23 results about "Deicing fluid" patented technology

The invention relates to the technical field of wind turbine generator maintenance, and discloses a wind turbine generator blade unmanned aerial vehicle deicing assembly and method.The wind turbine generator blade unmanned aerial vehicle deicing assembly comprises an unmanned aerial vehicle, and a laser radar and an installation shell integrating an ultrasonic transducer, a pulse nozzle and a hydraulic pump are installed at the bottom of the unmanned aerial vehicle. The deicing control system obtains focus space coordinates and interface resonance frequency of the blade surface by using a space state sensing module; the stress field focusing module calculates the phase delay amount of the ultrasonic transducer, compensates the pose deviation of the unmanned aerial vehicle by adjusting the emission time sequence, and drives the ultrasonic transducer to generate resonance stress on an ice layer-skin interface; and the sound stream synchronous control module determines a jet flow triggering moment according to synchronous phase locking solution, drives a pulse nozzle at an instantaneous negative pressure phase point of a sound wave period to inject a small amount of deicing fluid into an interface crack, and generates shear stress to induce the interface crack to expand and peel off an ice layer. Accurate throwing of deicing energy is achieved, and the icebreaking efficiency is improved on the premise that the safety of the blade structure is guaranteed.

An electrically operated aircraft deicing vehicle includes a chassis having longitudinally extending beams. The chassis supports a rechargeable battery system including one or more battery modules and a charging unit, front and rear axles, a positioning system for a fluid spraying system and a fluid tank system containing deicing fluid. An electric drive motor is operably coupled to the battery system. The electric drive motor is positioned aft of the front axle and between the longitudinally extending beams of the chassis. The electric drive motor is operable to rotate the front wheels. A hydraulic pump system is powered by the battery system. The hydraulic pump system is operably coupled to the positioning system enabling movement of the fluid spraying system. A heat transfer unit is positioned forward of and is operably coupled to the battery system for thermally conditioning the battery system.

The invention discloses a remote control type electric wire deicing unmanned aerial vehicle. The unmanned aerial vehicle comprises a deicing module, a moving module, an anti-freezing module and a flying module. Wherein the deicing module is used for removing ice on the surface of a wire; the moving module is used for realizing on-line and on-line walking of the whole rack and off-line work after deicing is finished; the anti-freezing module is used for realizing protection work after deicing and spraying an anti-freezing solution to prevent the electric wire from being coated with ice again; and the flight module is used for realizing flight and landing of the whole machine. According to the unmanned aerial vehicle, the technologies of roller ice grinding, triangular anti-falling, anti-freezing spraying and wing opening and closing are creatively adopted, the design of the unmanned aerial vehicle for deicing the high-voltage line is achieved, the manpower and time cost for deicing is saved, the deicing speed and efficiency of the high-voltage line are improved, the deicing coverage is expanded, and the potential safety hazard of manual deicing is reduced.

The invention provides an airport pavement freeze-thaw damage simulation test system in a complex service environment, which comprises a test cabin, a temperature control system, a loading system, a spraying system, a scanning system and a control system, and is characterized in that the temperature control system is arranged on the inner top wall and the inner side wall of the test cabin and is used for simulating sunlight and a temperature gradient which is gradually reduced from top to bottom; the loading system is arranged in the test cabin and used for loading loads to the test piece and the reduced-scale road surface, the spraying system is arranged at the top of the test cabin and used for simulating damage of moisture and deicing fluid to the test piece and the reduced-scale road surface, the scanning system is arranged at the top of the test cabin and used for scanning morphology characteristics of the test piece and the reduced-scale road surface, and the control system is arranged outside the test cabin and used for controlling the test piece and the reduced-scale road surface. And the controller is in communication connection with the temperature control system, the loading system, the spraying system and the scanning system. According to the invention, the temperature, humidity, deicing fluid and mechanical load of an actual environment can be comprehensively simulated, comprehensive data support in a test process is provided, and the accuracy of material performance evaluation is improved.

