63 results about "Air capture" patented technology

An apparatus for destroying mosquitoes by luring them into the apparatus where they are killed and their remains are incinerated. In order to lure the mosquitoes to the apparatus a mixture is emitted that attracts mosquitoes. The mixture contains a chemical attractant for mosquitoes that is stored in a container and metered out automatically. The mixture also contains carbon dioxide that is produced by the incineration of the mosquitoes and the chemical attractant. The apparatus includes an electric heater that heats the apparatus so that its skin temperature approximates the temperature of human skin. Once the mosquitoes are within the apparatus, a high velocity stream of recirculated air captures and carries them to a fan where they are killed and shredded. The shredded remains are incinerated to produce the carbon dioxide and to avoid the disposal of captured mosquitoes. Only a small portion of the recirculated air is emitted to the atmosphere thereby minimizing the consumption of electrical energy.

A void-free circuit board and a semiconductor package having the same includes a protective layer covering and protecting an electrode pattern formed on an upper surface of a substrate. The protective layer is applied around a solder ball provided on the electrode pattern except on an immediate vicinity of the solder ball to form an opening. The semiconductor package also includes at least one gap compensation part comprising a protrusion that comes in contact with an underfill material injected to the opening before the electrode pattern. The protrusion has a thickness substantially the same as that of a portion of the electrode pattern exposed in the opening. This prevents voids with air captured therein due to non-uniform capillary action during injection of the underfill material.

An air inlet duct for an air-breathing combined-cycle aircraft engines is internally divided into separate channels for low-speed and high-speed components of the engine, and contains one or more movable panels that are fully contained within the duct and pivotal between an open position in which incoming air is directed to both channels and a closed position in which all incoming air is directed to the channel leading to the high-speed engine. This integrated duct utilizes all incoming air at all stages of flight with no change in either the geometry of the air capture portion of the engine or the engine itself, and no exposure of movable leading edges. The result is a minimum of shock waves and a high degree of efficiency in operation of the engine.

Aft frame assemblies for a gas turbine transition pieces include a body comprising an exterior surface and a plurality of interior surfaces, one or more exterior cooling holes disposed on the exterior surface of the body for capturing compressor discharge air outside of the transition piece, and a supplemental component bonded to at least one of the plurality of interior surfaces of the body. At least one cooling channel is at least partially defined by the supplemental component and the interior surface that the supplemental component is bonded to, wherein the at least one cooling channel fluidly connects at least one of the one or more exterior cooling holes to one or more interior cooling outlets that discharge the compressor discharge air captured from the at least one of the one or more exterior cooling holes.

A vacuum chamber (2) for a direct air capture process and enclosing an interior space (13) for housing an adsorber structure (1) is given comprising a contiguous circumferential wall structure (115) along an axis (15), which circumferential wall structure (115) in an axial direction is closed by an inlet and an outlet axial wall (116), respectively, both axial walls (116) comprising at least one closing stainless steel lid (6) allowing for, in an open position, gas to be circulated through the vacuum chamber (2) for passing an adsorber structure (1), and, in a closed position, to close the interior space (13) and to allow evacuation of the interior space (13) down to pressure of 500 mbarabs or less.

An air inlet duct for an air-breathing combined-cycle aircraft engines is internally divided into separate channels for low-speed and high-speed components of the engine, and contains one or more movable panels that are fully contained within the duct and pivotal between an open position in which incoming air is directed to both channels and a closed position in which all incoming air is directed to the channel leading to the high-speed engine. This integrated duct utilizes all incoming air at all stages of flight with no change in either the geometry of the air capture portion of the engine or the engine itself, and no exposure of movable leading edges. The result is a minimum of shock waves and a high degree of efficiency in operation of the engine.

The invention discloses a solid rocket ramjet based on detonation combustion. The solid rocket ramjet comprises an outer shell, an inner core, an air inlet channel, an isolation section channel, a detonation combustion channel, a gas generator, a flow stabilizing ring cavity, a main fuel injection system, a rotary detonation combustion chamber, a tail spray pipe and other structures, wherein the air inlet channel, the isolation section channel and the detonation combustion channel are formed between the inner wall of the outer shell and the outer wall of the inner core; air captured by the air inlet channel is decelerated and pressurized in an isolation section and then enters the rotary detonation combustion chamber; the front portion of the inner core is of a hollow structure, the gas generator is arranged in the inner core, an oxygen-deficient solid propellant is combusted in the gas generator and forms fuel-rich gas, and the fuel-rich gas enters an expansion section of the isolation section channel through a main fuel injector, is fully mixed with fresh air and then is sprayed into the ring cavity of the rotary detonation combustion chamber; and the rotary detonation combustion chamber is provided with an ignition device, the tail spray pipe is installed at an outlet, chemical energy is converted into kinetic energy, and thrust is generated. The solid rocket ramjet has higher combustion efficiency and work performance.

