CN111114793B - Icing detection system capable of detecting large supercooled water drops - Google Patents
Icing detection system capable of detecting large supercooled water drops Download PDFInfo
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- CN111114793B CN111114793B CN201911282570.3A CN201911282570A CN111114793B CN 111114793 B CN111114793 B CN 111114793B CN 201911282570 A CN201911282570 A CN 201911282570A CN 111114793 B CN111114793 B CN 111114793B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/20—Means for detecting icing or initiating de-icing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/20—Means for detecting icing or initiating de-icing
- B64D15/22—Automatic initiation by icing detector
Abstract
The invention relates to an icing detection system capable of detecting supercooled large water drops, which comprises a plurality of icing sensors, an icing detection controller and a plurality of icing detectors, wherein the icing sensors are arranged on the icing detection controller; the icing detector is arranged on two sides of the aircraft nose, the icing sensor is arranged on the outer side of the edge of the icing area of the wing, and the icing sensor is connected with the icing detection controller. The system can send icing alarm to the airplane, can distinguish whether the icing is caused by large supercooled water drops or not at the same time of the icing speed, improves the detection capability of the icing detection system, and improves the adaptability of the system to various icing environments.
Description
Technical Field
The invention belongs to the technical field of ice prevention and deicing, and relates to an icing detection system capable of detecting supercooled large water drops.
Background
The icing detection system is special detection and alarm equipment for detecting whether icing exists at a certain part of the airplane when the airplane flies under icing meteorological conditions. The old-fashioned icing detection system or the integrated icing detector can only detect whether the aircraft is iced or not and cannot distinguish icing environments, and the existing icing detection system cannot meet the requirement of distinguishing whether the icing environment is supercooled large water drops or not by aiming at the aircraft of the current new model.
Disclosure of Invention
The purpose of the invention is: in order to meet the requirement that the airplane distinguishes the icing environment and further detects the icing state of the airplane, the traditional icing detector and the sensor are comprehensively optimized, and an icing detection system capable of detecting large supercooled water drops is designed and developed. The icing detection system capable of detecting the supercooled large water drops is provided, and the function of detecting the icing state of an airplane by the icing detection system is met.
The technical scheme of the invention is as follows: the icing detection system capable of detecting large supercooled water drops is characterized in that: the icing detection system comprises a plurality of icing sensors, an icing detection controller and a plurality of icing detectors; the icing detector is arranged on two sides of the aircraft nose, the icing sensor is arranged on the outer side of the edge of the icing area of the wing, and the icing sensor is connected with the icing detection controller;
the plurality of ice sensors includes a vibrating head assembly mounted within an ice sensor housing; the icing sensor is connected with the icing detection controller; the vibrating head assembly is used for detecting the icing thickness, converting the icing thickness into a first frequency signal and transmitting the first frequency signal to the icing detection controller;
the icing detection controller comprises a driving circuit component, a signal processing circuit component and a power circuit component; the driving circuit component is in cross-linking with a vibrating head component of the icing sensor to provide a driving signal for the vibrating head component, and the vibrating head component of the icing sensor feeds back a first frequency signal to the driving circuit component of the icing detection controller; a signal processing circuit component of the icing detection controller is crosslinked with a driving circuit component, the received first frequency signal is resolved, the icing state of the wing is obtained in real time, and an icing warning signal is fed back to the aircraft controller; a power circuit component of the icing detection controller is electrically connected with the driving circuit component and the signal processing circuit component respectively;
the plurality of icing detectors comprise a vibrator assembly, a signal processing circuit assembly, a power supply circuit assembly and a driving circuit assembly; a vibrator component of the icing detector detects the thickness of the ice layer, a driving circuit component is crosslinked with the vibrator component, the thickness of the ice layer is converted into a second frequency signal, and the second frequency signal is fed back to a signal processing circuit component; a signal processing circuit component of the icing detector is crosslinked with a driving circuit component, the received second frequency signal is resolved, the icing state of the airplane is obtained in real time, and an icing warning signal is fed back to the airplane controller;
when the aircraft controller receives icing alarm signals sent by the icing detector and the icing detection controller at the same time, the icing environment of the aircraft is an overcooling large water droplet icing environment.
Furthermore, the plurality of icing sensors comprise vibrating head heaters, and the vibrating head heaters of the icing sensors are electrically connected with the power circuit assembly of the icing detection controller and used for melting accumulated ice on the icing sensors.