The application discloses a super-long chain (carbon atom number in a hydrophobic tail chain is greater than or equal to 18) polyoxyethylene ether surfactant thickened aircraft deicing and anti-icing liquid and a preparation method. The super-long chain polyoxyethylene ether surfactant thickened aircraft deicing and anti-icing liquid comprises the following components and mass percentages: alcohol 40-69%, deionized water 30-59%, and surfactant 0.2-2.0%, wherein the surfactant is a polyoxyethylene monomethyl ether ester of docosanoic acid (C 22 -350) with the following structural formula: The application obtains a deicing and anti-icing liquid which is good in deicing and anti-icing performance and relatively environment-friendly, solves the problems that a polymer-based deicing and anti-icing liquid is easy to be rehydrated to form a hydrated gel on the surface of an aircraft and that a surfactant itself or other additives cause corrosion on the surface of the aircraft under the premise of ensuring the deicing and anti-icing effect.

The invention relates to a fuel cell fixed power generation cooling system and method and a power generation system. The fuel cell fixed power generation cooling system comprises an expansion water tank, the expansion water tank is connected with a cooling assembly, the expansion water tank is connected with a liquid supplementing pipeline, and the cooling assembly is connected with a liquid discharging pipeline; the inlet end of the liquid supplementing pipeline is connected with the outlet end of the liquid discharging pipeline and then connected with the deionized water pipeline and the anti-freezing liquid pipeline which are arranged in parallel, a first water pump and a first switch valve are arranged on the liquid supplementing pipeline, a second water pump and a second switch valve are arranged on the liquid discharging pipeline, and the deionized water pipeline is provided with a third switch valve and connected to the deionized water tank. The inlet of the deionized water tank is used for being connected with a tail exhaust pipeline of the power generation system, the anti-freezing liquid pipeline is provided with a fourth switch valve and connected to the anti-freezing liquid tank, the cooling system does not need manual operation, and the labor cost is saved.

The utility model belongs to the field of airport airplane deicing, and particularly relates to an automatic deicing fluid detection device which comprises a sample collection device, a detection device, a control device, a recovery device and a chassis device. The detection device is used for detecting liquid refractive index and particle data in liquid; the control device is used for controlling the work of each component in the detection device; the recovery device is used for storing and emptying waste liquid; the chassis device is used for integrally bearing the device and carrying out traction and fixation; the collection device is connected with the detection device, a control device is arranged in the detection device, and the detection device is connected with the recovery device. The device is installed at a fixed point of a liquid adding station, automatically identifies information of a deicing vehicle, and is used for collecting a deicing liquid sample, automatically detecting, displaying a detection result, judging liquid applicability and storing the detection result. The sampling detection efficiency of the deicing liquid spray gun opening in the deicing vehicle is improved, and a plurality of steps of the whole detection process are optimized to be completed in one station.

The invention provides a method for recovering performance of a fuel cell stack polluted by an anti-freezing solution, and belongs to the technical field of fuel cells. The performance recovery method comprises the following steps: (1) nitrogen is introduced into a cathode and an anode of a galvanic pile, and the relative humidity of the nitrogen is 50-80%; (2) hydrogen is introduced into the anode of the galvanic pile, no gas is introduced into the cathode of the galvanic pile, and the relative humidity of the hydrogen is 80-100%; (3) closing an outlet valve and an inlet valve of the anode, wherein the cathode is not ventilated; (4) cooperatively controlling the stack temperature, the cathode and anode gas flow, the gas inlet temperature and the relative humidity, and carrying the stack to 0.2-0.5 A / cm < 2 > for a period of time, so that a cathode oxygen-deficient and even hydrogen-rich environment is formed in the whole process; and (5) normally pulling and loading the electric pile to 2-2.5 A / cm < 2 > to complete the recovery process. According to the method disclosed by the invention, the cooling liquid on the membrane electrode can be efficiently and quickly removed, and the performance of the membrane electrode can be recovered to the performance before pollution.

