18 results about "Ram-air intake" patented technology

The invention particularly relates to a parallel combination engine starting and fuel oil supply system cross-linking structure and a control method, and the parallel combination engine starting and fuel oil supply system cross-linking structure comprises an air turbine, an aircraft accessory cartridge receiver, an engine transmission system and a stamping fuel oil pump; an air turbine shaft is connected with an aircraft accessory casing, a starting clutch is arranged between the air turbine shaft and the aircraft accessory casing, the aircraft accessory casing is connected with an engine transmission system, and the engine transmission system is connected with a turbine engine; an air turbine shaft is connected with a ramjet fuel pump, an oil supply clutch is arranged between the air turbine shaft and the ramjet fuel pump, and the ramjet fuel pump is used for The air turbine is connected with an airplane auxiliary power system through an air entraining pipeline; an auxiliary air entraining valve is arranged on the air entraining pipeline; the air turbine is connected with the turbine engine fan rear flow channel through an air entraining pipeline, and a fan air entraining valve is arranged on the air entraining pipeline. The air turbine is connected with the stamping air inlet channel through an air entraining pipeline, and a stamping air entraining valve is arranged on the air entraining pipeline.

The application relates to a main landing gear cabin ventilation device and an airplane comprising the device. In the device, a ram air inlet is located on a ram air side of a skin; a main air supply pipeline is connected to the ram air inlet; a ventilation disc is located at the end of the main air supply pipeline and used for conveying ram air to a wheel assembly in the main landing gear cabin; a bypass pipeline is connected to the ram air inlet; a skin air outlet is located at the end of the bypass pipeline; a flow self-adjusting module is installed in the bypass pipeline; a throttle contraction structure defines a flow channel; an air bag is located in the flow channel; the flow area of the flow channel is changed by expansion or contraction of the air bag; one end of a heat pipe is connected to a wind collecting cover, and the other end of the heat pipe is inserted into the air bag and used for transmitting heat of the wheel assembly to the air bag so that the air bag is expanded or contracted. According to the above technical scheme, the following beneficial technical effects can be achieved: the main air supply pipeline flow can be automatically adjusted according to the temperature state of the wheel assembly, and the main landing gear cabin is cooled on demand.

The application belongs to the field of aviation environmental control system design, and particularly relates to a bidirectional-ejection-based aircraft heat exchange system. The system comprises a ram air inlet channel, a heat exchanger and an air circulator. The ram air inlet channel comprises a ram air inlet section (1), a transition ejection section (4) and a ram air outlet section. The heat exchanger comprises an air-liquid heat exchanger (2), a first air-air heat exchanger and a second air-air heat exchanger. The air circulator comprises a first air circulator and a second air circulator. The bidirectional-ejection-based aircraft heat exchange system utilizes the principle of constant entropy ejection to limit the ram air flow entering the left and right ram air outlet channels, and integrates the cold side of the heat exchanger with the ram air inlet channel, and matches the dynamic pressure brought by the ram air with the flow resistance of the heat exchanger group, thereby effectively avoiding problems such as fan overspeed, windmill effect and surge of the air circulator.

The stamping air inlet system of the motorcycle comprises an air inlet, an air filter and an air inlet connecting pipe used for communicating the air inlet with the air filter, the air inlet is located in the front portion of the motorcycle, and the air inlet connecting pipe is provided with an air inlet front section communicated with the air inlet and an air inlet rear section communicated with the air filter. The air inlet front section is obliquely arranged forwards and downwards, and a drainage hole is formed in a bottom plate of the air inlet rear section; the air inlet hole is formed in the front portion of the motorcycle, the position is a stagnation point at the front end of the motorcycle and is a point with the highest air flow speed, the peripheral structure is relatively simple, a large stamping air inlet can be designed, the air inlet amount is increased, the air inlet front section of the air inlet connecting pipe is designed downwards, and large foreign matter such as stones can be prevented from entering the air inlet connecting pipe and being directly sucked into an air filter. And the drainage hole can ensure that stones and water drops entering the air inlet rear section of the air inlet connecting pipe can be discharged in time.

A system and method for ram air intake for pulse combustion systems is disclosed that improves the ability of pulse combustions to ingest air into the inlet pipe when the pulse combustion system is moving in a direction opposite the direction the open end of the inlet pipe is facing and the system and method includes the ability to increase the thrust output from the pulse combustion system.

The invention belongs to the technical field of aero-engine thermal management, and particularly relates to a multi-objective optimization method for configuration parameters of an NACA ram air inlet of an aero-engine. According to the aero-engine NACA ram air inlet configuration parameter multi-objective optimization method, an NACA air inlet bleed air characteristic database under different configuration parameters is created based on aero-engine NACA ram air inlet CFD fluid numerical simulation, and a BP neural network method is adopted; a mapping relation among the air inlet configuration parameters, the air flow and the aerodynamic resistance under typical working conditions is established, and an agent model for predicting the air entraining performance of the air inlet configuration parameters is constructed. On the basis, the large air entraining amount and low air entraining resistance of the NACA air inlet serve as optimization targets, multi-target optimization research on all configuration parameters of the NACA air inlet is carried out, a Pareto solution set is obtained, and an optimized NACA air inlet configuration is obtained based on a LINMAP decision scheme.

