182results about "Energy efficient board measures" patented technology

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 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.

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 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.

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.

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.

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.

The invention discloses an air distribution system and an airplane, and belongs to the technical field of air distribution. The air distribution system includes a mixing chamber, a first air conditioning assembly, and a first recirculation assembly. The first recirculation assembly comprises a first suction structure and a first water ejector, a proper amount of liquid water is sprayed into recirculation air through the first water ejector, efficient cooling of the recirculation air is achieved through the physical characteristics of low boiling point, large specific heat capacity and high latent heat of vaporization of water, and it is ensured that the temperature of the recirculation air entering the mixing cavity is obviously reduced. Under the scene that fresh air and recirculating air meet the requirement for the cabin air supply temperature after being mixed, the requirement for the flow of low-temperature fresh air can be greatly lowered, and then the requirement for the air entraining flow of an aircraft engine is lowered; and the working load of the first suction structure can be reduced, and the service life of the first suction structure is prolonged.

To provide an environmental control system pack for an aircraft.SOLUTION: An environmental control system pack 20 for an aircraft includes a ram air circuit 40 and a bleed flow circuit 30. 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.SELECTED DRAWING: Figure 4

An antenna for charging and measurement may comprise: a telescopic support installed at a lower portion of an aerial vehicle and configured to contract when the aerial vehicle lands on a wireless station and extend when the aerial vehicle takes off from the wireless station; and an antenna coil part deformed into a spiral shape when the telescopic support is contracted so that the wireless station receives wireless power and deformed into a conical shape when the telescopic support is extended to measure a radio signal.

This invention belongs to the field of UAV mapping target technology, and particularly relates to a UAV aerial photogrammetry ground target, including a base. A frame is mounted on the base via a support mechanism. A central shaft runs through the frame in the front-to-back direction. A display screen and a solar panel are mounted on the central shaft via a right-angle mounting bracket. A conversion mechanism is provided within the frame, which drives the central shaft to rotate, controlling the rotation of the right-angle mounting bracket and switching the positions of the display screen and solar panel. The advantages are: this invention can effectively perform UAV mapping target work in natural environments for extended periods, has self-powered and self-cleaning functions, and features a long service life and strong environmental adaptability.

An aircraft air conditioning system includes a lower cooling zone and an upper cooling zone. The lower cooling zone includes a lower recirculation heat exchanger (118) configured to receive cabin air from a cabin and convert the cabin air into lower cooled recirculated cabin air. The upper cooling zone includes an upper recirculation heat exchange (133) configured to receive the cabin air from the cabin and convert the cabin air into upper cooled recirculated cabin air. A power system (108) selectively delivers power to the lower cooling zone and the upper cooling zone. A controller (150) is in signal communication with the power system. The controller determines a target temperature of the cabin and invokes a recirculation ground maintenance mode that commands the power system to deliver power to one or both of the lower cooling zone and the upper cooling zone so that a temperature of the cabin reaches the target temperature.

A microtube heat exchanger is disclosed for an aerospace system including two end plates with an array of holes or openings and an array of microtubes disposed in the array of openings between the two end plates. The heat exchanger can be used in environmental control systems, including systems for aerospace applications.

An aerial vehicle electrical power system for providing regulated voltage and regulating power variances in a tethered aerial vehicle includes a plurality of light-emitting diodes (LEDs) carried by the aerial vehicle having at least one propulsion device. At least one electrical circuit is carried by the aerial vehicle. The at least one electrical circuit has an amperage boost regulator in parallel with a speed controller of the at least one propulsion device, wherein the amperage boost regulator in parallel with the speed controller delivers regulated voltage to the speed controller. A tether is connected between the aerial vehicle and a power source positioned remote from the aerial vehicle. Electrical power is transmitted to the aerial vehicle and at least a portion of the plurality of LEDs through the tether.

The application discloses a kind of aircraft electrically powered environmental control system (EECS) energy efficiency optimization control method, change traditional area control strategy into the combination of three-variable optimization and double-target control, with the coefficient of performance (COP) of system as index, by solving the optimal solution set of optimization variable under different working conditions to maximize COP.On this basis, the value of two control quantities is calculated by the controller to meet the performance requirements of the system.First, a GRNN model is established, which is trained by a large amount of offline data under various conditions, so that it can accurately predict the steady-state COP of the system under different conditions.Then, the DE algorithm searches for the optimal solution set of optimization variables corresponding to the optimal COP within the solution space that satisfies the performance constraints of the components.Finally, the corresponding control quantities are solved at the optimal operating point by the controller, thereby achieving energy efficiency optimization control.

Disclosed herein method and apparatus for charging control of air mobility device. The method includes: controlling, by one or more processors, an air mobility device and a charger to make a coupling, between a connector of the charger and a port of the air mobility device, for power transfer from the charger to the air mobility device; determining, based on a coupling parameter of the coupling between the connector and the port not satisfying a threshold condition, whether the air mobility device is stationary within a designated zone; and controlling, based on the air mobility device stopping outside the designated zone, the air mobility device and the charger to release the coupling between the port and the connector.

Number of phases N phase A lightweight, energy dense, and highly efficient hybrid power system (200) for an electric aircraft (99) includes a prime mover internal combustion engine or gas turbine (300) coupled to a self-cooled, multi-phase, axial-flux, dual Halbach array motor / alternator (306) having a N pha The motor / alternator and regenerative power conversion drive have a neutral connection.