Further, the plurality of icing detectors comprise heating components, and the heating components of the icing detectors are electrically connected with the power circuit component and used for melting accumulated ice on the icing detectors.
Furthermore, the vibration head assembly of the icing sensor comprises a coil assembly and a vibration element, wherein the coil assembly and the vibration element generate vibration under the action of an excitation signal provided by a driving circuit assembly of the icing detection controller;
when ice adheres to the vibration element, the vibration frequency changes; the coil assembly converts the icing thickness to a first frequency signal.
Further, the vibrator assembly, the signal processing circuit assembly, the power supply circuit assembly and the driving circuit assembly of the icing detector are integrated in the shell of the icing detector.
Further, the icing sensor shell is conformal to the wing skin, and the shell end face and the skin are in the same plane.
Furthermore, the signal processing circuit component of the icing detector is in signal connection with the aircraft controller through a 422 bus, a 429 bus or a hard wire to transmit an icing warning signal to the aircraft.
Furthermore, the aircraft controller is in signal connection with a signal processing circuit component of the icing detector and a signal processing circuit component of the icing detection controller; the aircraft controller to icing detector's signal processing circuit subassembly, icing detection controller's signal processing circuit subassembly transmission test signal, icing detector, icing detection controller carry out the self-checking.
The invention has the technical effects that:
icing detecting system comprises the freezing detector of integration and with the conformal sensor that freezes of wing and icing detection controller, the freezing detector can satisfy the requirement that the aircraft detected the icing state, provide and freeze the alarm signal and give the aircraft, simultaneously in the wing regional edge outside that freezes, 4 sensors that freeze have been installed, when ordinary supercooled water droplet environment, the sensor that freezes can not report and freeze, and when meeting with the big water droplet environment of supercooling, because it freezes regional big, the sensor can sense and freeze and report after handling through freezing detection controller.
The icing detection system is composed by an optimization system, calculates the installation position, redesigns the appearance and the circuit, realizes the function of distinguishing the environment without icing, and can send icing alarm and icing rate to the airplane through a bus and a hard wire and simultaneously distinguish whether icing is caused by large supercooled water drops. The detection capability of the icing detection system is improved, and the adaptability of the system to various icing environments is improved.
Drawings
FIG. 1 is a schematic block diagram of an icing detection system capable of detecting large supercooled water droplets
FIG. 2 is a schematic structural view of an icing sensor
FIG. 3 is a schematic diagram of an icing detector
FIG. 4 is a schematic diagram of an icing detection controller.
Detailed Description
When the airplane flies in the weather conditions of cloud, fog, rain or snow, the supercooled water drops exist in the air, so that the supercooled water drops are accumulated into ice layers on the surfaces of wings, a fuselage, an engine inlet and the like of the airplane. The average effective diameter of water drops which influence the safety of an airplane and are regulated by appendix C of FAR25 of Federal aviation regulations in the United states is 10-40 um, however, subsequent researches find that large-size supercooled water drops exist in the air, and the supercooled large water drops may deform, break, rebound and splash in the moving and impacting processes, so that the large-range ice is easy to freeze, ice angles in various shapes are formed, the aerodynamic performance of the airplane is influenced, and the hidden flight safety hazard is generated. This type of icing environment is specified in appendix O.
The traditional icing detection system can only detect whether the airplane is iced or not, and can not distinguish common supercooled water drops or supercooled large water drops which cause the airplane to be iced. The novel icing detection system can detect the icing state and can distinguish whether the icing is caused by the large supercooled water drops, so that a pilot is reminded to pay attention to the current icing environment, and special treatment is carried out on the large supercooled water drops.
This novel detection system that freezes has improved the adaptability of system to various different icing environment, to the environmental suitability requirement of the large aircraft that develops rapidly at present to icing detection system, the detection system that freezes that this paper designed has the advantage of distinguishing the big water droplet of subcooling.
Example 1
Fig. 1 is a schematic block diagram of an icing detection system capable of detecting supercooled large water droplets, and as shown in fig. 1, the present embodiment provides an icing detection system capable of detecting supercooled large water droplets, the icing detection system including a plurality of icing sensors, an icing detection controller, and a plurality of icing detectors; the icing detector is arranged on two sides of the aircraft nose, the icing sensor is arranged on the outer side of the edge of the icing area of the wing, and the icing sensor is connected with the icing detection controller. The system can send icing alarm to the airplane, can distinguish whether the icing is caused by large supercooled water drops or not at the same time of the icing speed, improves the detection capability of the icing detection system, and improves the adaptability of the system to various icing environments.
