CN112896525A - Resistance type icing detector - Google Patents
Resistance type icing detector Download PDFInfo
- Publication number
- CN112896525A CN112896525A CN202011555546.5A CN202011555546A CN112896525A CN 112896525 A CN112896525 A CN 112896525A CN 202011555546 A CN202011555546 A CN 202011555546A CN 112896525 A CN112896525 A CN 112896525A
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- icing
- probe
- heater
- detector
- resistance heater
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- 239000000523 sample Substances 0.000 claims abstract description 43
- 239000000463 material Substances 0.000 claims description 11
- 229910000838 Al alloy Inorganic materials 0.000 claims description 8
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 8
- 239000000956 alloy Substances 0.000 claims description 8
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052802 copper Inorganic materials 0.000 claims description 6
- 239000010949 copper Substances 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 6
- 229910001030 Iron–nickel alloy Inorganic materials 0.000 claims description 4
- 229910052759 nickel Inorganic materials 0.000 claims description 4
- 239000003973 paint Substances 0.000 claims description 4
- 230000007613 environmental effect Effects 0.000 claims description 3
- 239000000203 mixture Substances 0.000 claims description 3
- 230000008569 process Effects 0.000 claims description 3
- 238000004806 packaging method and process Methods 0.000 claims description 2
- 238000001514 detection method Methods 0.000 abstract description 12
- 230000008859 change Effects 0.000 abstract description 5
- 238000012544 monitoring process Methods 0.000 abstract 1
- 238000010438 heat treatment Methods 0.000 description 16
- 230000003750 conditioning effect Effects 0.000 description 8
- 238000012545 processing Methods 0.000 description 7
- 238000012546 transfer Methods 0.000 description 5
- 238000009413 insulation Methods 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000007747 plating Methods 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 238000001914 filtration Methods 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
Images
Classifications
-
- 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
Abstract
The invention belongs to the technical field of icing detection for aircrafts, and relates to a resistance type icing detector which achieves the purpose of icing detection through the change of the electrifying current of an armored resistance heater in an icing environment, is used for detecting the high-altitude icing environment of an aircraft and outputting an icing alarm and an icing grade signal. The icing detector is divided into an icing probe and a resolver. The icing probe is arranged outside an aircraft skin, is used for outputting currents in different icing environments, and mainly comprises a probe shell, an armored resistance heater and a heater switching end; the resolver is installed in the aircraft skin and used for monitoring the current of the heater, judging the icing condition and outputting an icing alarm signal and an icing grade, and mainly comprises a mounting flange, a shell, a collecting resolving circuit board and a connector.
Description
Technical Field
The invention belongs to an icing detection technology for an aircraft, and particularly relates to a resistance type icing detector which is used for detecting an aerial icing environment where the aircraft is located and outputting an icing alarm and an icing grade signal.
Background
The icing detector is applied to detecting the icing condition of the environment where the aircraft is located, and avoids the faults of parts such as an atmospheric probe, a wing, a windshield and the like caused by icing when the aircraft flies through the sky at high altitude.
The existing aircraft icing detectors are mainly image icing detectors and vibrating cylinder icing detectors, and the image icing detectors need to acquire, process, transmit and analyze image signals (such as patents with patent numbers of CN102313510A and CN 108128466A); the vibration cylinder icing detector needs vibration cylinder excitation, frequency acquisition and frequency signal processing and resolving (such as patents with patent numbers of CN105934005A and CN 108082496A). The two icing detectors are complex in structure composition and high in use and maintenance cost.
Disclosure of Invention
The purpose of the invention is: the icing detector for the aircraft has the advantages of simple structure, small volume, light weight and simple use and maintenance.
In order to solve the technical problem, the technical scheme of the invention is as follows:
a resistance type icing detector utilizes an armored resistance heater with a positive temperature coefficient to detect icing conditions of an aircraft by different electrifying currents under different icing environmental conditions;
the icing detector comprises an icing probe and a resolver;
the icing probe is arranged outside the aircraft skin and comprises a probe shell, an armored resistance heater and a heater switching end;
the resolver is installed inside the aircraft skin and comprises a mounting flange, a shell, a collecting and resolving circuit and a connector.
