosed by the invention can be applied on the nonlinear aeroelasticity analysis of aerospace aircrafts and the nonlinear aeroelasticity analysis of civil high-rise buildings and bridges.

A device for the reduction of aerodynamic drag and for improved performance and stability of ground vehicles by reducing the mass and velocity of the flow passing under a vehicle is described. The device is particularly suited for a tractor-trailer truck system that includes a motorized lead vehicle pulling one or more non-motorized vehicles. The device is designed to control the flow from entering the undercarriage region from the side of a trailer of a tractor-trailer truck system.

A leading edge structure for an aerodynamic surface includes a support structure made of fiber-reinforced synthetic material and a skin structure made of metal mounted on the support structure. The support structure includes an inner laminate, an outer laminate, and longitudinally extending tubes and channels arranged between the inner and outer laminates, as well as a synthetic foam filler material in the spaces between the tubes, channels, and laminates. The skin structure includes an outer skin having perforations, especially in the form of suction holes, an inner skin, and spacer members interconnected therebetween so as to form a substantially form-stable metal skin structure. Respective holes pass through the inner skin, the outer laminate, and the walls of the tubes and channels in order to communicate the suction hole perforations of the outer skin with the interior spaces within the tubes and channels. The skin structure is adhesively bonded to the support structure. In a method for making the leading edge structure, the prefabricated components of the support structure are laid up, molded and cured in a positive mold, the prefabricated components of the skin structure are formed and soldered together on a positive mold, and then the skin structure is adhesively bonded onto the support structure.