1494results about "Aircrafts" patented technology

The embodiments of the present disclosure involve the technical field of unmanned aerial vehicles, and disclose an unmanned aerial vehicle base station and an unmanned aerial vehicle system. The unmanned aerial vehicle base station includes a bracket, a tarmac, a charging component, and a temperature adjusting component. The bracket is provided with an accommodating cavity, the tarmac separates the accommodating cavity into an upper compartment chamber and a lower compartment chamber, the temperature adjusting component includes a semiconductor module, a first ventilation assembly, a second ventilation assembly, and a third ventilation assembly, and the semiconductor module is partially provided on the first ventilation assembly and partially provided on the second ventilation assembly.

The invention discloses a hydrogen-lithium dual-power system structure optimization design and integrated control method applied to an unmanned aerial vehicle. The method comprises the following steps: constructing a hydrogen-lithium dual-power system of the unmanned aerial vehicle; setting an integrated control strategy according to the hydrogen-lithium dual-power system; the integrated control strategy comprises an energy management strategy and a life and safety management strategy; the energy management strategy comprises a rule-based strategy, a power following strategy and a self-adaptive optimization strategy; the service life and safety management strategy comprises a hydrogen fuel cell protection strategy, a lithium battery health management strategy, a thermal management strategy, a dual-power coupling safety management strategy and a redundancy and fault processing strategy. By optimizing the power system design and the energy management strategy, the mass of the unmanned aerial vehicle device is reduced, the cruising ability, the load capacity and the environmental adaptability of the unmanned aerial vehicle are improved, and optimization processing of the control strategy is achieved.

A battery cell, a battery, and an electric device. The battery cell includes a housing assembly, an electrode assembly, and a current collecting member. The housing assembly includes an electrode lead-out portion for inputting or outputting electric energy. The electrode assembly is accommodated in the housing assembly, where the electrode assembly includes a body and a tab, the tab is disposed on the body, and a material of the tab is different from that of the electrode lead-out portion. The current collecting member includes an additional portion having a same material as that of the electrode lead-out portion and a body portion having a same material as that of the tab, the additional portion is connected to the body portion, the additional portion is connected to the electrode lead-out portion through welding, and the body portion is connected to the tab through welding.

A powertrain for an aerial vehicle may include a mechanical power source and an electric power generation device mechanically coupled to the mechanical power source. The powertrain further may include an electric motor electrically coupled to the electric power generation device. A first propulsion member may be mechanically coupled to the mechanical power source and configured to provide a first thrust force. The powertrain also may include a second propulsion member mechanically coupled to the electric motor and configured to provide a second thrust force. A vehicle controller may be provided and configured to at least partially control aerial maneuvering of the aerial vehicle, and cause supply of a first portion of the mechanical power to the first propulsion member and a second portion of the mechanical power to the electric power generation device based at least in part on at least one characteristic associated with maneuvering of the aerial vehicle.

The invention discloses an intelligent charging regulation and control system of a charger, and belongs to the technical field of charging regulation and control. The method is used for solving the technical problem that in an existing scheme, flight data, stress monitoring and environment parameters cannot be fused to achieve dynamic reconstruction of a charging strategy, so that the adaptability and reliability of intelligent charging regulation and control of an unmanned aerial vehicle charger are poor. All the modules realize full-process closed-loop control from data perception to safe execution through chain type cooperation of data acquisition, fusion, optimization, execution and early warning, so that the function precision of a single module is improved, and the safety of the system is improved through information transmission and dynamic adjustment among the modules. The whole system has the intelligent characteristics of scene self-adaption, fault self-repairing and performance self-optimization, and finally multi-dimensional improvement of the charging efficiency, the battery life and the safety performance is achieved.

An electric aircraft according to an embodiment of the present invention comprises: a fuselage equipped with a power means, a front spar and a rear spar extending from the fuselage to an end of a wing, and a plurality of ribs extending from the rear spar to the front spar and coupled to the front spar and the rear spar, in which a plurality of solid state batteries are mounted in a plurality of individual spaces partitioned by the front spar, the rear spar, and the plurality of ribs, respectively, and the front spar and the rear spar are used as members for serial connection of the plurality of solid state batteries, and the plurality of ribs are used as members for parallel connection of the plurality of solid state batteries.

