112 results about "Ice detector" patented technology

An improved apparatus and a method of measuring and interpreting reliably, simply and accurately the information on continuous liquid level, liquid temperature and other liquid properties within a vessel. The apparatus could be made of a powered heater element and temperature sensors can be screen-printed, vacuum deposited, etched, welded, soldered or plated on one or both sides of a single rigid or a flexible substrate. The geometry of the heater determines the curve shape, such as steepness or shallowness of a temperature profile along a heater. Various parallel and serial configurations of thermocouples or temperature sensors can be used to measure the temperature along a heater. Simultaneous measurements from all the temperature sensors, before and after heat is applied, are used to generate accurate temperature profiles for the entire heater. Different features of the temperature profiles will determine accurately the liquid level, liquid temperature and other liquid properties. Apparatus of the invention may also be used to detect ice formation.

A method for aircraft surface contamination detection and measurement includes: mounting a laser probe on an airfoil; positioning the laser probe to emit laser energy at multiple pre-determined surface points along the leading edge of the airfoil; and using a processor device for activating the laser probe and obtaining measurement data for generating a surface contour of the shape and accurate measurement of the depth of airfoil icing in the surface target area. The icing data is presented to the pilot in a display that alerts him to the icing and accurately shows the depth and shape of the airfoil icing.

The invention discloses an ice preventing and removing device for helicopter rotors. The device comprises an icing detector, an icing speed solver, an atmospheric temperature sensor, an ice preventing and removing control panel, a digital type ice preventing and removing controller, a main rotor distributor, an empennage distributor, a main rotor ice removing component, an empennage ice removing component, an No.1 AC power supply and an No.2 AC power supply, wherein the icing detector and the icing speed solver transfer liquid water content signals and atmospheric temperature signals to the digital type ice preventing and removing controller respectively, the digital type ice preventing and removing controller carries out computation according to the ice preventing and removing control panel and the input signals to output the control signals of the main rotor distributor and the control signals of the empennage distributor, and the main rotor distributor and the empennage distributor control the main rotor ice removing component and the empennage ice removing component to remove ice. By the ice preventing and removing device, the helicopter can safely fly under server weather conditions, and the safety accidents due to the icing of the rotors and the bad influence of pneumatic configuration caused by too low ambient temperature or too high water content are avoided.

An ice detector for providing a signal indicating ice formation includes a longitudinally extending probe protruding into an airflow. One or more surface roughness features on surfaces of the probe improve ice detection. Surface roughness features on the probe include ice accreting edges at a distal end of the probe and features arranged on a side surface of the probe which cause the airflow to increase in turbulence.

Ice accretion on a probe is detected by determining the change of frequency of a vibrating type ice detector or sensor as ice starts to build up. The rate of change of frequency is determined and is combined with parameters including air velocity and air temperature for providing a signal that indicates liquid water content in the airflow as well as ice accretion on the ice detector.

The invention discloses an image icing detector, which comprises an image acquiring system (1-A) and an image processing system (2-A), wherein the image acquiring system (1-A) can be used for acquiring an image of an object surface; the image processing system (2-A) can be used for analyzing the image so as to acquire the icing condition of the object surface; and the image acquiring system (1-A) comprises an image transmitting optical fiber bundle (104). By the detector, application requirements under a special spatial requirement can be met without the miniaturization design of the image acquiring system (1-A).

The invention discloses an ice breaking and removing method based on plasma impact jet flow. In an easily-icing zone of an object with the ice removing demand, a plasma actuator and an icing detector are installed in the mode of being flush with the object plane of the easily-icing zone, wherein the plasma actuator and the icing detector are connected with a controller; when the icing detector detects that the object plane of the easily-icing zone ices, the controller controls the plasma actuator located in the easily-icing zone to work and controls the discharging power and frequency and the working time of the plasma actuator, and periodic high-temperature and high-dynamic-pressure jet flow generated by the plasma actuator is used for impacting an ice layer to make the ice layer rapidly vibrate, deform and break and even directly crushing and thawing the ice layer to achieve ice breaking. The plasma ice removing technology makes electric parameter control, light-and-small design and distributed layout easy, has the advantages of rapidness, high efficiency and low energy consumption and can be widely applied to ice breaking and removing for various air vehicles or other objects with the ice removing demand.

An ice detector for providing a signal indicating ice formation includes a probe protruding into an airflow. The probe extends into the airflow from a strut. The strut has one or more features which allow the probe to accrete ice at a higher temperature than would conventionally be possible. Strut features can include a notch formed therein in an upwind direction relative to the probe, and a curved surface adjacent a point of extension of the probe from the strut.

The invention relates to a freezing detector and belongs to the technical field of freezing detection. The freezing detector comprises a freezing component, at least one vision sensor and a controller, the freezing component comprises a freezing rod with an ice accretion surface and a support structure, and the freezing rod is constructed into a streamlined wing structure and extends into air current from the support structure; the vision sensor is arranged to be an image which can acquire the ice accretion surface; and the controller is electrically connected with the vision sensor and comprises an image comparison module for comparing the acquired image with an initial image so as to judge whether the ice accretion surface of the freezing rod is frozen. According to the freezing detector, moving components are absent, and the reliability of image based judgment is high; and simultaneously, by means of the streamlined wing structure of the freezing rod, the ice accretion surface is provided with small pressure coefficients and large water collection coefficients, the freezing rod can faster and earlier freeze, and time for giving freezing warning can be brought forward.

