75 results about "Ground support equipment" patented technology

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

The invention discloses an automatic sealing detection and drainage device and method for an integrated pressure refueling connector, and belongs to the technical field of aviation ground support equipment. According to the device, a detection and drainage function module is highly integrated in a pressure refueling joint body, and the device mainly comprises an overturning covering and sealing module, an embedded detection and gas circuit module and a control and logic module; the core of the device is that a detection cover which can be movably overturned automatically covers the end part of the joint before refueling to form a closed detection cavity, then inflation and pressure maintaining are carried out through a built-in micro gas circuit, the sealing performance is automatically judged according to pressure attenuation or flow change, and the interior of the joint is purged and drained by utilizing detected gas pressure. According to the invention, rapid and automatic self-examination and maintenance of the pressure refueling joint before use are realized, operation with diseases is fundamentally avoided, the safety and reliability of aviation fuel refueling operation are remarkably improved, and meanwhile, digital management of the equipment state is realized.

A system for coordinating aircraft servicing tasks of a plurality of ground support equipment at an airport includes a plurality of beacons and one or more processing circuits. The plurality of beacons are configured to couple to the plurality of ground support equipment. The one or more processing circuits include one or more processors storing instructions thereon that, when executed by the one or more processors, cause the one or more processing circuits to acquire signals from the plurality of beacons and coordinate movement of the plurality of ground support equipment based on the signals and in accordance with an aircraft servicing plan.

The utility model discloses ground service equipment of an electric vehicle, and relates to the technical field of ground service support. The electric vehicle ground service equipment comprises a movable carrier; the electric energy driving module is arranged on the movable carrier and used for driving the movable carrier to move; the external charging module is arranged on the movable carrier, and the external charging module is used for charging a battery pack of the electric vehicle; and the energy storage batteries are detachably arranged on the movable carrier, the energy storage batteries are electrically connected with the electric energy driving module and the external charging module respectively, and the specifications of the energy storage batteries are consistent with those of the battery pack. According to the utility model, the guarantee capability of the ground service equipment is improved, and the guarantee cost of the electric vehicle is reduced.

The invention discloses a safety detection device and method for an air supply pipe of an airplane ground air conditioner, and belongs to the technical field of safety control of airplane ground support equipment, and the safety detection device comprises a touch screen all-in-one machine (HMI), an aviation plug sensor, a programmable logic controller (PLC), an overrun switch and a sound-light alarm unit. The aviation plug sensor is used for collecting a state signal of whether the air valve is mechanically inserted and locked in place in real time; the PLC receives and processes the input signal, executes a preset safety interlocking logic program and outputs a control instruction to the chassis running driving circuit; the touch screen all-in-one machine provides all-parameter state display, historical fault recording, system setting and man-machine interaction functions; the overrunning switch serves as a hardware emergency bypass and provides emergency evacuation authorization with the highest priority when the interlocking system breaks down. Through a software and hardware dual interlocking mechanism, accurate and reliable detection and forced interlocking of the air valve connection state are achieved, and the safety and the automation level of operation of an aircraft ground air conditioning system are greatly improved.

The invention discloses an unmanned aerial vehicle take-off and landing platform control method and system based on multi-motor self-leveling and radar state perception, and relates to the technical field of automatic control of unmanned aerial vehicle ground support equipment. The defect that an existing platform is insufficient in leveling precision is effectively overcome, the horizontal stability of the platform under the complex terrain is guaranteed, meanwhile, due to introduction of the millimeter-wave radar, real-time detection of the vertical distance and the radial speed of the unmanned aerial vehicle and dynamic evaluation of the working state are achieved, the defect that the existing platform lacks real-time sensing of the state of the unmanned aerial vehicle is overcome, and the working efficiency is improved. The display and voice module performs warning operation according to the working state, so that the state information of approaching, taking-off and landing and the like of the unmanned aerial vehicle can be timely transmitted to surrounding personnel in a working area with dense personnel, and the hidden danger that an existing platform cannot timely perform safety warning is thoroughly solved; and the take-off and landing safety and the operation normalization of the unmanned aerial vehicle in a complex operation scene are further improved.

