CN118565356B - Aircraft ice layer thickness monitoring method - Google Patents
Aircraft ice layer thickness monitoring method Download PDFInfo
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- CN118565356B CN118565356B CN202410887505.8A CN202410887505A CN118565356B CN 118565356 B CN118565356 B CN 118565356B CN 202410887505 A CN202410887505 A CN 202410887505A CN 118565356 B CN118565356 B CN 118565356B
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- laser
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- 238000000034 method Methods 0.000 title claims abstract description 15
- 238000012544 monitoring process Methods 0.000 title claims abstract description 13
- 230000005540 biological transmission Effects 0.000 claims abstract description 36
- 239000005341 toughened glass Substances 0.000 claims description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000002834 transmittance Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
- G01B11/06—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness for measuring thickness ; e.g. of sheet material
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
- G01V8/00—Prospecting or detecting by optical means
- G01V8/10—Detecting, e.g. by using light barriers
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
- Y02A90/10—Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- General Life Sciences & Earth Sciences (AREA)
- Geophysics (AREA)
- Length Measuring Devices By Optical Means (AREA)
Abstract
本发明涉及航空航天技术领域，特别涉及一种飞机冰层厚度监测方法。包括：由飞机蒙皮内发射激光，激光穿过平嵌在飞机蒙皮层内的激光透射反射层；在接收面接收激光透射反射层内表面反射回飞机蒙皮内部的激光的位置，标记该位置为第一位置；若飞机表面无冰层，则激光从激光透射反射层出射后进入大气，不会返回飞机蒙皮内；若飞机表面有冰层，则激光从激光透射反射层出射后，折射进入冰层，并在冰层与空气的界面处发生反射，反射的激光经由冰层和激光透射反射层返回飞机蒙皮内，在接收面接收该反射激光并记录该反射激光的第二位置；根据第一位置和第二位置之间的距离确定冰层的厚度。本发明提供的飞机冰层厚度监测方法，能够监测飞机上的冰层的厚度。
The present invention relates to the field of aerospace technology, and in particular to a method for monitoring the thickness of ice on an aircraft. The method comprises: emitting a laser from within the aircraft skin, the laser passing through a laser transmission and reflection layer embedded flat in the aircraft skin layer; receiving the position of the laser reflected from the inner surface of the laser transmission and reflection layer back to the aircraft skin on a receiving surface, and marking the position as a first position; if there is no ice on the aircraft surface, the laser enters the atmosphere after being emitted from the laser transmission and reflection layer, and will not return to the aircraft skin; if there is ice on the aircraft surface, the laser refracts into the ice after being emitted from the laser transmission and reflection layer, and is reflected at the interface between the ice and the air, and the reflected laser returns to the aircraft skin via the ice and the laser transmission and reflection layer, and the reflected laser is received on the receiving surface and the second position of the reflected laser is recorded; the thickness of the ice is determined according to the distance between the first position and the second position. The method for monitoring the thickness of ice on an aircraft provided by the present invention can monitor the thickness of ice on an aircraft.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a method for monitoring the thickness of an ice layer of an aircraft.
Background
Aircraft icing severely affects flight safety. The existing icing sensor can only be arranged on the outer surface of the aircraft for monitoring, so that aerodynamic force of the aircraft can be influenced.
Disclosure of Invention
The embodiment of the invention provides an aircraft ice layer thickness monitoring method, which can monitor the thickness of an ice layer on an aircraft in the interior of the aircraft.
The embodiment of the invention provides a method for monitoring the thickness of an ice layer of an aircraft, which comprises the following steps:
laser is emitted from the aircraft skin and passes through a laser transmission and reflection layer which is embedded in the aircraft skin;
receiving the position of the laser reflected back to the interior of the aircraft skin on the inner surface of the laser transmitting and reflecting layer on the receiving surface, and marking the position as a first position;
if the surface of the aircraft is free of the ice layer, the laser is emitted from the laser transmission and reflection layer and enters the atmosphere, and the laser cannot return into the aircraft skin;
If the surface of the aircraft is provided with an ice layer, after the laser exits from the laser transmission and reflection layer, the laser is refracted and enters the ice layer, and is reflected at the interface of the ice layer and the air, the reflected laser returns into the aircraft skin through the ice layer and the laser transmission and reflection layer, and the reflected laser is received at a receiving surface and recorded at a second position of the reflected laser;
and determining the thickness of the ice layer according to the distance between the first position and the second position.
