727results about "Air-treatment apparatus arrangements" patented technology

Aircraft capable of hovering comprising a fuselage at least one rotor that is rotatable with respect to the fuselage, electrical drive means adapted to rotate the rotor and electrically powered by a battery, and a cooling system of the battery. Said cooling system comprises, in turn, a first opening for the air to enter, second openings for the air to escape and a passage which places the first opening in fluidic communication with the second openings and within which the battery is placed. The cooling system further comprises a fan adapted to increase the kinetic energy of the air contained in the passage and which is operated when the forward speed of the aircraft with respect to the ground is lower than a speed threshold value and / or when the temperature of the battery exceeds a temperature threshold value.

An environmental control system of an aircraft, having: a cooling circuit including: a sealed housing; a turbo-compressor sealed within the housing, wherein the turbo-compressor includes: a compressor fluidly coupled to the circuit; a turbine fluidly coupled to the circuit downstream of the compressor, wherein the turbine is a flash turbine; a shaft operably coupling the compressor and the turbine; and a motor generator operably coupled to the turbo-compressor and disposed within the housing.

The invention relates to the technical field of aviation thermal management systems, in particular to a split-flow dual-mode refrigeration comprehensive thermal management system, a hybrid aircraft and a method. A split-flow dual-mode refrigeration comprehensive heat management system comprises a secondary refrigerant heat conduction loop and an evaporation circulation refrigeration loop. The secondary refrigerant heat conduction loop comprises a liquid cooling pump, a power battery heat conduction flow channel, a flow divider, a storage tank, a starter generator heat conduction flow channel and a liquid cooling radiator. The evaporation circulation refrigerating loop comprises a compressor, a condenser, a throttle valve and an evaporator which are communicated in sequence; the split-flow dual-mode refrigeration comprehensive heat management system comprises a mixed refrigeration mode; a secondary refrigerant flowing loop of the secondary refrigerant heat conduction loop in the mixed refrigeration mode comprises a first sub-loop and a second sub-loop; therefore, the problems of high evaporation circulation power and low power-to-weight ratio of the battery thermal management system are solved.

Systems and methods for cooling an aircraft galley cart compartment by providing cooling from a potable water flow circuit directed from an aircraft potable water supply to provide direct and indirect cooling are disclosed.

An aircraft includes an aircraft heat source; a propulsion system including an electric propulsion engine, the electric propulsion engine including an electric motor and a fan rotatable by the electric motor, the electric propulsion engine further defining a fan air flowpath; a thermal management system including a heat source exchanger in thermal communication with the aircraft heat source, a heat sink exchanger in thermal communication with the fan air flowpath of the electric propulsion engine, and a thermal distribution bus extending from the heat source exchanger to the heat sink exchanger; and a control system operably connected to the thermal management system for selectively thermally coupling the heat sink exchanger with the heat source exchanger.

An environmental control system pack for an aircraft that includes a ram air circuit and a bleed flow circuit. The ram air circuit receives air from an atmosphere on an exterior of the aircraft and expels the air through an outlet back into the atmosphere. The bleed flow circuit receives bleed air and cools the air prior to the bleed air being delivered to an interior space. The environmental control system pack uses energy from the bleed air to drive a fan in the ram air circuit. This causes an increase in a compression power of the air in the ram air circuit to increase a thrust of the air exiting the ram air circuit through the outlet.

The invention is suitable for the technical field of unmanned aerial vehicle energy consumption management and intelligent control, and provides an unmanned aerial vehicle logistics transportation intelligent management platform fusing multi-source data, and the platform comprises a flux regulation and control module which is used for predicting the gas release flux in an unmanned aerial vehicle cabin in unit time, and dynamically adjusting the ventilation flow rate of a ventilation system according to the gas release flux, the gas concentration in the cabin is maintained to be in a gas concentration steady-state interval corresponding to the heat balance optimal time period of the gas in the cabin. According to the technical scheme, the influence rule of the volatile pollutant micro-thermal effect on the energy efficiency of the unmanned aerial vehicle battery is disclosed, and the unmanned aerial vehicle battery continuously operates in the optimal energy efficiency state corresponding to the discharge efficiency peak value interval through real-time trend correction; therefore, the energy utilization rate and the flight stability of the unmanned aerial vehicle under the task of carrying the recycled objects are remarkably improved.