The resistance of the resistive icing probe as a function of temperature is given by the formula:
RT＝[1+a(T-T0)]R0
in the formula, RTArmoured resistance heater resistance at temperature T; r0At room temperature T0A time-armored resistance heater resistor; a is the temperature coefficient of the wire material in the armored resistance heater;
T0taking the mixture at 20-30 ℃.
The shell of the probe is made of red copper material with high thermal conductivity, the wall thickness of the probe is 0.7-1.5 mm, good thermal conductivity is guaranteed, nickel plating is carried out on the surface, and good three-proofing performance and appearance are guaranteed.
The inner wire material of the armored resistance heater is made of nickel-iron alloy with positive temperature coefficient, and is sensitive to temperature change.
The positive temperature coefficient is more than or equal to 0.0045/DEG C; preferably, 0.0051/deg.C is used.
The heater welds in icing probe inner wall through high frequency, and guarantees good adherence.
The heater switching end switches the heater into a conducting wire through a circuit switching process, and good insulation characteristics are guaranteed.
The mounting flange is mounted on an aircraft skin, the icing probe is fixed on the outside of the mounting flange, the interior of the mounting flange is fixed with the shell through screws, and the mounting flange is sprayed with paint on the surface of an aluminum alloy material, so that good three-proofing performance is guaranteed.
The shell is used for packaging internal components, fixedly collecting and resolving the circuit board and the connector, and the shell is painted on the surface of an aluminum alloy material.
The acquisition and resolving circuit board is connected with the electrifying lead and the connector, acquires and monitors the electrifying current of the heater, compares current signals and sends an icing warning signal and an icing grade signal outwards.
The connector is cross-linked with other systems on the external machine, sends an icing alarm signal to the outside and transmits a power supply to the armored resistance heater.
The invention has the beneficial effects that: a resistance type icing detector provides a new icing detection principle, and the icing detector utilizes the different electrifying currents of an armored resistance heater with a positive temperature coefficient to detect the icing condition of an aircraft under different icing environmental conditions. The icing detector can output icing alarm signals and icing grade signals only by acquiring the electrifying current of the armored resistance heater and comparing the current, electromagnetic excitation and frequency acquisition are not needed, the probe does not need to keep the constant vibration frequency in a magnetic field in long-term use, an external image acquisition probe of an aircraft is not needed to be erected, and image signal transmission, acquisition, storage and processing are not needed. And the icing signal acquisition, calculation and data transmission quantity is small. The icing detector has no electromagnetic drive coil and frequency acquisition and processing circuit, and has the advantages of simple overall structure, small volume, light weight and simple use and maintenance.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings used in the embodiment of the present invention will be briefly explained. It is obvious that the drawings described below are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be obtained from these drawings without inventive effort.
FIG. 1 is a schematic structural view of an ice detector of the present invention;
FIG. 2 is a cross-linked schematic view of a system of an ice detector of the present invention;
FIG. 3 is a schematic diagram of an acquisition and settlement circuit of the icing detector of the present invention;
the system comprises an icing probe 1, an armored resistance heater 2, a mounting flange 3, a heater transfer terminal 4, a shell 5, an acquisition and calculation circuit board 6, a connector 7, an icing detector 8 and other onboard systems 9.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Features of various aspects of embodiments of the invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without these specific details. The following description of the embodiments is merely intended to better understand the present invention by illustrating examples thereof. The present invention is not limited to any particular arrangement or method provided below, but rather covers all product structures, any modifications, alterations, etc. of the method covered without departing from the spirit of the invention.
In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.
Referring to fig. 1, the icing detector of the present invention includes a probe housing, an armored resistance heater, a mounting flange, a heater adapter, a housing, a collecting and resolving circuit board, and a connector 7.
The icing probe is arranged outside a fuselage skin and is positioned in an airplane icing environment, the probe is made of red copper material with high heat conductivity, the wall thickness of the probe is 0.7mm, good heat conductivity is guaranteed, and nickel plating is carried out on the surface of the probe.