In one possible design, the laser light transmissive reflective layer comprises toughened glass.
In one possible design, the laser light is emitted from within the aircraft skin, the laser light passing through a laser light transreflective layer embedded within the aircraft skin layer, comprising:
emitting a plurality of laser beams from the aircraft skin, wherein each laser beam passes through a laser transmission reflection layer which is embedded in the aircraft skin layer;
the determining the thickness of the ice layer according to the distance between the first position and the second position comprises:
each beam of laser obtains a first position and a second position, and the distance between the first position and the second position is calculated;
And calculating the thickness of the ice layer according to a plurality of the distances.
In one possible design, the multiple lasers are parallel to each other and equally spaced in an array.
In one possible design, the method further comprises:
The receiving surface collects the intensity of the reflected laser light at the second position;
And determining the thickness of the ice layer according to the intensity of the reflected laser light at the second position.
In one possible design, the wavelength of the laser is 900-1000 nm.
In one possible design, the laser has a wavelength of 300-600 nm.
In one possible design, the method further comprises:
And adjusting the angle of the laser to ensure that the propagation angle of the laser in the ice layer is greater than or equal to the critical angle for the laser to emit total reflection at the ice-gas interface.
In one possible design, the laser light is generated by a laser transmitter whose laser light emitting end is in close proximity to or embedded in the laser light transmissive reflective layer and whose receiving face is in close proximity to or embedded in the laser light transmissive reflective layer.
In one possible design, the thickness of the ice layer is calculated by the following formula:
h=[a×nk×sin(wk)×cos(wb)]/(2×nb)
Wherein h is the thickness of the ice layer, a is the distance between the first position and the second position, nk is the refractive index of the laser transmission and reflection layer, wk is the incident angle of the laser entering the ice layer from the laser transmission and reflection layer, wb is the refractive angle of the laser entering the ice layer from the laser transmission and reflection layer, nb is the refractive index of the ice layer.
Compared with the prior art, the invention has at least the following beneficial effects:
In this embodiment, the laser beam is incident on and passes through the laser transmissive/reflective layer at a certain angle, and is reflected by the upper interface of the laser transmissive/reflective layer, and the reflected laser beam is received at the receiving surface, and the position of the reflected laser beam on the receiving surface is marked, that is, the first position. If the surface of the airplane has the ice layer, the laser emitted by the laser transmission and reflection layer cannot be reflected, if the surface of the airplane has the ice layer, the laser enters the ice layer, then the interface on the ice layer is reflected again, the light reflected by the interface on the ice layer is incident on the receiving surface, and the position of the reflected light is marked to be the second position. The thicker the layer of ice, the greater the distance between the first and second locations, and the thickness of the layer of ice may be determined by the distance between the first and second locations.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of a method for monitoring the thickness of an aircraft ice layer provided by an embodiment of the invention;
Fig. 2 is a schematic diagram of a laser path according to an embodiment of the present invention.
In the figure:
1-laser;
2-a laser light transreflective layer;
3-an ice layer;
a-a first position;
and B-a second position.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments, and all other embodiments obtained by those skilled in the art without making any inventive effort based on the embodiments of the present invention are within the scope of protection of the present invention.
In the description of the embodiments of the present invention, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as limiting or implying any particular importance unless otherwise expressly so stated or illustrated, the term "plurality" is intended to be broadly interpreted as referring to two or more, and the terms "connected," "fixed," etc., for example, the term "connected" may be a fixed connection, a removable connection, an integral connection, or an electrical connection, and may be directly or indirectly connected via an intermediary. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the description of the present specification, it should be understood that the terms "upper", "lower", and the like used in the embodiments of the present invention are described in terms of the angles shown in the drawings, and should not be construed as limiting the embodiments of the present invention. In the context of this document, it will also be understood that when an element is referred to as being "on" or "under" another element, it can be directly on the other element or be indirectly on the other element through intervening elements.