The invention relates to the technical field of unmanned aerial vehicle charging control, and discloses an unmanned aerial vehicle charging control method and control system. The method comprises the following steps: after responding to an unmanned aerial vehicle charging request, starting a charging control flow comprising an environmental parameter acquisition stage and a battery state initialization stage; and after the charging connection is established, the adaptive observer executes system state estimation and external disturbance estimation in parallel based on the acquired environmental parameters and the initialized battery state. And dynamically adjusting a charging strategy according to the estimated real-time result, including refreshing a power control signal and activating a compensation mechanism, and cooperatively controlling the energy output of the charging equipment according to the power control signal and activating the compensation mechanism until the battery reaches a predetermined charging target. According to the method, through dual consideration of the environment and the battery state and in combination with a parallel estimation and dynamic adjustment mechanism, the charging process can accurately match the battery requirement of the unmanned aerial vehicle, various interference factors are effectively coped, the reliability and the adaptability of the charging process are improved, and a brand new solution is provided for efficient charging of the unmanned aerial vehicle.

A low-altitude single-person aircraft powered by a micro-turbojet engine relates to the field of manned aircraft. The invention solves the problems of existing jet aircraft suits, such as heavy weight, inconvenient posture adjustment, and easy injury to the pilot. The invention comprises a flight backpack and two arm propulsion devices (7); the flight backpack comprises: a safety belt (1), a shell (2), an oil supply system (3), an electrical system (4), and a backpack micro-turbine engine (5); the oil supply system (3) is installed inside the shell (2), the electrical system (4) is installed on the upper end surface of the shell (2), and the backpack micro-turbine engine (5) is installed on the lower part of the shell (2); wherein the two arm propulsion devices (7) are respectively installed on the left and right sides of the shell (2) of the flight backpack. The flight backpack of the invention is the most complex component of a low-altitude single-person aircraft powered by a micro-turbojet engine. The invention is used in aircraft.

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.

A pin for a pinned joint includes a hollow body with a first and second end caps coupled to first and second ends, respectively. The body and the end caps at least partially define a cavity within the body, wherein at least one aperture extends through the hollow body. A main piston is slidably disposed within the cavity and divides the cavity into a first chamber proximate to the first end and a second chamber proximate to the second end and fluidly isolated from an environment around the body. A lubricant is disposed within the first chamber. The main piston moves toward the first end of the body when a pressure in the second chamber is greater than a pressure of the environment. Movement of the main piston toward the first end of the body discharges lubricant through the at least one aperture.

Embodiments of the invention are directed to methods and systems for providing electric power with individualized charging parameters to each battery in a multi-battery system. Electric power from the single power source can be distributed in a controlled and unequal manner. Custom charging parameters can be designed for each battery. The custom charging parameters can be determined based on battery metrics gathered for that battery, and can be designed to optimize for a number of suitable priorities, such as recharging speed and battery health. As a result, each battery can be recharged according to individual needs.

A transportation system includes a body, a plurality of propulsion units, and a control unit. The body defines an interior space. The plurality of propulsion units are mounted on the body. Each of the plurality of propulsion units includes a thrust-generating mechanism and a power source. The thrust-generating mechanism is configured to produce a propulsion force. The control unit is operatively coupled to each of the plurality of propulsion units. The transportation system further includes a housing unit or a pilot attachment disposed within the interior space. The housing unit or the pilot attachment is suspended by at least one connecting element or a suspension mechanism which is configured to dampen and / or stabilize and / or actively adjust movement relative to the body.

An apparatus, including a controller; an air intake system located at a vehicle; an air filtration system; an environmental control system; an air tank located at the vehicle; a water harvesting system; a water filtration system; and a water storage tank located at the vehicle. The controller controls an operation of the air intake system, the air filtration system, the environmental control system, the water harvesting system, and the water filtration system. The air intake system intakes air from an external environment, and the air filtration system filters or purifies the air. The environmental control system heats the air or cools the air. The air tank stores the air and the water harvesting system harvests water from the air. The water filtration system filters or purifies the water and the water storage tank stores the water.