FIG. 2 is a schematic structural view of an ice sensor, as shown in FIG. 2, including a vibrating head assembly mounted within an ice sensor housing; the icing sensor is connected with the icing detection controller; the vibrating head assembly is used for detecting the icing thickness, converting the icing thickness into a first frequency signal and transmitting the first frequency signal to the icing detection controller.
FIG. 4 is a schematic diagram of an icing detection controller, as shown in FIG. 4, the icing detection controller including a drive circuit assembly, a signal processing circuit assembly, and a power circuit assembly; the driving circuit component is in cross-linking with a vibrating head component of the icing sensor to provide a driving signal for the vibrating head component, and the vibrating head component of the icing sensor feeds back a first frequency signal to the driving circuit component of the icing detection controller; a signal processing circuit component of the icing detection controller is crosslinked with a driving circuit component, the received first frequency signal is resolved, the icing state of the wing is obtained in real time, and an icing warning signal is fed back to the aircraft controller; a power circuit component of the icing detection controller is electrically connected with the driving circuit component and the signal processing circuit component respectively;
FIG. 3 is a schematic diagram of an ice detector, as shown in FIG. 3, the plurality of ice detectors including a vibrator assembly, a signal processing circuit assembly, a power circuit assembly, and a drive circuit assembly; a vibrator component of the icing detector detects the thickness of the ice layer, a driving circuit component is crosslinked with the vibrator component, the thickness of the ice layer is converted into a second frequency signal, and the second frequency signal is fed back to a signal processing circuit component; and a signal processing circuit assembly of the icing detector is crosslinked with the driving circuit assembly, the received second frequency signal is resolved, the icing state of the airplane is obtained in real time, and an icing alarm signal is fed back to the airplane controller. In the ordinary supercooled water droplet environment, the icing sensor can not report icing, and in the supercooled large water droplet environment, the sensor can sense icing and report the icing after being processed by the icing detection controller due to the large icing area.
When the aircraft controller receives icing alarm signals sent by the icing detector and the icing detection controller at the same time, the icing environment of the aircraft is an overcooling large water droplet icing environment.
Furthermore, the plurality of icing sensors comprise vibrating head heaters, and the vibrating head heaters of the icing sensors are electrically connected with the power circuit assembly of the icing detection controller and used for melting accumulated ice on the icing sensors.
Further, the plurality of icing detectors comprise heating components, and the heating components of the icing detectors are electrically connected with the power circuit component and used for melting accumulated ice on the icing detectors.
Furthermore, the vibration head assembly of the icing sensor comprises a coil assembly and a vibration element, wherein the coil assembly and the vibration element generate vibration under the action of an excitation signal provided by a driving circuit assembly of the icing detection controller; when ice adheres to the vibration element, the vibration frequency changes; the coil assembly converts the icing thickness to a first frequency signal.
Further, the vibrator assembly, the signal processing circuit assembly, the power supply circuit assembly and the driving circuit assembly of the icing detector are integrated in the shell of the icing detector.
Further, the icing sensor shell is conformal to the wing skin, and the shell end face and the skin are in the same plane.
Furthermore, the signal processing circuit component of the icing detector is in signal connection with the aircraft controller through a 422 bus, a 429 bus or a hard wire to transmit an icing warning signal to the aircraft.
Furthermore, the aircraft controller is in signal connection with a signal processing circuit component of the icing detector and a signal processing circuit component of the icing detection controller; the aircraft controller to icing detector's signal processing circuit subassembly, icing detection controller's signal processing circuit subassembly transmission test signal, icing detector, icing detection controller carry out the self-checking.
