905results 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.

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 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 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.

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.

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 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.

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.

To provide a system for preventing an accident by detecting a recognition discrepancy or an operation mistake between a controller and a pilot in real time.SOLUTION: A system comprising: means for receiving voice communication data between an air traffic controller and a pilot of an aircraft; means for converting the received voice communication data into text data; means for extracting instruction content from the converted text data; means for generating a predicted action based on the extracted instruction content; means for collecting current position data of the aircraft from a GPS; means for monitoring an actual action of the aircraft based on the collected GPS data; means for comparing the monitored action of the aircraft with the predicted action to detect an abnormality; and means for generating and notifying an alert when the abnormality is detected.SELECTED DRAWING: Figure 1

The invention belongs to the technical field of smart city infrastructure, and discloses a bus station smart cabin device integrated with a low-altitude aircraft multifunctional use scenario, which comprises a smart cabin, a low-altitude aircraft support system, a smart logistics system, a smart traffic management system and a power supply system, and is characterized in that the smart cabin comprises a passenger service area and a functional area; a parking platform is arranged in the functional area; the low-altitude aircraft support system comprises a navigation module, an obstacle avoidance module, a communication module and an energy management module; the intelligent logistics system comprises an intelligent sorting module, a distribution module and a data management platform. The intelligent traffic management system comprises a traffic monitoring module and a data analysis module. The system has the beneficial effects that multiple functions are creatively integrated into a whole, and the system adapts to the intelligent construction requirements of infrastructures of different cities; good economic benefits, social benefits and environmental benefits can be generated, and the method has a wide application prospect.

Provided is airport ground support equipment that makes it possible to calculate a discrepancy of an actual stop position of an aircraft from a regular stop position of the aircraft without requiring an input of aircraft type information about the aircraft. One example of the airport ground support equipment of the present invention is airport ground support equipment including: a support equipment body configured to perform an operation of coming close to a stopped aircraft from a standby position and to enable a person and / or an article to move between the support equipment body and the aircraft when the support equipment body is adjacent to or in contact with the aircraft; an aircraft type determiner (1B) that captures an image of the aircraft when the support equipment body is at the standby position and that determines an aircraft type of the aircraft based on the captured image; a nose gear image capturing camera (91) that is mounted to the support equipment body and that captures an image of a nose gear of the aircraft stopped on an apron when the support equipment body is at the standby position; and a stop discrepancy calculator (53) that detects a stop position of the nose gear based on the image captured by the nose gear image capturing camera and that calculates a discrepancy of the stop position of the nose gear from a regular stop position that is set in advance corresponding to the aircraft type determined by the aircraft type determiner (1B).

A kind of wheel holding device of aircraft tractor, it includes: car body, pedestal turntable, load floor, hydraulic cylinder group, clamping push plate, rotating motor and front pressing plate;Pedestal turntable, load floor, hydraulic cylinder group, clamping push plate, rotating motor and front pressing plate are all installed on car body.The wheel holding device of aircraft tractor provided by the present application has the advantages that: the wheel holding device does not need engine power, and moves by external ground power from the exit of the aircraft to the end of the runway waiting for takeoff, and the pilot controls the tractor to carry out departure operation, with the advantages of simple operation, safety, stable work, long service life, high lifting height, wide application range, etc.

The remote control wheel-holding transfer trailer comprises a trailer body, a bridging plate and a locking mechanism, the trailer body comprises a base plate and a plurality of pairs of moving wheels, the moving wheels are rotationally connected with the base plate through wheel shafts, a transfer bin is arranged on the top face of the base plate, and a bin opening is formed in the transfer bin; one side of the bridging plate is hinged to the base plate through a shaft, a crane is arranged at the position, located above a bin opening, of the transfer bin, a hook of the crane is detachably connected with the bridging plate so that the bridging plate can rotate between the loading and unloading station and the transfer station, and when the bridging plate is located at the loading and unloading station, the side, away from the base plate, of the bridging plate smoothly abuts against the ground to form a loading and unloading slope. When the bridging plate is located at the transfer station, the bridging plate is vertically arranged and blocks the bin opening; the locking mechanism is arranged in the transfer bin, and the locking mechanism can enable the remote control holding wheel to be detachably connected with the bin wall of the transfer bin. The problems that the bottom hanging phenomenon is prone to occurring during loading and unloading of existing transfer equipment, and a remote control holding wheel cannot be effectively fixed can be solved.

