Ice detection device

Abstract

To provide an icing detection device which is not easily affected by electromagnetic interference.SOLUTION: An icing detection device comprises: an aircraft structure; an exposed member which is connected to the aircraft structure, and is exposed to the exterior of the aircraft structure; an optical fiber sensor which is connected to the exposed member, and is covered by at least one of the aircraft structure and the exposed member; and a measuring apparatus which measures light obtained from the optical fiber sensor.SELECTED DRAWING: Figure 3

Description

[Technical field]

[0001] The present invention relates to an ice detection device. [Background technology]

[0002] Patent Document 1 discloses an ice accretion sensor that detects ice adhesion on the surface of an aircraft. The ice accretion sensor of Patent Document 1 detects ice adhesion by the resonant frequency of a finger generated by electrical excitation. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] JP 2005-145453 A Summary of the Invention [Problem to be solved by the invention]

[0004] Electrical ice sensors such as those described in Patent Document 1 have the problem of being susceptible to electromagnetic interference.

[0005] SUMMARY OF THE PRESENT EMBODIMENT An object of the present invention is to provide an ice detection device that is less susceptible to the effects of electromagnetic interference. [Means for solving the problem]

[0006] In order to solve the above problem, an ice detection device according to one embodiment of the present invention comprises: An aircraft structure; an exposed member connected to the aircraft structure and exposed to an exterior of the aircraft structure; an optical fiber sensor connected to the exposed member and coated on at least one of the aircraft structure and the exposed member; a measuring device for measuring light obtained from the optical fiber sensor; Equipped with 、 The exposed member has a weight for adjusting the weight of the exposed member. In order to solve the above problem, an ice detection device according to one embodiment of the present invention comprises: An aircraft structure; an exposed member connected to the aircraft structure and exposed to an exterior of the aircraft structure; an optical fiber sensor connected to the exposed member and coated on at least one of the aircraft structure and the exposed member; a measuring device for measuring light obtained from the optical fiber sensor; Equipped with The exposed member is A flexible member is connected to the optical fiber sensor and is disposed in a flexible state outside the aircraft structure. Effect of the Invention

[0007] According to the present invention, it is possible to provide an ice detection device that is less susceptible to the effects of electromagnetic interference. [Brief description of the drawings]

[0008] [Figure 1] FIG. 1 is a schematic perspective view of an aircraft according to one embodiment of the present invention. [Diagram 2] FIG. 2 is a schematic diagram of the ice accretion detection device of this embodiment. [Diagram 3] FIG. 3 is a diagram showing a state in which ice has adhered to the exposed member of this embodiment. [Figure 4] FIG. 4 is a diagram showing a first modified example of the weight. [Diagram 5] FIG. 5 is a diagram showing a second modified example of the weight. [Figure 6] FIG. 6 is a diagram showing a third modified example of the weight. [Figure 7] FIG. 7 is a diagram showing a fourth modified example of the weight. [Figure 8] FIG. 8 is a schematic diagram of an ice accretion detection device according to another embodiment. [Figure 9] FIG. 9 is a diagram showing a state in which ice has adhered to an exposed member in another embodiment. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0009] Hereinafter, an embodiment of the present invention will be described in detail with reference to the accompanying drawings. The specific dimensions, materials, numerical values, etc. shown in the embodiment are merely examples for facilitating understanding of the invention, and do not limit the present invention unless otherwise specified. In this specification and drawings, elements having substantially the same functions and configurations are given the same reference numerals to avoid repeated explanations, and elements not directly related to the present invention are not shown.

[0010] [1. Overall configuration of the aircraft] First, the overall configuration of an aircraft 1 according to an embodiment of the present invention will be described with reference to Fig. 1. Fig. 1 is a schematic perspective view of an aircraft 1 according to an embodiment of the present invention.

[0011] 1, the aircraft 1 includes a fuselage 3, a main wing 5, a horizontal tail 7, and a vertical tail 9. Hereinafter, the main wing 5, the horizontal tail 7, and the vertical tail 9 will also be referred to simply as wings.

[0012] The fuselage 3 is the central structural member of the body of the aircraft 1, and its length in the front-to-rear direction (roll axis direction) is longer than its lengths in the left-to-right direction (pitch axis direction) and up-down direction (yaw axis direction). Inside the fuselage 3, a boarding space is formed in which passengers can board, and various devices such as engines and other driving sources, fuel tanks, driving devices, and measuring instruments are mounted.

