1250results about "Aircrafts" patented technology

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.

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 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 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.

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 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 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.

A method for transmitting electrical power to a remote location. A power cell is charged and then transported to a distal location where it is installed into a battery system. The battery system has multiple sets of power cells and utilizes a first set before switching to a second set. When the first set is depleted, it is removed and transported to a charging station for recharging.

A propulsion system for an aircraft can include an electric power source and an propulsion assembly having a propulsor. An electric power bus can electrically connect the electric power source to the propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.

One embodiment is an aircraft having a least one of an aircraft motor or an aircraft motor drive, and a metal-air fuel cell. The aircraft has a waste heat transfer system including a diverter system. The diverter system selectively couples the metal-air fuel cell and the at least one of the aircraft motor or the aircraft motor drive. The aircraft has a control system to operate the waste heat transfer system to selectively transfer waste heat from the at least one of the aircraft motor or the aircraft motor drive to the metal-air fuel cell. The control system determines a power output status of the metal-air fuel cell, and to operate the diverter system to transfer the waste heat from the at least one of the aircraft motor or the aircraft motor drive to the metal-air fuel cell in response to determining the power output status.

Systems, apparatus and methods are provided for securing firmware and mission data in memory of an unmanned aerial vehicle. The unmanned aerial vehicle may include a central body and at least one electric motor. The central body may include a flight controller with a processor, a firmware memory configured to receive and store firmware, and circuit board with a fixed portion and a removable portion with a programming interface connector providing access through a signal connection to a firmware memory operatively connected to the flight controller. The central body may further include a volatile mission memory configured to receive mission data and automatically be erased upon power interruption.

An unmanned aerial vehicle includes: a mooring member capable of mooring an article; a linear member connected to the mooring member; a reel around which the linear member is wound. The unmanned aerial vehicle acquires information relating to wind strength around the article when the article is to be lowered from the unmanned aerial vehicle by controlling the reel; and controls the reel so as to provide a feeding amount of the linear member in dependence on the wind strength, on the basis of the acquired information.

The invention discloses a safe operation method of a real stone paint spraying unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicle production. According to the safe operation method of the real stone paint spraying unmanned aerial vehicle, an unmanned aerial vehicle spraying system is included, the unmanned aerial vehicle spraying system comprises the spraying unmanned aerial vehicle with an airborne paint pot and a spraying gun, an air conveying pipe, a storage tank and an air pump, the airborne paint pot is connected with the storage tank through the air conveying pipe, and the storage tank is connected with the air pump. By establishing a space coordinate system and based on the moment balance principle, scenes such as the relation between the load of the unmanned aerial vehicle and the length of a paint conveying pipe and the weight of paint, covering air pump position deviation and wall distance change are quantified, reference is provided for real stone paint spraying operation of the unmanned aerial vehicle, workers can be guided to select unmanned aerial vehicles with different loads, and the working efficiency is improved. Safe and smooth operation is ensured; the safe operation method of the real stone paint spraying unmanned aerial vehicle can cover various complex operation scenes, the model selection precision and the spraying safety of the unmanned aerial vehicle are improved, the trial and error cost is reduced through the parameterized model, and the construction efficiency is improved.

Provided are a fling mobile body, a flight position estimation method, a computer program, and a flight position estimation system that make it possible to estimate a flight position of the flying mobile body with high accuracy. The flying mobile body comprising: a receiver; and a control device. The receiver receives a terrestrial broadcast signal transmitted from a broadcasting station. The control device executes a step of estimating a flight position of the flying mobile body based on the received terrestrial broadcast signal.

A composite drive shaft includes a web-based body defining a longitudinal axis. The web-based body has a first composite layup end section, a second composite layup end section that is opposite to the first composite layup end section, a first spiral composite element extending between the first composite end section and the second composite layup end section, and a second spiral composite element extending between the first composite end section and the second composite layup end section. The first spiral composite element and the second composite spiral element are embedded into the first composite layup end section, and the second composite layup end section. The first composite spiral element and the second composite spiral element are arranged in a bi-directional orientation relative to the longitudinal axis. The first spiral composite element and the second spiral composite element are arranged at pre-determined angles and possess a uni-directional fiber-reinforced polymer-matrix composite structure.