The invention discloses an air door control method, an air door control mechanism and an aircraft, and relates to the technical field of aircrafts, the air door control method comprises the following steps: obtaining a current flight speed and a target air inflow; determining a target gear according to the current flight speed and the target air inflow; and the gear of the actuating piece is adjusted to the target gear, so that the opening degree of an air door of the stamping air inlet duct is adjusted to the target opening degree. The technical problem that the stamping air inflow cannot well meet the air inflow requirement of the cabin can be solved.

A spacecraft power system relates to the field of aerospace engine technology. The YRCW aerospace engine comprises an air intake system, a central RCW engine, and two side YRC engines. The YRCW aerospace engine can operate in four modes: ramjet turbine, ramjet, superramjet, and rocket. The ramjet combustor can accommodate four combustion modes. An inlet airflow separator randomly distributes the RCW and YRC airflows. The combustion gas impacts the turbine, driving the axial-flow intake compressor and centrifugal compressor to inhale and compress air. The compressed air is distributed through four bypass ducts, entering the cold air, hot exhaust gas, and vectored airflow hoods, respectively. This provides compressed cold air and cooling gas, as well as vectored injection air, for closed-loop combustion of the RCW and YRC engines. Adjusting the geometric positions of the conical ramjet intake valve, the compressed cold air, hot exhaust gas, the fuel injection plate, and the oil pressure and oil volume support channel valves ensures smooth transitions between the engine's multi-mode operating modes, stable flames, and sustained combustion, enabling the aerospace vehicle to achieve single-stage orbital flight within a full envelope.

The application discloses a kind of wind engined double-core vehicle-mounted power system based on iron air cell, it is related to new energy automobile power technical field.System includes iron air main battery module, auxiliary power lithium battery module, passive wind collision ram air intake component, intelligent power switching controller and modularization quick battery replacement structure.Iron air main battery as main energy realizes long endurance, zero combustion explosion, low-cost power supply, and auxiliary lithium battery is only used for instantaneous peak power supplement;Adopt car head wind collision guide groove and Venturi tube to form no-energy-consumption passive air intake system, provide high-pressure airflow for iron air cell, cancel gas storage tank and realize light weight;Through three-mode intelligent switching, economic, sports and kinetic energy recovery conditions are realized, and standardization battery replacement interface can complete battery replacement in 3-5 minutes.The application considers super-long endurance and explosive performance, completely gets rid of lithium cobalt resource dependence, has high safety, low maintenance cost, can seamlessly adapt to existing battery replacement network, is suitable for various passenger car models, has significant engineering landing and commercialization value.

The invention discloses a double-working-mode combustion chamber adapting to slow combustion and rotating detonation. The double-working-mode combustion chamber comprises a stamping air inlet structure, a swirler, a compression air inlet structure, a concave cavity section, a Laval nozzle section, an annular combustion chamber section and a turbine structure. An adjustable injection structure is arranged between the stamping air inlet structure and the swirler, an oil supply structure is arranged on the surface of the concave cavity section, and the annular combustion chamber section is provided with a detonating structure. Air is supplied from the stamping air inlet structure and the compression air inlet structure, fuel gas is formed after oil is sprayed by the oil supply structure, and the two working modes are met by adjusting the gas amount and the oil amount; when the air flow is small, the air flow is in a subsonic flow state, and a graded and partitioned slow-burning combustion mechanism is adopted; when the air flow is large, the air flow is in a transonic flow state, and a rotary detonation combustion mechanism is adopted. The two modes can meet the requirement for combustion stability of the combustion chamber under different working requirements, so that the combustion chamber has a wide working range, and by means of graded and partitioned combustion, the good emission characteristic is achieved under the slow combustion working condition.

The invention discloses an intelligent coupling system for aluminum melting heat storage and wind power air compression. The intelligent coupling system comprises an aluminum melting pool, a wind power / photovoltaic power generation device, a novel turbine, an intelligent speed change device, a heat recovery system and an intelligent control system. The aluminum melting pool uses metal aluminum as a heat storage medium, compressed air is heated through a stainless steel coil pipe, a large-scale structure is built by refractory bricks and heat preservation materials, and a small-scale structure is a stainless steel tank. The wind power fan directly drives the compression pump to store air, and the photovoltaic device is coupled with the air compressor and the heat storage electric appliance. The novel turbine is modified based on an automobile turbine, stamping air inlet nozzles are formed in the periphery of the novel turbine, and the rotating speed of the intelligent speed change device is adjusted through 16 sets of double-layer gears. The heat recovery system forms closed circulation through a carbon dioxide condensation pipe, and turbine exhaust waste heat is recovered. The intelligent control system adjusts the air inflow according to the electricity demand, and the overvoltage and undervoltage protection device guarantees the voltage stability.