The embodiment of the invention provides a simulation method and device for automatic deceleration of a spoiler of a medium-sized propeller-driven aircraft, computer equipment and a medium, and the method comprises the following steps: determining a use scene in which the spoiler of the aircraft needs to be automatically decelerated, according to the use scene of automatic deceleration, flight data needing to be introduced into the simulation system is determined, and the flight data comprises a ground signal, a speed signal, an engine power signal and a spoiler normal working signal; according to the flight data, judging whether an entry condition for starting to use an automatic deceleration function is met, and if yes, unfolding the spoilers on the two sides to the maximum through a simulation system to automatically decelerate the aircraft; and continuously monitoring the flight data until the quit condition of quitting the automatic deceleration function is met, quitting the automatic deceleration, and resetting the double-side spoilers through the simulation system. According to the scheme, a method for automatically decelerating the ground through the spoiler is designed, and the effectiveness of the scheme is verified through simulation.

The utility model relates to the technical field of airplane emergency rescue traction, in particular to an emergency runway separation device which comprises a hydraulic lifting device used for jacking airplane wheels and a trailer used for placing the airplane wheels, the hydraulic lifting device comprises an oil tank, a multi-stage hydraulic cylinder is installed at one end of the oil tank, a jacking head screw is installed on the multi-stage hydraulic cylinder, and the trailer is connected with the hydraulic lifting device. A hydraulic pump is installed at the other end of the oil tank, a low-pressure piston rocker and a high-pressure piston rocker are installed on the hydraulic pump, and handle temporary placing rods and inserting rods are installed on the two sides of the hydraulic pump; the trailer comprises a tire placing plate, and a front universal wheel is installed at one end of the tire placing plate. According to the device, the multi-stage hydraulic jack is adopted to quickly jack up the airplane wheels, the trailer can be conveniently placed below the airplane wheels, the airplane can slowly descend through the multi-stage hydraulic jack so that the airplane wheels can be placed on the trailer, and the airplane can be conveniently dragged and moved through the trailer.

The invention relates to the technical field of aircraft structure design, in particular to an air inlet channel mounting structure and a design method. Comprising an air inlet channel and a peripheral structure, the air inlet channel is formed by connecting an air inlet channel lip and an air inlet channel inner channel, a lip turnup is designed on the air inlet channel lip in the main direction of airflow, and an air inlet channel clamping groove is formed in the lip turnup. The peripheral structure is formed by connecting a peripheral structure channel and a peripheral structure flange, a peripheral structure buckle is arranged at the tail end of the peripheral structure flange, the air inlet channel inner channel and the peripheral structure channel are combined in a sleeved mode, and the peripheral structure buckle is clamped in the air inlet channel clamping groove to achieve butt joint installation. The number of assembly connecting parts is greatly reduced, and the number of assembly part connecting points is reduced. And too large operation space is not needed.

The utility model relates to the technical field of cabin working ladders, in particular to a universal cabin working ladder, which comprises a rear ladder assembly, a front ladder assembly and an upper ladder assembly hinged with the front ladder assembly, and further comprises a group of moving wheels arranged on the rear ladder assembly, a supporting assembly is arranged between the rear ladder assembly and the upper ladder assembly; according to the working ladder, the problem that an existing working ladder for a cabin of a main battle aircraft is not universal is effectively solved, all the assemblies are formed by installing and welding aluminum profiles, and the working ladder is low in machining cost, simple in overall structure, light in weight, capable of being rapidly folded and high in operability; through rough adjustment of the supporting point and fine adjustment of the adjusting screw rod, it is guaranteed that the top stepping stick is close to the edge of the cabin, air and ground crew of different types can enter the cabin for use, and universal guarantee of multiple types of aircrafts is achieved.

The application discloses an online configuration system and method for landing gear control redundancy, wherein a comprehensive control system publishes a redundancy scheme according to system working states and application scene requirements; a redundancy monitoring module analyzes redundancy configuration and scheduling strategy information according to the received redundancy scheme, realizes online redundancy configuration and recombination of a control module, carries out redundancy management on the control module according to the redundancy strategy, monitors the health state of the control module and reports the comprehensive control system, and outputs an effective driving signal to an element driving module; a landing gear control signal is provided for the control module by a landing gear control device; and the control module outputs a driving signal to the element driving module after logical calculation according to the received landing gear control signal. The application realizes online on-demand configuration of control redundancy and dynamic management of redundancy scheduling strategy.

