1401results about "Ground installations" patented technology

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

A 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.

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 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.

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 discloses an amphibious aircraft alarm database design method, an alarm system and an alarm method. Determining the alarm demand of each alarm demand side based on scenarized demand capture and confirmation; converting each alarm demand into an alarm entry with an alarm attribute, wherein each alarm entry is in a decoupling state; and finally, constructing an alarm database through the alarm entries. According to the invention, the alarm demand conversion efficiency and the alarm realization accuracy of the airplane can be improved.

The invention provides a high aspect ratio wing topological optimization method considering pneumatic-structure coupling. The method comprises the following steps: establishing a pneumatic-structure strong coupling topological optimization model; performing finite element analysis to obtain an original variable field of the high aspect ratio wing; generating a filtering variable field and a projection variable field; deformation displacement of each finite element unit is obtained based on a UMMI material interpolation model; establishing information transmission, structure displacement response, aerodynamic load transmission and aerodynamic load updating strategies under pneumatic-structure coupling, and analyzing and updating the aerodynamic load; according to the method, manufacturing constraints such as geometric nonlinearity, multi-material layout and wing rib orientation size are comprehensively considered, design variables in an original variable field are subjected to iterative optimization solution, a wing optimization configuration is obtained, the three core problems of calculation distortion, performance deviation and manufacturing difficulty in lightweight design of the high aspect ratio wing are successfully solved, and the method is suitable for the lightweight design of the high aspect ratio wing. And the comprehensive performance and economical efficiency of the aircraft are remarkably improved.

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.

The invention belongs to the technical field of aircraft structure design, and particularly relates to an aircraft arbitrary space four-bar mechanism parameter optimization method, which comprises the following steps: firstly, determining input conditions or preposed requirements of a four-bar mechanism, secondly, establishing a mathematical model of a four-bar mechanism optimization problem, and then, carrying out derivation and analysis to obtain a four-bar mechanism parameter optimization result. The method comprises the following steps: establishing an analytic expression of parameter variables of the four-bar mechanism and compiling a corresponding calculation program, then carrying out iterative optimization on the parameters of the four-bar mechanism by utilizing an optimization algorithm, and finally outputting an optimization result to obtain an optimal design parameter.

Disclosed is a cart (2) for transporting an aircraft engine, comprising a base frame (4) equipped with wheels (6) for riding on a floor; at least two engine arms (14, 16) extending horizontally and movable vertically relative to the base frame, structured and designed for supporting the aircraft engine; and at least two adapter arms (20) extending horizontally at a higher level than the at least two engine arms, structured and designed for supporting an adapter coupled at the top of the aircraft engine. Disclosed is also a method of transporting an aircraft engine to a test cell.

A computerized method for operating a digital twin representing a personal security checking system, comprising the following method steps: Obtaining influencing data that influence the operation of the personal security checking system; simulating the operation of the personal security checking system with the aid of the digital twin on the basis of the influencing data; generating output data on the basis of at least one simulation, wherein the output data are provided for operating the personal security checking system and / or for operating an entity separate from the personal security checking system.

This invention relates to the field of computer technology, and in particular to a customizable aircraft design process element-based management system, including an element management module, a functional process module, an end-to-end process module, a process optimization module, and a process governance module. It solves the problems of existing process management IT systems, which are unable to build an "integrated" management system for related business in the aircraft design process, as well as the problems of fixed and inflexible frameworks for the element-based decomposition of management models.

The invention relates to a method for detecting aircraft icing of an aircraft, the method comprising the following steps: - Recording at least a part of an outer flow surface of the aircraft by means of at least one optical image sensor of a detection device and generating digital image data containing the recorded part of the outer flow surface of the aircraft, - inputting the digital image data into a machine learning system of the detection device as input data, which has learned a correlation between digital image data as input data and various types of aircraft icing as output data by means of at least one machine-learned decision algorithm in order to obtain output data, and - Detecting aircraft icing depending on the output data received and, if aircraft icing has been detected, classifying the aircraft icing with regard to at least one icing type depending on the output data received.