This invention discloses a damper control method, a damper control mechanism, and an aircraft, relating to the field of aircraft technology. The damper control method includes the steps of: acquiring the current flight speed and the target air intake volume; determining a target gear position based on the current flight speed and the target air intake volume; and adjusting the gear position of the actuator to the target gear position, so that the damper opening of the ram air intake duct is adjusted to the target opening. This invention can solve the technical problem that the ram air intake volume cannot be well adapted to the cabin air intake requirements.

The invention belongs to the technical field of aero-engine structural design, and relates to a wide-area ramjet combustion chamber. The structure comprises a spindle-shaped pre-combustion chamber arranged in a stamping combustion chamber, and the front end of the spindle-shaped pre-combustion chamber is connected with an ignition area fuel oil pipeline, an oxygen supplementing pipeline and a stamping air inlet channel through an ignition fuel oil swirl nozzle, an oxygen swirl nozzle and an air swirl nozzle which are coaxially arranged in a sleeved mode; and the rear end of the pre-combustion chamber is connected with a flared flame stabilizer. A main fuel oil circulation cavity channel is formed between the inner wall and the outer wall of the pre-combustion chamber and communicated with a fuel oil pipeline of a main combustion area through a rectification throat channel, and fuel oil is distributed to a spraying hole of the flame stabilizer and a tail oil spraying ring through a rectification partition plate. Wide-area reliable work of the stamping combustion chamber is achieved.

The invention belongs to the technical field of aircraft environment control systems, and particularly relates to an aircraft inside and outside air inlet high-temperature air pre-cooling mechanism which comprises an openable and closable stamping air inlet mechanism, an air inlet channel switching mechanism, a plate-fin heat exchanger and a controller. An inlet of the openable and closable stamping air inlet mechanism is communicated with the outside atmosphere, and an outlet is connected to a cold side inlet of the plate-fin heat exchanger; an inlet of the air inlet channel switching mechanism communicates with an aircraft air inlet channel, and an outlet of the air inlet channel switching mechanism is connected to a cold edge inlet of the plate-fin heat exchanger. The controller controls opening and closing switching of the openable and closable stamping air inlet mechanism and the air inlet channel switching mechanism according to a flight state signal, and cold edge air source switching is achieved. According to the low-detectability air inlet and air inlet channel switching system, a traditional stamping air inlet mode is replaced with a stamping air inlet and air inlet channel switching mode, and the low-detectability performance and the cruising ability of an aircraft are effectively improved.

The invention discloses a wide-temperature-range strong pre-cooling system, an aircraft and an air inlet pre-cooling control method, and the wide-temperature-range strong pre-cooling system comprises a cooling unit; the cooling unit comprises a capillary tube bundle, and cooling water is pre-stored in the capillary tube bundle to form a pulsating heat tube; the liquid metal supply unit can be communicated with the cooling unit; the gas path unit can be communicated with the cooling unit; the water spraying unit can be communicated with the cooling unit; the air inlet cooling device meets the stamping air inlet cooling requirement of a wide speed range.

The utility model belongs to the technical field of aircraft environment control, and relates to a split riveting combined type waterproof stamping air inlet pipeline which comprises a stamping air inlet base, the stamping air inlet base is connected with an aircraft body, and a riveting combined stamping air inlet pipeline is connected to the stamping air inlet base. A stamping transition pipe is inserted into the front end of the riveting combination stamping air inlet pipeline, and waterproof butt straps are arranged on the front side and the rear side of the stamping air inlet base correspondingly and connected with an aircraft body. The problem of fatigue fracture caused by welding deformation is solved, the service life of the stamping air inlet pipeline is prolonged, and the reliability of the stamping air inlet pipeline is improved.

The application discloses a kind of quick evaluation methods of rotating detonation ramjet overall performance, the calculation method is smoothly started, and the input parameters such as flight condition, engine key geometric parameter and inlet characteristic parameter are used as pre-constraint condition to ram intake, flow matching, engine stable work, based on chemical reaction dynamics calculation airflow along the way variation and detonation combustion process. Through the iteration calculation of combustion chamber entrance choke ratio, combustion chamber and isolation section pressure matching, realize the conservation of aerodynamic parameter and thermodynamic parameter, and there is loss factor correction calculation result. Finally, engine overall performance parameters (thrust, specific impulse) can be obtained, and detailed aerodynamic parameters and thermodynamic parameters of main internal flow section. The application is fast and reliable in calculation, and can obtain engine component performance parameters, which is helpful for engineering application of rotating detonation ramjet, and provides technical support for hypersonic vehicle and its propulsion technology performance analysis.

An environmental control system for a vehicle includes an environmental control system pack including a ram air circuit and a thermodynamic device. The ram air circuit includes a ram air shell having a ram inlet and a ram outlet and at least one ram air heat exchanger arranged within the ram air shell. A ram air fan is fluidly coupled to the ram air shell. A bypass conduit is fluidly connected to a source of compressed medium. The bypass conduit has an outlet end positioned adjacent to a surface of the ram air fan for delivering a compressed medium to the surface.