[0013] A pair of main wings 5, 5 are provided on both the left and right sides of the center of the fuselage 3. The pair of main wings 5, 5 are arranged to protrude in the left and right directions from the center of the fuselage 3. The main wings 5 ​​generate upward lift for the aircraft 1.

[0014] A pair of horizontal stabilizers 7, 7 are provided on the left and right sides of the rear of the fuselage 3. The pair of horizontal stabilizers 7, 7 are arranged to protrude in the left and right directions from the rear of the fuselage 3. The horizontal stabilizers 7 have the function of maintaining stability of the aircraft 1 around the pitch axis.

[0015] A vertical tail 9 is provided above the rear of the fuselage 3. The vertical tail 9 is disposed so as to protrude upward from the rear of the fuselage 3. The vertical tail 9 has the function of maintaining the stability of the aircraft 1 about the yaw axis.

[0016] When such an aircraft 1 is in flight or located in a cold region, an icing phenomenon in which ice adheres to the aircraft may occur. For example, ice may adhere to the surface of the nose portion of the fuselage 3 (hereinafter referred to as aircraft structure AS). When ice adheres to the surface of the aircraft 1, the weight of the aircraft 1 increases, and there is a problem that the lift force decreases.

[0017] Therefore, the aircraft 1 of this embodiment is equipped with an icing detection device 100 that detects the adhesion of ice to the surface of the aircraft structure AS. Note that, in this embodiment, a case will be described in which the aircraft structure AS is the nose portion of the fuselage 3, but this is not limiting. For example, the aircraft structure AS may be the main wing 5, the horizontal stabilizer 7, the vertical stabilizer 9, etc.

[0018] [2. Configuration of ice detection device] 2 is a schematic diagram of the icing detection device 100 of this embodiment. As shown in FIG. 2, the icing detection device 100 includes an aircraft structure AS, an exposed member 110, an optical fiber sensor 120, and a measuring device .

[0019] The exposed member 110 is connected to the outer surface SU of the aircraft structure AS. Therefore, the exposed member 110 is exposed to the outside of the aircraft structure AS. The exposed member 110 includes a support 111 and a weight 113.

[0020] The support pillar 111 is erected on the outer surface SU of the aircraft structure AS and covers at least a portion of the optical fiber sensor 120. One end of the support pillar 111 is connected to the outer surface SU, and the other end of the support pillar 111 is connected to the weight 113. The weight 113 is a weight adjustment member that adjusts the weight of the exposed member 110.

[0021] The optical fiber sensor 120 is embedded in the strut 111 and is located in the center of the strut 111. The optical fiber sensor 120 extends in the longitudinal direction of the strut 111. The optical fiber sensor 120 is covered by the exposed member 110 and is configured integrally with the exposed member 110. In this manner, the optical fiber sensor 120 is connected to the exposed member 110. The optical fiber sensor 120 penetrates inside the aircraft structure AS and is connected to a measuring device 130.

[0022] The measurement device 130 is disposed inside the aircraft structure AS. The measurement device 130 irradiates light into the optical fiber sensor 120 and measures the light obtained from the optical fiber sensor 120. In this embodiment, the measurement device 130 measures backscattered light of the light traveling through the optical fiber sensor 120.

[0023] When the optical fiber sensor 120 is distorted or deformed, the frequency of the backscattered light generated at the distorted portion where the distortion or deformation occurs changes. The measuring device 130 measures the change in frequency of the backscattered light of the light traveling through the optical fiber sensor 120. However, without being limited to this, the measuring device 130 may measure the change in frequency of the reflected light of the light traveling through the optical fiber sensor 120.

[0024] Furthermore, when the optical fiber sensor 120 is distorted or deformed, the loss of light traveling through the optical fiber sensor 120 increases at the distorted portion where the distortion or deformation has occurred, and the backscattered light generated at the distorted portion also decreases. Therefore, the measuring device 130 may measure the change in the amount of backscattered light of the light traveling through the optical fiber sensor 120.

[0025] The natural frequency f of the exposed member 110 integrated with the optical fiber sensor 120 is f=1 / (2π)×(k / m). 1 / 2 Here, k is the spring constant of the exposed member 110, and m is the weight of the exposed member 110. In other words, the natural frequency f of the exposed member 110 integrated with the optical fiber sensor 120 can be tuned by adjusting the spring constant k and weight m of the exposed member 110.