A power storage module which includes a plurality of batteries connected in series and is capable of controlling operation of a heater on the basis of a battery with the lowest battery temperature is provided. The power storage module includes a first battery and a second battery connected in series, the heater, and a control circuit; the heater is provided close to the first battery and the second battery and is electrically connected to an IC included in the control circuit; the control circuit includes a first voltage sensor that senses a voltage of the first battery, a second voltage sensor that senses a voltage of the second battery, and a current sensor that senses a current flowing through the first battery and the second battery; and in charging the first battery and the second battery, the heater is turned on by a signal from the IC in the case where a differential voltage between a first peak voltage of dQ / dV calculated from a detection value of each of the first voltage sensor and the current sensor and a second peak voltage of dQ / dV calculated from a detection value of each of the second voltage sensor and the current sensor is higher than or equal to 5 mV.

A system and method in a building or vehicle for an actuator operation in response to a sensor according to a control logic, the system comprising a router or a gateway communicating with a device associated with the sensor and a device associated with the actuator over in-building or in-vehicle networks, and an external Internet-connected control server associated with the control logic implementing a PID closed linear control loop and communicating with the router over external network for controlling the in-building or in-vehicle phenomenon. The sensor may be a microphone or a camera, and the system may include voice or image processing as part of the control logic. A redundancy is used by using multiple sensors or actuators, or by using multiple data paths over the building or vehicle internal or external communication. The networks may be wired or wireless, and may be BAN, PAN, LAN, WAN, or home networks.

The invention discloses an unmanned aerial vehicle rapid autonomous battery replacement monitoring management method and system. The unmanned aerial vehicle rapid autonomous battery replacement monitoring management method comprises the following steps: acquiring battery replacement request data initiated by an unmanned aerial vehicle to be subjected to battery replacement in a battery replacement network; generating a port congestion risk prediction curve; calculating reputation points, and generating a comprehensive reputation value; generating a comprehensive utility value; generating an optimal power conversion scheduling sequence, and issuing an instruction of entering a specified power conversion port to execute power conversion to the unmanned aerial vehicle; and writing back the execution log data containing the actual waiting duration and the load of the power conversion port to the block chain. According to the invention, through block chain right confirmation, twin prediction and closed-loop log write-back, decentralized power conversion scheduling with high-value task priority and controllable battery risk is realized; the problems that high-value tasks are blocked by low-value tasks, priorities cannot reflect battery health differences, and simulation results cannot be subjected to closed-loop correction during multi-machine concurrent battery replacement in the prior art are solved.

An electrical power supply system for an aircraft comprising: a string of a plurality of connected smart battery modules, wherein the string is configured to provide a common output voltage; wherein each of the smart battery modules comprises, terminals for outputting an output voltage to a device external to the smart battery module; a battery assembly configured to supply a DC voltage between two poles; a power converter electrically connected to the terminals and the poles, and a controller operably coupled to the semiconductor stage and configured to control the semiconductor stage for regulating the voltage conversation of the DC voltage into the output voltage a control unit operably coupled to the controller of each smart battery module and configured to set an output voltage and / or current setpoint or limit for each controller individually or configured to set an output voltage and / or current setpoint or limit for all controllers collectively.

A system and method in a building or vehicle for an actuator operation in response to a sensor according to a control logic, the system comprising a router or a gateway communicating with a device associated with the sensor and a device associated with the actuator over in-building or in-vehicle networks, and an external Internet-connected control server associated with the control logic implementing a PID closed linear control loop and communicating with the router over external network for controlling the in-building or in-vehicle phenomenon. The sensor may be a microphone or a camera, and the system may include voice or image processing as part of the control logic. A redundancy is used by using multiple sensors or actuators, or by using multiple data paths over the building or vehicle internal or external communication. The networks may be wired or wireless, and may be BAN, PAN, LAN, WAN, or home networks.

A system and method in a building or vehicle for an actuator operation in response to a sensor according to a control logic, the system comprising a router or a gateway communicating with a device associated with the sensor and a device associated with the actuator over in-building or in-vehicle networks, and an external Internet-connected control server associated with the control logic implementing a PID closed linear control loop and communicating with the router over external network for controlling the in-building or in-vehicle phenomenon. The sensor may be a microphone or a camera, and the system may include voice or image processing as part of the control logic. A redundancy is used by using multiple sensors or actuators, or by using multiple data paths over the building or vehicle internal or external communication. The networks may be wired or wireless, and may be BAN, PAN, LAN, WAN, or home networks.

