472 results about "Air breathing" patented technology

The present invention is a space launch system and method to propel a payload bearing craft into earth orbit. The invention has two, or preferably, three stages. The upper stage has rocket engines capable of carrying a payload to orbit and provides the capability of releasably attaching to the lower, or preferably, middle stage. Similar to the lower stage, the middle stage is a reusable booster stage that employs all air breathing engines, is recoverable, and can be turned-around in a short time between missions.

The invention discloses an air-breathing pulse detonation engine and a detonation method thereof. An air inlet channel, a mixed evaporator, a detonation chamber and a tailpipe are connected along an air inlet direction in turn, and a leaf valve, a main fuel nozzle and an air discharge cavity are arranged in an air inlet ring cavity along the air inlet direction in turn, wherein the fuel radially injects through the main fuel nozzle; the air discharge cavity and an air discharge tube are communicated through a through hole of a central body bracket to the exterior of an outer wall of the air inlet channel; the leaf valve maintains a forward normally opened state; a detonation tube is arranged in the detonation chamber through a mounting bracket; a drainage tube, an igniter and a heat exchanger are arranged on the detonation tube; a plurality of jet holes are formed on a tail side wall or a tail end face; the igniter is positioned on the front section of the detonation tube; and the drainage tube is gapped in the detonation chamber and near the igniter inside the detonation tube respectively. The air-breathing pulse detonation engine has the advantages of capabilities of reliably working under severe condition, realizing lower forward flow resistance, simultaneously suppressing and using reverse flow and improving the engine thrust, along with simple structure and wide flight range.

Pressure and density of a gaseous mixture are increased in the process of introducing the gaseous mixture into the combustor of an air-breathing pulse detonation engine employing atmospheric oxygen as an oxidizer. The exit valve 20 able to be opened and closed is provided at the outlet of the combustor 15, an air cooler 12 is provided in the exit of the intake, and density is increased by exchange of heat of the air received at the intake with a coolant in the air cooler 12. Furthermore, by closing the exit valve 20 provided in the outlet of the combustor during the process of loading the gaseous mixture, transition to the detonation process is possible without expansion of the high-pressure high density air obtained by ram-compression at the intake.

A gas diffusion cathode for electrochemical cells provides higher power capability through the use of nano-particle catalysts. The catalysts comprise nanometer-sized particles of transition metals such as nickel, cobalt, manganese, iron, palladium, ruthenium, gold, silver, and lead, as well as alloys thereof, and respective oxides. These catalysts can substantially replace or eliminate platinum as a catalyst for oxygen reduction. Cathodes using such catalysts have applications to metal-air batteries, hydrogen fuel cells (PEMFCs), direct methanol fuel cells (DMFCs), direct oxidation fuel cells (DOFCs), and other air breathing electrochemical systems.

An end plate of an air breathing fuel cell stack and an air breathing fuel cell stack including the same. The air breathing fuel cell stack includes a membrane electrode assembly, including an anode electrode, a cathode electrode, and an electrolyte positioned between the anode electrode and the cathode electrode; and an end plate contacting the membrane electrode assembly. The end plate includes a first surface contacting the membrane electrode assembly, an opposing second surface; and a collector positioned at the first surface and contacting the cathode electrode.

The invention discloses a hypersonic variable-geometry air inlet channel with a rectangular section and belongs to the field of pneumatic design of aerospace aircrafts. A seam through which a lip mask adjustable side plate penetrates and moves is formed in the front body of an aircraft; one end of the lip mask adjustable side plate is linked with the leading edge of a lip mask with a rectangular section through a rotating motion pair and the other end of the lip mask adjustable side plate is connected with a side plate actuating barrel arranged in the front body of the aircraft; the side plate actuating barrel controls the lip mask adjustable side plate to rotate with single freedom degree. The invention further provides a design method and a work mode of the hypersonic variable-geometry air inlet channel with a rectangular section. By adjusting the sweep angle of the lip mask adjustable side plate, the adjustment of the air inlet channel from idle state to starting state and the increasing and decreasing of mach number flow rate capture rate of the air inlet channel are realized; the hypersonic variable-geometry air inlet channel with a rectangular section is simple in structure and easy to control; the work efficiency of the propulsion system of a suction type hypersonic aircraft is greatly increased.

