2700results about "Ground installations" patented technology

A base station is disclosed for an unmanned aerial vehicle (UAV) that includes: an enclosure defining a window that is configured to receive the UAV to allow for entry of the UAV into the base station and exit of the UAV from the base station; a door that is movably connected to the enclosure such that the door is repositionable between a closed position and an open position; a sealing member that extends about the window and which is configured for engagement with the door so as to form a seal therewith in the closed position; and a heating system that is supported by the enclosure and which is configured to heat the door and / or the sealing member to support operation (e.g., opening and closure) of the door in a cold environment, wherein the heating system includes at least one light source and at least one heating element.

A base station is disclosed for an unmanned aerial vehicle (UAV). The base station includes: an enclosure; a slide mechanism that is connected to the enclosure and which is repositionable between a retracted position and an extended position; and a cradle that is connected to the slide mechanism and which defines a chamber that is configured to receive the UAV such that the UAV is movable into and out of the enclosure during repositioning of the slide mechanism between the retracted position and the extended position. The cradle includes: an upper shell; a lower shell that is connected to the upper shell; and at least one thermal insulator that is located between the upper shell and the lower shell.

A drone pod may receive, stow, and launch a drone. The drone pod may include a housing, a canopy movably coupled to the housing, a platform movably coupled to the housing, and a drone bay. The drone pod may be configured to move the canopy to expose the drone bay and raise the platform relative to a floor of the drone bay to receive the drone, lower the platform toward the floor of the drone bay and move the canopy to enclose the drone bay to stow the drone, move the canopy to expose the drone bay and raise the platform relative to the floor of the drone bay to launch the drone. The drone pod may be mounted on a vehicle. A system may include a drone pod and a drone, wherein the drone pod is configured to receive, stow, and launch the drone.

A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) storage and launch system includes a UAV pod having a UAV pod processor and a UAV selectively enclosed in the UAV pod, the UAV having only two rotors.

The invention discloses an energy-saving control method and system for an airplane ground air conditioning unit, and belongs to the technical field of air conditioning system energy saving.The method comprises the steps that internal and external environment parameters of a cabin are collected in real time, temperature prediction is conducted based on the internal and external environment parameters of the cabin, and a predicted temperature change curve is constructed; running state parameters of the aircraft ground air conditioning unit are called, dynamic energy-saving control is carried out in combination with the predicted temperature change curve, and an energy-saving control strategy is formulated; cabin internal variable parameters are introduced to optimize the energy-saving control strategy, and an optimized energy-saving control instruction set is generated; and the optimized energy-saving control instruction set is executed for cooperative driving, cooling circulation is conducted according to the cooperative driving result, and self-adaptive energy-saving control over the aircraft ground air conditioning unit is achieved. The technical problems of high energy consumption, unstable temperature control and low equipment operation efficiency caused by the lack of precise response capability of an air conditioning unit to dynamic changes of internal and external environments of a cabin in the prior art are solved.

A docking system is disclosed for an unmanned aerial vehicle (UAV). The docking system includes a base station that is configured to receive the UAV and a pedestal that is configured to support the base station in an elevated position. The pedestal defines an interior space that is configured in correspondence with an outer contour of the base station such that the base station is positionable within the pedestal to protect the base station during nonuse.

A drone system and method for deploying and autonomously refuelling. The drone system includes a base station and a drone. The base station and drone are configured for autonomous refuelling when the drone has landed in the base station. The base station also provides portability and security of the drone.

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 hybrid power system configuration optimization method based on a self-adaptive genetic algorithm, and the method comprises the following steps: S1, determining an unmanned aerial vehicle flight platform and collecting task parameters of an unmanned aerial vehicle, the task parameters of the unmanned aerial vehicle comprising flight duration, load capacity W and task environment parameters, recording power consumption of the unmanned aerial vehicle in different flight stages; s2, establishing an unmanned aerial vehicle energy consumption mathematical model, and calculating the total energy consumption of the unmanned aerial vehicle in each flight stage; s3, constructing an optimization objective function of the hybrid power supply of the unmanned aerial vehicle; and S4, performing optimization according to the target function, and outputting an optimal hydrogen fuel cell proportion to enable the target function to be minimum. By optimizing the power distribution proportion of the hydrogen fuel cell and the lithium battery and combining the efficient global optimization capability of the adaptive genetic algorithm, the power supply configuration is dynamically adjusted, and the cruising ability and the energy utilization efficiency of the unmanned aerial vehicle are remarkably improved.

There is provided a system for determining a route for an item and / or a passenger, the system comprising a processor. The processor is configured to: determine whether the item and / or passenger has missed or is expected to miss a first predetermined departure time of a first scheduled route; retrieve an origin for the item and / or passenger based on the first scheduled route; determine a destination for the item and / or passenger; determine a new, second, scheduled route between the origin and the determined destination wherein the second scheduled route departs from the origin at a second predetermined time which is different from the first predetermined time; and process the item and / or passenger according to the second scheduled route. A corresponding mobile device and user-accessible device for communicating with the system and corresponding methods are also provided.