[0026] Fig. 3 is a diagram showing a state in which ice has adhered to the exposed member 110 of this embodiment. As shown in Fig. 3, when ice adheres to the exposed member 110, the weight and rigidity of the exposed member 110 change. When the weight and rigidity of the exposed member 110 change, the frequency of vibration of the exposed member 110 changes.

[0027] When the vibration frequency of the exposed member 110 changes, the amount of strain or deformation of the optical fiber sensor 120 changes, and the frequency of the backscattered light measured by the measuring device 130 changes. The measuring device 130 can detect that ice has adhered to the exposed member 110 by measuring the change in the frequency of the backscattered light.

[0028] Thus, according to the icing detection device 100 of this embodiment, by providing the optical fiber sensor 120 covered on the exposed member 110, it is possible to detect the adhesion of ice to the exposed member 110 and, ultimately, to the aircraft 1.

[0029] The optical fiber sensor 120 is less susceptible to the effects of electromagnetic interference, and therefore the icing detection device 100 of this embodiment can be applied to locations subject to the effects of electromagnetic interference.

[0030] Furthermore, an electric icing sensor such as that in Patent Document 1 uses a magnetic material, a quartz oscillator, or the like. Therefore, with an electric icing sensor such as that in Patent Document 1, it is difficult to freely tune the resonant frequency according to the application environment or the application structure. On the other hand, with exposed member 110 of the present embodiment, for example, by changing the weight of weight 113, the natural frequency (resonant frequency) of exposed member 110 integrated with optical fiber sensor 120 can be freely tuned.

[0031] In this embodiment, the optical fiber sensor 120 is covered by the exposed member 110. Therefore, deterioration in durability of the optical fiber sensor 120 can be suppressed compared to a case where the optical fiber sensor 120 is provided exposed to the outside of the aircraft structure AS.

[0032] Fig. 4 is a diagram showing a first modified example of weight 113. As shown in Fig. 4, weight 113A of the first modified example has a spiral shape. Weight 113A of the first modified example has, for example, a plurality of portions 150 spaced apart in the central axis direction R of support 111. Gaps Sa are formed between the plurality of portions 150. Thus, weight 113A of the first modified example has gaps Sa formed between the plurality of portions.

[0033] Fig. 5 is a diagram showing a second modified example of weight 113. As shown in Fig. 5, weight 113B of the second modified example has a conical spiral shape. Weight 113B of the second modified example has, for example, a plurality of portions 160 spaced apart in the central axis direction R of support 111. Gaps Sb are formed between the plurality of portions 160. Thus, weight 113B of the second modified example has gaps Sb formed between the plurality of portions.

[0034] FIG. 6 is a diagram showing a third modified example of weight 113. As shown in FIG. 6, weight 113C of the third modified example has a spider web shape. Weight 113C of the third modified example has a plurality of extending portions 170 extending radially and a plurality of arc portions 171 connecting the plurality of extending portions 170 in an arc shape. Gaps Sc are formed between the plurality of extending portions 170 and the plurality of arc portions 171. Thus, weight 113C of the third modified example has gaps Sc formed between a plurality of portions.

[0035] FIG. 7 is a diagram showing a fourth modified example of the weight 113. As shown in FIG. 7, the weight 113D of the fourth modified example has a diamond shape. The weight 113D of the fourth modified example has, for example, an extension portion 180 extending in the central axis direction R of the support 111, an orthogonal portion 181 extending in a direction V perpendicular to the extension portion 180, and a plurality of inclined portions 183 inclined in the central axis direction R and the orthogonal direction V. The plurality of inclined portions 183 are spaced apart from each other and connected to the extension portion 180 and the orthogonal portion 181. A gap Sd is formed between the extension portion 180, the orthogonal portion 181, and the plurality of inclined portions 183. In this way, the weight 113D of the fourth modified example has a gap Sd formed between a plurality of portions.

[0036] Weights 113A, 113B, 113C, and 113D have gaps Sa, Sb, Sc, and Sd formed between a plurality of portions, and therefore ice is more likely to adhere to them than weight 113 of the above embodiment. The adhesion of ice can easily increase the weight of exposed member 110, and as a result, icing detection by measuring device 130 can be facilitated.

[0037] [Another embodiment] 8 is a schematic diagram of an icing detection device 200 of another embodiment. Components substantially the same as those in the icing detection device 100 of the above embodiment are denoted by the same reference numerals and will not be described. The icing detection device 200 includes an exposed member 210 and an optical fiber sensor 220. The exposed member 210 includes a flexible member 211. The optical fiber sensor 220 is connected to the exposed member 210 (flexible member 211).

