CN114132512A - Optical fiber icing sensor probe and adjusting method - Google Patents
Optical fiber icing sensor probe and adjusting method Download PDFInfo
- Publication number
- CN114132512A CN114132512A CN202210115915.1A CN202210115915A CN114132512A CN 114132512 A CN114132512 A CN 114132512A CN 202210115915 A CN202210115915 A CN 202210115915A CN 114132512 A CN114132512 A CN 114132512A
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- optical fiber
- sensor probe
- face
- mounting
- supporting arm
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- 239000013307 optical fiber Substances 0.000 title claims abstract description 76
- 239000000523 sample Substances 0.000 title claims abstract description 31
- 238000000034 method Methods 0.000 title claims abstract description 13
- 238000001514 detection method Methods 0.000 claims abstract description 58
- 238000009434 installation Methods 0.000 claims abstract description 13
- 238000010438 heat treatment Methods 0.000 claims description 21
- 239000000835 fiber Substances 0.000 claims description 16
- 230000007704 transition Effects 0.000 claims description 3
- 230000003750 conditioning effect Effects 0.000 claims 1
- 230000008569 process Effects 0.000 abstract description 3
- 230000002265 prevention Effects 0.000 abstract 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 6
- 230000008014 freezing Effects 0.000 description 4
- 238000007710 freezing Methods 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000035945 sensitivity Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000004062 sedimentation Methods 0.000 description 1
Images
Classifications
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D5/00—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable
- G01D5/26—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable characterised by optical transfer means, i.e. using infrared, visible, or ultraviolet light
- G01D5/32—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable characterised by optical transfer means, i.e. using infrared, visible, or ultraviolet light with attenuation or whole or partial obturation of beams of light
- G01D5/34—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable characterised by optical transfer means, i.e. using infrared, visible, or ultraviolet light with attenuation or whole or partial obturation of beams of light the beams of light being detected by photocells
- G01D5/353—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable characterised by optical transfer means, i.e. using infrared, visible, or ultraviolet light with attenuation or whole or partial obturation of beams of light the beams of light being detected by photocells influencing the transmission properties of an optical fibre
Abstract
The invention is suitable for the technical field of ice prevention and deicing of aircrafts, and provides an optical fiber icing sensor probe and an adjusting method, wherein the optical fiber icing sensor probe comprises an installation part, a tail wing, a supporting arm, an installation seat and an optical fiber bundle, the optical fiber bundle comprises a transmitting optical fiber and a receiving optical fiber, the end part of the optical fiber bundle forms a detection end face, the detection end face is bound to one end of the installation part, and the tail wing is arranged at the other end of the installation part; one end of the supporting arm is connected with the middle part of the mounting part, and the other end of the supporting arm is rotatably connected with the mounting seat. When the aircraft flies, the airflow direction and the detection end face form a certain angle, the airflow generates pressure on the tail wing, the area of the detection end face is smaller, and the wind area of the tail wing is larger, so that the sensed wind pressure is unequal, and the wind pressure perpendicular to the tail wing generates a pressure moment, so that the support arm rotates around the mounting seat until the detection end face is opposite to the incoming flow, thereby improving the detection precision of the icing sensor, and ensuring that the detection end face is always opposite to the incoming flow in the flight process.
Description
Technical Field
The invention relates to an optical fiber icing sensor probe, in particular to an adjusting method of the optical fiber icing sensor probe.
Background
An icing probe of the conventional optical fiber icing sensor is arranged on the surface of an aircraft or the surface of a fixed base at a fixed angle and a fixed height; meanwhile, under different cloud and mist parameter conditions and flight speeds of the aircraft, the height of the anhydrous shielding area on the installation surface of the icing probe is different, for example, supercooled large water drops or liquid water with a particle size exceeding a certain value are influenced by inertia at a certain speed, the sedimentation is small, the anhydrous shielding area on the surface or the installation surface of the aircraft may exceed 100mm, the icing probe cannot detect icing, and the detection accuracy and reliability of the optical fiber icing sensor are seriously influenced.
Disclosure of Invention
The invention aims to provide an optical fiber icing sensor probe which comprises an installation part, a tail wing, a support arm, an installation seat and an optical fiber bundle, wherein the optical fiber bundle comprises a transmitting optical fiber and a receiving optical fiber, the end part of the optical fiber bundle forms a detection end surface, the detection end surface is bound to one end of the installation part, and the tail wing is arranged at the other end of the installation part; one end of the supporting arm is connected with the middle part of the mounting part, and the other end of the supporting arm is connected with the mounting seat in a rotating mode.