This invention relates to a quadcopter Mars spacecraft and its upright deployment and platform takeoff deployment device. The invention addresses the current lack of a suitable structure, deployment, and takeoff deployment scheme for quadcopter Mars spacecraft. The invention includes a lander, an outer envelope assembly, a bottom extension component, a multi-degree-of-freedom robotic arm, and a Mars spacecraft. The bottom extension component and the multi-degree-of-freedom robotic arm are mounted side-by-side on the lander, the outer envelope assembly is mounted on the bottom extension component, and the Mars spacecraft is housed within the outer envelope assembly. This invention belongs to the field of aerospace vehicle technology.

The application provides a solar energy suction type electric propulsion unmanned aerial vehicle, which comprises a fuselage, wherein a ring truss type photoelectric conversion device is arranged on the fuselage, the photoelectric conversion device comprises a ring truss unfolding mechanism and a foldable thin film type photoelectric conversion array, the thin film type photoelectric conversion array is supported and connected by the ring truss unfolding mechanism, and the unfolding or folding of the thin film type photoelectric conversion array is realized through the ring truss unfolding mechanism; a thrust device is arranged on the fuselage, and the thrust device adopts a suction type electric propulsion device. The application uses the ring truss type photoelectric conversion device, can realize a large deployment and folding ratio design of the solar energy thin film, has a simple structure and can effectively reduce the structural mass. The application uses the suction type electric propulsion as a power device, does not need to carry additional propellants, can take gas from the surrounding thin atmosphere as the propellants, and can generate corresponding thrust after the gas is ionized and accelerated, so that the unmanned aerial vehicle can work on the orbit for a long time.

Disclosed is a UAV wireless charging system, comprising: a plurality of charging pads arranged in an array; an identification unit connected to each of the charging pads and operated when a terminal of a UAV is placed; and a control unit connecting a charger to the charging pad operated by the identification unit.

The invention provides a temperature control method and device, electronic equipment and a storage medium, and relates to the technical field of aircraft air conditioners, the method comprises the steps that a set of input parameters are obtained, the set of input parameters comprise the environment temperature, a temperature setting signal and a defrosting demand signal, the defrosting demand signal is used for representing whether defrosting needs to be started or not, and the set of input parameters comprise the environment temperature and the temperature setting signal; the temperature setting signal comprises a signal of functional gears, and the functional gears comprise a refrigeration gear, a middle gear and a heating gear; a corresponding target operation mode is automatically selected according to the set of input parameters, wherein the target operation mode at least comprises a refrigeration mode, a heat pump heating mode, a ventilation mode and a defrosting mode; the aircraft air conditioning system is controlled according to the target operation mode to adjust the temperature in the aircraft cabin, and the heat pump air conditioning system comprises a compressor, an indoor heat exchanger, an outdoor heat exchanger, an expansion valve and a four-way valve. According to the technical scheme, the reliability of the air conditioning system of the aircraft is improved.

An aircraft includes a body defining an interior compartment configured to hold at least one of a passenger and a payload, a battery system, a plurality of arms coupled to and extending from the body, and a plurality of propulsion devices configured to provide thrust to fly the aircraft. Each of the plurality of propulsion devices is coupled to a respective one of the plurality of arms. The plurality of propulsion devices are powered by the battery system. Each of the plurality of propulsion devices is selectively pivotable about at least one axis. The plurality of propulsion devices include at least one of (i) counter rotating ducted fans and (ii) ionizing electrode engines.

An environmental control system includes a ram air circuit having a ram air duct and at least one ram heat exchanger arranged within the ram air duct, a compression device, and an expansion device. The compression device is configured to receive at least one of a first medium, a second medium, and a third medium. The environmental control system is operable in a plurality of modes including at least one normal mode and a failure mode. In the at least one normal mode, the first medium output from the compression device is exhausted into the ram air duct upstream from the at least one ram heat exchanger, and in the failure mode, only the third medium output from the compression device is exhausted into the ram air duct upstream from the at least one ram heat exchanger.

An environmental control system, ECS, (20) for use with a gas turbine engine has an air cycle system, ACS, (22) and a vapor cycle system, VCS, (24). The VCS (24) has along a vapor compression flowpath (630): a VCS compressor (30); a heat donor leg (33) of a VCS condenser (32); an expansion device (36); and a heat receiving leg (39) of a VCS evaporator (38). The ACS (22) has along a bleed flowpath (600): a bleed air inlet (100); a primary heat exchanger (102); an ACS compressor (106); a secondary heat exchanger (108); a turbine (112) coupled to the ACS compressor (106) to drive the ACS compressor (106); a heat donor leg (40) of the VCS evaporator (38); a water collector (118); and a heat receiving leg (121) of the VCS condenser (32).

Space vehicles with paraglider re-entry, and associated systems and methods are disclosed. A representative system includes a re-useable space vehicle, a collapsible, deployable and re-stowable re-entry heat shield carried by the space vehicle, and a collapsible, deployable and re-stowable flexible paraglider wing also carried by the space vehicle. The space vehicle can accordingly carry out repeated space-based missions, and can be refurbished and replenished on Earth and / or at an orbiting dock between missions.