The invention relates to an airport foreign matter detection and cleaning robot, a control method thereof and a dual-redundancy device fault processing method, and aims to solve the technical problems that an existing airport foreign matter detection and cleaning robot is difficult to meet the detection-cleaning integrated requirement of an airport complex scene and is low in working efficiency. The invention provides an airport foreign matter detecting and cleaning robot. The airport foreign matter detecting and cleaning robot comprises a quadruped robot, a mechanical arm assembly, a visual assembly and a clamping jaw assembly. The clamping jaw assembly comprises a clamping jaw driving assembly, two in-place sensors, a clamping jaw and a supporting frame. The clamping jaw driving assembly comprises a metal shell, a clamping jaw control plate arranged in the metal shell, a driving plate and a motor, and an encoder is arranged on the motor; the support frame is arranged at the top of the metal shell through the in-place spring; the two in-place sensors are arranged on the two sides of the supporting face of the supporting frame respectively.

The express cabinet comprises an unmanned aerial vehicle intelligent connection express cabinet body arranged at a bus station, an unmanned aerial vehicle take-off and landing platform is arranged on the unmanned aerial vehicle intelligent connection express cabinet body, an intelligent express delivery unmanned aerial vehicle is arranged at the top of the unmanned aerial vehicle take-off and landing platform, and a parcel distribution mechanism is arranged in the unmanned aerial vehicle intelligent connection express cabinet body. The unmanned aerial vehicle take-off and landing platform is connected to the top of the unmanned aerial vehicle intelligent connection express delivery cabinet through a connecting piece and used for allowing an unmanned aerial vehicle to stay and work, and the unmanned aerial vehicle intelligent connection express delivery cabinet is arranged at the position of a bus station. The surface of the unmanned aerial vehicle intelligent connection express cabinet is provided with the bus information electronic display board, so that a bus station is formed, and the mode of combining the unmanned aerial vehicle intelligent connection express cabinet and the bus station is integrated, so that public resources are integrated and utilized.

A storage and order picking system (10) is disclosed, comprising: a drone (22) equipped for transporting a load carrier (32) and comprising a landing gear (62); and a guide frame (44) comprising at least one rail (68) extending in a longitudinal direction (X), preferably comprising an inlet section (72) and an outlet section (74) adjoining thereto, wherein the landing gear (62) and the at least one rail (68) are configured to couple to each other in order to move the drone (22) guided along the at least one rail (68); and wherein the at least one rail (68) is arranged in an area within the system (10) through which the drone is moved to perform an intralogistics function.

A method of aligning an aircraft with a landing platform in motion comprises measuring a GPS heading with at least one GPS sensor positioned at a known location relative to the landing platform while the landing platform is in motion, measuring an orientation of the aircraft with an orientation sensor fixed relative to the aircraft, calculating an orientation of the landing platform from the GPS heading, calculating an orientation offset between the measured orientation of the aircraft and the calculated orientation of the landing platform, and changing an orientation of the aircraft or the landing platform to reduce the orientation offset. A system for landing and securing an aircraft in an enclosure, a system for disconnecting a tether from an aircraft, and a system for landing an aircraft in an enclosure are also described.

The invention discloses an energy-saving type aircraft tractor intelligent driving control system, and relates to the technical field of vehicle driving control, an electric control clutch is connected in series between a transfer case and a rear axle, a controller unifies mechanical capacity, thermal capacity and synchronous bandwidth as permission functions, and permissible four-wheel drive is output; the pedal change rate and the motor torque are mapped into intention intensity, the two-drive slipping critical torque is estimated, a four-drive request / two-drive keeping is generated in combination with steering consistency and task intensity, and the four-drive request / two-drive keeping is submitted only when permission is established; arbitrating by using a state machine with manual priority, setting an entry / exit threshold value and de-jittering, and executing and coding back-off according to a pre-synchronization and torque law containing heat / speed difference suppression; actual energy and a constant four-wheel drive base line are metered in a fixed window, the duty and switching are counted, the energy / heat / smoothness composite cost is constructed, and weighted write-back is carried out on threshold projection. And safe connection is achieved, impact overheating is restrained, the duty energy consumption is reduced, and parameter consistency and migration are improved.

A technique for a UAV includes acquiring a query aerial image with an onboard camera of the UAV and a reference aerial image, the query aerial image including multiple instances of an asset and the reference aerial image including annotated pixels indicating an expected location and an identification for the multiple instances of the asset. The technique further includes identifying a plurality of corresponding pixels between the query aerial image and the reference aerial image, determining a homography transformation describing a relationship between the query aerial image and the reference aerial image, annotating the query aerial image to identify a first instance of the asset included in the multiple instances of the asset within the query aerial image, and instructing the UAV to perform an action associated with the first instance of the asset.

