3786 results about "Aerodynamics" patented technology

An improved gas deposition chamber includes a hollow gas deposition volume formed with a volume expanding top portion and a substantially constant volume cylindrical middle portion. The hollow gas deposition volume may include a volume reducing lower portion. An aerodynamically shaped substrate support chuck is disposed inside gas deposition chamber with a substrate support surface positioned in the constant volume cylindrical middle portion. The volume expanding top portion reduces gas flow velocity between gas input ports and the substrate support surface. The aerodynamic shape of the substrate support chuck reduces drag and helps to promote laminar flow over the substrate support surface. The volume reducing lower portion helps to increase gas flow velocity after the gas has past the substrate support surface. The improved gas deposition chamber is configurable to 200 mm diameter semiconductor wafers using ALD and or PALD coating cycles. An improved coating method includes expanding process gases inside the deposition chamber prior to the process gas reaching surfaces of a substrate being coated. The method further includes compressing the process gases inside the deposition chamber after the process gas has flowed past surfaces of the substrate being coated.

An unmanned aerial vehicle (UAV) for making partial deliveries of cargo provisions includes a UAV having one or more ducted fans and a structural interconnect connecting the one or more fans to a cargo pod. The cargo pod has an outer aerodynamic shell and one or more internal drive systems for modifying a relative position of one or more cargo provisions contained within the cargo pod. Control logic is configured to, after delivery of a partial portion of the cargo provisions contained within the cargo pod, vary a position of at least a portion of the remaining cargo provisions to maintain a substantially same center of gravity of the UAV relative to a center of gravity prior to delivery of the partial portion. Other center of gravity compensation mechanisms may also be controlled by the control logic to aid in maintaining the center of gravity of the UAV.

A golf club that is preferably made from fiber-reinforced plastic composite by an injection molding process. The preferred golf club head includes a striking face for striking a golf ball, an outer periphery, a cavity formed between the outer periphery and the back of the striking face, a sole enclosing the bottom portion of said cavity, and at least one elongate power bar extending across the cavity from the striking face to the outer periphery. The sole is preferably integrally formed with the face plate and outer periphery. The cavity of the golf club head opens to the top of the club head. Each elongate power bar separates the cavity into receptacles. Inserts may be placed within the receptacles for aesthetic, aerodynamic, acoustic, and other purposes.

The present invention provides an improved antenna system that, in one embodiment, includes an antenna array comprised of a plurality of elements, each of which is capable of providing a signal. Also included in the improved antenna system is a multi-beam beamformer for producing two spatially independent overlapping beams from the signals provided by two different subsets of the antenna array. The phase of the two beams is compared to realize an interferometer that can provide high or fine resolution data on the position of an object relative to the antenna system. The amplitude of the two beams can also be compared to obtain coarse data on the position of the object. The beamformer includes a switching network for selecting which elements of the antenna array form the two subsets. This permits, for example, the position of the beams to moved, the baseline of the two beams to be varied, and / or the beam width of the beams to be altered. To reduce adverse aerodynamic effects in certain applications, the antenna array is located conformal to the exterior surface of the body on which the array is mounted. Further, to reduce temperature related problems associated with high speed movement of the body on which the array is located, the array is located on the side of the body, as opposed to the front of the body. The side location also provides space for other types of sensors that are preferably located adjacent to the front surface of the body.

The disclosed invention consists of several improvements to well known Quad Tilt-Rotor (QTR) aircraft. The first is that during a wing-borne flight, one pair of tilt-rotors, which can be substantially larger than the other pair, is feathered and stopped. This can promote vehicle aerodynamic efficiency and can be utilized to increase vehicle speed. Second is that the wings are not attached to the fuselage at a fixed angle of incidence like on conventional QTR aircraft, but can also be tilted in respect to the fuselage independently of the tilt-rotors. Furthermore, each rotor and each wing can be tilted with respect to fuselage to any tilt-angle without limit, which gives the vehicle unprecedented ability to position the fuselage in any attitude in respect to the vehicle direction of flight.

A metalwood type golf clubhead including a clubhead body having a toe, heel, upper crown surface, bottom sole surface, side surfaces, rear surface and ball-striking clubface having at least one raised, elongated, aerodynamically shaped reinforcing and stabilizing member extending outwardly from the clubhead body and having at least one frontal ball-striking surface coincident with the ball-striking clubface. The structure provides improved weight distribution for better balance, additional strength and stability to clubhead and provides more effective aerodynamic surfaces to increase clubhead speed.