The invention relates to the technical field of airborne heat management systems, in particular to an airborne low-compensation heat management system, an aircraft and a system control method. The heat management system comprises an air compression assembly, a refrigeration assembly, a heating assembly and an air supply assembly. The air compression assembly comprises an air compressor and an air inlet unit; the air inlet unit communicates with an inlet of the air compressor. The refrigeration assembly comprises a first cooling turbine, a second cooling turbine, an equipment radiator, a refrigeration pipeline unit and a refrigeration valve unit; the heating assembly comprises a first air entraining pipeline and a temperature adjusting valve. The first air entraining pipeline is used for communicating with an air entraining opening of the engine assembly. The temperature adjusting valve is communicated with the first air entraining pipeline; the air supply assembly comprises an air supply pipeline; an outlet of the first cooling turbine is communicated with an air supply pipeline through a flow limiting valve; and the first air entraining pipeline is communicated with the air supply pipeline. In this way, the problems that the controllability is low after a refrigerating circuit and a warm air supply pipeline of airborne equipment intersect, and too much engine bleed air needs to be consumed for cabin temperature adjustment are solved.

A system that provides a cooling liquid to a component of an aircraft, the system having: a cooling circuit that includes a fuel cell that receives a first flow and transfers first waste heat to the first flow; an air cycle machine (ACM) that transfers second waste heat to a second flow; a first heat exchanger, fluidly coupled to the cooling circuit downstream of the fuel cell, that thermally couples the first and second flows to superheat the first flow; a turbine, fluidly coupled to the cooling circuit downstream of the first heat exchanger, that extracts energy from the first flow; and a condenser, fluidly coupled to the cooling circuit downstream of the turbine, that condenses the first flow into the cooling liquid, wherein the component is fluidly coupled to the circuit downstream of the condenser.

A smart air ionizer is disclosed herein. The smart air ionizer includes a power circuit, a high voltage circuit, an electrode coupled to the high voltage circuit, the electrode configured to ionize air surrounding the electrode, and a controller circuit coupled to the power circuit and the high voltage circuit, the controller circuit including a controller configured to control a voltage output of the high voltage circuit to the electrode based on a feedback received from the high voltage circuit.

An environmental control system (ECS) of an aircraft, having a heat exchanger; a compressor that receives a first airflow from a first air source, compresses the first airflow, and directs the first airflow to the heat exchanger; an axial flow turbine that receives a second airflow from a second air source, extracts energy from the second airflow, and directs the second airflow to the heat exchanger, wherein the heat exchanger directs the first airflow to a cabin of the aircraft and directs the second airflow overboard; and a shaft connected between the turbine and the compressor.

The invention relates to a heat exchange device comprising: a heat exchange matrix (50) accommodated in a circulation enclosure and formed of a plurality of heat exchange pipes, each pipe comprising at least one duct extending mainly in a longitudinal direction, each duct at least partially defining a flow channel for a second heat transfer fluid, at least one manifold (20) comprising at least one duct portion (22, 23, 24) extending mainly in a plane orthogonal to the longitudinal direction, the manifold comprising a plurality of ports (30), at least one fluid distribution header (40) configured to allow a second heat transfer fluid to flow between at least one port of the manifold and at least one duct, each port of the manifold opening into a distribution header. The invention relates to an air conditioning system and to an aircraft comprising such a heat exchange device.

A ventilation device for an aircraft cockpit. The aircraft cockpit comprises a heat-insulating and sound-insulating layer (1) and an interior trim structure (10); the interior trim structure (10) is arranged on the inner side of the heat-insulating and sound-insulating layer (1), and the interior trim structure (10) and the heat-insulating and sound-insulating layer (1) define a cavity (11); the cavity (11) has an air outlet side (12); and the air outlet side (12) is provided with airflow outlets (121) communicated with the interior of the cavity (11). The ventilation device comprises a main ventilation pipe (2) used for guiding airflow from an air conditioning system of an aircraft to the ventilation device; distribution pipes (3) each having one end communicated with the main ventilation pipe (2) and the other end communicated with an internal space defined by the interior trim structure (10); diversion pipes (4) each having one end communicated with the main ventilation pipe (2) and the other end communicated with the cavity (11); and regulation valves (5) provided on the diversion pipes (4).

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.

A gas turbine engine assembly includes a core engine (20) that includes a core flow path where a core airflow (25) is compressed in a compressor section (24), communicated to a combustor section (56), mixed with fuel and ignited to generate an exhaust gas flow (74, 75) that is expanded through a turbine section (28). The turbine section (28) is coupled to drive the compressor section (24) through an engine drive shaft (88). A tap (64) is at a location up stream of the combustor section (56) for drawing a bleed airflow (66, 65). A bleed air heat exchanger (72) places the bleed airflow (66, 65) in thermal communication with an auxiliary flow (68) for heating the bleed airflow (66, 65). An exhaust heat exchanger (76) is configured to transfer thermal energy from the exhaust gas flow (75) into the bleed airflow (66, 65).