The invention discloses an aircraft structure health state evaluation method and belongs to the field of aircraft design. The method comprises the following steps: 1, determining an aircraft structure health state evaluation principle; 2, analyzing and determining key indexes for evaluating the health state of the whole aircraft structure of the aircraft; thirdly, analyzing and determining key indexes for evaluating the health state of the local structure of the aircraft; 4, carrying out aircraft structure health key index attenuation hazard evaluation, and determining a structure health state grade; the method can determine the structural health state key index based on the characteristics of each aircraft, monitors the dynamic change process of the structural health state key index in the use process of the aircraft, and gives the attenuation harmfulness to the structural health state key index to determine the structural health state grade. An important basis is provided for formulating a subsequent training use and maintenance guarantee scheme of the aircraft, so that the use efficiency of the aircraft is effectively improved, and the maintenance period and cost are reduced.

A method is disclosed here. The method includes receiving an input from an aircraft, determining a towing status of the aircraft based on the input, and sending a message to a transmitter to transmit the towing status of the aircraft. Also disclosed herein is a system including an aircraft including a nose landing gear, a first controller, and a transmitter, wherein the first controller is configured to determine a towing status of the aircraft based on a number of sensor signals received from the aircraft, and the transmitter is configured to transmit the towing status and a tow truck configured to tow the aircraft, the tow truck including a second controller and a receiver, wherein the receiver is configured to receive the towing status from the transmitter, and the second controller is configured to provide an indication of the towing status of the aircraft.

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.

An example system includes a vehicle having a platform, a linear slide configured on the platform, a robotic retrieval system configured on the linear slide, a shelf configured adjacent to the linear slide and a control system that controls a reception of a first item and a second item by the robotic retrieval system and a placement of the first item and the second item, by the robotic retrieval system, on the shelf. A drone can be configured to retrieve the first item or the second item from the robotic retrieval system on the vehicle and deliver the first item or the second item to a destination location. The vehicle can thereby enable delivery of many items without the vehicle stopping or even driving to a specific destination location.

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.

Stowing systems and methods to disassemble, store, and / or protect an aircraft, and in particular a VTOL aircraft, for transportation along standard public roadways. A stowing system attaches to the aircraft in a flight-ready state, and guides, supports, and / or stabilizes sub-assemblies of the aircraft as they are removed and moved into their stowed positions in preparation for transportation. In some embodiments, the stowing system is implemented as a trailer. The trailer, in some embodiments, is towable by car, such that the aircraft can be carried on and transported with the car and trailer by road. In some embodiments, the stowing system defines landing platform for the aircraft. It may provide facilities to help direct the aircraft to a precise location allowing support elements of the stowing system to be moved to engage with sub-assemblies of the aircraft along predefined degrees of freedom.

A drone station according to an embodiment of the present invention may comprise: a station main body (10) having, mounted thereon, a charging device (20) allowing a drone to land thereon so as to be charged with drone power; a cover (30) provided at the station main body (10) so as to open / close the charging device (20) while rotating around an axle (12); and a window panel (34) provided in the cover (30), and made of a nonconductor material to transmit a GPS signal therethrough.

A rotor moment-of-inertia design method based on an autorotation landing capability. In the method, a characteristic quantity, i.e., "an autorotation characteristic time", for describing an autorotation-landing safety characteristic of a multi-engine helicopter is established, and a design objective of "the autorotation characteristic time" is provided, such that the relationship between the autorotation-landing safety characteristic of the multi-engine helicopter and a rotor moment of inertia is determined, and a theoretical formula and design method for a design objective of the rotor moment of inertia are provided. On the basis of an objective evidence-collection condition for a helicopter, the method can complete an objective design for a rotor moment of inertia in the overall design stage of the helicopter, and determine whether an autorotation-landing safety characteristic of the current overall technical scheme can meet the airworthiness requirements under the objective evidence-collection condition, thereby balancing the gain of the autorotation-landing safety characteristic and the weight of a rotor system.

The invention discloses a folding wing and rudder design method and an unfolding locking mechanism thereof. The locking mechanism comprises a connecting handle, an elastic torsional spring and a rotating shaft. A locking head and a connector are arranged on the two sides of the bottom of the folding wing or the folding rudder respectively; the design method comprises the steps of obtaining performance parameters, and determining specific indexes such as folding sizes and unfolding time of the folding wing and the rudder. And designing a structural model according to principles of generalization, reliability and the like, and determining geometric parameters of the wing and the rudder. Verifying the strength of parts of the locking mechanism, calculating a plurality of parameters of an elastic torsion spring, and analyzing the unfolding time and synchronism. Finally, consistency checking is conducted based on finite element simulation analysis, torque and bending moment are applied in ABAQUS software according to parameters, the structural strength of the folded rudder is analyzed, and it is ensured that the design meets the requirement. According to the folding wing and rudder design method, through the scientific design process and multi-principle comprehensive application, the high-performance requirement is met, meanwhile, the cost is effectively reduced, the reliability and maintainability of products are improved, and the remarkable beneficial effects are achieved.