A fuel line terminating in a refuel connector is used to fuel or defuel an aircraft, for example with liquid hydrogen. A supply of nitrogen housed on an aircraft, for example a Nitrogen Generating System, is used in conjunction with a gas line to supply nitrogen into the fuel line, to flush out potentially combustible materials before liquid hydrogen is supplied through the fuel line. The aircraft supply of nitrogen is also used to supply inert gas, via a gas line, to the Ground Support Equipment refuelling or defuelling the aircraft. This can provide redundancy for the Ground Support Equipment's systems, and may allow the aircraft to operate at less well-equipped airports.

A portable sediment discharge ground supporting device is suitable for carrying out sediment discharge maintenance operation on an auxiliary fuel tank of an airplane and comprises a rod-shaped ejector rod, a plurality of supporting rods and a plurality of supporting rods, the shape of the cross section of the ejector rod is matched with the shape of a sediment discharge valve of the auxiliary fuel tank, and the supporting rods are arranged on the supporting rods. A space for accommodating fuel oil deposits is formed in the oil collecting part; the auxiliary fuel tank is provided with an oil collecting part and an oil collecting part, the flow guiding part is formed into a long and thin pipeline, one end of the flow guiding part is connected to the oil collecting part in a fluid communication mode, and the clamping part is connected with the auxiliary fuel tank in a mechanical matching mode. By means of the portable sediment discharging ground supporting equipment, a ground operator can complete auxiliary sediment discharging maintenance operation of the fuel tank under the condition that long-term handheld operation is not needed, and therefore the operation efficiency can be effectively improved.

An apparatus for supplying gas from an aircraft (100, figure 1) to ground equipment (110) comprising a gas supply 318 housed within an aircraft, and at least one gas line 322 in communication between the aircraft gas supply and the ground equipment. The gas used may in this instance comprise liquid hydrogen. A supply of nitrogen 318 housed on an aircraft, for example a Nitrogen Generating System, is used in conjunction with a gas line 322 to supply nitrogen into the fuel line 316, to flush out potentially combustible materials before liquid hydrogen is supplied through the fuel line 316. The aircraft supply of nitrogen 318 is also used to supply inert gas, via a gas line 334, to the Ground Support Equipment (110, figure 1) refuelling or defueling the aircraft 100. This can provide redundancy for the Ground Support Equipment’s systems, and may allow the aircraft (100) to operate at less well-equipped airports. The application comprises a plurality of apparatus and methods relatable to hydrogen / cryogenic refuelling.

The application discloses an airplane ground air conditioner energy-saving control method combining environmental parameter prediction, and relates to the technical field of airplane ground support equipment. The method comprises the following steps: collecting airport environmental parameters in real time, training a machine learning prediction model in combination with historical data, and predicting environmental change trends in advance; analyzing the thermal characteristics of an airplane according to the characteristics of the airplane, performing landing time error compensation, and accurately obtaining an environmental parameter sequence of a landing period; calculating an environmental parameter and a cabin thermal characteristic deviation coefficient, and dynamically configuring temperature and energy-saving weights; and iteratively optimizing air conditioner control parameters by using a multi-objective optimization algorithm to obtain optimal air conditioner control parameters. The application realizes the transformation from passive control to active prediction, effectively solves the problems of control lag and high energy consumption in the prior art, significantly reduces energy consumption while ensuring comfort, and improves the intelligent level and operation efficiency of an airplane ground air conditioner system.