Referring to fig. 1 and 2, an embodiment of the present invention provides a method for monitoring an ice thickness of an aircraft, including:
laser is emitted from the aircraft skin and passes through a laser transmission and reflection layer which is embedded in the aircraft skin;
receiving a position of laser reflected back to the interior of the aircraft skin at the inner surface of the laser transmitting and reflecting layer at the receiving surface, and marking the position as a first position;
if the surface of the aircraft is free of the ice layer, the laser is emitted from the laser transmission reflection layer and enters the atmosphere, and the laser cannot return into the aircraft skin;
If the surface of the aircraft is provided with the ice layer, after the laser exits from the laser transmission and reflection layer, the laser is refracted and enters the ice layer, and is reflected at the interface of the ice layer and the air, the reflected laser returns into the aircraft skin through the ice layer and the laser transmission and reflection layer, and the reflected laser is received at the receiving surface and recorded at the second position of the reflected laser;
The thickness of the ice layer is determined based on the distance between the first location and the second location.
In this embodiment, the laser beam is incident on and passes through the laser transmissive/reflective layer at a certain angle, and is reflected by the upper interface of the laser transmissive/reflective layer, and the reflected laser beam is received at the receiving surface, and the position of the reflected laser beam on the receiving surface is marked, that is, the first position. If the surface of the airplane has the ice layer, the laser emitted by the laser transmission and reflection layer cannot be reflected, if the surface of the airplane has the ice layer, the laser enters the ice layer, then the interface on the ice layer is reflected again, the light reflected by the interface on the ice layer is incident on the receiving surface, and the position of the reflected light is marked to be the second position. The thicker the layer of ice, the greater the distance between the first and second locations, and the thickness of the layer of ice may be determined by the distance between the first and second locations.
The functional components in the monitoring method provided by the application are embedded in the skin or are positioned below the skin, so that the appearance of the machine body is not influenced, and the aerodynamic performance of the machine body is not influenced.
In some embodiments of the invention, the laser light transmissive reflective layer comprises toughened glass.
In this embodiment, the tempered glass has higher strength, higher flatness, and excellent light transmittance.
In some embodiments of the invention, laser light is emitted from within an aircraft skin, the laser light passing through a laser light transreflective layer embedded within the aircraft skin, comprising:
emitting a plurality of laser beams from the aircraft skin, wherein each laser beam passes through a laser transmission reflection layer which is embedded in the aircraft skin layer;
determining a thickness of the ice layer based on a distance between the first location and the second location, comprising:
each beam of laser obtains a first position and a second position, and the distance between the first position and the second position is calculated;
The thickness of the ice layer is calculated from the plurality of distances.
There may be some depressions or protrusions on the upper interface of the ice layer, which may cause a large error in thickness data if laser light is incident on the depressions or protrusions. In order to improve accuracy, a plurality of lasers are provided, resulting in a plurality of distances between the first and second positions. The data analysis is carried out on the distances, the extremely high value or the extremely low value is removed, and then the rest data are averaged, so that the thickness data with higher accuracy can be obtained through calculation.
The plurality of lasers need not use a laser transmissive/reflective layer having a large area, and may be disposed only in a region through which the laser path may pass.
In some embodiments of the present invention, the multiple lasers are parallel to each other and equally spaced in an array. Thus, more comprehensive and uniform data can be obtained.
In some embodiments of the invention, further comprising:
the receiving surface collects the intensity of the reflected laser at the second position;
the thickness of the ice layer is determined based on the intensity of the reflected laser light at the second location.
In this embodiment, the intensity of the reflected laser light at the second position is recorded, and part of the energy of the laser light is absorbed by the ice layer during the propagation of the ice layer, and the thicker the ice layer is, the longer the propagation path of the laser light in the ice layer is, the weaker the intensity of the reflected laser light at the second position is, so that the thickness of the ice layer can be determined by the intensity of the reflected laser light.
In some embodiments of the present invention, the wavelength of the laser is 900-1000 nm.
In this embodiment, the long-wave laser has better penetrability, is easier to be absorbed by the ice layer, can improve the sensitivity of the ice layer height change, and the wavelength of the long-wave laser is 900-1000 nm, so that the laser is easier to be absorbed by the ice.
In some embodiments of the present invention, the wavelength of the laser is 300-600 nm.
In this embodiment, the short-wave laser is not easy to emit, has excellent directivity, is easy to form a good reflection light spot on the receiving surface, and has a wavelength of 300-600 nm, and the short-wave laser in the above wavelength range is more easily reflected by ice.