The invention relates to an image icing detector, which comprises an image acquisition system (1-A) and an image processing system (2-A). The image acquisition system (1-A) is used for obtaining an image of the surface of an object, and the image processing system (2-A) is used for analyzing the image to obtain information on icing of the surface of the object. The detector has a simple structureand high reliability, icing types can be effectively identified, the icing detection accuracy can be significantly improved, detection of the surface of the whole object can be realized, and information on icing of large supercooled water drops can also be detected.

The invention discloses a novel antifreezing and deicing device for a spillway gate. The device comprises a controller, an icing detector, immersible pumps, automatic check valves, connecting water pipes, a water spray pipe, buoyancy units and span wire fixing units. The icing detector is arranged on the surface of a snorkeling unit water area, and the immersible pumps are arranged under the water surface of the snorkeling unit water area. The immersible pumps and the icing detector are connected with the controller. The controller reads current state information. The connecting water pipes are connected between the immersible pumps and the water spray pipe and connect the immersible pumps and the water spray pipe. The water spray pipe adopts water extracted by the immersible pumps to stir a water body. The water spray pipe is connected with the buoyancy units, so that the water spray pipe floats on the water surface all the time along with variation of the water level. The water spray pipe and the buoyancy units are fixed in a set zone through the span wire fixing units.

The invention belongs to the field of aircrafts, and discloses an ice crystal detector probe and a complex icing condition detector. The ice crystal detector probe comprises a first section and a second section arranged in sequence from top to bottom; the first section and the second section are in smooth connection; the outer surface of the first section is in a shape suitable for separating liquid droplets from ice crystals in airflow and bearing impact of the ice crystals; a heating device and a plurality of fine particle impact sensors are installed inside the first section; and the second section is a heat insulation layer so as to avoid heat exchange between the first section and external probe installation equipment. The complex icing condition detector comprises the ice crystal detector probe and an icing detector probe. Liquid water in airflow does not generate obvious impact on the windward side of the probe, the ice crystals generate pulse impact on the windward side of the icing detector probe, and therefore the ice crystals and the liquid water droplets are distinguished and accurate detection of icing of the ice crystals can be achieved.

The invention relates to a novel integrated ice detector. A detection portion is mainly composed of a sensitive component and a resolving component. The resolving component provides a drive signal for the sensitive component. The sensitive component detects the thickness of an ice layer, converts the thickness into an electric signal and provides an ice component for the resolving component. Due to the integrated design, the size and weight of the detector are reduced, the adaptability of the detector for various types is improved; as for existing rapidly-developing unmanned aerial vehicles and helicopters, the integrated ice detector has the advantages of being small in size and low in weight and has the anti-electromagnetic interference capacity which a common ice detection device does not have.

The invention discloses a fan blade anti-icing and deicing system based on air heating. The system comprises a controller, heaters, vent pipes, ice detectors, a temperature and humidity sensor, electric turbochargers and a plurality of blade internal temperature sensors; the temperature and humidity sensor is connected to a fan hub; the ice detectors are connected to fan blades; each vent pipe is arranged on the inner sides of two blade internal supporting framework baffles; the heaters are arranged at the front ends of the vent pipes; the electric turbochargers are arranged at air inlets at the front ends of the heaters; the multiple blade internal temperature sensors are uniformly arranged on the fan blades; and the controller is electrically connected to the temperature and humidity sensor, the ice detectors, the heaters, the electric turbochargers and the blade internal temperature sensors. According to the fan blade anti-icing and deicing system, closed-loop linear control is carried out on the power of the heaters and the turbine rotating speed of the electric turbochargers, and therefore the energy consumption of the system can be reduced, the use cost can be lower, heating can be more uniform, anti-icing and deicing can be effectively realized, and the service life and the performance of the fan blades can be improved.

A system for detecting the presence of ice crystals in a cloud comprising two thin walled semicylinder-shaped sensors, one having a concave inner surface and oriented longitudinally in a leading edge of an airfoil and the other having a convex outer surface being oriented longitudinally in the leading edge of the airfoil so that cloud water flows towards and into contact with the convex outer surface; a temperature controlling arrangement for heating the two sensors and maintaining them at a substantially constant temperature; and a comparison arrangement for finding a difference between (i) a power to maintain the temperature of the first sensor at its substantially constant temperature (ii) a power to maintain the temperature of the second sensor at its substantially constant temperature; and comparing the difference of the powers to a threshold value for evidencing the presence or predetermined amount of ice in the cloud water.

