3190results about "Aircrafts" patented technology

The preferred embodiments disclose a hangar comprising a gantry robot which includes a lifting tool. The gantry robot is provided for lifting and lowering batteries to replace them, for example, in a drone disposed in the hangar.

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 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 urban air mobility building-top skyport for landing. loading and unloading. servicing. and parking short field takeoff and landing (STOL) aircraft. which includes a rotatable flight deck having at least one runway on which aircraft takeoff and land: a rotatable lower deck immediately below the flight deck and including an aircraft taxiway surrounding an enclosed central terminal with an elevator bank: and first and second aircraft ramps connecting the flight deck and the lower deck on which to taxi aircraft between the flight deck and the lower deck. A battery-swap station robotically replaces depleted batteries with fully charged batteries without the need for aircraft to cease moving at slow taxi speeds at any point during the process.

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.

A rapid monitoring and discrimination method for drought conditions in summer maize based on chlorophyll content includes: 1) Obtaining multi-spectral imagery through UAV multi-payload low-altitude remote sensing technology and measuring chlorophyll content on the ground. Additionally, calculating vegetation indices including Normalized Difference Vegetation Index (NDVI), Soil-Adjusted Vegetation Index (SAVI), and Renormalized Difference Vegetation Index (RENDVI). 2) Selecting vegetation indices and constructing regression equations with measured chlorophyll content during different growth stages. The regression equation with the highest correlation for each growth stage is chosen as the optimal model equation for that particular stage. 3) Using the optimal model equations to retrieve chlorophyll content for each period and determining thresholds for chlorophyll content across different drought levels through calibration. 4) Calculating the required vegetation indices from real-time multi-spectral imagery of the field under test, retrieving chlorophyll content, and comparing it with the established thresholds to assess the real-time drought level.

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.

The invention discloses an intelligent heat dissipation control method and system for a lighting unmanned aerial vehicle, and the method comprises the steps: collecting the temperature of an LED lamp panel in real time through a temperature sensor during starting, carrying out the prediction calculation of the temperature of the LED lamp panel through an embedded controller, and calculating the predicted temperature which can be reached by the LED lamp panel in a future preset time period through a multi-parameter correlation model; according to the prediction and calculation result, the control system generates a corresponding heat dissipation adjustment strategy, and the control system adjusts an air opening of the air guide groove through the electric control element according to the heat dissipation adjustment strategy; wherein the electric control element comprises a thermosensitive memory metal piece and a heating piece which are arranged in an attached mode, and after the opening degree of the tuyere is adjusted, the control system achieves dynamic heat dissipation adjustment by monitoring temperature changes in real time and through a cyclic data processing and feedback mechanism; the heat dissipation efficiency and the intelligent level of the lighting unmanned aerial vehicle are improved, the service life is prolonged, and the use stability and safety of the unmanned aerial vehicle are enhanced.

An aircraft air management system comprises an air heat exchanger; an intercooler; and a conduit system connected to the air heat exchanger, the intercooler, and a fuel cell stack. Heated air flows through the conduit system to the air heat exchanger. The air heat exchanger is configured to cool the heated air to form cooler air, wherein the cooler air flows from the air heat exchanger through the conduit system to the intercooler; and the intercooler is configured to cool the cooler air to form cooled air, wherein the cooled air flows from the intercooler through the conduit system to the fuel cell stack.

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.

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.

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 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.

A power source assembly is provided having a fuel cell module configured to provide a first direct current power output; a battery module configured to provide a second direct current power output; a direct current electric bus configured to provide a net direct current power output to a load; a DC / DC converter in electrical connection with the direct current electric bus, the DC / DC converter configured to receive the first direct current power output from the fuel cell module or the second direct current power output from the battery module; and a controller operably coupled to the DC / DC converter and configured to receive data indicative of the first direct current power output, the controller configured to control the DC / DC converter based on the data indicative of the first direct current power output to maintain a slew rate from the fuel cell module within a slew rate range.

An electric vehicle battery control system including a first electric motor configured to propel a vehicle in a drive mode in response to a drive current, a second electric motor operative to generate a back electromotive force voltage in a fault mode, a battery, having an open circuit battery discharge voltage, for generating the drive current for coupling to the first electric motor, and a vehicle controller for limiting the drive current in response to a difference between the back electromotive force voltage and the open circuit battery discharge voltage being less than a threshold voltage difference.

An aircraft cooling system comprises an evaporator, condenser, an accumulator, and a pump system. The evaporator is configured to cool a set of heat loads in an aircraft using a liquid. The liquid forms a vapor in response to cooling the set of heat loads. The condenser is configured to receive the vapor from the evaporator and cool the vapor in which cooling the vapor forms the liquid. The accumulator is configured to receive the liquid from the condenser and store the liquid. The pump system is configured to pump the liquid stored in the accumulator to the evaporator.