In this embodiment, the operation principle of each unit is as follows:
(1) an icing detector:
the sensitive part of the icing detector consists of an electromagnetic oscillation system, a deicing heating assembly and a base. The electromagnetic oscillation system consists of five parts, namely an excitation coil, a feedback coil, an isolation washer, a magnet and a supporting spring. The driving magnetic field of the vibrating tube is formed by superposing an alternating magnetic field with changeable positive and negative directions generated by the driving coil and a bias magnetic field generated by the permanent magnet, so that the vibration frequency of the vibrating tube is consistent with the frequency of an alternating current signal. The signal pick-up coil extracts the frequency signal, amplifies the signal and feeds the amplified signal back to the drive circuit. In order to increase the magnetic field intensity, reduce the magnetic leakage and ensure the uniform magnetic field distribution, a steel sheet is arranged outside the coil winding to form a cylindrical closed magnetic circuit.
The resolving component of the detector comprises a signal processing module, an output signal detection module and a driving module. The function is to receive the frequency signal from the probe, output the probe heating instruction and icing warning signal according to different frequency values, output icing fault signal when the fault occurs, monitor the output icing warning signal and fault signal in real time, and record fault information and icing warning information. The driving module is used for driving the sensitive component to work in an oscillating mode and tracking the frequency change of the sensitive component. The design of the circuit mainly selects a control device taking a BM89C52 singlechip as a core, and a peripheral circuit mainly comprises a crystal oscillator, a watchdog and an inverter.
When the probe of the detector is frozen, the vibration frequency of the probe can change along with the change of the frozen thickness, the frequency can change by a certain amount delta f corresponding to an ice layer of 0.5mm +/-0.2 mm, and the resolving component realizes the frequency detection function through internal measurement and control software and an internal timer and a counter. And when the frequency change value reaches delta f, outputting an icing alarm signal.
(2) Icing sensor
The icing sensor consists of a vibrating head component, a regulator component and a socket, wherein the shell material of the vibrating head component of the icing sensor is made of high-temperature-resistant constant-elasticity alloy, and a reed, a diaphragm, a magnet, an exciting coil, a signal pickup coil and a heater are arranged in the shell. Under the combined action of the vibrating head shell, the reed, the diaphragm, the magnet, the exciting coil and the signal pickup coil, the vibrating head component vibrates at the natural frequency, and when ice is attached to the vibrating head shell, the vibration frequency of the vibrating head component is changed along with the ice.
(3) Icing detection controller
The icing detection controller consists of an outer cover, a base, a socket, a shielding box, a filter array, a signal processing circuit board assembly, a driving circuit board assembly and a power supply circuit board assembly
The driving circuit board assembly, the exciting coil and the vibration pickup coil in the icing sensor form a resonance loop together to drive the diaphragm on the vibration head of the icing sensor to continuously vibrate. The drive circuit amplifies the sinusoidal signal output by the icing sensor and can adjust the phase of the sinusoidal signal so as to meet the requirements of the icing sensor on the phase and amplitude required by continuous oscillation.
The signal processing circuit board assembly counts the frequency of the icing sensor, the frequency of the icing sensor changes along with the change of the thickness of the ice layer, when the frequency of the icing sensor reaches a set threshold value, an icing warning signal is output through the 422 bus data transmission circuit, a heating instruction is output, the ice layer on the icing sensor is removed, and preparation is made for the next icing detection. The signal processing circuit board assembly can also monitor the working state of the icing sensor in real time, and when the frequency of the icing sensor does not meet the error requirement or the heating wire is disconnected, a fault signal is output through the 422 bus data transmission circuit.
The power circuit board assembly converts the 28VDC power provided by the airplane into +12V direct current voltage and 5V direct current voltage required by the icing detection controller to work and executes a heating instruction of the signal processing circuit board. In order to prevent the power supply module in the power circuit board from being damaged due to overheating, a heat sink is mounted on the power module.
The frequency signal range output by the icing sensor is 5900 Hz-6100 Hz, which is easy to be influenced by the electromagnetic environment and the power supply interference. To solve this problem, the signal processing circuit board assembly and the driving circuit board assembly are mounted in a shield case. The shielding box is of a full-sealing structure and made of 10# steel, and can effectively shield electromagnetic interference. The signal processing circuit board assembly, the driving circuit board assembly and the power circuit board are connected through a filter array, and the filter array is composed of filter capacitors and can effectively inhibit power interference.