The invention provides a trailing edge variable camber airfoil composed of a bistable composite material structure and a design and control method of the trailing edge variable camber airfoil, and relates to the technical field of aircraft design and aerodynamics. Wherein the trailing edge variable camber airfoil sequentially comprises a leading edge section, an airfoil middle section and a trailing edge section in the chordwise direction, a front beam is arranged between the leading edge section and the airfoil middle section, the trailing edge section is fixed to an airfoil rear beam, and the trailing edge section is a core function section and is formed by arranging multiple layers of glass / carbon hybrid bistable composite material structures from top to bottom in the wingspan direction; each glass / carbon hybrid bistable composite material structure has a first stable state and a second stable state which correspond to a first flight state and a second flight state of the airfoil profile respectively, one end of each glass / carbon hybrid bistable composite material structure is fixedly connected to the airfoil profile rear beam, and the other end of each glass / carbon hybrid bistable composite material structure is fixed into a whole through glue joint. According to the invention, the steady-state characteristic of the bistable composite material is utilized, so that non-driven conversion between two stable bending states is realized.

The invention discloses a complex sea condition take-off and landing interaction platform based on a virtual reality technology and a design method. The complex sea condition take-off and landing interaction platform comprises a virtual take-off and landing simulation platform software module and a virtual take-off and landing hardware system. The virtual take-off and landing simulation platform software module is used for providing environment configuration, task scenario and simulation test functions; and the virtual take-off and landing hardware system is used for receiving driving operation input of a user and feeding back a virtual reality visualization effect and six-degree-of-freedom motion of the cabin. According to the invention, on the basis of complex sea condition take-off and landing motion safety evaluation requirements of the amphibious aircraft, simulation verification of a whole process of task scenario setting-human-in-the-loop simulation verification-execution condition evaluation can be realized through software module and hardware system design, and a coupling task efficiency result of unit operation and a design scheme is evaluated; and the complex sea condition take-off and landing adaptability design scheme iteration of the amphibious aircraft is supported.

The invention relates to an electrical energy receiving element (202) configured to receive electrical energy in the form of a magnetic field from an electrical energy emitting element, comprising a coil (208), a ferromagnetic element (210) and spacing means (230) for said coil (208) and said ferromagnetic element (210) made of electrically non-conductive and non-magnetic material and configured to maintain a predefined spacing between said coil (208) and said ferromagnetic element (210).These spacing methods allow the magnetic flux received by the coil to be constrained by the ferromagnetic element, thereby reducing the number of ferrite units constituting the ferromagnetic element and thus lightening the electrical energy receiving element. Figure 3.

The utility model discloses a transverse moving device which comprises two C-shaped frames, a lead screw rectangular pipe is arranged between the two C-shaped frames, universal wheels are arranged at the two ends of the lower walls of the two C-shaped frames, a supporting mechanism is arranged between the two C-shaped frames and the ground, and two force arm rods are symmetrically and movably arranged on the side wall of one side of the lead screw rectangular pipe. A hydraulic cylinder and an enclasping limiting piece are connected between the two force arm rods, round pipes are rotationally arranged on the side walls of the two force arm rods correspondingly, the other ends of the two round pipes are connected with an airplane wheel limiting plate, and two first rollers and two second rollers are rotationally arranged between the force arm rod and the airplane wheel limiting plate which are located on the same side correspondingly. And a manual pump is mounted on the side wall of the other side of the screw rod rectangular pipe, and the manual pump and the hydraulic cylinder are arranged in a matched mode. The utility model relates to the technical field of transverse movement of unmanned aerial vehicles. According to the transverse moving equipment, the hydraulic rods in the hydraulic cylinders contract to drive the airplane wheel limiting plates to be lifted through oil return of the manual pumps, and stable holding and lifting of the unmanned airplane wheels are achieved.

An aircraft dolly includes a plate having opposing mirror-imaged longitudinal sides. Each side includes a continuous first portion and a second portion of spaced-apart fingers contiguous with the first portion. A support disposed at each side of the plate includes a tube of triangular cross-section. The tube has a first leg, a second leg inboard of the first leg and coupled thereto, and a third leg consisting of the first portion of the plate extending between the first and second legs. Each support also includes a horizontal member coupled to the tube and extending over the plate's fingers, and a set of bracing members coupled to the fingers and the horizontal member. Casters are coupled to each horizontal member with each caster disposed between two adjacent fingers. One caster at each side is spring-biased away from its horizontal member. A ramp engages the plate and a ground surface.