365results about "Energy efficient board measures" patented technology

The system can include an on-board thermal management subsystem. The system 100 can optionally include an off-board (extravehicular) infrastructure subsystem. The on-board thermal management subsystem can include: a battery pack, one or more fluid loops, and an air manifold. The system 100 can additionally or alternatively include any other suitable components.

The system can include an on-board thermal management subsystem. The system 100 can optionally include an off-board (extravehicular) infrastructure subsystem. The on-board thermal management subsystem can include: a battery pack, one or more fluid loops, and an air manifold. The system 100 can additionally or alternatively include any other suitable components.

A transport vehicle includes: a frame having an internal area; a driver on top of the frame, the driver being configured to travel along a rail; a support structure in the internal area, the support structure being configured to seat, thereon, a drone configured to transport an article; and a controller configured to control an operation of at least one of the driver and the support structure.

A electric aircraft power distribution system includes a first battery pack connected to at least a first load and to a common bus that connects the first battery pack in parallel to at least a second battery pack; a first electrical component electrically connected between the first battery pack and the first load and configured to disconnect the first load from the first battery pack in response to current above a first threshold current, wherein the first electrical component has a first disconnection time at the first threshold current; and a second electrical component electrically connected between the first battery pack and the common bus and configured to disconnect the first battery pack from the common bus in response to current above a second threshold current, wherein the second electrical component has a second disconnection time at the second threshold current that is higher than the first disconnection time.

A vertical take-off and landing (VTOL) aircraft is disclosed. The VTOL aircraft may include: a fuselage, a thrust rotor to produce a propulsion thrust, rotor booms, canard surfaces, wing surfaces, tail surfaces, and lift rotors to produce lifting thrust force.

The invention provides an unmanned aerial vehicle for intelligent identification of a polar ice rink. The unmanned aerial vehicle comprises an aerial vehicle main body, a solar battery pack, rudder wings, a spiral propeller and an observation cabin, the aircraft is powered by solar energy, so that long endurance time can be achieved; the rudder wings are symmetrically installed on the two sides of the aircraft body to achieve lifting and steering of the aircraft body. The spiral propeller provides propulsive force and cooperates with the rudder wings to complete lifting steering motion. A plurality of functional modules are arranged in the observation cabin, and the functions of ice rink recognition, aircraft and transport ship positioning, data transmission, state monitoring and the like can be achieved. Illumination warning lamps are arranged on the front edges of the two wings of the aircraft, so that ice rink identification and aircraft landing under the extremely night condition are facilitated. The invention also provides a polar ice rink intelligent identification method of the unmanned aerial vehicle. The sea ice morphology around the navigation channel can be observed in detail and accurately, accurate sea ice data can be obtained, the polar transport ship is helped to sail, a captain is assisted to make a decision, and the risk of distress is reduced.

Provided are computer-implemented methods for autonomously controlling an aircraft with vertical take-off and landing capabilities and folding wings that includes controlling a plurality of thrust producing components of an aircraft to cause the aircraft to rise vertically when wings of the aircraft are in a first folded configuration, where when the wings of the aircraft are in the first folded configuration, a leading edge of each wing is oriented in a vertical direction setting motor controller gains based on the wings of the aircraft being in the first folded configuration, and causing the aircraft to align with a direction of airflow when the wings of the aircraft are in the first folded configuration, and controlling thrust producing components and control surfaces and internal articulation mechanisms of the aircraft to cause the aircraft to transition from folded wing configuration to unfolded wing configuration. Systems and computer program products are also provided.

The invention relates to an air system for an aircraft, that includes air consumers; air sources and a network of ducts and associated control valves controlled by a control unit. The air system is characterized in that: the network of ducts and associated valves includes at least one isolation valve, arranged between an air bleed device and an air duct connecting an air conditioning pack and an auxiliary power unit; the control unit is configured to be able to determine an ideal configuration of the control valves according to the identified requirements of each consumer and a degraded configuration that makes it possible to supply air to predetermined air consumers from the available air sources when the ideal configuration is not attainable.

Towed aerodynamic platforms approach the behavior of flat plate airfoils to achieve high lift-to-drag (L:D) performance when operated at low pitch angles. A lead aircraft may tow multiple platforms to form train units. Low form drag and high L:D enable solar aircraft that are more robust and faster than approaches extending wingspan rather than extending the length of the aerial train. Applications extend beyond solar aircraft and include vehicles towed along an overhead monorail system and aerial drones.