The heater comprises a shell, a combustor, an inner partition plate, a coil pipe set, a heat conduction column, a pipe spacer, a filter screen body and an elastic quick release mechanism, the shell is provided with a cavity, a connector, a liquid inlet, a first liquid outlet and a flue opening, the combustor is installed on the connector, the inner partition plate is connected into the cavity and forms a liquid inlet cavity, the liquid inlet is communicated with the liquid inlet cavity, and the coil pipe set is connected with the heat conduction column. The coil pipe set comprises coil pipes arranged in the cavity in a surrounding mode, the liquid inlet cavity is communicated with the first liquid outlet through the coil pipe set, one end of the heat conduction column is arranged in the liquid inlet cavity, the other end of the heat conduction column is arranged in the cavity, the pipe spacer is connected between the coil pipes, the filter screen body covers the flue opening, and the elastic quick release mechanism is arranged between the filter screen body and the flue opening. The cavity is heated through the combustor, heating of liquid in the coil pipe set and the liquid inlet cavity is achieved, the heating efficiency of the liquid in the liquid inlet cavity can be improved through the heat conduction column, and the heated deicing liquid is discharged into the deicing vehicle through the first liquid discharging opening so that the deicing vehicle can conduct deicing operation on an airplane.

A method for applying a fluid, such as deicing fluid, to a surface of an airplane. A vehicle loaded with a fluid has a nozzle for spraying said fluid onto said surface and at least one sensor and a processing unit is provided for determining a 3D representation of the surface onto which fluid is to be added. The 3D representation is used to determine boundary conditions for a path along which the nozzle is moved relative to the surface and the fluid is being dispensed onto the surface as said nozzle is being moved along the path.

The invention relates to the field of power transmission line deicing. The invention relates to an unmanned aerial vehicle, in particular to an engine water cooling system control method and device and a power transmission line deicing unmanned aerial vehicle. According to the engine water cooling system control method and device and the power transmission line deicing unmanned aerial vehicle, when the power transmission line deicing unmanned aerial vehicle works, deicing liquid is heated through the engine water cooling system of the oil-driven unmanned aerial vehicle, and the rotating speeds of a cooling fan and a circulating water pump of the engine water cooling system are adjusted in real time; and the temperature of the deicing liquid sprayed by the deicing liquid spraying system is adjusted, so that the deicing liquid is kept at the optimal temperature, and ice coated on the surface of the power transmission line is effectively removed.

The invention provides an integrated deicing device and method for a high-voltage line. The device is integrally formed by a folding unmanned aerial vehicle and an intelligent deicing device. The deicer adopts a multi-module cooperative deicing mechanism, efficient ice breaking is achieved through clamping and rolling of a mechanical claw, rolling of a fixed wheel and milling of a deicing cutter, and an anti-freezing solution spraying module is integrated to restrain secondary icing. A full-variable-diameter design based on an iris mechanism, double rockers and a five-connecting-rod mechanism is adopted to adapt to different wire diameters; the unmanned aerial vehicle can be folded mainly through gear transmission, and light weight of the whole machine is achieved through structural optimization and topological optimization by using eight symmetrical wings. The device is mainly used for deicing and anti-icing operation of the high-voltage transmission line, and has the characteristics of high deicing efficiency, strong obstacle crossing capability, safety and reliability; meanwhile, air transportation, inspection and obstacle crossing transfer of the device are achieved through the integrated unmanned aerial vehicle, manual pole tower climbing or high-altitude operation is not needed, and the safety risks of high-altitude falling and electric shock in a traditional manual ice knocking method are thoroughly avoided.

The utility model discloses a deicing fluid collecting and processing system for a deicing apron, which belongs to the technical field of airport ground cleaning and comprises intercepting screens and a collecting pool, the intercepting screens are arranged on the deicing apron with a certain gradient, and the intercepting screens comprise a plurality of longitudinal intercepting screens and a plurality of transverse intercepting screens which are arranged in a line. Wherein the longitudinal intercepting screens are located at the bottom of a transverse slope of the deicing apron, the transverse intercepting screens are located at the bottom of a longitudinal slope of the deicing apron, a gap is formed in the included angle between each longitudinal intercepting screen and the corresponding transverse intercepting screen, the collecting pool is located in the gap, and each intercepting screen comprises two stainless steel plates; the two stainless steel plates are rotationally connected through a stainless steel connecting piece, one stainless steel plate is fixed to the surface of the deicing apron through a fixing piece, and the back face of each stainless steel plate is covered with a layer of polyvinyl chloride isolation cloth. Waste liquid is collected in an intercepting and guiding mode, arrangement of a ditch body is avoided, a foldable mode is adopted, and use in spring, summer and autumn is facilitated.

