2335results about "Aircrafts" patented technology

An apparatus may include a substrate. The apparatus may also include a first charger terminal disposed on the substrate and configured to apply a first electric potential to a first battery terminal of a battery. The apparatus may additionally include a second charger terminal disposed on the substrate and configured to apply a second electric potential to a second battery terminal of the battery. The apparatus may further include a barrier located on the substrate between the first charger terminal and the second charger terminal and configured to electrically isolate the first charger terminal and the second charger terminal by obstructing formation of a conductive path by way of a liquid disposed on the substrate.

An apparatus for facilitating the landing and takeoff of electric vertical takeoff and landing aircraft (EVTOL) can comprise a moveable landing platform, a moveable charging assembly comprising a high voltage cable adapted for electrical, magnetic induction positioned within a vertically moveable column having a magnetic plate and multiple access connections, and weight sensors positioned on the landing platform. The weight sensors are operatively connected to the charging assembly such that when the sensors detect the landing of an EVTOL on the platform, the sensors trigger the charging assembly to rise up to contact the EVTOL and begin charging the EVTOL.

An apparatus may include a substrate. The apparatus may also include a first charger terminal disposed on the substrate, including silver, and configured to apply a first electric potential to a first battery terminal of a battery. The apparatus may additionally include a second charger terminal disposed on the substrate, comprising silver, and configured to apply a second electric potential to a second battery terminal of the battery.

The invention discloses an unmanned aerial vehicle autonomous homeward voyage charging system based on wireless charging, and relates to the field of flight control and energy management, and the system comprises the steps: monitoring the flight path, remaining power and environmental parameters of an unmanned aerial vehicle, predicting the remaining power required for completing a task, and triggering a homeward voyage condition signal and the current position information of the unmanned aerial vehicle; generating an optimal homeward flight path of the nearest wireless charging platform based on the homeward flight triggering condition signal and the current position information of the unmanned aerial vehicle; obtaining an optimal charging point based on the generated return path, and sending a deployment instruction to the mobile charging platform; the mobile charging platform advances according to the deployment instruction path, the unmanned aerial vehicle returns according to the optimal return path, the course is corrected through inertial navigation and a visual algorithm, and the landing point of the unmanned aerial vehicle is obtained. Fine adjustment and positioning of the flight attitude are formed by using the visual identification and attitude control module, and a closed-loop flight control mechanism based on image processing and attitude adjustment amount calculation is realized.

A disclosed leaky coaxial resonant sensor system and methods. In use, the system includes at least one split-ring resonator (SRR) embedded within a material of the component. The at least one SRR is formed from a composite material. Additionally, the at least one SRR is configured to resonate at a first frequency in response to an interrogation signal from a leaky coaxial cable antenna. In some aspects, each SRR may resonate at a first frequency in response to an electromagnetic ping when the composite material is in a first state, and may resonate at a second frequency in response to the electromagnetic ping when the composite material is in a second state. A resonant frequency of the composite material may be based on physical characteristics of the composite material.

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 unmanned aerial vehicle hydrogen-electricity hybrid power system comprises a vehicle body, a hydrogen fuel cell system, a power cell system and an energy management system are arranged in the vehicle body, and electric energy output by the hydrogen fuel cell system and the power cell system supplies power to a motor through the energy management system; the motor controls the spiral blades, the rotating speed of the motor is independently adjusted, and the posture and movement of the unmanned aerial vehicle are controlled by changing the direction and size of the lifting force; the energy management system is used for performing energy conversion during air speed change and braking of the unmanned aerial vehicle, converting mechanical energy into electric energy, inputting the electric energy into the power battery system, and meanwhile, converting the electric energy to judge whether the unmanned aerial vehicle has a high-power energy supply demand currently so as to adjust energy supply; according to the invention, the service life of the galvanic pile monomers can be prolonged, so that the service life of the hydrogen-electricity hybrid power system module can be prolonged; according to the energy management method, unnecessary energy loss is reduced, and the endurance time of the unmanned aerial vehicle is further prolonged.

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 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 gas leakage detection apparatus may include a movement control unit that controls a movement of a moving object on which a gas sensor is mounted. The gas leakage detection apparatus may include an acquisition unit that acquires a measurement result of target gas that is obtained by a measurement by the gas sensor while the moving object is moving over a target area, and a response time from a start of a measurement of the gas sensor until an output of the measurement result. The gas leakage detection apparatus may include a detection unit that detects a leakage of the target gas in the target area based on the measurement result and the response time. The detection unit may detect the leakage of the target gas in the target area based on the measurement result and location information of the moving object, to identify a gas leakage spot.