Claims (8)
1. An icing detection system capable of detecting supercooled large water drops is characterized in that: the icing detection system comprises a plurality of icing sensors, an icing detection controller and a plurality of icing detectors; the icing detector is arranged on two sides of the aircraft nose, the icing sensor is arranged on the outer side of the edge of the icing area of the wing, and the icing sensor is connected with the icing detection controller;
the plurality of ice sensors includes a vibrating head assembly mounted within an ice sensor housing; the icing sensor is connected with the icing detection controller; the vibrating head assembly is used for detecting the icing thickness, converting the icing thickness into a first frequency signal and transmitting the first frequency signal to the icing detection controller;
the icing detection controller comprises a driving circuit component, a signal processing circuit component and a power circuit component; the driving circuit component is in cross-linking with a vibrating head component of the icing sensor to provide a driving signal for the vibrating head component, and the vibrating head component of the icing sensor feeds back a first frequency signal to the driving circuit component of the icing detection controller; a signal processing circuit component of the icing detection controller is crosslinked with a driving circuit component, the received first frequency signal is resolved, the icing state of the wing is obtained in real time, and an icing warning signal is fed back to the aircraft controller; a power circuit component of the icing detection controller is electrically connected with the driving circuit component and the signal processing circuit component respectively;
the plurality of icing detectors comprise a vibrator assembly, a signal processing circuit assembly, a power supply circuit assembly and a driving circuit assembly; a vibrator component of the icing detector detects the thickness of the ice layer, a driving circuit component is crosslinked with the vibrator component, the thickness of the ice layer is converted into a second frequency signal, and the second frequency signal is fed back to a signal processing circuit component; a signal processing circuit component of the icing detector is crosslinked with a driving circuit component, the received second frequency signal is resolved, the icing state of the airplane is obtained in real time, and an icing warning signal is fed back to the airplane controller;
when the aircraft controller receives icing alarm signals sent by the icing detector and the icing detection controller at the same time, the icing environment of the aircraft is an overcooling large water droplet icing environment.
2. An icing detection system for detecting large supercooled water droplets according to claim 1, characterized in that: the plurality of icing sensors comprise vibrating head heaters, and the vibrating head heaters of the icing sensors are electrically connected with the power circuit assembly of the icing detection controller and used for melting accumulated ice on the icing sensors.
3. An icing detection system for detecting large supercooled water droplets according to claim 1, characterized in that: the icing detectors comprise heating components, and the heating components of the icing detectors are electrically connected with the power circuit component and used for melting accumulated ice on the icing detectors.
4. An icing detection system for detecting large supercooled water droplets according to claim 1, characterized in that: the vibration head assembly of the icing sensor comprises a coil assembly and a vibration element, wherein the coil assembly and the vibration element generate vibration under the action of an excitation signal provided by a driving circuit assembly of the icing detection controller;
when ice adheres to the vibration element, the vibration frequency changes; the coil assembly converts the icing thickness to a first frequency signal.
5. An icing detection system for detecting large supercooled water droplets according to claim 1, characterized in that: the vibrator assembly, the signal processing circuit assembly, the power supply circuit assembly and the driving circuit assembly of the icing detector are integrated in the shell of the icing detector.
6. An icing detection system for detecting large supercooled water droplets according to claim 1, characterized in that: the icing sensor shell is conformal with the wing skin, and the end face of the shell and the wing skin are in the same plane.
7. An icing detection system for detecting large supercooled water droplets according to claim 1, characterized in that: and the signal processing circuit component of the icing detector is in signal connection with the aircraft controller through a 422 bus, a 429 bus or a hard wire and transmits an icing warning signal to the aircraft.
8. An icing detection system for detecting large supercooled water droplets according to claim 1, characterized in that: the aircraft controller is in signal connection with the signal processing circuit component of the icing detector and the signal processing circuit component of the icing detection controller; the aircraft controller to icing detector's signal processing circuit subassembly, icing detection controller's signal processing circuit subassembly transmission test signal, icing detector, icing detection controller carry out the self-checking.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111792039A (en) * | 2020-06-29 | 2020-10-20 | 山东大学 | Deicing device, system and method for airplane wing |
| CN112591106A (en) * | 2020-12-24 | 2021-04-02 | 太原航空仪表有限公司 | Resonant mode detector drive circuit that freezes |
| CN114194399A (en) * | 2021-12-10 | 2022-03-18 | 武汉航空仪表有限责任公司 | Icing sensor based on short wave infrared type |
| CN114476080A (en) * | 2021-12-27 | 2022-05-13 | 武汉航空仪表有限责任公司 | Icing detection system for medium and large-sized transport plane |
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