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

The utility model relates to the technical field of aviation ground support equipment, in particular to an integrated seat for a ferry vehicle, which comprises a seat body and a cushion, the cushion comprises a backrest part and a seat body part which are matched with the seat body, the upper end of the backrest part is fixed with a vertical insertion plate, an elastic connecting component is fixed below the seat body part, and the elastic connecting component is fixed below the seat body part. The surface of the seat body is provided with a main insertion opening used for allowing the vertical insertion plate to be inserted in a matched mode and a groove used for installing an elastic connecting assembly, and two oppositely-arranged positioning holes are formed in the groove in the width direction of the seat body. The elastic connecting assembly is provided with a positioning part matched with the positioning hole and a driving part for driving the positioning part to move in the direction far away from / close to the positioning hole under the action of external force, and the front end of the seat body is provided with a dismounting channel connected with the groove; the integrated seat for the ferry vehicle is provided with the cushion which can be conveniently detached, and the integral appearance is ensured to be attractive.

Airport ground support equipment includes: a support equipment body configured to come close to a stopped aircraft from a standby position and enable a person and / or an article to move between the support equipment body and the aircraft; an aircraft type determiner 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 camera that is mounted to the support equipment body and 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 that detects a stop position of the nose gear based on the image captured by the camera and calculates a discrepancy from a regular stop position that is set in advance corresponding to the determined aircraft type.

This invention provides an automatic cleaning method and system for the hangar door side of polar shipborne helicopters. This invention belongs to the technical field of aviation ground support equipment and ship auxiliary machinery. The cleaning method includes: acquiring helicopter images, extracting key features of the fuselage, identifying the aircraft type and calculating the initial pose based on the PnP algorithm, and converting the preset cleaning path to the coordinate system of the cleaning device; generating a propeller cleaning sub-path, employing a master-slave control strategy to control two robotic arms to synchronously flush and clean the upper and lower surfaces of the propeller blades, and maintaining the balance of jet impact force through pressure closed-loop feedback; establishing a ship swaying dynamics model to estimate and predict the ship's motion state in real time, and combining the real-time feedback deviation vector obtained from laser ranging and visual acquisition to generate a corrected speed command; identifying the surface state category through temporal filtering and texture analysis, and adaptively adjusting according to the identification results.

The invention relates to the technical field of aerostat ground support equipment, and discloses a jacking type short-distance transfer system and method for a mooring aerostat. The system comprises a ground anchoring device and a self-propelled ground flat car, the bottom of the ground anchoring device is provided with a standard connector and a lifting supporting mechanism with high-strength lifting supporting capacity, and the self-propelled ground flat car is provided with a butt joint locking mechanism and a universal driving wheel set which are matched. The ground anchoring device and the self-propelled ground flat car are rigidly fixed through a standardized connector and a butt joint locking mechanism, and integrated short-distance transfer of the mooring aerostat in the mooring keeping state is achieved. The semi-hanging type mooring device solves the technical problems that a traditional semi-hanging type mooring device is low in transfer efficiency, poor in maneuverability, high in safety risk and the like, has the advantages of being short in preparation time, flexible, safe, reliable, high in universality and the like, and is suitable for short-distance transfer scenes of large captive balloons between different stations and boats in a field.

The invention discloses a double-lifting unmanned aerial vehicle intelligent automatic airport, and belongs to the technical field of unmanned aerial vehicle ground support equipment. The device comprises a navigation station frame assembly, a three-axis mechanical arm, a clamping mechanism, a double-lifting platform and a sliding cover. The navigation station frame assembly serves as a supporting carrier, and electric control, temperature control and safety guarantee units are integrated in the navigation station frame assembly. The three-axis manipulator achieves accurate grabbing and carrying of the unmanned aerial vehicle through cooperation of the X-axis module, the Y-axis module and the Z-axis module. The clamping mechanism performs multi-dimensional stable fixation on the unmanned aerial vehicle through combination of transverse and longitudinal push rod motors. The double-lifting platform comprises a main stand column and a lifting platform driven by the main stand column, a charging cabin in butt joint with the unmanned aerial vehicle is integrated on the lifting platform, and the lifting function and the charging function are integrated. Through cooperation of the structures, the problems that an existing automatic airport is poor in lifting adaptability, low in positioning precision, low in automation degree and the like are solved, full-process intelligent operation of the unmanned aerial vehicle is achieved, and the ground guarantee efficiency and reliability are remarkably improved.