[0038] The flexible member 211 is, for example, an optical fiber cable. One end of the flexible member 211 is connected to the optical fiber sensor 220, and the other end of the flexible member 211 is connected to the weight 113. The flexible member 211 is wound around the support 111 with at least a portion of the flexible member 211 spaced apart from the support 111. Therefore, the flexible member 211 is disposed outside the aircraft structure AS in a bent state. When the flexible member 211 is in a bent state, almost no load is transmitted from the flexible member 211 to the optical fiber sensor 220.

[0039] The optical fiber sensor 220 is embedded in the aircraft structure AS and located at the center of the aircraft structure AS. The optical fiber sensor 220 is covered by the aircraft structure AS and is configured integrally with the aircraft structure AS. The optical fiber sensor 220 is connected to the measurement device 130.

[0040] In the above embodiment, the optical fiber sensor 120 is covered by the exposed member 110. On the other hand, the optical fiber sensor 220 is covered by the aircraft structure AS. In this respect, the two sensors are different. Note that the optical fiber sensors 120 and 220 may be covered by both the exposed member 110 and the aircraft structure AS. In this manner, the optical fiber sensors 120 and 220 are covered by at least one of the aircraft structure AS and the exposed member 110.

[0041] Fig. 9 is a diagram showing a state in which ice has adhered to an exposed member 210 in another embodiment. As shown in Fig. 9, when ice adheres to the exposed member 210, the flexible member 211 is integrated with the support column 111 by the ice.

[0042] Therefore, when the strut 111 and the weight 113 vibrate while the aircraft 1 is flying, the flexible member 211 also vibrates, and a load is transmitted to the optical fiber sensor 220. When a load is transmitted to the optical fiber sensor 220, distortion or deformation occurs in the optical fiber sensor 220, and the frequency of the backscattered light measured by the measuring device 130 changes. The measuring device 130 can detect that ice has adhered to the exposed member 210 by measuring the change in the frequency of the backscattered light.

[0043] As described above, the optical fiber sensor 220 is covered by the aircraft structure AS. Therefore, deterioration in durability of the optical fiber sensor 220 can be suppressed compared to a case where the optical fiber sensor 220 is provided exposed to the outside of the aircraft structure AS.

[0044] Furthermore, since the flexible member 211 exposed to the outside of the aircraft structure AS is provided, the vibration and load caused by icing of the exposed member 210 can be effectively transmitted to the optical fiber sensor 220. Furthermore, the effects described in the above embodiment can be obtained.

[0045] Although the embodiment of the present invention has been described above with reference to the attached drawings, it goes without saying that the present invention is not limited to such an embodiment. It is clear that a person skilled in the art can think of various modified or altered examples within the scope of the claims, and it is understood that such examples also naturally belong to the technical scope of the present invention.

[0046] In the above embodiment, an example has been described in which the weight 113 is provided on the exposed members 110 and 210. However, the weight 113 is not an essential component, and the exposed members 110 and 210 do not necessarily have to be provided with the weight 113. [Explanation of symbols]

[0047] AS aircraft structure SU external surface 1 aircraft 100 Ice detection device 110 Exposed parts 111 Post 113 Weight 120 Optical fiber sensor 130 Measuring Equipment 200 Ice detection device 211 Flexible Member 220 Optical Fiber Sensor

Claims

1. An aircraft structure; an exposed member connected to the aircraft structure and exposed to an exterior of the aircraft structure; an optical fiber sensor connected to the exposed member and coated on at least one of the aircraft structure and the exposed member; a measuring device for measuring light obtained from the optical fiber sensor; Equipped with The exposed member has a weight for adjusting the weight of the exposed member. Ice detection device.

2. An aircraft structure, an exposed member connected to the aircraft structure and exposed to an exterior of the aircraft structure; an optical fiber sensor connected to the exposed member and coated on at least one of the aircraft structure and the exposed member; a measuring device for measuring light obtained from the optical fiber sensor; Equipped with The exposed member is a flexible member connected to the optical fiber sensor and disposed in a bent state outside the aircraft structure; Ice detection device.

3. The exposed member has a weight for adjusting the weight of the exposed member.

3. The ice detection device of claim 2.

4. The weight has gaps formed between a plurality of portions. An ice detection device according to claim 1 or 3.

5. The exposed member is A support pillar is provided on an outer surface of the aircraft structure and covers the optical fiber sensor. An icing detection device according to any one of claims 1 to 4.

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