The invention disclose a method for designing the configuration of a big supercooling water droplet icing detector based on a numerical computation method of movement and knock-on effect of supercooling water droplets. The existing icing detector can analyze whether an ice-formation condition exists or not through detecting the information such as liquid water content and temperature in the atmosphere. The invention aims to solve the problem that the conventional detecting method is only sensitive to the liquid water content, cannot differentiate water droplet sizes, and cannot be used for SLD icing detection. The detector comprises a first bulge and a rear part, wherein the first bulge is connected with the rear part through a groove. According to the invention, the configuration of the detector with curvature change is designed, so that in the conventional water dropping condition, water droplets all strike the front part of the configuration, so that only one continuous striking area is formed in the detector; while under the condition of SLD, the supercooling water droplets strike both the front part and the rear part, therefore, a plurality of incontinuous icing areas are formed in the detector.

The present invention relates to the technical field of vehicle deicing, in particular to a deicing subsystem, a deicing system and a deicing method, including a near-infrared light emitting device, an icing detector and a controller, a near-infrared light emitting device, an icing detection Both the sensor and the controller are set on the rail vehicle, and the near-infrared light emitting device is aimed at the deicing position on the rail vehicle. The ice detector is used to detect the thickness of the ice and compare it with the set value. The switch signal is sent by the device, and the controller is used to control the switch of the near-infrared light emitting device. The system is based on the near-infrared light coating on the rail vehicle. When the de-icing opening condition is met, an opening signal is sent to the near-infrared light emitting device installed above the foundation brake device, so that the near-infrared light emitting device is turned on. The near-infrared light irradiates the surface of the near-infrared light coating through the ice and snow layer to rapidly generate heat, so that the ice and snow layer is easily removed from the coating surface under the action of vehicle vibration and external wind.

An ice detector includes an icing assembly that includes a transparent icing rod with an illuminating element is disposed therein and having an ice accretion surface and a support structure. The icing rod has at least one visual sensor configured to obtain an image of the ice accretion surface; a controller electrically connected to the visual sensor and including an image contrast module configured to compare the obtained image with an initial image so as to judge whether ice is formed on the ice accretion surface of the icing rod. The icing assembly includes a refrigerating element respectively connected to the icing rod and the support structure. The refrigerating element may perform active refrigeration for the icing rod, reduce the surface temperature of the icing rod and facilitate the ice detector detecting ice accretion before ice is formed on a wing/nacelle.

The invention discloses a system for preventing deicing by using a gliding discharge plasma. The system comprises gliding discharge plasma actuators, ice detectors, a power supply system and an anti-icing controller. The power supply system provides working power for all electric equipment. The gliding discharge plasma actuators and the ice detectors are separately connected with the anti-icing controller. A method for applying the gliding discharge plasma to prevent deicing is specifically divided into two working stages of preventing icing and breaking icing, a wide range of sliding discharge is produced by using the gliding discharge plasma actuators, rapid energy injection is generated to rapidly heat the entire area of the upper surfaces of the gliding discharge plasma actuators, iceat the interface between the surfaces of wings and the bottom of an ice layer is melted, the surfaces of the wings are broken away from the ice layer, and the problems of large fuel consumption and low heat utilization rate of a conventional hot air anti-icing system on an aircraft are solved.

The invention discloses a composite aircraft icing detector and an icing detection method, and belongs to the technical field of aviation detection. The composite aircraft icing detector comprises a double-electrode complex impedance sensing mechanism, a multispectral optical fiber sensing mechanism and a composite probe outer frame, wherein the double-electrode complex impedance sensing mechanism and the detection end surface of the multispectral optical fiber sensing mechanism form a sensitive surface and are positioned on the inclined end surface; the double-electrode complex impedance sensing mechanism collects complex impedance frequency characteristic data in a to-be-detected environment; the multispectral optical fiber sensing mechanism collects spectral response data in the to-be-detected environment, recognizes an ice layer and a water film on a sensitive surface in combination with complex impedance frequency characteristic data, and meanwhile, monitors the dynamic process of water film freezing and ice layer melting in an ice-water mixed phase state, so that icing detection is achieved. The problem that a single principle type sensor fails in a complex icing environment is effectively avoided, the reliability and accuracy of the aircraft icing detector are greatly improved, and the aircraft icing detector has practical significance in guaranteeing efficient and reliable operation of an aircraft anti-icing and deicing system.

The invention provides an acoustic measuring method of the thickness of an ice layer. An ice detector vertically upwardly emitting high-frequency, broadband and narrow wave beam signals, and the thickness of the ice layer is measured by use of reflection echo signals irradiated on the upper surface and the lower layer of the ice layer by sound waves. Further brought forward is a sound ray correction technology, for solving the problem of precision reduction of the ice detector when the upper surface and the lower surface of the ice layer are fluctuated. According to the sound ray correction technology, an incident angle of sound waves is estimated by use of uniform-speed movement of an ice detector carrying platform (such as an underwater AUV and the like), a refraction angle formed when the sound waves are spread in the ice layer is solved according to an snell refraction low, and the spreading locus of the sound waves in the ice layer is corrected accordingly, so that the measuring precision of the thickness of the ice layer is improved.