A conditioning system for recirculation air of an aircraft cabin includes an air cycle system (18) in fluid communication with the aircraft cabin and configured to receive a recirculation airflow from the aircraft cabin and a mixing chamber (56) disposed in fluid communication between the air cycle system and the aircraft cabin. The mixing chamber is configured to mix the recirculation airflow received from the air cycle system with a conditioned airflow received from an environmental control system pack of the aircraft.

A cooling system for an aircraft fuel cell system includes a coolant pump to circulate coolant through the cooling system and a radiator to reject heat to ambient air. A cooler zone is provided downstream of the radiator, comprising a plurality of parallel cooling branches. A warmer zone is provided downstream of the cooler zone, the warmer zone including a fuel cell stack. A bypass valve is arranged to provide coolant to the warmer zone from upstream of the radiator. A restrictor may be arranged to provide coolant to the warmer zone from downstream of the radiator.

The invention relates to a device (1) for cooling electrical equipment (2), said device (1) comprising: - a circulation channel (11) containing a flow (110) of a two-phase cooling fluid (111); - a thermally conductive wall (13) for separating the channel (11) and the electrical equipment; - at least one fin (15) disposed within the channel (11) and extending from the wall (13), each fin (15) being configured to be in a position close to the wall when the temperature of the fin (15) is below a predetermined temperature, and to be in a position far from the wall when the temperature of the fin (15) is greater than or equal to the predetermined temperature. Such a device makes it possible to efficiently cool electrical equipment without having to reduce its power output during periods of very high heat loss.

Sensor information from a plurality of sensors (104, 105) that monitor a heat exchanger (103) is accessed and then sensed information that corresponds to that sensor information is input into a control circuit (101) configured to output virtual parameters corresponding to the heat exchanger as a function, at least in part, of the sensed information. A particular fault class is determined from amongst a plurality of fault classes as a function, at least in part, of the virtual parameters and at least one task is identified regarding the heat exchanger that corresponds to the particular fault class.

Aircraft air cycle machines include a first stage turbine, a second stage turbine that receives air from the first stage turbine, and a duct arranged between the first stage turbine and the second stage turbine. A circular finned coalescer is arranged within the duct and includes a central body, a first fin layer wrapped about the central body, a first parting sheet wrapped about the first fin layer, and a second fin layer wrapped about the first parting sheet. Each of the fin layers include a plurality of fin elements and channels are defined between circumferentially adjacent fin elements of each of the first and second fin layers. The channels are tortuous channels such that moisture carried on a flow through the channels will impinge upon surfaces of the fin elements and coalesce into water droplets.

HEAT EXCHANGER WITH HOLLOW CLOSING BAR INCLUDING INTERNAL STIFFENERS, AIR CONDITIONING SYSTEM AND VEHICLE The invention relates to a heat exchanger comprising a plate exchanger block comprising a plurality of plates arranged substantially parallel to each other, characterized in that it comprises a plurality of hollow closing bars (60), each hollow closing bar (60) extending mainly in a longitudinal direction and being arranged between two plates (13, 15), each hollow closing bar (60) having an internal cavity extending in said longitudinal direction, a first and a second contact faces (21, 22) that are flat and parallel to each other, a first side wall (23) having a generally concave outer edge (28), a second side wall (24) having a second generally convex outer edge (29) and at least one stiffener (25, 26,27) internal extending within said internal cavity (20). Figure for the abbreviation: figure 4,

The invention relates to a valve for regulating an air flow, which valve comprises a valve body (100), at least one air flow channel extending between an air inlet (102) and an air outlet (103), the valve body comprising a pair of mechanical stops (110a, 110b) arranged peripherally; at least one sealing member (200) formed by a plurality of radial flaps (210), each rotatably mounted about a radial shaft (220) between an open position corresponding to the open position of the sealing member and a closed position corresponding to the closed position of the sealing member, at least one actuator of the sealing member comprising a notched ring (300) mechanically engaged with a plurality of pinions (230), each respectively mounted such that it is rigidly connected to a radial shaft (220) of a radial flap of the plurality of radial flaps such that the rotation of the notched ring causes the concomitant pivoting of each radial flap about its radial shaft in order to move the sealing member from the open position to the closed position and vice versa, the notched ring further comprising a radially projecting lug (310).

A support box apparatus includes longitudinal members that span forward to aft and transverse members that span inboard to outboard between the longitudinal members. The longitudinal members and the transverse members are formed of composite honeycomb sandwich panels. The support box apparatus also includes attachment components configured to couple the longitudinal members or the transverse members to structural components of an aircraft, electrical wiring attached to the longitudinal members or the transverse members, environmental control system (ECS) ducting attached to the longitudinal members or the transverse members, and life support lines attached to the longitudinal members or the transverse members.