The armored resistance heater is welded inside the icing probe, the resistance of the armored resistance heater changes along with the change of an external icing environment, the heater is welded on the inner wall of the icing probe through high-frequency welding, and good adherence is guaranteed; preferably, the inner wire material of the armored resistance heater is nickel-iron alloy with the temperature coefficient of 0.0051/DEG C.
The adapter of the heater transfer end is welded and fixed on the icing probe, the armored resistance heater is transferred to be a lead, the transfer is carried out through the red copper sleeve, and the insulation performance is ensured through glue filling.
The mounting flange is mounted on the aircraft skin, the icing probe is mounted and fixed and is fixed with the shell through screws, and the mounting flange is subjected to paint spraying treatment by using the surface of an aluminum alloy material.
The shell is provided with an encapsulated internal component, a connector is fixed, a circuit is resolved by collection, the shell is made of aluminum alloy material, and the surface of the shell is painted.
The acquisition and resolving circuit is connected with a power-on lead of the armored resistance heater and the connector, compares current signals and sends an icing warning signal and an icing grade signal outwards;
as shown in FIG. 2, the connector is cross-linked with other systems on the external machine, sending an icing warning signal to the outside and providing power to the sheathed resistance heater.
Referring to fig. 3, the acquisition and calculation circuit is divided into a power processing circuit, a heating control circuit, a heating current detection circuit, and a signal conditioning and acquisition circuit.
The power supply processing circuit is used for realizing the functions of filtering, energy storage, protection, slow start, DC/DC conversion and the like of a product working power supply and providing working voltage for each component in the product; the heating control circuit is used for realizing the heating control function of the armored resistance heater; the heating current detection circuit is used for converting the current in the heating loop of the armored resistance heater into direct-current voltage analog quantity and providing the direct-current voltage analog quantity to the signal conditioning and acquisition circuit for signal conditioning; the signal conditioning and acquisition circuit realizes the heating control of the armored resistance heater on one hand, and sends an icing warning signal and an icing grade signal outwards through the acquired heating detection signal on the other hand.
The icing detection principle of the icing detector is that the armored resistance heater with high temperature coefficient has different electrified currents under different icing environment conditions, and the current magnitude is used for determining whether icing is carried out or not and the icing grade.
Referring to fig. 1, the icing detector of the present invention includes a probe housing, an armored resistance heater, a mounting flange, a heater adapter, a housing, a collecting and resolving circuit board, and a connector 7.
The icing probe is arranged outside a fuselage skin and is positioned in an airplane icing environment, the probe is made of red copper material with high heat conductivity, the wall thickness of the probe is 0.7mm, good heat conductivity is guaranteed, and nickel plating is carried out on the surface of the probe.
The armored resistance heater is welded inside the icing probe, the resistance of the armored resistance heater changes along with the change of an external icing environment, the heater is welded on the inner wall of the icing probe through high-frequency welding, and good adherence is guaranteed; preferably, the inner wire material of the armored resistance heater is nickel-iron alloy with the temperature coefficient of 0.0051/DEG C.
The adapter of the heater transfer end is welded and fixed on the icing probe, the armored resistance heater is transferred to be a lead, the transfer is carried out through the red copper sleeve, and the insulation performance is ensured through glue filling.
The mounting flange is mounted on the aircraft skin, the icing probe is mounted and fixed and is fixed with the shell through screws, and the mounting flange is subjected to paint spraying treatment by using the surface of an aluminum alloy material.
The shell is provided with an encapsulated internal component, a connector is fixed, a circuit is resolved by collection, the shell is made of aluminum alloy material, and the surface of the shell is painted.
The acquisition and resolving circuit is connected with a power-on lead of the armored resistance heater and the connector, compares current signals and sends an icing warning signal and an icing grade signal outwards;
as shown in FIG. 2, the connector is cross-linked with other systems on the external machine, sending an icing warning signal to the outside and providing power to the sheathed resistance heater.
Referring to fig. 3, the acquisition and calculation circuit is divided into a power processing circuit, a heating control circuit, a heating current detection circuit, and a signal conditioning and acquisition circuit.