A power converter topology, comprising: a cascade connection of a first converter stage and a second converter stage; wherein the first converter stage comprises a current mode controlled pulse width modulation (PWM) converter having one or more pairs of switches forming a first switching bridge and an inductor connected to the output of the first switching bridge, the switching bridge generating a voltage Vlink; and wherein the second converter stage is a resonant converter having a switching stage having one or more pairs of switches forming a second switching bridge across the voltage Vlink generated by the first converter stage and a resonant tank connected to the output of the second switching bridge, to generate a resonator output voltage; the topology further comprising a transformer to transform the resonator output voltage to a transformed output voltage and a rectifier to rectify the transformed output voltage to an output voltage Vout, and wherein the duty cycle of the first switching bridge is varied according to a voltage derived from the value of the output voltage Vout, and wherein the duty cycle of the second switching bridge is fixed at 50:50.

An air supply apparatus for an aerial mobility vehicle, which is provided with a fuel cell stack, includes an air compressor mounted in the aerial mobility vehicle and configured to compress air introduced into the aerial mobility vehicle, and an air chamber provided in the aerial mobility vehicle and connecting the air compressor and the fuel cell stack, wherein the air chamber defines a conditioning space for conditioning the air having passed through the air compressor, obtaining an advantageous effect of ensuring a stable supply of air to the fuel cell stack and improving operational stability and reliability.

A method of determining the capability of a nonlinear aircraft power source includes accessing status values representing a current state of an energy storage system in an aircraft, accessing demand values related to expected power demands on the energy storage system, modeling an ongoing status of the energy storage system using the status values and the demand values to predict when one of the status values will reach a threshold value, and providing an output of a capability of the aircraft based on the status value reaching the threshold value.

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

An apparatus and method for increasing security of a virtual machine are disclosed. The apparatus includes a host circuit having at least a processor and a memory, wherein the at least a processor is configured to receive at least a software module, create a virtual environment, which includes creating a plurality of partitions including a virtual machine (VM), determine a compliance category of the at least a software module as a function of an adherence of the at least a software module to at least one operational rule, isolate the at least a software module to the VM of a software module partition of the plurality of partitions, which includes adjusting partition connections between the software module partition and other partitions of the plurality of partitions within the virtual environment as a function of the compliance category and execute the at least a software module within the virtual environment.

The invention discloses an ejection device, a control method of the ejection device and electric mobile equipment, and the ejection device comprises a guide structure which is connected to a body; the ejected body is contained in the guide structure and is connected to the body in a releasable manner through a fastener; the parachute is accommodated in the guide structure in a foldable manner and is connected with the ejected body; the gas generator is mounted on the outer wall of the guide structure; wherein the fastener releases the catapulted body when responding to ignition current to be broken, and the gas generator inflates the parachute when responding to the ignition current, so that the parachute is converted into an unfolded state from a folded state, and the catapulted body is driven to fall. The dangerous source or the unit needing to be protected serves as the ejected body to be ejected from the body, damage to the body caused by fire of the dangerous source is effectively reduced, the safety of passengers is greatly improved, and an efficient and practical safety solution is provided for various scenes related to flight safety and equipment protection.

A method of preconditioning a battery for use in an unmanned aerial vehicle unmanned aerial vehicle may include fluidly coupling a fluid channel of a thermal management apparatus to an opening in fluid communication with the battery, determining a predicted temperature change of the battery as a result of the unmanned aerial vehicle traversing a predetermined flight path, determining a target initial temperature for the battery, wherein the target initial temperature is based at least in part on the predicted temperature change and is configured to operate the battery within a preferred temperature range during traversal of the predetermined flight path, selectively actuating a covering of the opening to allow air from the fluid channel of the thermal management apparatus to the battery, and at least one of heating or cooling the battery to the target initial temperature by directing air to the battery.

A method for inverting soil moisture in heterogeneous covered farmland based on microwave and multi-spectral data from drones, the steps of which are as follows: the atmosphere is equivalent to a transparent medium, the vegetation layer is equivalent to a heterogeneous semi-transparent medium, and the ground surface is equivalent to a rough surface natural medium, so that the covered farmland under near-ground remote sensing conditions is physically abstracted as a heterogeneous multi-layer medium model; the radar echo transmission mechanism of the heterogeneous multi-layer medium model is studied by multi-physics field coupling simulation; the influence of non-homogeneous factors on soil moisture inversion is eliminated by collaboratively applying drone multi-spectral data and microwave remote sensing data, and soil moisture sensitivity parameters are extracted; the drone microwave inversion model of soil moisture in covered farmland is established by using the soil moisture sensitivity parameters. This invention will provide new technical methods and model tools for remote sensing monitoring of soil physiological and biochemical parameters of covered farmland, and at the same time provide a scientific basis for rapid perception of soil moisture and water and fertilizer regulation and management at the farmland scale with high precision and high efficiency.