Preferably, one end of the mounting portion includes a housing, the housing is an annular closed structure, and the end portion of the optical fiber bundle is accommodated in the housing.
Preferably, the detection end face of the optical fiber bundle forms a smooth transition face with the end of the housing.
Preferably, the shape of the detection end face is a cambered surface or a plane.
Preferably, the outer wall of the optical fiber bundle is coated with a heating module.
Preferably, the mounting seat comprises a flange, and one end of the support arm is rotatably mounted on the flange.
Preferably, a bearing is fixedly arranged on the flange, and the supporting arm is mounted on a bearing hole of the bearing.
Preferably, the mounting seat further comprises a seat body, the flange is provided with a fixing hole, the seat body is provided with a first mounting hole, the seat body is fixedly connected with the flange, the fixing hole and the first mounting hole are coaxially arranged and communicated, and the support arm penetrates through the fixing hole and the first mounting hole; a bearing is arranged in the first mounting hole, the bearing is connected with the inner wall of the first mounting hole in a sliding mode, and one end of the supporting arm penetrates through a bearing hole in the bearing.
Preferably, a second mounting hole is formed in the side wall of the mounting seat, the second mounting hole is communicated with the first mounting hole, and the second mounting hole extends into the first mounting hole through a fixing bolt and is fixedly abutted to the outer wall of the bearing.
The invention also provides an adjusting method of the optical fiber icing sensor probe, the optical fiber icing sensor probe is arranged on the outer surface of the airplane, and the method comprises the following steps:
s1: acquiring height parameters of an aircraft surface waterless shielding area of the aircraft in a flight area;
s2: and adjusting the height of the supporting arm to enable the detection end face to extend to a height higher than the height of the water-free shielding area.
Has the advantages that:
1. according to the ice-deposition sensor, the mounting seat is fixedly mounted on the mounting surface of an aircraft, the mounting part is supported by the supporting arm, and the supporting arm and the mounting seat are rotatably mounted, so that when the aircraft flies and the airflow direction and the detection end surface form a certain angle, the airflow generates pressure on the tail wing, the pressure can be decomposed into two forces which are parallel to and perpendicular to the airflow, the detection end surface area is smaller, the wind pressure of the tail wing is larger, the sensed wind pressure is unequal, the wind pressure perpendicular to the tail wing generates a pressure moment, the supporting arm rotates around the mounting seat until the detection end surface is opposite to the incoming flow, the detection accuracy of the ice-deposition sensor is improved, the two sides of the tail wing are stressed in balance at the moment, and the detection end surface is always opposite to the incoming flow in the flying process. The icing sensor probe disclosed by the invention has the advantages that the detection end face is opposite to the incoming flow by adaptively adjusting the incoming flow direction, the liquid water collection rate can be improved, and the sensitivity and the detection precision of the optical fiber icing sensor are improved.
2. According to the invention, the optical fiber bundle is arranged in the shell, and the shell can protect the optical fiber bundle and prevent the optical fiber bundle from being branched, cracked or damaged under the action of strong airflow.
3. According to the invention, the heating module is coated on the outer wall of the optical fiber bundle, and when the detection end face is frozen or the freezing sensing surface is frozen, the heating module can heat the detection end face to melt the ice layer, so that the further detection work of the freezing sensor is facilitated.
4. In the invention, an operator can flexibly adjust the height of the supporting arm and fix the height of the detection end surface to be higher than a shielding area on the surface of the aircraft, thereby improving the detection efficiency of the icing sensor.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention or in the description of the prior art will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a first schematic diagram of a three-dimensional structure of a probe of an optical fiber icing sensor according to an embodiment of the invention;
FIG. 2 is a second schematic diagram of a three-dimensional structure of a probe of an optical fiber icing sensor according to an embodiment of the invention;
FIG. 3 is a first schematic view of a detection end face of an optical fiber bundle provided by an embodiment of the present invention;
FIG. 4 is a second schematic view of a detection end face of an optical fiber bundle provided by an embodiment of the present invention;
FIG. 5 is a third schematic view of a detection end face of an optical fiber bundle provided in an embodiment of the present invention;
FIG. 6 is a fourth schematic view of a detection end face of an optical fiber bundle provided by an embodiment of the present invention;
FIG. 7 is a fifth schematic view of a detection end face of an optical fiber bundle provided in an embodiment of the present invention;
FIG. 8 is a first schematic view of a fiber optic bundle heating module mounting location provided by an embodiment of the present invention;
FIG. 9 is a second schematic view of a fiber optic bundle heating module mounting location provided by an embodiment of the present invention;
FIG. 10 is a cross-sectional view of a fiber optic ice sensor probe A according to an embodiment of the present invention.