The power supply processing circuit is used for realizing the functions of filtering, energy storage, protection, slow start, DC/DC conversion and the like of a product working power supply and providing working voltage for each component in the product; the heating control circuit is used for realizing the heating control function of the armored resistance heater; the heating current detection circuit is used for converting the current in the heating loop of the armored resistance heater into direct-current voltage analog quantity and providing the direct-current voltage analog quantity to the signal conditioning and acquisition circuit for signal conditioning; the signal conditioning and acquisition circuit realizes the heating control of the armored resistance heater on one hand, and sends an icing warning signal and an icing grade signal outwards through the acquired heating detection signal on the other hand.
The icing detection principle of the icing detector is that the armored resistance heater with high temperature coefficient has different electrified currents under different icing environment conditions, and the current magnitude is used for determining whether icing is carried out or not and the icing grade.
The resistance of the resistance type icing detector of the invention has the following formula along with the change of the temperature:
RT＝[1+a(T-25)]R0
in the formula, RTArmoured resistance heater resistance at temperature T; r0The resistance of the armored resistance heater is 25 ℃ at normal temperature; a is an armoured resistance plusThe temperature coefficient of the wire material in the heater was 0.0051/deg.C.
When the icing environment of the probe of the icing detector changes, the heat conduction of the armored resistance heater changes, so that the temperature of the armored resistance heater changes; because the armored resistance heater has a positive temperature coefficient, when the temperature of the armored resistance heater changes, the resistance of the armored resistance heater changes correspondingly, and accordingly the electrifying current of the armored resistance heater changes. Selecting different normal temperature resistors R according to different power supplies on the machine0The sheathed resistance heater of (1); calculating R according to the formula0、R10、R30Correspondingly calculating the current I of the armored resistance heater0、I10、I30。
When the current I of the armored resistance heater is less than I30When the signal is normal, outputting a normal signal; when the energization current I of the armored resistance heater satisfies I10＞I≥I30Outputting an icing warning signal and a light icing signal under the condition; when the energization current I of the armored resistance heater satisfies I0＞I≥I10Outputting an icing alarm signal and a moderate icing signal when the condition is met; when the electrifying current I of the armored resistance heater meets the condition that I is larger than I0And outputting an icing alarm signal and a severe icing signal under the condition.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (10)
1. A resistive icing detector, comprising: the icing detector detects the icing condition of the aircraft by utilizing different electrifying currents of the armored resistance heater with the positive temperature coefficient under different icing environmental conditions;
the icing detector comprises an icing probe and a resolver;
the icing probe is arranged outside the aircraft skin and comprises a probe shell, an armored resistance heater and a heater switching end;
the resolver is installed inside the aircraft skin and comprises a mounting flange, a shell, a collecting and resolving circuit and a connector.
2. The ice detector of claim 1, wherein: the resistance of the resistive icing probe as a function of temperature is given by the formula:
RT＝[1+a(T-T0)]R0
in the formula, RTArmoured resistance heater resistance at temperature T; r0At room temperature T0A time-armored resistance heater resistor; a is the temperature coefficient of the wire material in the armored resistance heater;
T0taking the mixture at 20-30 ℃.
3. The ice detector of claim 1, wherein: the shell of the probe is made of red copper material with high thermal conductivity, the wall thickness of the probe is 0.7-1.5 mm, and the surface of the probe is plated with nickel.
4. The ice detector of claim 1, wherein: the inner wire material of the armored resistance heater is made of nickel-iron alloy with positive temperature coefficient.
5. The ice detector of claim 2, wherein: the temperature coefficient a is more than or equal to 0.0045/DEG C.
6. The ice detector of claim 1, wherein: the heater is welded on the inner wall of the icing probe through high frequency.
7. The ice detector of claim 1, wherein: the heater switching end switches the heater into a lead through a circuit switching process.
8. The ice detector of claim 1, wherein: the mounting flange is mounted on an aircraft skin, the icing probe is fixed on the outside of the mounting flange, the interior of the mounting flange is fixed with the shell through screws, and the mounting flange is sprayed with paint on the surface of an aluminum alloy material, so that good three-proofing performance is guaranteed.