The invention provides a personal aircraft chassis and a personal aircraft. The chassis comprises a main framework and a chassis body, the personal aircraft comprises a main framework and a thrust array assembly, the thrust array assembly is fixed to the main framework, thrust of the thrust array assembly is achieved through a plurality of first turbojet engines, the geometric position relation between the thrust action point and the thrust direction of the thrust array assembly and the main framework is kept fixed, and when the personal aircraft stops on the ground, the thrust array assembly is fixed to the main framework. The thrust direction of the thrust array assembly is perpendicular to the ground. The vector nozzle assemblies are fixed to the main framework, thrust of the vector nozzle assemblies is achieved through the second turbojet engines, the central axes of the second turbojet engines are perpendicular to the central axis of the first turbojet engine, and vector nozzles of the vector nozzle assemblies at least have one degree of freedom relative to the main framework. And high-dynamic, high-fault-tolerance and reconfigurable flight control which cannot be realized by utilizing pure thrust difference control can be realized.

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.

An unmanned aerial vehicle system including an unmanned aerial vehicle (UAV); a tether having a first end positioned in a winch system of the UAV and a second end secured to a payload coupling apparatus; a payload coupling apparatus receptacle positioned in the UAV; a payload having a handle, wherein the handle of the payload is positioned within a slot in the payload coupling apparatus; wherein the UAV has a recessed restraint slot for receiving a top portion of the payload.

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.

A hybrid propulsion update system includes a controller in signal communication with a replaceable battery. The controller includes a tuning parameters storage unit configured to store at least one tuning parameter corresponding to the replaceable battery. The controller is configured to execute at least one optimization algorithm that utilizes the tuning parameters to control operation of the hybrid electric aircraft according to a first performance. The tuning parameters storage unit is configured to receive at least one updated tuning parameter from a controller updating device. The controller executes the at least one optimization algorithm that utilizes the at least one updated tuning parameter such that the hybrid electric aircraft operates according to a second performance that improves upon the first performance.

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.

Docking apparatus and methods for providing charging power to a power storage device of an external device, the docking apparatus including a docking portion for the external device to dock with; a plurality of power-supply contacts mounted on a surface of the docking portion and arranged in an L shape; and a control circuit configured to detect whether the external device docks with the docking portion and supply power to the power-supply contacts on the docking portion in response to detecting that the external device docks with the docking portion.

The present disclosure provides systems and methods for storing, transporting, and using hydrogen. In some embodiments, the method may comprise (a) storing hydrogen fuel in one or more fuel storage modules; (b) transporting the one or more fuel storage modules to a vehicle fueling site, wherein one or more hydrogen fuel compatible vehicles are located at or near the vehicle fueling site; (c) loading the one or more fuel storage modules into the one or more hydrogen fuel compatible vehicles, wherein the one or more fuel storage modules are configured to be releasably coupled to the one or more hydrogen fuel compatible vehicles; and (d) decoupling the one or more fuel storage modules from the one or more hydrogen fuel compatible vehicles after the one or more fuel storage modules are depleted or partially depleted.

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 deep learning, aircrafts and the like, and provides an intelligent outdoor flight waistcoat based on deep learning, the intelligent outdoor flight waistcoat is provided with a waistcoat body and an intelligent flight control system, the intelligent flight control system comprises a deep learning control module, a main flight power device, an attitude auxiliary adjusting device and an environment sensing system; the environment sensing system comprises a visual sensor, a laser radar sensor, an ultrasonic sensor, a height sensor and a GPS positioning module and is used for collecting outdoor environment data in real time and transmitting the outdoor environment data to the deep learning control module, and the deep learning control module analyzes the environment data in real time and automatically optimizes the flight state through an autonomous learning algorithm. The main flight power device is controlled to provide lift force and propulsion power, and the attitude auxiliary adjusting device is utilized to automatically correct the flight attitude, so that the flight waistcoat is convenient to wear, intelligent in environmental perception, high in self-adaptability, safe and stable, and meets diversified outdoor flight and rescue task requirements in the future.

A flying vehicle that is compact and portable and can be carried over the roof rack of a passenger car. The flying vehicle includes an upper chassis and a lower chassis removably mounted to the upper chassis. The lower chassis is positioned below the upper chassis. Eight rotors, a battery pack, and a control unit are mounted to the upper chassis. A seat for the rider is mounted to the lower chassis directly below the battery pack. Such a position of the seat allows a rider to egress from the vehicle safely without requiring the vehicle to land and turn off the rotors.

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.