A watercraft including a hull; a deck; a battery and an electric motor; a cooling system including: a heat exchanger; a closed cooling path in thermal contact with the heat exchanger and the battery; and an open cooling path in thermal contact with a portion of the closed cooling path. Also a cooling system including: a heat exchanger including: a heat exchanger body, a first channel defined in the heat exchanger body, the first channel being in thermal contact with the outer surface for conducting heat therebetween, and a second channel defined in the heat exchanger body, the second channel being in thermal contact with the first channel, a first cooling path in thermal contact with the battery, a portion of the first cooling path being defined by the first channel; and a second cooling path defined by the second channel.

A ground station of a UAS for an unmanned aerial vehicle (UAV) includes a landing pad assembly and a carousel assembly that allow for passive removal and replacement of a battery from and to a UAV. The UAS can include a battery replacement system that uses the mechanical movement of a landing pad of the ground station to control movement of a battery door of the landing pad assembly.

A method for managing a charging process of a battery pack for an electric vehicle is provided herein. The method includes initiating a charging cycle for the battery pack, actively managing temperature of the battery pack during the charging cycle by flowing a temperature-controlled coolant through a thermal management system integrated with the battery pack, monitoring state-of-charge (SOC) and temperature of the battery pack, adjusting a charging current and a coolant temperature of the temperature-controlled coolant based on a coupled electro-thermal model to achieve a target SOC and a target temperature range for electric vehicle operation, and terminating the charging cycle based on the target SOC and the target temperature range being achieved within predefined constraints.

A control system for rotating an airfoil along one axis that is offset from a perpendicular axis that varies the angle of attack (AOA), dihedral, and center of lift based on the position of the attachment to precisely maneuver an aircraft. This technique can eliminate the need for traditional control surfaces such as ailerons, elevators, and rudders. allowing for an aerodynamically advantaged shape.

An imaging system is provided. A first imaging system captures initial sensor data in a form of visible domain data. A second imaging system captures subsequent sensor data in a form of second domain data, wherein the initial and subsequent sensor data are of different spectral domains. A controller subsystem detects at least one region of interest in real-time by applying a machine learning technique to the visible domain data, localizes at least one object of interest in the at least one region of interest to generate positional data for the at least one object of interest, and autonomously steers a point of focus of the second imaging system to a region of a scene including the object of interest to capture the second domain data responsive to the positional data.

A method for finding a charging station for electric motor vehicles using at least one drone that has a monitoring device, includes the following steps: generating control signals for controlling the drone such that, when controlling the drone based on the generated control signals, the drone monitors an environment of an electric motor vehicle using its monitoring device and outputs monitoring data based on the monitoring; outputting the generated control signals to control the at least one drone based on the generated control signals; after outputting the generated control signals, receiving the monitoring data from the at least one drone; analysing the monitoring data to find a charging station for electric vehicles; and outputting an analysis result of the analysis of the monitoring data. The application also relates to an apparatus, a system for finding a charging station for electric motor vehicles, a computer programme, and a machine-readable storage medium.

A method of evaluating a battery cell within a battery module of an aircraft hybrid-electric propulsion (HEP) system is provided. The HEP system includes a thermal engine, an electric motor, and a propulsion unit. The HEP system is configured to control at least one of the thermal engine or the electric motor to be in drive communication with propulsion unit. The method includes: controlling the HEP system to have the battery module and the battery cell disposed in a rest mode; determining an open-circuit voltage (OCV) of the battery cell after a settling period of time; determining an internal resistance value of the battery cell using the determined OCV; and evaluating the battery cell based on the determined OCV and the determined internal resistance value.

A hangar is provided for an unmanned aerial vehicle, and is suitable for being arranged on a vehicle. The hangar includes a hangar body, the hangar body being configured to accommodate the unmanned aerial vehicle; a charging apparatus, the charging apparatus being arranged in the hangar body, and the charging apparatus being configured to charge an unmanned aerial vehicle battery, wherein the unmanned aerial vehicle battery includes a first battery mounted on the unmanned aerial vehicle and / or a second battery outside the unmanned aerial vehicle; and a battery pick-and-place apparatus, the battery pick-and-place apparatus being arranged in the hangar body, and the battery pick-and-place apparatus being configured to detach the first battery from the unmanned aerial vehicle and / or mount the second battery into the unmanned aerial vehicle.

A craft is provided comprising: a propulsion system; a fuselage coupled with the propulsion system, wherein the fuselage is configured to carry a payload and fuel for the propulsion system; and a pre-assembled wing coupled with the fuselage; wherein the craft is designed to take-off without using a runway and does not have landing gear to land.