An aircraft comprising an aircraft transceiver to transfer data to and from the aircraft by free-space-optical communication when parked. The aircraft transceiver comprises a transmitter to generate outgoing light carrying aircraft-to-ground data; a lens to collimate the outgoing light to generate a collimated beam; a beam steering device to transform the collimated beam to generate a steered beam; a control system to operate the beam steering device to adjust an angle of the steered beam; and a receiver to sense incoming light carrying ground-to-aircraft data. The receiver receives the incoming light via the beam steering device and the lens. Also a vehicle with a similar transceiver to transfer data to and from a parked aircraft by free-space-optical communication.

A system and a method include a user interface having a display. A control unit is configured to monitor a position of an aircraft in relation to one or more other structures at an airport, associate an aircraft model with the position of the aircraft, associate one or more structure models with the one or more other structures, and show the aircraft model and the one or more structure models on the display.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.

A charging hub for a base station configured to receive an unmanned aerial vehicle (UAV) during docking. The charging hub includes electrical contacts that are configured for electrical connection to the UAV and a wick that is configured to draw water away from the electrical contacts.

A drone system includes a headquarter station and one or more drone port stations. Each drone port station includes a platform configured to receive a drone, a radar system configured to detect and identify the drone, and one or more locker clips disposed on the platform, wherein the one or more locker clips are configured to lock onto one or more legs extending from the drone. Each drone port station also includes an internal computer configured to control operations of the drone port station, an internal camera operatively connected to the internal computer, where the internal camera is configured to detect a charging port or a fuel tank of the drone, a glass panel placed on the platform, where the glass panel is configured to protect the internal camera, and an antenna extending from the platform and configured to provide a communications pathway from the drone port station to the headquarter station.

The present disclosure relates to a hangar for at least one unmanned aerial vehicle, comprising: an interior, which is delimited by a lower side, an upper side and at least one side part, at least one manipulator arm in the interior, wherein the manipulator arm is designed to transport the at least one unmanned aerial vehicle through a closable opening in the at least one side part from the interior to the outer upper side of the hangar and / or wherein the manipulator arm is configured to transport the at least one unmanned aerial vehicle through a closable opening in the at least one side portion from the outer top of the hangar into the interior, wherein the manipulator arm is programmable and / or adapted to transport different unmanned aerial vehicles having different characteristics. Furthermore, the present disclosure relates to a system comprising at least two hangars.

The invention provides a tailstock type tailless layout amphibious aircraft adopting foldable wings and a design method, and relates to the field of amphibious aircraft design. According to the invention, aiming at a tailless-layout tailstock-type amphibious aircraft, by designing a foldable wing mechanism, the wings are unfolded to keep a high aspect ratio layout during air cruise, and the wings are folded to form an envelope layout for a fuselage during water surface dwelling and stopping; therefore, the aerodynamic performance requirement of the tailless layout tailstock type amphibious aircraft in an air cruising mode and the requirement of the tailless layout tailstock type amphibious aircraft in a water surface dwelling mode for the gravity center stabilizing distance and the floating stability are met, and the tailless layout tailstock type amphibious aircraft can take off quickly under the high sea condition. The problems that the relative positions of the gravity center, the pneumatic focus and the stable center of a traditional tailstock type fixed wing aircraft in the water surface floating state and the air cruising flight state are difficult to design, and the stability of the aircraft in the water surface floating state is difficult to guarantee through a traditional layout design are solved.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.

A method of docking an unmanned aerial vehicle (UAV) with a base station. The method includes: landing the UAV on a landing platform of the base station; generally aligning the UAV with a charging hub of the base station; extending the charging hub; and repositioning a locking mechanism on the charging hub from an unlocked position into a locked position to thereby secure the charging hub to the UAV.

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.

The invention discloses a finite element method for calculating an airfoil lift coefficient based on a potential flow theory, and belongs to the field of aircraft airfoil aerodynamic characteristic calculation and analysis. The method comprises the following steps: giving geometric information of an airfoil; determining an airflow area according to the geometric information of the airfoil; a gap is formed in the airflow area, and no airflow exists in the gap; taking the air flow area without the gap area as a solution domain; taking superposition of uniform incoming flow and pure circular flow as an undisturbed flow field to determine boundary conditions of the solution domain; a series of circulation values are given, the solution domain and the boundary conditions are combined, a potential flow control equation is solved by applying a finite element method for each circulation value, and a corresponding speed potential is obtained; and determining a real circular rector value by utilizing a Kutta condition, and calculating the lift coefficient of the airfoil profile according to the real circular rector value. According to the method, it is possible to obtain the airfoil lift coefficient by solving the potential flow control equation in the finite element framework, and the method is high in solving efficiency and easy to operate.