A direct methanol fuel cell unit is provided with a fuel cell including an anode, a cathode with a hydrophobic microporous layer, an electrolyte membrane put in-between, and a fuel supply path supplying fuel to the anode. The fuel supply path is provided with an upwind water barrier preventing back-diffusion of water and a gas flow path channeling gas generated at the anode and disposed between the barrier and the anode. A water-rich zone is formed between the water barrier and the cathode microporous layer. Water loss from either side of this zone is eliminated or minimized, thereby permitting direct use of highly concentrated methanol in the fuel flow path with good fuel efficiency and power performance. The cell unit can be applied equally well to both an active circulating air cathode and an air-breathing cathode.

The invention discloses a pre-cooling air-breathing type variable cycle engine and relates to the reusable pre-cooling air-breathing type variable cycle engine applied to aeronautics and astronautics devices. The engine mainly consists of a pre-cooler, a turbine engine, a super combustion chamber and a super combustion ramjet engine, wherein the pre-cooler and the super combustion chamber form a subsonic combustion ramjet engine; a turbine subsonic combustion ramjet engine is connected with the super combustion ramjet engine in parallel; working states of the turbine subsonic combustion ramjet engine and the super combustion ramjet engine are selected by adjusting a switching adjusting device, so that the working modal of the whole engine is controlled. The pre-cooler can reduce an inlet gas flow temperature of a super combustion chamber, can increase the efficiency of the super combustion chamber, can expand the working range of a subsonic combustion punching modal, and can make up insufficient thrust force when turbine subsonic combustion ramjet engine is transferred to the super consumption ramjet engine, so that the pre-cooling air-breathing type variable cycle engine has the advantage that the transfer class of a combined engine is stably transferred.

A system for adjusting ambient air temperature shielding an engine. The system includes an engine having first and second ends and a heat generating source, and a shield having a substantially cylindrical portion defining an interior cavity. At least a portion of the heat generating source is disposed in the cavity. The shield has a heat reflecting interior surface facing the cavity and an opposing exterior surface. The interior surface reflects heat generated by the heat source.

Passive water management techniques are provided in an air-breathing direct oxidation fuel cell system. A highly hydrophobic component with sub-micrometer wide pores is laminated to the catalyzed membrane electrolyte on the cathode side. This component blocks liquid water from traveling out of the cathode and instead causes the water to be driven through the polymer membrane electrolyte to the cell anode. The air-breathing direct oxidation fuel cell also includes a layer of cathode backing and additional cathode filter components on an exterior aspect of the cell cathode which lessen the water vapor escape rate from the cell cathode. The combination of the well laminated hydrophobic microporous layer, the thicker backing and the added filter layer, together defines a cathode structure of unique water management capacity, that enables to operate a DMFC with direct, controlled rate supply of neat (100%) methanol, without the need for any external supply or pumping of water. The cell anode is provided with a hydrophilic backing layer. When the water is driven through the polymer membrane electrolyte from the cell cathode to the cell anode chamber, it is available for the anodic reaction, and any excess water is carried out along CO₂ ventilation channels to the outside environment.

Air-blowing or air-breathing compressor cascade experimental system relates to an experimental installation of testing compressor cascade. The present invention solves the problem of prior test equipment can not test inner flowing in air-blowing or air-breathing compressor cascade. The right and left two ends between said top plate (7) and bottom plate (8) are equipped with at least one solid blade (9) separately, three hollow blades (10) are installed between the top plate (7) and the bottom plate (8) in said solid blade (9), said upper Air-blowing/air-breathing interface (11-1) are installed on the top horizontal section of each hollow blades (10), said lower Air-blowing/air-breathing interface (11-2) are installed on the bottom horizontal section of each hollow blades (10), said probe (12) is installed between the top plate (7) and the bottom plate (8). The invention can be considered as the simplified model of carefully analysis of three-dimensional flow field structure and the aerodynamic performance in compressor cascade, it is the effective approach of the searching of compressor performance improvements.

When operating an air-breathing engine, a liquid is injected in atomized form into an air intake duct of the engine. A measurement apparatus for determining the injected drop size or the drop concentration is arranged in or on the intake duct downstream of the location of the injection. These measured values are input into a control system, which controls suitable parameters of the injection apparatus in such a manner that the determined variables are controlled to desired values or into desired value ranges.