A fuselage structure of an aircraft includes a first fuselage section and a second fuselage section connected to the first fuselage section, the second fuselage section including at least one first fuselage vessel extending the first fuselage section in a longitudinal direction, with the first fuselage section and the first fuselage vessels comprising circumferential flanges arranged at longitudinal ends of the first fuselage section and the first fuselage vessels extending radially in the first fuselage vessels and the first fuselage section wherein fasteners extend through abutting flanges of the first fuselage section and the fuselage vessel to establish a force-fit connection between the first fuselage section and the first fuselage vessels, when assembled, and wherein the first fuselage vessel provides a storage space for at least one tank structure. Also disclosed are a method for assembling the fuselage structure and an aircraft including the fuselage structure.

The utility model provides an electric aircraft cold and hot mixing device which comprises a cold air collecting assembly, a mixing assembly and a heat dissipation assembly, the mixing assembly is arranged above a battery assembly, the mixing assembly is provided with a mixing cavity, and an outlet section of the mixing cavity is communicated with a cabin environment control system through a ventilation pipeline; the cold air collecting assembly comprises a plurality of cold air pipelines, cold air inlets of the cold air pipelines are formed in wings or fuselage of the electric aircraft and correspond to the battery assembly, and cold air outlets of the cold air pipelines extend into the inlet section of the mixing cavity; the heat dissipation assembly comprises a plurality of heat conduction coil pipes, the heat conduction coil pipes are arranged on the bottom surface of the battery assembly, hot air inlets of the heat conduction coil pipes are communicated with the battery assembly, and hot air outlets of the heat conduction coil pipes extend into the inlet section of the mixing cavity and are staggered with the cold air pipeline. Natural high-altitude cold air is fully utilized, and the cold air and hot air generated by the battery are fully mixed in the mixing cavity, so that the temperature of the air is effectively reduced, and the heat dissipation efficiency of the battery system is improved.

TITLE OF THE INVENTION: PNEUMATIC AIR CONDITIONING SYSTEM FOR AN AIRCRAFT CABIN COMPRISING AN AMBIENT AIR COMPRESSOR. The invention relates to an air conditioning system for an aircraft cabin (10) comprising a pressurized air source (12), a fresh air source (14), a dynamic air circulation duct (16), a network of pipes (40, 41, 42, 43, 44, 45, 46, 47, 48, 49) and control valves (50, 51, 52, 53, 54, 55, 56, 57, 58, 59), a primary cooling exchanger (PHx), a main cooling exchanger (MHx), a turbomachine (20) comprising at least one first compressor (22) and an expansion unit. (24, 26).The air conditioning system is characterized in that: said first compressor (22) comprises an air inlet adapted to be connected, upon control of said valves, to said fresh air source (14) and / or said primary cooling exchanger (PHx), and an air outlet connected to said main cooling exchanger (MHx); said expansion unit (24, 26) comprises an air inlet adapted to be connected, upon control of said valves, either to said primary cooling exchanger (PHx) or to said main cooling exchanger (MHx) and an air outlet adapted to be connected to said cabin (10). Figure for the abbreviation: Figure 1.

This invention provides an aircraft ram air intake system and control method. The system includes a ram air intake and an emergency ram air regulating valve. The upstream side of the ram air intake is connected to the outside atmosphere, and the downstream side is connected to a heat exchange ram air line and an emergency ram air line. The heat exchange ram air line is arranged to provide heat exchange ram air, and the emergency ram air line is arranged to provide emergency ram air to the aircraft cabin. The emergency ram air regulating valve is arranged in the emergency ram air line to control the on / off state of the emergency ram air line. The aircraft ram air intake system according to this invention is more economical and safer, and also improves the comfort of the aircraft cabin.

An apparatus and method for irradiating air in an air circulation system of a vehicle is disclosed. The apparatus includes a filter unit configured to be coupled to a recirculation air conduit connected to a manifold of the air circulation system, the filter unit having an inlet end, and a filter disposed in the inlet end of the filter unit and including a filter media wall having a shape defining an interior volume of the filter. The apparatus further includes a UV lamp disposed on an end plate configured to be mounted to position the UV lamp in the interior volume of the filter and the end plate against an open end of the filter. The UV lamp can be configured to emit UV radiation substantially between 222 nm to 265 nm for irradiating air flowing through the filter into the air circulation system.

An air monitoring system with a controller in a computer system that operates to control a pump system to move air from a collection port for a cavity as diverted air to a tube connected to the collection port, move the diverted air into an input port of an air interface connected to the tube, through a chamber in the air interface, and out of a pump port of the air interface without increasing a pressure of the diverted air greater than a pressure level for a gas analyzer system to analyze an air sample collected from the diverted air. The controller operates to control the gas analyzer system connected to a sampling port in the air interface by a probe to obtain the air sample from the diverted air moving through the air interface and analyze the air sample to determine a set of components in the air sample.