A helmet cover that has an outer skin, an impact absorbing material and at least one vent comprising an aperture tough the helmet cover is described. A helmet cover vent may be aligned with a vent in a helmet, thereby providing for improved ventilation and cooling, and may be attached to a helmet. A helmet cover vent may be configured as a tapered or flared vent, and may be an air capture vent. The impact absorbing material may be configured over substantially the entire helmet cover surface, or may cover only a portion of the surface. In one embodiment, the impact absorbing material is configured as a discrete pad that is located where impact is most common, such as on the front, sides, or back of the helmet cover. A discrete pad may be interchangeable, allowing for customizing the type and location of impact absorption on the helmet cover.

The present invention describes device and method for redirecting airflow from a ventilation system, such as that of a vehicle, in order to warm, cool, or dry one or more articles, such as gloves, socks, or the contents of a beverage container. The dryer device comprises a housing comprising an air-capture portion, a body portion, and a nozzle portion. It further comprises an article-attachment system for holding one or more articles on the nozzle and a vent-attachment system for holding the dryer in place on a vent. Because the present invention beneficially exploits a preexisting ventilation system as a convenient source of forced air, it does not require an internal power source, heat source, or blower fan.

Permanent magnets are arranged at the interior of a rotating body at uniform intervals. The device comprises: a rotating body which is rotated by a motor; a heat generation part, which is disposed in the vicinity of the rotating body, which includes an electroconductive material, and which is disposed within the magnetic fields of the permanent magnets; and a hot air capture plate, which is disposed in the vicinity of the heat generation part, and in which a plurality of hot air flow passage holes are provided, the rotating body being rotated by a rotating shaft, which is coupled to the motor. Furthermore, a thermocouple may be connected to the heat generation part, and the heat energy that would be dissipated to the outside air is converted to electrical energy by the thermocouple. Furthermore, the electromagnetic induction device is constituted such that a hot air capture plate, in which a plurality of hot air flow passage holes are provided, is disposed in the vicinity of the heat generation part.

The present invention relates to a process and an apparatus of ocean carbon capture and storage (Ocean CCS), which can be used for carrying out carbon capture and storage of flue gas discharged from marine facilities using fossil energy such as coastal power plants and marine ships, and direct air capture (DAC). The natural engineering method are adopted in the present invention, and natural seawater is used for washing and dissolving CO2 gas for carbon capture; and natural seawater carbonate neutralization and formed bicarbonate is used for ocean storage in water column; and low head and large water flow is used to save energy. The discharged water complies with environmental regulations. The present invention provides an affordable and green effective mean for using marine ecosystems of carbon sinks and reservoirs to respond to the climate change.

Overflow systems are described for non-atmospheric pressure, slurry tank, which can reduce stagnation of excess flurry in an overflow pipe. In such systems, stagnation of the excess slurry in the overflow pipe is reduced via a recirculation conduit that allows for recirculation of at least a portion of the slurry from the tank. Moreover, an air capture unit collects a portion of an oxidation air from the tank. As a result, the fluid in the overflow system is representative of the aerated slurry within the tank.

A self-starting, self-aspirating valveless pulse-jet engine maximized to capture air during static operation. This invention is an improved adaptation of my U.S. Pat. No. 6,216,446, and continues to utilize a combustor tube, a forward-facing intake duct, a flame holder, a fuel supply means, and a spark plug to ignite the fuel-air mixture. To improve static air capture, the intake tubes of the intake duct, forward of the primary intake tube, that is joined to the combustion chamber, feature aggressively enlarged forward inlet mouths. By adjusting the relative diameters of the intake tubes that are inserted into each other, to achieve a greater difference of diameters, this adjustment, combined with aggressively enlarged intake tube mouths dramatically increases the ability of the intake duct to capture a maximum of air during static operation. Tests have shown the enlarged mouths are equally effective either as enlarged cupped mouths or as enlarged cones. Further improvement in air capture has been gained by adjusting the position of the aft end of the intake tube that is inserted inside the primary intake tube, so its position is in a range that is even with the plane created by the combustion chamber forward wall or just outside of the combustion chamber and closer to the mouth of the primary intake tube. (According to my U.S. Pat. No. 6,216,446, this intake tube was located so its aft end was inside the combustion chamber.) Further improvement in static air capture is made by specifying a diameter of the exhaust tube tail that has proved superior for air capture during static research testing. Capture of more air during static operation increases burn rate and thrust, and lowers specific fuel consumption, due to burning of leaner air-fuel mixtures. This invention also has improved thrust during dynamic operation, because the enlarged intake tube mouths capture more air during forward movement of the engine.