In the drawing, 100, end face detection; 11. a housing; 110. mounting grooves; 12. a heating module; 13. a fiber optic bundle; 20. an installation part; 200. a first cavity; 30. a tail wing; 40. a support arm; 400. a second cavity; 50. a flange; 51. installing a bolt; 52. mounting holes; 60. a base body; 61. a first mounting hole; 62. a second mounting hole; 63. fixing the bolt; 70. a first bearing; 71. a second bearing; 80. an aircraft fuselage.
Detailed Description
The following description provides many different embodiments, or examples, for implementing different features of the invention. The particular examples set forth below are illustrative only and are not intended to be limiting.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or the orientations or positional relationships that the products of the present invention are conventionally placed in use, and are only used for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the present invention, unless otherwise expressly stated or limited, the first feature may be present on or under the second feature in direct contact with the first and second feature, or may be present in the first and second feature not in direct contact but in contact with another feature between them. Also, the first feature being above, on or above the second feature includes the first feature being directly above and obliquely above the second feature, or merely means that the first feature is at a higher level than the second feature. A first feature that underlies, and underlies a second feature includes a first feature that is directly under and obliquely under a second feature, or simply means that the first feature is at a lesser level than the second feature.
Referring to fig. 1 and 2, an object of the present invention is to provide an optical fiber icing sensor probe, which includes a mounting portion 20, a tail 30, a supporting arm 40, a mounting seat, and an optical fiber bundle 13, wherein the optical fiber bundle 13 includes a transmitting optical fiber and a receiving optical fiber, the transmitting optical fiber is used for transmitting light, the receiving optical fiber is used for receiving light transmitted by the transmitting optical fiber, and a plurality of transmitting optical fibers and a plurality of receiving optical fibers may be arranged in operation to improve the transmitting efficiency and the receiving efficiency of the transmitting optical fiber and the receiving optical fiber.
As shown in fig. 3 to 5, a detection end face 100 is formed at an end portion of the optical fiber bundle 13, the detection end face 100 is bound to one end of the mounting portion 20, one end of the mounting portion 20 includes a housing 11, the housing 11 is an annular closed structure, and the end portion of the optical fiber bundle 13 is accommodated in the housing 11. Wherein, the detection end face 100 of the optical fiber bundle 13 and the tail end of the shell 11 form a smooth transition face. By mounting the fiber bundle 13 in the housing 11, the housing 11 can protect the fiber bundle 13 from being split, broken or damaged by the strong airflow.
Further, as shown in fig. 3 and 4, the detection end surface 100 is shaped as an arc surface; referring to fig. 5 and 6, the detection end surface 100 is shaped as a plane, wherein the plane includes a vertical surface perpendicular to a horizontal surface, as shown in fig. 6, and an inclined surface forming an angle with the vertical surface, as shown in fig. 5.
In the present invention, as shown in fig. 5 to 7, the cross-sectional structural shape of the single optical fiber bundle 13 and the shape of the housing 11 are not limited, and the cross section of the optical fiber may be circular, polygonal, etc.; the shape of the housing 11 may be a circular tube, an elliptical tube, or a polygonal tube such as a quadrangle, a pentagon, or a hexagon.