Embodiments of the present disclosure are directed to a vehicle battery situational awareness (VBSA) platform configured to monitor one or more vehicles. An onboard VBSA system associated with a vehicle is communicably coupled to a vehicle operations center associated with the VBSA platform and can monitor a current energy expenditure of the vehicle as the vehicle executes a trip plan. The onboard VBSA system can also determine that the current energy expenditure of the vehicle does not match a predicted energy expenditure. The onboard VBSA system can generate, based on output from a vehicle performance prediction model, a predicted energy overlay representing the predicted energy expenditure. The onboard VBSA system can also determine a safety boundary characterized by a maximum safe travel time. The onboard VBSA system can also cause display of the predicted energy overlay and the safety boundary on one or more computing devices.

The invention relates to the technical field of leaf bee prevention and control, and particularly discloses a leaf bee pest adult prevention and control method, which comprises the steps of S1, data collection, S2, climate prediction model establishment, S3, precise monitoring, S4, precise prevention and control, S5, dynamic adjustment and S6, monitoring optimization. By using the unmanned aerial vehicle and the remote sensing technology, a gathering area of the adult leafbees can be accurately identified, a high-risk area can be intensively prevented and treated, blind large-area pesticide spraying is avoided, the prevention and treatment effect is remarkably improved, the climate prediction model can predict the activity peak period of the adult leafbees in advance, farmers are helped to take prevention and treatment measures at the best opportunity, and the prevention and treatment efficiency is improved. Through real-time analysis of a climate prediction model and remote sensing data, a farmer can formulate a scientific prevention and control strategy according to the data, dependence on experience and subjective judgment is reduced, the decision accuracy is improved, and according to feedback of real-time monitoring data and the prediction model, changes of pests are coped with in time, so that the prevention and control effect is improved. The continuous optimization of the control effect is ensured.

A surveillance drone system is provided herein generally including an UAV, a base power station, and, a tether for connecting the UAV to the base power station to provide electrical power to the UAV when airborne. The base power station may include a cable take-up assembly for releasing and taking up the tether. A plug or power module is provided at the free end of the tether configured to be detachably coupled with the UAV, to transmit electrical power to, and, possibly, data to and from, the UAV. With the plug or power module being detached, the UAV is free to fly unrestricted. This arrangement allows for the UAV to be airborne for prolonged periods to allow for monitoring a region and for release to allow the UAV to investigate anomalies in the monitored region.

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.

To enable a route that satisfies a request of a user who operates an unmanned aerial vehicle to be presented in a style according to a predetermined format, the present invention involves: acquiring departure location information indicating the departure location of an unmanned aerial vehicle and destination location information indicating the destination location thereof; generating a plurality of candidate routes from the departure location to destination location of the unmanned aerial vehicle; executing processing for outputting route information indicating candidate routes that satisfy a predetermined condition among the plurality of generated candidate routes; and outputting the route information in a style that enables output of the routes, which are indicated by the candidate routes that satisfy the predetermined condition, according to the predetermined format.

There is provided a system of displaying an augmented reality (AR) image on a viewable surface of a vehicle, the system comprising a processing circuitry configured to: receive data indicative of a location of a target external to the vehicle; determine a line-of-sight to the target in accordance with, at least, an operator viewing position and an operator viewing orientation; and control a scanning projector to display the AR image on a location of the viewable surface that is located substantially along the line-of-sight.

A propulsion system including: a fuel cell assembly having a fuel cell defining an outlet positioned to remove output products from the fuel cell and a fuel cell assembly operating condition; a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the combustion section configured to receive a flow of aviation fuel from an aircraft fuel supply and further configured to receive the output products from the fuel cell; and a controller comprising memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the propulsion system to perform operations including receiving data indicative of a mid-flight flameout within the combustion section; modifying the fuel cell assembly operating condition in response to receiving data indicative of the mid-flight flameout within the combustion section; and initiating a relight of the combustion section.

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.

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.

Methods, systems, and devices for wireless communications are described. Specifically, techniques and signaling for configuring and utilizing parameters for unmanned aerial vehicle (UAV)-to-everything (U2X) communications are described, including registration procedures for U2X communications. A user equipment (UE), such as a UAV, may receive control signaling indicating a UE policy configuration including a set of radio parameters usable by the UE to perform sidelink communications to support one or more UAV services. The UE may receive an altitude limitation parameter associated with the one or more UAV services via the control signaling, additional control signaling, or both. The UE may then perform a sidelink message associated with the one or more UAV services in accordance with the UE policy configuration and altitude limitation parameter.

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.