A thermally insulated hand glove for use in sporting activities. The hand glove has a main body for enclosing a user's hand, with a palm area having an exposed wall surface being substantially waterproof. A window aperture is made in a fraction of the palm area. A moisture permeable stretchable membrane is applied to fully close the window aperture, so as to provide an air vent system integral to the palm area for promoting moisture outflow generated from the user's hand palm perspiration outwardly from said glove main body, while controlling accidental moisture inflow seepage from outside weather conditions. The stretchable nature of the arcuate membrane pad biases the thumb finger part of the glove to a tilted location overhanging spacedly over the window, thus reducing the likelihood of accidental access of water or snow to the non waterproof membrane pad covering the window.

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 multi-physical fused fire monitoring system and method thereof for predicting fire probability of occurrence. The monitoring system comprises a point type smoke sensing detector, a point type temperature sensing detector, a line type beam smoke sensing detector, an air-breathing smoke sensing fire detector, a cable line type temperature sensing detector, a cable multi-point type temperature detector, an in-place module, a first station layer switch and a cable fire monitoring early-warning system server. The method comprises the following steps: step one, orderly performing initialization, denoising and normalization on sensor data; step two, initializing a feature layer, selecting a random input weight beta and an output target T to form an input matrix H; step three, processing the feature layer data in batch, performing weight iteration after the initialization; step four, making the final judgment through an algorithm; and step five, judging that the fireoccurs and giving an alarm if a fusion result is greater than a set threshold, or repeating the steps 1-4. Through the system and method disclosed by the invention, the false alarm and the failed alarm of the fire can be effectively reduced, and the accuracy of the fire prediction can be greatly improved.

The invention discloses a low-cost tapping deoxidizing technique of an electric-arc furnace, which is characterized in that the low-cost carbon power is used for predeoxidizing in the prophase of tapping, the cheap ferrosilicon is used for shallow-deoxidizing in the metaphase of tapping, the aluminum block with strong deoxidizing ability is used for deep-deoxidizing in the anaphase of tapping, thereby the molten steel becomes to the aluminum killed steel finally, the oxygen activity of the molten steel is controlled to the control range of the clean steel. The invention has the technical proposal that: (1) by optimizing the operating process of tapping deoxidizing, the deoxidization is controlled, the acieration is eliminated and the air-breathing is lessened, (2) the low-cost carbon power and ferrosilicon substituting for part of expensive aluminum are used for controlling the tapping deoxidizing , the cost of tapping deoxidizing of electric-arc furnace is greatly reduced.

The invention discloses an air inlet of an air-breathing pulse detonation engine. The housing of the engine constitutes the circular air inlet, wherein an inlet cone is arranged on the medial axis at the rear end of the air inlet; a cylindrical structure at the rear part of the inlet cone and the housing of the engine constitute a ring-shaped channel; the air flow is fed into a special-shaped channel having a special-shaped structure via the ring-shaped channel; the special-shaped channel is evenly distributed on the circumference of the air inlet with the distance between the central symmetrical curve of the special-shaped channel and the medial axis of the engine remaining unchanged but deviating along the circumference; a fuel channel is arranged on the medial axis of the inlet cone, and the two ends of the fuel channel are connected with the fuel inlet and a fuel injection lever located on the medial axis outside the rear end of the cylindrical structure; the fuel injection lever is particularly a hollow oil tube with one end thereof being closed; a plurality of fuel injection holes are formed on the lateral surface of the fuel injection lever; the housing of the engine and the rear end surface of the cylindrical structure constitute a mixing chamber; and an igniter is located on the lateral wall of the mixing chamber. The invention can improve the atomization and evaporation of the fuel and reduce the impact of reversed fuel on the air inlet.

The invention relates to a hypersonic velocity air-breathing type ramjet pneumatic thrust integrated analysis method. The method comprises the steps of: S1, acquiring the parameters of a to-be-analyzed hypersonic velocity air-breathing type ramjet; S2, calculating the mass flow rate of incoming flow air and the Mach number of an outlet of an admission passage according to the input parameters; S3, calculating the Mach number of an outlet of a combustor heat release section according to the Mach number of the outlet of the admission passage obtained through calculation in S2; S4, calculating the Mach number of an outlet of an exhauster of gas flow according to the Mach number of the outlet of the heat release section obtained through calculation in S3; S5, calculating ramjet thrust data according to the Mach number of the outlet of the exhauster obtained through calculation in S4. The method can perform hypersonic velocity air-breathing type ramjet pneumatic thrust calculation rapidly, provide a powerful tool for the pneumatic layout design optimization of hypersonic aerocrafts, provide optimal analysis results, and save the development time cost and the money cost for numerical simulation and experiment verification in the development of hypersonic aerocrafts.