Improved aerodynamically light particles for drug delivery to the pulmonary system, and methods for their synthesis and administration are provided. In a preferred embodiment, the aerodynamically light particles are made of a biodegradable material and have a tap density less than 0.4 g / cm3 and a mass mean diameter between 5 mum and 30 mum. The particles may be formed of biodegradable materials such as biodegradable polymers. For example, the particles may be formed of a functionalized polyester graft copolymer consisting of a linear alpha-hydroxy-acid polyester backbone having at least one amino acid group incorporated therein and at least one poly(amino acid) side chain extending from an amino acid group in the polyester backbone. In one embodiment, aerodynamically light particles having a large mean diameter, for example greater than 5 mum, can be used for enhanced delivery of a therapeutic agent to the alveolar region of the lung. The aerodynamically light particles incorporating a therapeutic agent may be effectively aerosolized for administration to the respiratory tract to permit systemic or local delivery of wide variety of therapeutic agents.

A variable geometry inlet guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning inlet flow to a turbine or compressor and an internal spar spaced from the airfoil shell by an air gap. A number of actuation mechanisms grounded to the spar and connected to the inner surface of the aerodynamic shell adjust the shape of the shell in response to varying operating conditions of the engine, imbalanced aerodynamic loading of the shell or vibration or other transient loads on the shell.

A dry powder inhaler having improved aerodynamic properties for diluting, dispersing, and metering drug particles for increasing the efficiency of pulmonary drug delivery to a patient is described. The inhaler comprises, in general, a housing having an air intake, an air flow-control / check-valve, a mixing section and a mouthpiece. A cartridge loaded with a single dose of medicament can be installed in the mixing section.

A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle and a plurality of tabs which extend in a generally axial direction from a downstream portion of the nozzle wherein the nozzle further comprises an actuation mechanism capable of moving the tabs between a first deployed position, where the tabs interact with a gas stream to reduce exhaust noise thereof, and a second non-deployed position, where the tabs are substantially aerodynamically unobtrusive.

An augmented-reality helmet comprises a full-face motorcycle helmet with a look-down micro-display that projects a virtual image in-line with the helmet's chin bar. In order to accommodate the power requirements, the helmet includes a battery pack mounted at the base of the motorcyclist's skull. A wind turbine charges the batteries. Exhaust from the turbine is then deducted through the helmet to cool the battery pack and / or the motorcyclist's head. The turbine is controllable so that it can operate as a circulating fan to provide ventilation. A digital gyroscope provides a control input to a controller for operating a steerable headlight of the motorcycle to track the rider's head movements; and provides acceleration output to an algorithm that will contact emergency responders if the rider is non-responsive after a collision. A 170 degree rear-view camera is mounted within an aerodynamic fairing on the back of the helmet.

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.

The present invention provides a computer-implemented method of producing a description of aircraft intent expressed using a formal language. The description may be used to predict aircraft trajectory, for example by air traffic management. Rules are used in association with information provided to generate a set of instructions describing both the aerodynamic configuration of the aircraft and the motion of the aircraft. These instructions are checked to ensure that they describe unambiguously the aircraft's trajectory. The instructions are then expressed using a formal language.

A sound attenuating duct unit suitable for connection to an outlet of a gas turbine and an improved heat recovery apparatus for use with such a turbine are disclosed. The former unit includes a duct housing having exterior sides, an air inlet at one end and first and second air outlets. Interior walls define a main airflow passageway extending from the air inlet to both of the outlets. Sound absorbing and heat insulation material is arranged between these walls and the exterior sides. Sound attenuating members are mounted in the passageway and a diverter damper is mounted in the housing and is able to direct air flow to either one of the air outlets. The sound attenuating members are mounted between the diverter damper and the air inlet. The heat recovery apparatus includes a series of aerodynamic diffusers mounted in a housing adjacent an air flow inlet connectable to the gas turbine.

An improved method and device for reducing the base drag of bluff bodies, including large boxy highway vehicles such as semi-trailer trucks, which uses low drag vortex generators in combination with either a trailing panel or shortened boattail plates, to provide greater base drag reduction than other previously known methods. The preferred embodiment reduces the required length of boattail plates by over half, making it compatible with current U.S. regulations for trailer underride bars, and providing easier access for rear cargo doors. The device is easily installed as an add-on device on both new and existing truck bodies. In an alternate configuration, the shape of one or more sets of shortened boattail plates can be built into the rear body shape of vehicles, to maximize the interior volume for a given total vehicle length.

Method and apparatus for direct writing of passive structures having a tolerance of 5% or less in one or more physical, electrical, chemical, or optical properties. The present apparatus is capable of extended deposition times. The apparatus may be configured for unassisted operation and uses sensors and feedback loops to detect physical characteristics of the system to identify and maintain optimum process parameters.