The utility model discloses a portable anti -icing fluid tester, including casing, gasbag, several different buoyancy ball of density, the cavity of accommodating anti -icing fluid, inlet and outlet liquid passage, gasbag opening are equipped in casing, wherein inlet and outlet liquid passage, gasbag opening all are linked to the inside of cavity, several different buoyancy ball of density all set up in the cavity, and one end of gasbag is installed on gasbag opening.

The application belongs to the technical field of aircraft deicing parameter control and processing, and discloses a kind of aircraft secondary icing time margin control method, system and computer equipment.The method is by collecting meteorological parameters and aircraft primary deicing parameters, testing aircraft surface roughness related data, computer body surface residual deicing fluid concentration;Calculate the critical radius of ice nucleus and the free energy of ice phase interface in the initial stage of the body surface icing with deicing fluid residue;Calculate the wall ice nucleus nucleation rate and ice nucleus growth rate;Calculate the ice crystal coverage rate in the near-wall space of the body surface and the secondary icing time margin.The control method has the characteristics of low cost, easy implementation, strong anti-interference ability, etc., can predict the secondary icing time margin and icing time point of the whole aircraft, provide scientific and accurate reference for dispatching command department, and effectively improve the flight take-off and landing efficiency.

The invention discloses an active wing deicing system based on a metal nanowire heating film. The active wing deicing system comprises a dynamic temperature control module and a collaborative anti-icing assembly. The dynamic temperature control module comprises a control unit, a partition temperature control circuit and a meteorological data linkage interface, and is used for receiving multi-sensor data and generating a control instruction to realize partition power adjustment of the flexible metal nanowire heating film; the cooperative anti-icing assembly comprises an Ag / Au core-shell nanowire heating film sprayed on the surface of the wing, a fluorinated nano coating, a pneumatic deicing belt and an anti-freezing solution circulating system, and efficient deicing is achieved through cooperation of multiple technologies. Through sensor miniaturization, intelligent cooperative anti-icing and self-maintenance design, the bottlenecks in the aspects of detection precision, flight safety and operation and maintenance cost in the prior art are solved, high efficiency, intelligence and sustainability of unmanned aerial vehicle precipitation enhancement operation are finally achieved, and technical support is provided for water resource management in arid regions.

The invention relates to the technical field of overhead ground wire anti-freezing solution spraying, in particular to a nozzle spraying speed control method based on a spraying mechanism nozzle adjusting principle. The device comprises a rotating ring arranged adjacent to the tail end of the ground wire deicing device, a ring body of the rotating ring is provided with a notch for a ground wire to pass through, and the inner side of the rotating ring is provided with a nozzle for spraying an anti-freezing solution; the three rotating rings are coaxially distributed with the ground wire and sequentially arranged in the length direction of the ground wire, each rotating ring is driven by a rotating driving mechanism and can independently rotate around the axis of the ground wire to be adjusted so as to adjust the relative position, located on the periphery of the ground wire, of the spray head, and in the state that the notches of the three rotating rings are aligned, the spray head can rotate around the axis of the ground wire. And the three nozzles are circumferentially and uniformly distributed around the axis of the ground wire. According to the anti-freezing device, the anti-freezing solution can be uniformly sprayed on the overhead ground wire, so that the waste of the anti-freezing solution is greatly reduced, and a good anti-freezing effect on the ground wire is ensured.

1. Name of the design product: Deicing liquid automatic detection device. 2. Use of the design product: The design product is used for deicing liquid sample collection, autonomous detection, display of detection results, judgment of liquid applicability and storage of detection results. 3. Design points of the design product: in shape. 4. Pictures or photos best indicating the design points: perspective view.

An electrically operated aircraft deicing vehicle includes a chassis having longitudinally extending beams. The chassis supports a rechargeable battery system including one or more battery modules and a charging unit, front and rear axles, a positioning system for a fluid spraying system and a fluid tank system containing deicing fluid. An electric drive motor is operably coupled to the battery system. The electric drive motor is positioned aft of the front axle and between the longitudinally extending beams of the chassis. The electric drive motor is operable to rotate the front wheels. A hydraulic pump system is powered by the battery system. The hydraulic pump system is operably coupled to the positioning system enabling movement of the fluid spraying system. A heat transfer unit is positioned forward of and is operably coupled to the battery system for thermally conditioning the battery system.