9. The ice detector of claim 1, wherein: the shell is used for packaging internal components, fixedly collecting and resolving the circuit board and the connector, and the shell is painted on the surface of an aluminum alloy material.
10. The ice detector of claim 1, wherein: the acquisition and resolving circuit board is connected with the electrifying lead and the connector, acquires and monitors the electrifying current of the heater, compares current signals and sends an icing warning signal and an icing grade signal outwards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011555546.5A CN112896525A (en) | 2020-12-24 | 2020-12-24 | Resistance type icing detector |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011555546.5A CN112896525A (en) | 2020-12-24 | 2020-12-24 | Resistance type icing detector |
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| Publication Number | Publication Date |
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| CN112896525A true CN112896525A (en) | 2021-06-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011555546.5A Pending CN112896525A (en) | 2020-12-24 | 2020-12-24 | Resistance type icing detector |
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3277459A (en) * | 1963-11-19 | 1966-10-04 | Rosemount Eng Co Ltd | Conductivity-type ice detector |
| US4333004A (en) * | 1980-02-19 | 1982-06-01 | Dataproducts New England, Inc. | Detecting ice forming weather conditions |
| US5003295A (en) * | 1987-06-10 | 1991-03-26 | Rosemount Inc. | Ice detector probe |
| US20110106331A1 (en) * | 2009-10-29 | 2011-05-05 | Rosemount Aerospace Inc. | Impending icing probe with thermal isolation pedestal |
| CN102313510A (en) * | 2010-07-02 | 2012-01-11 | 中国商用飞机有限责任公司 | Image icing detector |
| CN105571478A (en) * | 2015-12-24 | 2016-05-11 | 太原航空仪表有限公司 | Piezoelectric vibration cylinder icing sensor and method for measuring icing condition thereof |
| CN105934005A (en) * | 2016-05-06 | 2016-09-07 | 武汉航空仪表有限责任公司 | Novel heater of icing detector |
| CN108082496A (en) * | 2017-11-21 | 2018-05-29 | 武汉航空仪表有限责任公司 | A kind of driving circuit of resonant mode icing detector |
| CN108128466A (en) * | 2018-04-26 | 2018-06-08 | 中国商用飞机有限责任公司 | Image-type icing detector and icing detection method |
| CN111114792A (en) * | 2019-12-19 | 2020-05-08 | 武汉航空仪表有限责任公司 | Icing sensor and method capable of calculating icing rate |
-
2020
- 2020-12-24 CN CN202011555546.5A patent/CN112896525A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3277459A (en) * | 1963-11-19 | 1966-10-04 | Rosemount Eng Co Ltd | Conductivity-type ice detector |
| US4333004A (en) * | 1980-02-19 | 1982-06-01 | Dataproducts New England, Inc. | Detecting ice forming weather conditions |
| US5003295A (en) * | 1987-06-10 | 1991-03-26 | Rosemount Inc. | Ice detector probe |
| US20110106331A1 (en) * | 2009-10-29 | 2011-05-05 | Rosemount Aerospace Inc. | Impending icing probe with thermal isolation pedestal |
| CN102313510A (en) * | 2010-07-02 | 2012-01-11 | 中国商用飞机有限责任公司 | Image icing detector |
| CN105571478A (en) * | 2015-12-24 | 2016-05-11 | 太原航空仪表有限公司 | Piezoelectric vibration cylinder icing sensor and method for measuring icing condition thereof |
| CN105934005A (en) * | 2016-05-06 | 2016-09-07 | 武汉航空仪表有限责任公司 | Novel heater of icing detector |
| CN108082496A (en) * | 2017-11-21 | 2018-05-29 | 武汉航空仪表有限责任公司 | A kind of driving circuit of resonant mode icing detector |
| CN108128466A (en) * | 2018-04-26 | 2018-06-08 | 中国商用飞机有限责任公司 | Image-type icing detector and icing detection method |
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| 张庆松: "《智能传感器项目实践》", 30 August 2020, 西安电子科技大学出版社 * |
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