In some embodiments of the invention, further comprising:
And adjusting the angle of the laser to ensure that the propagation angle of the laser in the ice layer is greater than or equal to the critical angle for the laser to emit total reflection at the ice-gas interface.
In this embodiment, by controlling the angle of the laser, the laser is totally reflected when being incident into the air from the ice layer, so that the laser is totally reflected, the loss of the laser intensity is reduced, and the laser is more easily received by the receiving surface.
In some embodiments of the invention, the laser is generated by a laser transmitter with a laser emitting end that is positioned against or embedded in the laser transflector and a receiving surface that is positioned against or embedded in the laser transflector.
In some embodiments of the invention, the thickness of the ice layer is calculated by the following formula:
h=[a×nk×sin(wk)×cos(wb)]/(2×nb)
Where h is the thickness of the ice layer, a is the distance between the first position and the second position, nk is the refractive index of the laser transmission and reflection layer, wk is the incident angle of the laser entering the ice layer from the laser transmission and reflection layer, wb is the refraction angle of the laser entering the ice layer from the laser transmission and reflection layer, and nb is the refractive index of the ice layer.
It should be noted that the above-mentioned embodiments are merely for illustrating the technical solution of the present invention, and not for limiting the same, and although the present invention has been described in detail with reference to the above-mentioned embodiments, it should be understood by those skilled in the art that the technical solution described in the above-mentioned embodiments may be modified or some technical features may be equivalently replaced, and these modifications or substitutions do not make the essence of the corresponding technical solution deviate from the spirit and scope of the technical solution of the embodiments of the present invention.
Claims (2)
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| CN202410887505.8A CN118565356B (en) | 2024-07-03 | 2024-07-03 | Aircraft ice layer thickness monitoring method |
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| CN202410887505.8A CN118565356B (en) | 2024-07-03 | 2024-07-03 | Aircraft ice layer thickness monitoring method |
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| CN118565356A CN118565356A (en) | 2024-08-30 |
| CN118565356B true CN118565356B (en) | 2024-12-13 |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS63135810A (en) * | 1986-11-28 | 1988-06-08 | Nippon Sheet Glass Co Ltd | Detector for light pervious deposit |
| CN103047937A (en) * | 2012-12-24 | 2013-04-17 | 中国科学院西安光学精密机械研究所 | Pavement meteorological state detection method and pavement meteorological state sensor |
| CN118328870A (en) * | 2024-06-14 | 2024-07-12 | 中国民用航空飞行学院 | An aircraft ice thickness monitoring system |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7158240B2 (en) * | 2004-06-16 | 2007-01-02 | The United States Of America As Represented By The Secretary Of The Army | Measurement device and method |
| FR2872897B1 (en) * | 2004-07-06 | 2006-10-13 | Commissariat Energie Atomique | OPTICAL DEVICE FOR MEASURING THE THICKNESS OF AT LEAST PARTIALLY TRANSPARENT MEDIA |
| EP2798207B1 (en) * | 2011-12-29 | 2016-03-09 | Vestas Wind Systems A/S | A wind turbine and a method for determining the presence and/or thickness of an ice layer on a blade body of a wind turbine |
| US10429511B2 (en) * | 2017-05-04 | 2019-10-01 | The Boeing Company | Light detection and ranging (LIDAR) ice detection system |
| CN112146584B (en) * | 2020-09-24 | 2022-07-01 | 重庆光年感知科技有限公司 | Laser detection algorithm for accurately measuring thickness of pavement water film |
| CN114279348A (en) * | 2021-12-29 | 2022-04-05 | 中国电子科技集团公司第十一研究所 | Ice layer thickness measuring device |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS63135810A (en) * | 1986-11-28 | 1988-06-08 | Nippon Sheet Glass Co Ltd | Detector for light pervious deposit |
| CN103047937A (en) * | 2012-12-24 | 2013-04-17 | 中国科学院西安光学精密机械研究所 | Pavement meteorological state detection method and pavement meteorological state sensor |
| CN118328870A (en) * | 2024-06-14 | 2024-07-12 | 中国民用航空飞行学院 | An aircraft ice thickness monitoring system |
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