The present application belongs to the technical field of aircraft automatic deicing, and discloses a kind of aircraft deicing fluid spraying trajectory planning and control method, system and equipment.The method includes: host computer uses gradient calculation method and double threshold detection method to extract the target profile in the depth image;Three-dimensional space coordinate system is constructed, and the depth feature of preselected deicing area is preselected, and the position coordinates of the preselected deicing area are obtained based on the depth feature;Drive the spraying device to move to the initial center position of preselected deicing area, and the host computer further adjusts the deicing fluid spraying angle and spraying flow of the spray head through closed-loop control;Real-time path planning is carried out by the depth image obtained by dTOF sensor, and the position coordinates of the next preselected deicing area are determined until the deicing is completed.The present application utilizes the characteristics of high imaging frame rate and strong integration of dTOF depth perception technology, establishes a closed-loop feedback channel for deicing fluid spraying angle and flow control, and realizes accurate control of deicing fluid landing point.

The present application belongs to the technical field of aircraft ground deicing, and discloses a method and system for collaborative optimization of aircraft ground deicing configuration parameters, and a computer device. The method comprises: obtaining a correlation topology result of the aircraft ground deicing configuration parameters by analyzing the distribution fitting law of multi-scale correlation coupling of the aircraft ground deicing configuration parameters and the quantitative deicing efficiency relationship, and constructing a correlation coupling graph model of the deicing configuration parameters based on the result; establishing a collaborative optimization model of the deicing configuration parameters with the objectives of maximum safety margin of the retention time, shortest deicing time, most balanced configuration parameters, and least deicing fluid consumption; simplifying the complex constraints of the deicing configuration parameters, and solving the collaborative optimization model of the deicing configuration parameters after relaxation. The average absolute error between the measured result and the calculated value meets the airport operation requirements, and the collaborative optimization and solving method of the deicing configuration parameters reduces the deicing fluid consumption on the basis of ensuring absolute safety and efficient operation in combination with the actual deicing configuration parameters of the airport.

The invention discloses an intelligent monitoring and active anti-corrosion method and system for residual de-icing and anti-icing fluid on airport pavements, and relates to the technical field of airport pavement maintenance, and the method comprises the steps: obtaining first monitoring data and second monitoring data of a plurality of airport pavements in a target airport; judging whether the feature data of the corrosive medium of the airport pavement is abnormal data, if the judgment result is yes, calculating a dynamic risk value of the airport pavement according to the first monitoring data and the second monitoring data, comparing the dynamic risk value with a preset threshold value, and determining a risk level of the airport pavement according to a comparison result; determining a pavement maintenance decision of each airport pavement in the target airport according to the risk assessment level; according to the method, rapid identification and response of deicing liquid residues in a high-risk area can be realized, the residence time of high-concentration corrosive liquid is greatly shortened, and the chemical erosion process of a concrete surface layer is effectively inhibited.

The application discloses a circulating recovery system for aircraft deicing fluid, which comprises a collecting unit, a conveying unit, a solid-liquid separation unit and a recovery unit. The collecting unit is used for collecting the solid-liquid mixture containing the deicing fluid after deicing of an aircraft; the conveying unit is used for conveying the solid-liquid mixture of the collecting unit; the solid-liquid separation unit receives the solid-liquid mixture of the conveying unit and carries out solid-liquid separation to obtain a solid mixture and a liquid mixture containing the deicing fluid; and the recovery unit recovers the liquid mixture containing the deicing fluid separated by the solid-liquid separation unit. The solid-liquid separation unit of the application flexibly controls the overturning degree of the switch partition plate by the rising and falling of the floating plate, thereby controlling the opening and closing of the feeding port, so that the supporting separation rod is cyclically and staggeredly moved at the separation hole of the flow guide separation cover plate, and then the solid mixture on the flow guide separation cover plate can be separated to the separation cavity.