A wind electrical generation system includes a relatively large number of small, miniature wind-driven electrical generators or turbines arranged together in various predetermined configurations. Each generator includes a spinning wheel with a plurality of vanes driven by the wind flowing through a plurality of air channels. Each vane may be formed as a scoop to increase the surface area thereby increasing the air capture area of each vane. As each wheel rotates the wheel generates electricity that is captured and utilized for residential and / or commercial use. A control system preferably provides for a constant air velocity and pressure of the air stream in the air channels during operation of the system.

A system for providing ventilation to rack-mounted computers includes a plurality of rack-mounted computers on a plurality of motherboards each having a front end near a work space and a back end, a plurality of fans mounted near the back end of each of the plurality of motherboards and adapted to deliver heated air from the computers to a common warm-air plenum, and a plurality of motor controllers coupled to the plurality of fans and adapted to maintain a substantially constant exhaust temperature for each of the fans.

A system for neutralization of a target aerial vehicle comprises one or more counter-attack unmanned aerial vehicles (UAVs) and an aerial vehicle capture countermeasure tethering the counter-attack UAV(s) to a structure or ground. The counter-attack UAV(s) are operable to capture and neutralize the target aerial vehicle with the aerial vehicle capture countermeasure (e.g., a net). The system can comprise an on-board aerial vehicle detection system, and / or an external aerial vehicle detection system each having at least one sensor configured to detect the target aerial vehicle while in flight. The counter-attack UAV(s) and the associated detection systems may be autonomously operated for detecting and neutralizing a target aerial vehicle. The aerial vehicle capture countermeasure can be moved from a stowed position to a deployed position in response to coordinated flight of the counter-attack UAV(s). Associated methods and systems are provided.

A void-free circuit board and a semiconductor package having the same includes a protective layer covering and protecting an electrode pattern formed on an upper surface of a substrate. The protective layer is applied around a solder ball provided on the electrode pattern except on an immediate vicinity of the solder ball to form an opening. The semiconductor package also includes at least one gap compensation part comprising a protrusion that comes in contact with an underfill material injected to the opening before the electrode pattern. The protrusion has a thickness substantially the same as that of a portion of the electrode pattern exposed in the opening. This prevents voids with air captured therein due to non-uniform capillary action during injection of the underfill material.

An apparatus that can be used with a sleeve style receptacle to make an animal waste bag holder apparatus or used with a trash can receptacle to allow air captured between the bag and the inside surface of the trash can to escape. The apparatus includes a threaded bolt that extends through a side hole formed on the receptacle. The bolt's wide head is placed adjacent to the inside surface of the receptacle and the threaded shaft extends through the side hole. When a plastic bag is inserted into the receptacle, the bag's top edge is folded over the outside surface of the receptacle and placed below or adjacent to the side hole. The holder includes a wide flange nut with internal threads attached to the threaded shaft. When the flange nut is tightened on the shaft, the flange nut presses against the portion of plastic bag adjacent to the side hole. When tightened, the portion of the plastic bag is pulled which tightens the entire plastic bag around the receptacle.

Methods of sequestering carbon dioxide (CO2) are provided. Aspects of the methods include contacting an aqueous capture liquid, such as an aqueous capture ammonia, with a direct air capture (DAC) generated gaseous source of CO2 under conditions sufficient to produce an aqueous carbonate liquid, such as an aqueous ammonium carbonate. The aqueous carbonate liquid is then combined with a cation source under conditions sufficient to produce a solid CO2 sequestering carbonate. Also provided are systems configured for carrying out the methods.

The invention discloses an identity identification system for personnel by air at an airport boarding gate and a control method. The system comprises a plurality of information gathering modules, an information control module and a plurality of information comparison modules, wherein the information gathering modules comprise an identity document recognizer for personnel by air and a plurality of image capturing cameras; the information comparison modules comprise a boarding check code scanner, a plurality of image capturing cameras, and a multi-screen display; the information control module comprises an information receiver, an information storage analyzer and an information transmitter which are connected with one another. The system has the advantages that firstly, the system has security, and security personnel at the boarding gate can rapidly judge whether the personnel by air intentionally exchange boarding checks or carry objects which are not carried with the personnel by air during checking in by comparing image information of the personnel by air; secondly, the system has high efficiency, the system can rapidly call images of the personnel by air captured by a flight security counter at the boarding gate, the operation efficiency of the system is high, the requirement on hardware is low, and the system is convenient for promotion and application; thirdly, the system is combined with the current check-in process, and is convenient to upgrade and reconstruct.