Further, the outer wall of the optical fiber bundle 13 is covered with a heating module 12. Referring to fig. 8 and 9, a mounting groove 110 for accommodating the heating module 12 is formed in the housing 11, in this embodiment, the heating module 12 is a tubular heating film or heating sheet, and the inner diameter of the heating film or heating sheet is the same as the inner diameter of the housing 11 when the heating module is mounted in the mounting groove 110, and a and b in fig. 8 respectively show schematic diagrams after and before the optical fiber bundle 13 is mounted; or as shown in c and d in fig. 9, the structure of the optical fiber bundle 13 wrapped in the heating module 12 and the structure of the housing 11 when the optical fiber bundle 13 is not installed, the heating module 12 is completely wrapped on one end of the surface of the optical fiber bundle 13 and is flush with the detection end face 100 of the optical fiber bundle 13; the purpose is to ensure that the optical fiber bundles 13 are in the same straight line, and in other embodiments, the heating module 12 may be in a sheet shape or a block shape, and may be closely attached to the optical fiber bundles 13, so as to achieve a better heating and deicing effect. The outer wall of the optical fiber bundle 13 is coated with the heating module 12, and when the detection end face 100 is frozen or the freezing sensing surface is frozen, the heating module 12 can heat the detection end face to melt the ice layer, thereby facilitating the further detection work of the freezing sensor.
As shown in fig. 10, the tail 30 is disposed at the other end of the mounting portion 20; one end of the supporting arm 40 is connected with the middle part of the mounting part 20, and the other end of the supporting arm 40 is rotatably connected with the mounting seat; further, the mounting seat includes a flange 50, and one end of the support arm 40 is rotatably mounted on the flange 50. The purpose of this is that the detection end face 100 carried on the support arm 40 can be rotated by the wind. In the invention, the mounting seat is fixedly arranged on the mounting surface of an aircraft, the mounting part 20 is supported by the supporting arm 40, and the supporting arm 40 and the mounting seat are rotatably mounted, so that when the aircraft flies, and the airflow direction forms a certain angle with the detection end surface 100, the airflow generates pressure on the tail wing 30, the pressure can be decomposed into two forces which are parallel to and perpendicular to the airflow, because the area of the detection end surface 100 is smaller and the wind area of the tail wing 30 is larger, the sensed wind pressure is unequal, and the wind pressure perpendicular to the tail wing 30 generates pressure moment, so that the supporting arm 40 rotates around the mounting seat until the detection end surface 100 is opposite to the incoming flow, the detection precision of the icing sensor is improved, at the moment, the two sides of the tail wing 30 are balanced in stress, and the detection end surface 100 is always opposite to the incoming flow in the flying process. The icing sensor probe of the invention enables the detection end surface 100 to be over against the incoming flow by self-adaptively adjusting the incoming flow direction, thereby improving the liquid water collection rate and improving the sensitivity and detection precision of the optical fiber icing sensor.
Further, a second bearing 71 is fixedly arranged on the flange 50, and the support arm 40 is mounted on a bearing hole of the second bearing 71. Furthermore, the mounting seat further includes a seat body 60, the flange 50 is provided with a fixing hole, the seat body 60 is provided with a first mounting hole 61, the seat body 60 is fixedly connected with the flange 50, the fixing hole is coaxial and communicated with the first mounting hole 61, and the supporting arm 40 passes through the fixing hole and the first mounting hole 61; a first bearing 70 is arranged in the first mounting hole 61, the first bearing 70 is slidably connected with the inner wall of the first mounting hole 61, and one end of the support arm 40 passes through a bearing hole in the first bearing 70.
A second mounting hole 62 is formed in the side wall of the mounting seat, the second mounting hole 62 is communicated with the first mounting hole 61, and a fixing bolt 63 is arranged on the second mounting hole 62 and extends into the first mounting hole 61 to be abutted against and fixed with the outer wall of the first bearing 70; therefore, in combination with the above structure, an operator can flexibly adjust the height of the support arm 40 and fix the height of the detection end surface 100 to be higher than the shielded area of the aircraft surface, thereby improving the detection efficiency of the icing sensor.
Specifically, as shown in fig. 10, in the present invention, the mounting portion 20 is a tube, the first cavity 200 is formed therein, the supporting arm 40 is also a tube, the second cavity 400 is formed therein, the first cavity 200 is communicated with the second cavity 400, and the optical fiber bundle 13 penetrates through the first cavity 200 in the mounting portion 20 and passes through the end of the second cavity 400 in the supporting arm 40, which is communicated with the first cavity 200.
It should be particularly noted that the seat body 60 in this embodiment is a cylindrical structure, the outer diameter of which is matched with a hole formed in the aircraft body 80, the seat body 60 is inserted into the hole of the aircraft body 80, the outer edge contour diameter of the flange 50 is larger than the hole of the aircraft body 80, the flange 50 is provided with a mounting hole 52, and the flange 50 is fixedly mounted on the aircraft body through a mounting bolt 51.