A series of convertible aircrafts with a core with an airframe defining a first axis is described; a first, a second, a third, a fourth, a fifth and a sixth rotor which are rotatable about respective first, second, third, fourth, fifth and sixth axis, and operable independently of each other so as to generate respectively a first, a second, a third, a fourth, a fifth and a sixth thrust value independent of each other; the core comprises an electric power source and electric motors which are connected to said first, second, third, fourth, fifth and sixth rotor; each aircraft of the series comprises a module associated with a respective architecture and interfaced with said core.

The utility model belongs to the technical field of aircraft thermal management, and particularly relates to a skin temperature adjustment control system. According to the system, a skin temperature detection unit is arranged on a skin; the skin heat exchange unit is connected with the skin; the fluid circulation pipeline comprises a circulation main path, a first circulation branch and a second circulation branch, the skin heat exchange unit and the power unit are connected in series through the circulation main path, the first circulation branch and the second circulation branch are connected in parallel and then connected with the circulation main path, and an airborne heat source and an airborne heat source adjusting valve are arranged on the first circulation branch in series. An airborne cold source and an airborne cold source adjusting valve are arranged on the second circulation branch in series; the control unit is connected with the skin temperature detection unit, the power unit, the airborne heat source adjusting valve and the airborne cold source adjusting valve and used for controlling starting, stopping and the rotating speed of the power unit according to temperature signals of the skin temperature detection unit and controlling the opening degree of the airborne heat source adjusting valve and the opening degree of the airborne cold source adjusting valve.

The present disclosure relates to a reconfigurable battery system and method of operating the same. An example apparatus includes at least one memory, instructions in the apparatus, and processor circuitry to execute the instructions to determine a state of charge of a battery, determine a closed circuit voltage of the battery, determine a value of a parameter based on a ratio of the state of charge and the closed circuit voltage, and control a switch coupled to the battery based on the value of the parameter, the controlling of the switch to either cause the battery to be coupled to a battery string or cause the battery to be disconnected from the battery string.

The utility model discloses a solar unmanned aerial vehicle, and particularly relates to the technical field of unmanned aerial vehicle equipment, the solar unmanned aerial vehicle comprises a fuselage, wings, an empennage and a power system, the fuselage is internally provided with a cabin for placing a control system and an effective load, and the upper surfaces of the wings are provided with solar cell panels electrically connected with the power system. The control system is connected with the solar cell panel and stores electric energy collected by the solar cell panel, the control system is in signal connection with the power system and controls the power system to provide power, and the two sides of a middle-section horizontal wing of the wings are fixedly connected with two outer-section wings with dihedral angles of the wings respectively. The middle-section horizontal wing is fixedly connected to the top of the fuselage, a plane formed by the symmetry axis of the fuselage and the symmetry axis of the middle-section horizontal wing is perpendicular to the middle-section horizontal wing, one end of the fuselage is fixedly connected with the empennage through a connecting piece, and the power system is installed on the wing. The unmanned aerial vehicle can carry loads, has long endurance time, and can enable the flight process to be more stable and safer.

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 embodiments disclose a method including providing an aerial drone coupled wirelessly to a social distancing application on a user digital device, wherein the drone is coupled to solar cell panels for recharging its batteries, providing a strobe light coupled to the drone for signaling an S.O.S. automatically in emergency situations, cellular communication device coupled to the drone for transmitting and receiving messages from the social distancing application, wherein the drone includes a cellular signal strength sensor to automatically move to a location to boost cellular signal strength, and providing at least one camera for capturing images and videos during user directed reconnaissance, drone sensors to detect and measure aerosols including biologics and DNA in an area, electromagnetic fields, barometric pressure, humidity, ambient temperature, wind speed and direction, detection and identification devices to detect unnatural sounds, to analyze and identify manmade, animal and environmental objects and conditions using computer vision.