A reconfigurable landing platform for a base station that is configured to receive an unmanned aerial vehicle (UAV). The landing platform includes alignment members, which are configured for engagement with the UAV, and a drive mechanism, which is connected to the alignment members to facilitate repositioning of the alignment members from an extended position into a retracted position to thereby reposition the UAV on the landing platform. The drive mechanism includes a drive member and pulley assemblies, which engage the drive member and are configured to vary a lateral tension and an axial tension therein.

The utility model belongs to the field of unmanned aerial vehicle training grounds, particularly relates to a quick-disassembly type unmanned aerial vehicle air confrontation training ground, and aims to solve the problems that an existing training frame cannot be quickly disassembled and assembled during use and is not suitable for temporary or movable use, and even if the training frame is moved for use, the whole training frame is inconvenient to carry and convey, and the training frame is inconvenient to use. According to the scheme, the unmanned aerial vehicle air confrontation training device comprises a frame assembly for providing an air confrontation training field for an unmanned aerial vehicle, and the frame assembly comprises a bottom frame, supporting rods, a top frame, supporting columns, a first inserting plate, a second inserting plate, a first inserting block and a second inserting block; the two bottom frames are arranged at the bottoms of the supporting rods. When the frame assembly is used, the whole frame assembly is easy to assemble and stable in structure, the whole training frame can be rapidly disassembled and assembled, the frame assembly is suitable for temporary or movable use, the whole training frame is convenient to carry and convey when the frame assembly is used in a movable mode, and therefore the application effect is improved.

The invention belongs to the technical field of aircraft assembly, and discloses an aircraft front wheel turning angle monitoring device and method, and the device comprises a mechanical sensing module, a signal processing module and a signal receiving device. The mechanical sensing module is detachably mounted on a shock strut of a nose landing gear of an aircraft, and the rotary motion of the shock strut is converted into a linear displacement signal through a gear transmission mechanism in the mechanical sensing module; the signal processing module analyzes the displacement signal into a front wheel turning angle electric signal; and the signal receiving device receives and displays the angle value. The invention further discloses a corresponding monitoring method. The device adopts a modular and non-invasive design, solves the problems that the turning angle of the front wheel cannot be monitored in real time and the over-limit risk exists in the aircraft traction process, has the advantages of being convenient and fast to install, accurate in measurement and wide in applicability, and remarkably improves the safety and the working efficiency of flight guarantee.

The application discloses a high-speed aircraft folding rudder aerodynamic configuration design method based on aerodynamic heat constraint, determines a rudder leading edge radius and a rudder leading edge sweepback angle based on a current state nominal trajectory and a rudder leading edge thermal response temperature as a judgment standard; secondly, a conical angle of a folding rudder-cone surface is determined through iterative calculation, so that a chordwise dimension of a high-temperature-resistant refractory metal material, and a thickness of a skin and a heatproof coating at the cone are designed; thirdly, through interference position design of a heatproof cup bow shock wave, a gap between a fixed rudder and a movable rudder avoids the bow shock wave interference zone, so that a chordwise distance between a folding gap and a rudder shaft is determined. Through the aerodynamic configuration design method, the rudder leading edge radius can be as low as 3mm, and the cone angle can be as low as 4°, so that ablation deformation does not occur when the maximum heat flow of the rudder leading edge is less than 10MW / m 2 2, the resistance characteristics of the high-speed aircraft can be effectively reduced, the aircraft has a near-zero ablation feature, and a good aerodynamic shape is maintained.

Electric aircraft charging system including charging cable configured to carry electricity and energy source, wherein the energy source is electrically connected to the charging cable. The system also including a cable reel module, the cable reel module including a reel, wherein the reel is rotatably mounted to the cable reel module, wherein the reel is configured to rotate in a forward direction and a reverse direction, and the charging cable, in a stowed configuration, is wound around the reel. The cable reel module further including a rotation mechanism configured to rotate the reel in reverse, and a cable reel module door having a closed position and an open position, wherein the closed position prevents access to the reel and the open position allows access to the reel. The system additionally including a controller communicatively connected to the rotation mechanism and configured to send a retraction signal to the rotation mechanism.