A low drag ducted ram air turbine generator and cooling system is provided. The ducted ram air turbine generator and cooling system has reduced drag while extracting dynamic energy from the air stream during the complete range of intended flight operating regimes. A centerbody / valve tube having an aerodynamically shaped nose is slidably received in a fairing and primary structure to provide a variable inlet area. An internal nozzle control mechanism attached to the valve tube positions nozzle control doors to provide variable area nozzles directing air flow to the turbine stator and rotor blades to maintain optimum generator efficiency. An alternate embodiment includes an annular internal nozzle having interleaved panels to modulate the air flow to the turbine.

Aspects of the invention relate to a modular turbine vane assembly. The vane assembly includes an airfoil portion, an outer shroud and an inner shroud. The airfoil portion can be made of at least two segments. Preferably, the components are connected together so as to permit assembly and disassembly of the vane. Thus, in the event of damage to the vane, repair involves the replacement of only the damaged subcomponents as opposed to the entire vane. The modular design facilitates the use of various materials in the vane, including materials that are dissimilar. Thus, suitable materials can be selected to optimize component life, cooling air usage, aerodynamic performance, and cost. Because the vane is an assemblage of smaller sub-components as opposed to one unitary structure, the individual components of the vane can be more easily manufactured and more intricate features can be included.

A hybrid aerodynamic thrust system as a prime mover for aircraft or other high-speed vehicles. An arrangement of dual thrust resources to alternately accommodate low and high airspeed regimes. Electromotive force is used in lieu of hot section power turbines to achieve engine air compression or alternately perform thrust work at low velocities.

A vertical takeoff and landing aircraft, using for vertical lift and lateral thrust a redundant plurality of essentially similar electrically-powered and electronically-controlled thrust units mounted in a mechanically static or fixed fashion relative to one another in a substantially horizontal plane. The thrust units are situated in this planar array in aerodynamically approximate pairs, such that a complete failure of a single thrust unit would not substantially compromise the ability of the aircraft to maintain flight.

A vertical takeoff and landing (VTOL) rotary-wing air-craft is sized and configured to match a payload container such as a standardized Joint Modular Intermodal Container (JMIC). The aircraft may be an Unmanned Air Vehicle (UAV) that is capable of autonomously engaging and disengaging the container so that the aircraft can pick up and drop off the JMIC with minimum human intervention.

An aerodynamic-hybrid, vertical-axis wind turbine which includes a rotor airfoil and stator blade combination which maximizes energy production by increasing wind velocity and pressure while eliminating back pressure and improving the laminar flow of wind both around and through the device. The rotor airfoils have a horizontal cross-section with a crescent shape including a convex leading side and a concave trailing side with a thicker middle section that tapers to narrower sections at ends. The stator blades have a horizontal cross-section with a planar side and a convex side. Rotor airfoil and stator blade combinations are secured between upper and lower annular sails.

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.

A system and method for the conversion of fuel tanks, detachably mountable on the exterior of an aerial vehicle, into high volume, high capacity, diverse functionality and aerodynamically efficient airborne stores is disclosed. A conventional external fuel drop tank is modified such that the exterior shape of the tank is substantially retained while the interior of the tank is suitable restructured to allow for the introduction of diverse airborne stores, associated airborne store mounting means, control and monitoring means and support means therein, which replace the fuel store. The airborne store is suitably interfaced to the stores control and management system of the aerial vehicle. The airborne store is integrated into a new external stores configuration The enhanced airborne store will have aerodynamic characteristics substantially similar to the original external fuel tank while its payload capacity is substantially improved.

A Mixer / Ejector Wind Turbine (“MEWT”) system is disclosed which routinely exceeds the efficiencies of prior wind turbines. In the preferred embodiment, Applicants' MEWT incorporates advanced flow mixing technology, single and multi-stage ejector technology, aircraft and propulsion aerodynamics and noise abatement technologies in a unique manner to fluid-dynamically improve the operational effectiveness and efficiency of wind turbines, so that its operating efficiency routinely exceeds the Betz limit. Applicants' preferred MEWT embodiment comprises: an aerodynamically contoured turbine shroud with an inlet; a ring of stator vanes; a ring of rotating blades (i.e., an impeller) in line with the stator vanes; and a mixer / ejector pump to increase the flow volume through the turbine while rapidly mixing the low energy turbine exit flow with high energy bypass wind flow. The MEWT can produce three or more time the power of its un-shrouded counterparts for the same frontal area, and can increase the productivity of wind farms by a factor of two or more. The same MEWT is safer and quieter providing improved wind turbine options for populated areas.

A hollow component for gas turbine engine, for example an outlet guide vane, is assembled from a body having at recessed pocket formed therein, and an aerodynamic cover bonded over the pocket. Both the cover and the body are constructed from materials which are not readily fusion weldable. The cover is attached to the body by a solid state bonding process, for example friction stir welding. The hollow component may also be built up from multiple individual components which are bonded to each other by a solid state bonding process such as friction stir welding.