This cargo carrying device (10p) comprises: a main body (machine main body (2301), first machine main body (2301a), second machine main body (2301b)); a rail holding unit (connection body) which is held on a rail (7) positioned at the top of the main body; a rotary base (2319) which is positioned between the main body and the rail holding unit, and which rotates the main body; a slider (2310) which extends from the main body; and a cargo holding unit (2315) which holds cargo that has been attached to the slider unit (2310).

The invention relates to the technical field of unmanned aerial vehicles, in particular to an energy control method, system and equipment for a heavy oil hybrid power unmanned aerial vehicle, and the method comprises the steps: recognizing a current working condition based on the flight state parameters of the unmanned aerial vehicle collected by a sensor, and if the flight height change rate is greater than or equal to a preset change rate and lasts for a first preset time period, starting a controller; if yes, identifying the current working condition as a take-off working condition; if the flight height change rate is smaller than the preset change rate and lasts for a second preset time period, identifying the current working condition as a cruise working condition; the flight state parameter comprises a flight height change rate; when the unmanned aerial vehicle is in a take-off working condition, the power generation all-in-one machine is started to cooperatively supply energy with the energy storage device, and power is provided for the brushless direct-current motor; and when the unmanned aerial vehicle is in a cruise working condition, the power generation all-in-one machine is started to output in two paths, one path drives the brushless direct-current motor, the other path charges the energy storage equipment, power requirements of different stages are matched through a differential energy supply strategy, and the energy utilization rate and the endurance time of the unmanned aerial vehicle are improved.

A compliant mount for an aircraft, for attaching equipment (such as a latching unit, for example) to a structural member of the aircraft, the compliant mount comprising: a mounting member for attachment to the structural member of the aircraft; a receptacle for supporting the equipment, the receptacle being coupled to the mounting member along a longitudinal axis; and one or more spring elements arranged to resiliently bias the receptacle into alignment with the longitudinal axis and to allow angular movement of the receptacle away from the longitudinal axis. Also provided is an aircraft equipment assembly comprising such a compliant mount, and aircraft equipment supported by the receptacle, and an aircraft having one or more such equipment assemblies. The aircraft may be a folding wingtip aircraft and the equipment assembly may be part of a folding wingtip actuation mechanism.

An unmanned aerial vehicle (20) for inspecting linear infrastructure (60, 61) is described.The unmanned aerial vehicle (20) comprises: a camera (23), a gimbal (24) carrying the camera (23), a light detection and ranging (Lidar) system configured to scan linear infrastructure and generate 3D point cloud data, and a processing device configured to receive the 3D point cloud data from the Lidar system, analyze the 3D point cloud data to detect features of interest on the linear infrastructure, calculate, based on the detected features of interest, camera angles and / or distances to the features of interest, and generate, based on the calculated camera angles and / or distances to the features of interest, commands for the gimbal (24), wherein the gimbal (24) is configured to change the orientation of the camera (23) based on the commands of the processing device (26).

According to an embodiment, a control device controls a user-wearable flight device and includes a processing unit configured to acquire state data related to a state of the flight device and manipulation data related to a manipulation of the flight device, input the acquired state data and the acquired manipulation data to a model trained using deep reinforcement learning, and control the flight device on the basis of an output result of the model to which the state data and the manipulation data are input.

Methods, apparatus, systems, and articles of manufacture are disclosed for a hydrogen fuel distribution system (100) with integrated thermal management. An example fuel distribution system (100) with integrated thermal management comprises a hydrogen fuel distributor (402) including a first tank (406) and a second tank (408). The hydrogen fuel distributor (402) circulates hydrogen fuel to a first fuel cell (606) and a second fuel cell (608). A coolant distributor (702) includes a heat exchanger (416). The coolant distributor (702) regulates a temperature of the fuel distribution system (100). A compressed air distributor (706) provides compressed air from a propulsor (730) to the first fuel cell (606) and the second fuel cell (608). An electrical distributor (602) transports electricity from the first fuel cell (606) and the second fuel cell (608) to an electric motor (726). The electric motor (726) drives the propulsor (730).