The utility model relates to an aircraft landing gear brake cooling device, and relates to the field of aircraft ground support equipment. The device comprises a machine base, a centrifugal fan and a fan cover, the centrifugal fan and the fan cover are both installed on the machine base, the two ends of the fan cover are open, one end of the fan cover is connected with an air inlet of the centrifugal fan, and the other end of the fan cover is used for being connected with a hub. A plurality of servo cylinders arranged at equal intervals in the circumferential direction of the axis of the servo cylinders are arranged at the end, facing the hub, of the fan cover, push rods of the servo cylinders are connected with arc-shaped sealing strips, the sealing strips are elastic and can define an annular sealing part, and the inner contour of the sealing part is matched with the outer contour of the fan cover and the outer contour of the hub. Multiple airflows are used for heat dissipation, the brake cooling speed is increased, the brake cooling time is shortened, the brake cooling efficiency is improved, and the possibility of aircraft delay is reduced; and adsorption of carbon powder is realized through the air tap, so that a cleaning effect is achieved.

The invention specifically discloses an airport flight area pollution reduction and carbon reduction effect evaluation method based on operation optimization, and relates to the technical field of airport environment management. The method comprises the following steps: firstly, collecting operation data of an aircraft and ground support equipment, and constructing a high-precision carbon pollution emission calculation model in combination with emission factors; calculating the carbon pollution emission under the reference scene and the optimization strategy scene, and determining the carbon pollution emission reduction of different optimization strategies; then identifying the emission peak period and the hot spot area, matching the pollution source type and setting pollution source emission parameters; simulating and calculating the concentration contribution value variation of the pollutants by using an atmospheric diffusion model; and finally, comprehensively evaluating the pollution and carbon reduction effect of the operation optimization strategy in combination with the carbon pollution emission reduction amount and the concentration contribution value variation. According to the method, the problems of single evaluation dimension and insufficient precision in the prior art are solved, the pollution and carbon reduction effect of the airport flight area operation optimization strategy can be accurately quantified, and reliable support is provided for airport strategy optimization.

The present disclosure provides a ground support equipment for servicing an aircraft on the ground. The ground support equipment comprises a pre-conditioned air. PCA, unit configured to provide pre-conditioned air to an aircraft on the ground. The ground support equipment also comprises a ground power unit. GPU, configured to provide power to the aircraft on the ground. The ground support equipment also comprises an input stage connectable to a power source and configured to provide a DC voltage. The input stage is operatively connected to the PCA unit and the GPU, and the GPU comprises an inverter circuit for transforming the DC voltage to a pre-determined output AC voltage for powering the aircraft.

The invention discloses an aircraft ground air conditioner energy-saving control method combined with environmental parameter prediction, and relates to the technical field of aircraft ground support equipment. The method comprises the steps that airport environment parameters are collected in real time, a machine learning prediction model is trained in combination with historical data, and the environment change trend is predicted in advance; thermal characteristics are analyzed according to aircraft characteristics, landing time error compensation is carried out, and a landing time period environment parameter sequence is accurately obtained; dynamically configuring temperature and energy-saving weight by calculating an environment parameter and cabin thermal characteristic deviation coefficient; and a multi-objective optimization algorithm is adopted to carry out iterative optimization on the air conditioner control parameters, and the optimal air conditioner control parameters are obtained. According to the method, the conversion from passive control to active prediction is realized, the problems of control lag and high energy consumption in the prior art are effectively solved, the energy consumption is remarkably reduced while the comfort is guaranteed, and the intelligent level and the operation efficiency of an aircraft ground air conditioning system are improved.

