2072results about "Ground installations" patented technology

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

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

A 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.

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.

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.

The invention belongs to the technical field of overall aerodynamic design of helicopters, and particularly relates to an infrared suppressor fairing of a helicopter and an air heat optimization design method of the infrared suppressor fairing. The fairing comprises a fairing body, a shutter air inlet, a square protective net air inlet, a second-stage exhaust pipe and a first-stage mixed exhaust pipe. The front of the fairing body is regarded as a half ellipse which is laterally cut along a long axis; a shutter air inlet is formed in the front portion of the fairing body, and the plane of a shutter is crescent A square protective net air inlet is formed in front of the top of the fairing body; an oval second-stage exhaust pipe is arranged behind the top of the fairing body so that high-temperature exhaust can be further cooled by means of downwash airflow of the rotor wings. A first-stage mixed exhaust pipe is sleeved in the second-stage exhaust pipe; and the primary mixing exhaust pipe is connected with an outlet of the transmitter. According to the method, the problem that the pneumatic performance and the thermal performance are difficult to consider in a traditional design method is solved, comprehensive optimization of the pneumatic performance and the thermal performance of the fairing is achieved, and a pneumatic design scheme of the infrared suppressor fairing is formed.

The invention provides an undercarriage system scheme design method based on heterogeneous design simulation data management, which comprises the following steps of: firstly, analyzing, abstracting and standardizing different types of heterogeneous design and simulation data in a development process of an undercarriage system, and constructing a uniform abstract data model; secondly, according to the defined semantic rules, an undercarriage semantic ontology model is constructed, then the semantic rules are loaded through a semantic reasoning engine, and processed data are associated; according to the research and development process of the undercarriage system and the semantic association relationship between the data, data storage and display are realized; after data abstract analysis, semantic association and unified storage are completed, functional information, design information and simulation information are further derived based on an undercarriage semantic ontology and a reasoning result, so that an undercarriage system development scheme driven by requirements is constructed. According to the method, multi-source heterogeneous design and simulation data generated in the research and development process of the undercarriage system can be effectively managed, and a design scheme of the undercarriage system is constructed on the basis of the multi-source heterogeneous design and simulation data.

The invention provides a section-operation-power system joint optimization design method for an electric vertical take-off and landing aircraft. The method comprises the following steps: defining a power system design variable, a section design variable and an operation optimization variable of the electric vertical take-off and landing aircraft; a power system quality model, an aircraft profile demand analysis model, a variable pitch propeller operation performance model and a motor operation performance model are established; power system design and operation control plan making of the electric vertical take-off and landing aircraft are combined, section-operation-power system joint optimization design of the electric vertical take-off and landing aircraft is achieved, and the characteristic of great difference between the wide-speed-range operation characteristic of a variable-pitch propeller and the hovering and cruising flight stage of the vertical take-off and landing aircraft is considered to the maximum extent. And compared with the design of firstly carrying out physical system design and then carrying out operation control design, the optimal design of the overall performance of the aircraft is realized.

Improved systems, apparatus, and methods for enhanced positioning of an airborne relocatable communication hub supporting wireless devices are described. Such a method begins with moving an aerial communication drone operating as the airborne relocatable communication hub to a first deployed airborne position, detecting a first signal broadcast by a first wireless device using a communication hub interface on the drone, and detecting a second signal broadcast by a second wireless device using the communication hub interface. The method has the drone comparing a first connection signal strength for the first signal and a second connection signal strength for the second signal, and repositioning the aerial communication drone to a second deployed airborne position based upon the comparison. Once repositioned at the second deployed airborne position, the method has the drone linking the first and second wireless devices using the communication hub interface on the aerial communication drone.

A conveying device (100) and an inspection system (1000) are provided. The conveying device includes: a first support frame (1); a first conveying mechanism (2) and a second conveying mechanism (3) which are installed on the first support frame; and a switching mechanism (4) configured to selectively lift the first conveying mechanism or the second conveying mechanism in a vertical direction, such that the first conveying mechanism or the second conveying mechanism carries goods (401) and conveys the goods in a first horizontal direction or a second horizontal direction different from the first horizontal direction. The conveying device may achieve a positioning and a smooth continuous conveying of goods, and achieve a smooth conveying and a calibrated positioning of the goods in different postures.

The invention relates to a foldable tilting four-rotor aircraft concept scheme design method based on task requirements. According to the method, task demand indexes such as voyage, cruising speed, task load, cruising height and hovering height are used as input, and the total design weight, power device parameters, rotor wing geometric parameters and fuselage and wing parameters of the aircraft are determined in sequence; and performance indexes such as hovering lift limit, level flight speed, climbing performance, practical lift limit, voyage and endurance in a helicopter mode and a fixed wing mode are calculated and analyzed respectively. And performing matching judgment on a performance calculation result and a task requirement, and performing iterative adjustment on key parameters such as a paddle disc load when the task requirement is not met, so as to form a closed-loop concept design process driven by the task requirement. According to the method, the vertical take-off and landing capacity and the fixed wing cruising performance can be systematically considered in the conceptual design stage, and systematicness, repeatability and engineering feasibility of scheme design of the folding type tilting four-rotor aircraft are improved.