The invention also provides an adjusting method of the optical fiber icing sensor probe, the optical fiber icing sensor probe is arranged on the outer surface of the airplane, and the method comprises the following steps:
the method comprises the following steps: acquiring a height parameter h of an aircraft surface waterless shielding area in a flight area;
the height parameter H of the anhydrous sheltering area is influenced by the cloud fog parameter M of the aircraft flight area, the flight height H and the speed V of the aircraft, the distance H between the anhydrous sheltering area and the surface of the aircraft is different under the conditions, and the height parameter H of the anhydrous sheltering area can be obtained by the following parameters: fitting the cloud and fog parameter M, the flying height H and the speed V of the airplane in the flying area to obtain the height H of the waterless shielding area;
secondly, adjusting the height of the supporting arm 40 according to the obtained height h of the anhydrous shielding area;
step three: the height of the supporting arm 40 is adjusted to enable the detection end face 100 to extend to a height higher than that of the non-water shielding area, so that the detection end face 100 of the optical fiber sensor is located in the detection incoming flow, the liquid water collection rate can be improved, and the sensitivity and the detection precision of the optical fiber icing sensor can be improved.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. An optical fiber icing sensor probe, comprising: the optical fiber bundle comprises a transmitting optical fiber and a receiving optical fiber, a detection end face is formed at the end part of the optical fiber bundle and is bound to one end of the installation part, and the tail wing is arranged at the other end of the installation part; one end of the supporting arm is connected with the middle part of the mounting part, and the other end of the supporting arm is connected with the mounting seat in a rotating mode.
2. The fiber optic ice sensor probe of claim 1, wherein: one end of the mounting part comprises a shell, the shell is of an annular closed structure, and the end part of the optical fiber bundle is contained in the shell.
3. The fiber optic ice sensor probe of claim 2, wherein: and the detection end face of the optical fiber bundle and the tail end of the shell form a smooth transition face.
4. The fiber optic ice sensor probe of claim 1, wherein: the shape of the detection end face is an arc face or a plane.
5. The fiber optic ice sensor probe of claim 1, wherein: the outer wall of the optical fiber bundle is coated with a heating module.
6. The fiber optic ice sensor probe of claim 1, wherein: the mounting base comprises a flange, and one end of the supporting arm is rotatably mounted on the flange.
7. The fiber optic ice sensor probe of claim 6, wherein: the flange is fixedly provided with a bearing, and the supporting arm is arranged on a bearing hole of the bearing.
8. A fibre optic ice sensor probe according to claim 6 or 7 wherein: the mounting seat further comprises a seat body, a fixing hole is formed in the flange, a first mounting hole is formed in the seat body, the seat body is fixedly connected with the flange, the fixing hole and the first mounting hole are coaxially formed and communicated, and the supporting arm penetrates through the fixing hole and the first mounting hole; a bearing is arranged in the first mounting hole, the bearing is connected with the inner wall of the first mounting hole in a sliding mode, and one end of the supporting arm penetrates through a bearing hole in the bearing.
9. The fiber optic ice sensor probe of claim 8, wherein: the side wall of the mounting seat is provided with a second mounting hole, the second mounting hole is communicated with the first mounting hole, and the second mounting hole extends into the first mounting hole through a fixing bolt and is fixedly abutted against the outer wall of the bearing.
10. A method of conditioning a fibre optic ice sensor probe according to claim 9, the fibre optic ice sensor probe being mounted on an external surface of an aircraft, comprising the steps of:
s1: acquiring height parameters of an aircraft surface waterless shielding area of the aircraft in a flight area;
s2: and adjusting the height of the supporting arm to enable the detection end face to extend to a height higher than the height of the water-free shielding area.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202210115915.1A CN114132512B (en) | 2022-02-07 | 2022-02-07 | Optical fiber icing sensor probe and adjusting method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210115915.1A CN114132512B (en) | 2022-02-07 | 2022-02-07 | Optical fiber icing sensor probe and adjusting method |
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| CN114132512B CN114132512B (en) | 2022-04-29 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114754971A (en) * | 2022-06-15 | 2022-07-15 | 中国空气动力研究与发展中心低速空气动力研究所 | Method and device for testing height of waterless shielding area |
| CN115585753A (en) * | 2022-12-13 | 2023-01-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Optical fiber type icing sensor and method for identifying external appearance of ice |
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