The invention relates to a bidirectional carrier rocket launching and recycling device based on ground-rocket magnetic field coupling, a launching method and a recycling method, and belongs to the field of aerospace ground support equipment. Comprising an integrated ring and an active magnetic energy base. The integrated ring is connected to the tail end of a rocket through a flange and comprises an aluminum silicon carbide structure base body, an aluminum-coated steel coil, a cooling channel and a crushable honeycomb module, and the periphery of the integrated ring is coated with a carbon fiber outer wrapping layer and a carbon / silicon carbide shielding layer. The top of the active magnetic energy base is provided with a Halbach magnet array and a driving coil, and the bottom is provided with a moving mechanism. During launching, the driving coil is electrified to generate a traveling wave magnetic field which acts with the integrated ring to generate electromagnetic repulsive force to boost takeoff; during recovery, the integrated ring cuts into a static magnetic field to generate eddy current damping deceleration, the cooling channel dissipates heat through phase change of a propellant, and the honeycomb module absorbs residual kinetic energy to achieve soft landing. Bidirectional energy reuse of launching boosting and damping recovery is achieved, and the rocket carrying efficiency and recovery reliability are remarkably improved.

The invention relates to a flight ground support data processing method and system and electronic equipment, and the method comprises the steps: obtaining the equipment real-time data of at least one piece of ground support equipment and the dynamic flight data of a plurality of flights; the equipment real-time data comprises operation state data, equipment service machine position number data and data acquisition time; the dynamic flight data comprises flight occupied stand number data; obtaining an airport pickup service state of the ground support equipment according to the real-time data of the equipment; performing real-time matching on the equipment real-time data and the dynamic flight data according to the airport pickup service state to obtain an airport pickup service record of the ground support equipment; the airport pickup service record comprises a corresponding relation among an equipment ID, a flight ID, an airport number, airport pickup service starting time and airport pickup service ending time; according to the method, real-time processing and real-time matching can be performed on the flight ground support data, accurate matching of the ground support equipment and the flights can be realized, and the airport operation efficiency is improved.

1. Name of the Design Product: Radar Scattering Characteristic Detection Equipment. 2. Use of the Design Product: It is used by grass-roots troops. By means of the cooperation of the walking and scanning components, it is used to measure and scan targets, and it is a ground support equipment for system function and partial performance inspection under the condition of using in an environment with uncontrolled conditions. 3. Design Key Points of the Design Product: Lies in the shape. 4. Picture or Photo that Best Illustrates the Design Key Points: Perspective View 1.

The invention discloses a communicable frequency converter which comprises a frequency converter body with an inner cavity of a hollow structure and a functional device arranged in the inner cavity of the frequency converter body, the functional device comprises an AC / DC module, a DC / AC module, a rectification module, a transformer assembly, a control unit and a filtering module, and the input end of the AC / DC module is connected with a three-phase AC power supply. The output end of the AC / DC module is connected with the DC / AC module; the device has the advantages of being small in size and light in weight, under the cooperation of the AC / DC module and the DC / AC module, three-phase 115V / 360Hz-720Hz three-phase four-wire alternating current generated by onboard equipment such as a generator can be converted into single-phase pure and stable 220V / 50Hz alternating current standard mains supply, high efficiency and output power are achieved, power can be directly supplied to ground standard equipment, and the device can be widely applied to the field of power supply. The power supply can be used as aviation ground support equipment, a green gallery bridge, airport field operation, airplane maintenance and test, and a vehicle-mounted mobile power supply.

The invention relates to the field of airport ground support equipment, in particular to a navigation-aid lamplight maintenance operation shelter which comprises a shelter body, a maintenance operation opening, a sealing device and an annular check curtain. The cabin body frame is manufactured by welding profile steel, and the wall plates are made of sandwich rock wool heat preservation plates and have good structural strength and heat insulation performance. The maintenance operation port is located at the bottom of the shelter, a metal frame of the sealing device and a bottom plate of the shelter body are welded into a whole, the sealing device is detachably connected into the maintenance operation port, and an access cover plate of the sealing device is a transparent endurance plate, so that the situation of an operation area is conveniently positioned and observed; the annular check curtain is folded and hung at the cabin bottom at ordinary times, is slightly larger than the maintenance window in size, and is manually released to be attached to and sealed with the road surface during use. The device is mainly applied to airport light maintenance operation in winter and extreme weather in northern cold areas.