The invention discloses a self-adaptive leveling and anti-disturbance vehicle-mounted unmanned aerial vehicle lifting platform and method, and relates to the technical field of automation control technologies, and the vehicle-mounted unmanned aerial vehicle lifting platform comprises a lifting mechanism assembled on a vehicle; the leveling mechanism is assembled at the lifting top of the lifting mechanism, and an unmanned aerial vehicle nest is assembled at the top of the leveling mechanism; the attitude sensing unit is used for measuring attitude data of the unmanned aerial vehicle nest in real time; the disturbance sensing unit is used for detecting external disturbance data of the unmanned aerial vehicle nest in real time; and the control unit is electrically connected with the lifting mechanism, the leveling mechanism, the attitude sensing unit and the disturbance sensing unit respectively. According to the invention, a high-frequency-response attitude sensing and multi-degree-of-freedom rapid leveling mechanism and a closed-loop control system of an advanced adaptive control algorithm are integrated. The system can monitor the posture of the platform in real time and quickly drive the leveling mechanism to compensate, so that the leveling mechanism always keeps a high-precision horizontal state under the condition that a vehicle inclines in a large range and is dynamically disturbed.

The invention discloses a pressure distribution guided target constrained airfoil Bayesian optimization method and a pressure distribution guided target constrained airfoil Bayesian optimization device, and belongs to the technical field of aircraft design. The method comprises the following steps: constructing an airfoil profile sample; evaluating the aerodynamic performance of the airfoil profile sample; calculating an airfoil profile sample target value and a constraint violation value, and constructing a sample set containing the airfoil profile sample, the airfoil profile sample target value and the constraint violation value; training a Gaussian process agent model by adopting a sample set, and outputting a prediction mean value and a prediction variance of an airfoil sample target and a constraint violation value; based on the prediction mean value and the prediction variance, optimizing the confidence boundary acquisition function with constraints to obtain a next to-be-evaluated airfoil profile sample; and after iteration, selecting a feasible airfoil profile sample with optimal target performance as an optimal solution. According to the method, the effective constraint on the pressure distribution of the sampling airfoil is realized, the performance of the final optimization airfoil at a non-design point is ensured, and the actual engineering requirements are better met.

An engine protection cover device for airtight sealing an engine of an aircraft or spacecraft includes an air intake cover being inflatable to correspond to the internal dimension of the air intake for airtight sealing the same, wherein the air intake cover includes an airtight sealable access opening for attaching or passing through an air dryer for drying the air inside the engine. An aircraft or spacecraft is disclosed with such an engine protection cover device.

The invention discloses a multi-degree-of-freedom supporting mechanism which comprises a base and a motion platform and further comprises a constant force compensation module connected between the base and the motion platform and used for balancing the motion platform and most of gravity loaded by the motion platform; the six-degree-of-freedom parallel fine adjustment module is connected between the base and the motion platform and used for providing six-degree-of-freedom accurate pose adjustment; the air floatation vibration isolation module is arranged between the base and the motion platform; the sensing system comprises a plurality of pressure sensors, and the pressure sensors are arranged on the constant force compensation module and / or the six-degree-of-freedom parallel fine adjustment module and used for monitoring stress information in real time; and the control system is in communication connection with the sensing system and the six-degree-of-freedom parallel fine adjustment module, and is used for controlling the six-degree-of-freedom parallel fine adjustment module to perform active vibration isolation and pose adjustment based on a feedback signal of the pressure sensor.

The invention relates to the technical field of spacecraft general assembly, in particular to a spacecraft general assembly operation platform which comprises a basic frame, at least one supporting frame, a lifting mechanism and a flexible enveloping mechanism, the supporting frames are arranged on the basic frame, and the supporting frames are sequentially connected in the vertical direction; the lifting mechanisms are arranged in the supporting frames correspondingly and used for adjusting the height of the supporting frames. The flexible enveloping mechanisms are arranged between the basic frame and the adjacent supporting frames and between every two adjacent layers of supporting frames and comprise a plurality of enveloping units, and each enveloping unit can move in the preset direction to adjust the edge shape of an enveloping area formed by the corresponding flexible enveloping mechanism. The overall height of the operation platform and the edge shape of the enveloping area can be adjusted, so that multiple adjustment process equipment for outboard general assembly and test tests of spacecrafts with various shapes is met, and the requirements for universal design of various spacecrafts and test tests under different working conditions are met.