87results about "Energy efficient board measures" patented technology

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 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.

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.

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.

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.

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.

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.

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.

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 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).

An aircraft includes a fuselage defining a longitudinal axis between a forward end and an aft end. The aircraft includes an electrical system having an electric storage. The electric storage is positioned within the fuselage.

The present disclosure relates to systems and methods of distributing propulsion load power drawn from high-energy and high-power batteries. Specifically, a system and method of distributing load power drawn from a plurality of batteries for electric propulsion of a vehicle. The system includes: a high-energy battery and a high-power battery designed for optimal production of DC power during high specific energy propulsion and high specific power propulsion, respectively; and a battery health management system configured to monitor state of charge and state of health of the batteries and generate battery state signals. The system further includes a propulsion load configured to produce propulsion force using power converted from power generated by at least one of the batteries; and a system controller configured to distribute load power drawn from the high-energy battery and the high-power battery for use by the propulsion load according to a propulsion phase of the vehicle and the battery state.

An electric aircraft, in detail: a hull; one or more first electric propulsion units (EPUs) and one or more second EPUs arranged on one side of the fuselage, the one or more first EPUs being arranged in front of the one or more second EPUs; one or more third EPUs and one or more fourth EPUs arranged on another side of the fuselage, with the one or more third EPUs arranged in front of the one or more fourth EPUs; and a plurality of battery packs, wherein at least one of the plurality of battery packs is configured to supply energy to: a part of one of the first EPUs or more and a part of one of the fourth EPUs or more.

A compressed air supply system of an aircraft includes: a bleed air passage through which bleed air from a gas turbine engine flows; an auxiliary compressor including a compressor inlet and a compressor outlet, the compressor inlet being fluidly connected to the bleed air passage; a supply passage which is fluidly connected to the compressor outlet and through which compressed air from the auxiliary compressor is supplied to an air system of the aircraft; a driver that rotates the auxiliary compressor; a sensor that detects pressure or temperature of the supply passage; and circuitry that controls an output rotational frequency of the driver in accordance with a detection signal of the sensor.

An aircraft can comprise an engine, an environmental control system, an engine controller, and a plurality of sensors detecting engine or aircraft parameters. Engine or aircraft operation can be updated in real time based on input from the sensors, including airflow management or operation parameters.

An aircraft power system for providing regulated voltage and regulating power fluctuations in a tethered aircraft includes a plurality of light-emitting diodes (LEDs) onboard an aircraft having at least one propulsion unit. At least one electrical circuit is onboard the aircraft. The at least one electrical circuit includes a current-amplifying regulator in parallel with a speed controller of the at least one propulsion unit, the current-amplifying regulator in parallel with the speed controller providing the regulated voltage to the speed controller. A tether is connected between the aircraft and a power source located remotely from the aircraft. Power is transmitted via the tether to the aircraft and at least a portion of the plurality of LEDs.

A flying machine storage container is provided that comprises multiple charging stations and a clamping mechanism. The clamping mechanism is configured to secure flying machines in the charging stations and securely close charging circuits between the storage container and the flying machines. A system for launching flying machines is also provided. The system comprises two regions and a transition region between the two regions. The two regions each constrain the positioning of a flying machine and the transition region enables a flying machine to move from the first region to the second region to reach an exit. A flying machine having sufficient performance capabilities will be able to successfully launch. Centralized and decentralized communication architectures are also provided for communicating data between a central control system, multiple storage containers, and multiple stored flying machines stored at each of the storage containers.

We provide a power supply system with a highly reliable battery architecture for electric motors suitable for use in aircraft. [Solution] Individual batteries can be used to power two or more motors in a subset of a system with, for example, six or more motors. Each motor is powered by two or more subsets of batteries and can cope with motor failure. If a motor fails in vertical takeoff and landing mode, the power is diverted to other motors to maintain proper attitude control and provide sufficient thrust. If a motor fails, a second motor offset from the failed motor can be powered down to achieve attitude control.

An air conditioning system for a seat, comprising an arm rest (4a, 4b) of the seat (1), the arm rest having a top side (40), and inner wall (41) and an outer wall (42), a front end (43) and a back end(44) defining a hollow interior (10) between them, means for providing air conditioned to a desired temperature, from a source to the hollow interior of the arm rest, and a plurality of nozzles (20) formed through the inner wall, defined between a nozzle inlet (21) on an inner surface of the inner wall facing into the hollow interior and a nozzle outlet (22) on an outer surface of the inner wall facing towards a seating area of a person when sitting in the seat, the nozzles providing a path through which air flows from the hollow interior, into the nozzle inlet and out of the nozzle outlet.

An inter-floor transport system includes an aerial vehicle configured to move vertically and horizontally along a passage and a power assembly including a power supply adjacent to the passage and a guide cable extending along the passage and connected to the power supply, where the aerial vehicle is configured to receive power through the guide cable without contacting the guide cable.

The invention relates to the technical field of aircrafts, in particular to an airborne cooling system, an aircraft and a control method. The system comprises a power assembly, a pipeline assembly and a refrigeration assembly. The power assembly comprises a gas compressor, a motor module, a first refrigeration turbine and a transmission shaft; the pipeline assembly comprises an air inlet pipeline, an air conveying pipeline and an air supply pipeline. The air inlet pipeline is connected with an air inlet of the air compressor; the gas conveying pipeline is connected between an exhaust port of the gas compressor and a gas inlet of the first refrigeration turbine; the air supply pipeline comprises an air supply branch and an air supply valve; one end of the air supply branch is connected with an exhaust port of the first refrigeration turbine, and the other end is used for supplying cold air to the aircraft; the air supply valve is connected with the air supply branch; the refrigeration assembly is connected with the air supply branch; the refrigeration assembly is used for refrigerating gas in the gas supply branch; the refrigeration assembly and the transmission shaft work independently. Therefore, the problems that an environment control assembly cannot complete pressure regulation and temperature regulation decoupling control at the same time, and the air entraining loss of an engine is high are solved.

Methods, Systems, and Apparatus for coordinating drones to communicate with reduced signal to noise, harvest energy, or provide camouflage.

An autonomous air conditioning system for an aircraft includes a compressor compressing ambient air and supplying compressed air, a first portion of the compressed air being injected into a cabin of the aircraft so as to condition the cabin air in terms of pressure and of temperature. The autonomous system further includes an electric motor providing mechanical energy to the compressor. The system includes a fuel cells stack supplied with air by a second portion of the compressed air supplied by the compressor and supplying electrical energy, the electric motor being electrically powered with electrical energy supplied by the fuel cells stack. Thus, the cabin air conditioning is performed autonomously, avoiding the need to modify a pre-existing electrical network of the aircraft.

The application discloses a flying car cabin oxygen concentration regulation method, device, equipment and program product, comprising: obtaining the cabin environment parameters, the current flight height and the passenger physiological parameters of the flying car; determining the oxygen supply demand level of the flying car according to the cabin environment parameters and the passenger physiological parameters; determining the target oxygen supply strategy according to the current flight height and the oxygen supply demand level, and regulating the oxygen concentration of the target flying car through the air circulation system and / or the oxygen generation and supply system. The application realizes dynamic and accurate adjustment of the oxygen concentration of the flying car, guarantees the breathing safety of the passengers, and can be applied to the technical field of flying cars.