The utility model discloses a kind of reflective cone windproof fixing devices, belong to airport ground support equipment technical field.It include trolley body, multiple reflective cone body and fixed component, multiple the reflective cone body is stacked and placed on the trolley body, the fixed component is installed on the trolley body.A kind of reflective cone windproof fixing device of the application, by the combination design of iron ring, iron chain and hook, reflective cone can be firmly fixed on trolley body, effectively prevent under adverse weather such as gale, typhoon, reflective cone is blown displacement, to avoid the security risk that reflective cone intrudes taxiway or runway etc., the device adopts trolley form, it is convenient for ground crew to move and deploy reflective cone quickly, compared with traditional manual recovery mode, greatly save manpower and time, improve operating efficiency.Under emergency weather warning condition, the recovery or deployment work of reflective cone can be quickly completed, meet the demand of airport rapid response.

The application relates to the technical field of ground support equipment of aviation equipment, and provides a remote-stand corridor, which comprises a telescopic canopy and at least two fixing frames, the at least two fixing frames are arranged along the telescopic direction of the telescopic canopy and are covered outside the telescopic canopy, the bottom of each fixing frame is provided with a roller, and at least part of the telescopic canopy can be accommodated in the at least two fixing frames and can be unfolded outward from the at least two fixing frames. The remote-stand corridor provided by the application has a relatively simple and light structure.

The invention discloses a satellite supporting and overturning device and a working method thereof, and belongs to the technical field of spacecraft ground supporting equipment. The device comprises a base, an overturning platform, a power mechanism and a control system. The base provides stable support and has a leveling function; the overturning platform is connected with the base through the rotating support set and used for bearing a satellite. The power mechanism is driven by an electric cylinder, provides overturning power and controls the speed and the angle. The core lies in that the control system adopts a closed-loop control scheme based on a PLC (Programmable Logic Controller), an angle sensor and a proximity switch, so that the overturning process can be accurately and automatically controlled, the running state is monitored in real time, data is fed back, faults are processed, and process load data is recorded; and the safety, the precision and the reliability of the satellite in the process of overturning from the vertical state to the horizontal state are ensured. The method is particularly suitable for the horizontal final assembly test work of the star cover assembly in a three-level test-launch mode.

1. The name of this design product: integrated radar scattering characteristics detector. 2. Purpose of the product with this design: It is a ground support equipment that scans the target equipment through a combination of a mobile mounting platform, instrument cabin, computing platform, positioning system, etc., and performs system function and partial performance inspections under conditions of use in uncontrolled environments. 3. The key point of the design of this product lies in its shape. 4. The picture or photo that best illustrates the design points: Stereoscopic drawing 1.

The utility model discloses a kind of special-shaped large piece supporting mechanisms, it is related to aviation ground support equipment technical field, comprising: base, thrust joint bearing, support assembly and buffer limiting mechanism, base is used to install in the chassis top surface of moving trolley;Thrust joint bearing's race is fixedly connected with the top surface of base;The bottom of support assembly is fixedly connected with the axle ring of thrust joint bearing, the top surface of support assembly is support surface, support surface is used to be set with the special-shaped large piece of needing moving;The bottom end of buffer limiting mechanism is fixedly connected with the top surface of base, the top end of buffer limiting mechanism is fixedly connected with the bottom surface of rotary support plate, buffer limiting mechanism contraction can buffer the impact force in the tilting process of support assembly, and buffer limiting mechanism contraction is to design position and can limit the inclination angle of support assembly, simple structure, convenient to use, effectively guarantee the operation safety in moving process, effectively guarantee equipment life.