The present invention pertains to a process for producing captured carbon dioxide. Calcium carbonate may be reacted with sulfur dioxide to produce calcium sulfite and gaseous carbon dioxide. Calcium sulfite may be thermally decomposed to produce gaseous sulfur dioxide. The processes may be used in conjunction with combusting various fuels such as a carbonaceous fuel, or a sulfurous fuel, or a nitrogenous fuel, or a hydrogen fuel, or a combination thereof.

The invention provides an investigation battle robot which comprises an unmanned aerial vehicle, a camera, a winch, a sleeve ring, a steering engine, a hinge support, a miniature rocket, an electromagnet, a catching net, a permanent magnet, sleeves, a steel wire rope, a rope winding motor and a rope winding wheel. The investigation battle robot is characterized in that the winch is fixedly installed below a machine frame of the unmanned aerial vehicle, the lower portion of the steel wire rope of the winch is connected with the catching net, and the periphery of the catching net is provided with the sleeves. By arranging the unmanned aerial vehicle and the catching net, enemy side solders can be caught from the air, and the flight route of the catching net can be adjusted through the miniature rocket in the flight process.

Permanent magnets are arranged at the interior of a rotating body at uniform intervals. The device comprises: a rotating body which is rotated by a motor; a heat generation part, which is disposed in the vicinity of the rotating body, which includes an electroconductive material, and which is disposed within the magnetic fields of the permanent magnets; and a hot air capture plate, which is disposed in the vicinity of the heat generation part, and in which a plurality of hot air flow passage holes are provided, the rotating body being rotated by a rotating shaft, which is coupled to the motor. Furthermore, a thermocouple may be connected to the heat generation part, and the heat energy that would be dissipated to the outside air is converted to electrical energy by the thermocouple. Furthermore, the electromagnetic induction device is constituted such that a hot air capture plate, in which a plurality of hot air flow passage holes are provided, is disposed in the vicinity of the heat generation part.

The present disclosure provides systems and methods useful in capture of one more moieties (e.g., carbon dioxide) from a gas stream (i.e., direct air capture). In various embodiments, the systems and methods can utilize at least a scrubbing unit, a regeneration unit, and an electrolysis unit whereby an alkali solution can be used to strip the moiety (e.g., carbon dioxide) from the gas stream, the removed moiety can be regenerated and optionally purified for capture or other use, and a formed salt can be subjected to electrolysis to recycle the alkali solution back to the scrubber for re-use with simultaneous production of one or more further chemicals.

The present invention provides a novel system and method for collecting CO2 and H2O from ambient air, using the power of a blower forcing air or another gas through a Reverse Venturi device (also called a divergent-convergent duct), to decrease the velocity of the air over a carbon capture device, and thereby increase the pressure of the unit, which results in raising of the dew point and the subsequent condensation of water in the air. This reduces the sorbent that is absorbed by the passing air stream, and increases the uptake of water vapor when a sorbent is used that attracts water.

A helmet cover that has an outer skin, an impact absorbing material and at least one vent comprising an aperture through the helmet cover is described. A helmet cover vent may be aligned with a vent in a helmet, thereby providing for improved ventilation and cooling, and may be attached to a helmet. A helmet cover vent may be configured as a tapered or flared vent, and may be an, air capture vent. The impact absorbing material may be configured over substantially the entire helmet cover surface, or may cover only a portion of the surface. In one embodiment, the impact absorbing material is configured as a discrete pad that is located where impact is most common, such as on the front, sides, or back of the helmet cover. A discrete pad may be interchangeable, allowing for customizing the type and location of impact absorption on the helmet cover.

Provided is a positive-pressure floating type airplane comprising an airfoil portion, left-right fuselages, a central fuselage, an elevator and a rudder disposed at the back of the airfoil portion, a thruster disposed at the back of the central fuselage, and a horizontal stabilizer disposed at the rear ends of the left-right fuselages. The individual front ends of the airfoil portion, the left-right fuselages and the central fuselage are formed into arcuate shapes in longitudinal sections. On the lower side of the airfoil portion, a recessed air capture is formed from the front end to the rear end. As a result, the positive-pressure floating type airplane is floated by the reaction from the air at the time when the air to pass the air capture through the airfoil portion is pushed by the thrust of the thruster, and is propelled forward by the component of that thrust.

A helmet cover that has an outer skin, an impact absorbing material and at least one vent comprising an aperture through the helmet cover is described. A helmet cover vent may be aligned with a vent in a helmet, thereby providing for improved ventilation and cooling, and may be attached to a helmet. A helmet cover vent may be configured as a tapered or flared vent, and may be an, air capture vent. The impact absorbing material may be configured over substantially the entire helmet cover surface, or may cover only a portion of the surface. In one embodiment, the impact absorbing material is configured as a discrete pad that is located where impact is most common, such as on the front, sides, or back of the helmet cover. A discrete pad may be interchangeable, allowing for customizing the type and location of impact absorption on the helmet cover.