An unmanned aerial vehicle airport, an unmanned aerial vehicle system, a tour inspection system, a tour inspection method, a control device, an apparatus and a storage medium, and an unmanned aerial vehicle cruise system relate to the field of unmanned aerial vehicles, and are used to optimize a structure of the unmanned aerial vehicle airport. The unmanned aerial vehicle airport comprises a support base (1), a parking apron (2), a protective cover (3) and a protective cover opening and closing driving device (4). The parking apron (2) is installed on the top of the support base (1); the protective cover (3) covers the top of the parking apron (2); the protective cover opening and closing driving device (4) is installed between the support base (1) and the protective cover (3), and the protective cover opening and closing driving device (4) is configured to cause a bar linkage mechanism to drive the protective cover (3) to switch between an open position and a closed position. The unmanned aerial vehicle airport is provided with the protective cover (3) for the parking apron (2). If the protective cover (3) is open, the unmanned aerial vehicle is parked on the parking apron (2), and takes off from the parking apron. When the protective cover (3) is in the closed position, the protective cover (3) plays a protective role on the unmanned aerial vehicle, and prevents external rain, impurities and the like from damaging and polluting the unmanned aerial vehicle.

An aircraft air supply system for generating pressurized air includes a compressor (114, 214) configured to receive and pressurize a flow of outside air, a turbine (118, 218) operatively coupled to the compressor (114, 214) by a shaft and configured to drive the compressor (114, 214), a fluid pathway fluidly connecting the compressor (114, 214) to an environmental control system pack, an outflow pathway fluidly connecting a cabin of the aircraft to the turbine (118, 218), a surge relief pathway fluidly connecting the compressor (114, 214) to the outflow pathway and the turbine (118, 218), and a surge relief valve disposed within the surge relief pathway. In a first operational state, the surge relief valve is open to allow a flow of surge relief air to flow from the compressor (114, 214) to the outflow pathway via the surge relief pathway, the surge relief air further flowing through the turbine (118, 218).

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.

The invention relates to the technical field of heat exchanger detection, in particular to an aircraft environment control system heat exchanger leakage rate detection table and detection method. One end of the hot side air inlet pipe is communicated with an air source and is provided with a first laminar flow meter and a first valve, and the other end is communicated with a heat exchanger to be tested; one end of the cold side air inlet pipe is communicated with the air source and is provided with a second laminar flow meter and a second valve, and the other end is communicated with the heat exchanger to be tested; one end of the cold edge measuring tube is communicated with the heat exchanger to be tested and is provided with a third valve, and a port of the other end is provided with a first float flowmeter; one end of the hot edge measuring tube is communicated with the heat exchanger to be measured and is provided with a fourth valve, and a port of the other end is provided with a second float flowmeter. The system can accurately measure the flow of the inlet and the outlet of the hot side and the cold side of the heat exchanger, and effectively detect external leakage and blow-by. And the heat exchanger does not need to be dried for the second time after detection is finished. Not only is the complexity of manual operation reduced, but also the repeatability and reliability of the test can be improved through an automatic program.

An architecture for supplying air to a high-pressure compressor of an auxiliary gas generator from a pressurized cabin of an aircraft, comprising: a load compressor rotationally driven by a common rotation shaft providing a mechanical coupling between the high-pressure compressor and a high-pressure turbine of the auxiliary gas generator and supplied by an outside air intake; a first regulation valve assembled at the outlet of the load compressor to control all or part of the air flow delivered by the load compressor; a second regulation valve assembled at the outlet of the pressurized cabin to control the air flow drawn from inside the pressurized cabin; a mixer receiving the outputs of the first and second regulation valves to add the air drawn from inside the pressurized cabin to all or part of the air delivered by the load compressor.

An aircraft system includes a turbine engine (32, 34) having a compressor (44), a combustor (48) having an inlet (105) and an outlet (107), and a turbine (46) having an inlet portion (110) and an outlet portion (112). An auxiliary power unit (37), APU, is operatively connected to the turbine engine (32, 24). The APU (77) includes a compressor portion (70), a generator (74), and a turbine portion (72). The compressor portion (70) is operatively connected to the turbine portion (72) through the generator (74). A source of cryogenic fluid (62) is operatively connected to the turbine engine (32, 34) and the APU (37). A heat exchange member (84) includes an inlet section (116) operatively connected to the source of cryogenic fluid (62), a first outlet section (120) operatively connected to the turbine engine (32, 34) and a second outlet section (122) operatively connected to the compressor portion (70).

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.

The present invention discloses a split-type reconnaissance and detection robot and method. The split-type reconnaissance and detection robot includes a quadruped robot and a drone module; the drone module includes a stacked-wing drone carrying platform and a stacked-wing drone; the stacked-wing drone is installed in a launch tube, and a gas ejection device for launching the stacked-wing drone is provided in the launch tube; a lifting device is provided at the bottom of the stacked-wing drone carrying platform, and the lifting device is installed on the robot body. The split-type reconnaissance and detection robot provided by the embodiment of the present invention enables the quadruped robot to carry out aerial reconnaissance and detection of the area to be detected through the stacked-wing drone, and the quadruped robot performs land detection, and has the ability to realize two detection modes, land and air, and can adapt to a variety of complex working environments.

This invention provides an unmanned aerial vehicle (UAV) for intelligent identification of polar ice rinks, comprising a main body, a solar panel, control wings, a propeller, and an observation cabin. The UAV is powered by solar energy, enabling a long endurance. The control wings are symmetrically mounted on both sides of the main body, enabling ascent, descent, and steering. The propeller provides propulsion, working in conjunction with the control wings to complete ascent, descent, and steering movements. The observation cabin incorporates multiple functional modules for ice rink identification, UAV and transport ship positioning, data transmission, and status monitoring. Illumination warning lights are installed on the leading edges of the wings to facilitate ice rink identification and landing during polar night conditions. A method for intelligent identification of polar ice rinks using this UAV is also provided. This invention enables detailed and accurate observation of sea ice morphology around shipping lanes, obtaining precise sea ice data to aid polar transport ships in navigation, assist captains in decision-making, and reduce the risk of distress.

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.

A method, apparatus, and system for supplying power during the takeoff and landing of an Urban Air Mobility (UAM) aircraft is disclosed herein. A power supplying method is performed by a power supply system comprising a drone and a hub. The power supplying method includes: determining whether power is required for an Urban Air Mobility (UAM) aircraft to land on the hub using battery information of the UAM aircraft when the UAM aircraft is determined to be in a landing mode; moving the drone from the hub to the UAM aircraft using location information of the UAM aircraft when it is determined that power is additionally required for the UAM aircraft to land on the hub; docking the drone to the UAM aircraft to couple with; and supplying power required for the UAM aircraft to land on the hub to the UAM aircraft by the drone.

An environmental control system includes an environmental control system pack (20) having a trim outlet and a primary outlet. A trim medium (A1b) is output from the trim outlet and a first medium is output from the primary outlet. An inlet of a mixing manifold (102) is connected to the primary outlet of the at least one environmental control system pack. A trim heat exchanger (104) is connected to the trim outlet and the at least one inlet of the environmental control system pack. Within the trim heat exchanger, the trim medium is arranged in a heat exchange relationship with a second medium. From the trim heat exchanger, the second medium is provided to an inlet of the least one environmental control system pack and the trim medium is mixed with a flow output from an outlet of the mixing manifold.

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.

To provide a solar panel and a method for producing the solar panel, the solar panel being produced by populating a front portion of a substrate with cover glass interconnected cells (CICs) and / or wiring, before bonding the front portion to a back portion of the substrate.SOLUTION: A method for producing a solar panel includes producing a tile. Producing the tile includes bonding an electrical insulation layer and a front face sheet layer together to produce a front portion of a substrate. Producing the tile also includes bonding the front portion of the substrate and a cell together. Producing the tile also includes bonding the front portion of the substrate and a wire together. The method also includes bonding a honeycomb core layer and a back face sheet layer to produce a back portion of the substrate. The method also includes bonding the tile and the back portion of the substrate together to produce the solar panel.SELECTED DRAWING: None

Disclosed is a five-constant air-conditioning system of an aircraft cabin. The system includes an airframe and an internal cabin, where the airframe includes an air inlet and an air outlet provided on a surface and a fresh air assembly arranged between the airframe and the cabin; and the cabin includes an air supply outlet and an air exhaust outlet provided on an inner wall. According to the present disclosure, a temperature in the cabin is preliminarily regulated through a temperature regulating chamber by using air brought by the fresh air assembly, and the temperature is continuously regulated and controlled through a cold and hot medium pipeline assembly such that a constant temperature can be achieved. Constant humidity and constant quietness can be achieved through the fresh air assembly. Constant purification can be achieved through an air filter. Constant oxygen can be achieved through an oxygen increasing component.