WO2019163379A1 - 騒音低減装置、航空機及び騒音低減方法 - Google Patents

騒音低減装置、航空機及び騒音低減方法 Download PDF

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Publication number
WO2019163379A1
WO2019163379A1 PCT/JP2019/002065 JP2019002065W WO2019163379A1 WO 2019163379 A1 WO2019163379 A1 WO 2019163379A1 JP 2019002065 W JP2019002065 W JP 2019002065W WO 2019163379 A1 WO2019163379 A1 WO 2019163379A1
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WIPO (PCT)
Prior art keywords
perforated plate
noise reduction
fluid flow
noise
aircraft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/JP2019/002065
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
亨 平井
光宏 村山
一臣 山本
伊藤　靖
健太郎 田中
武久 高石
譲 横川
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Japan Aerospace Exploration Agency JAXA
Original Assignee
Japan Aerospace Exploration Agency JAXA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Japan Aerospace Exploration Agency JAXA filed Critical Japan Aerospace Exploration Agency JAXA
Priority to EP19756790.2A priority Critical patent/EP3760882B1/en
Priority to US16/976,020 priority patent/US11577823B2/en
Publication of WO2019163379A1 publication Critical patent/WO2019163379A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C7/00—Structures or fairings not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/001—Devices not provided for in the groups B64C25/02 - B64C25/68
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface  wheeled type, e.g. multi-wheeled bogies
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/0005—Baffle plates
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/10—Influencing flow of fluids around bodies of solid material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/001—Devices not provided for in the groups B64C25/02 - B64C25/68
    • B64C2025/003—Means for reducing landing gear noise, or turbulent flow around it, e.g. landing gear doors used as deflectors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/08—Boundary layer controls by influencing fluid flow by means of surface cavities, i.e. net fluid flow is null
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/14—Boundary layer controls achieving noise reductions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/04—Arrangement or disposition on aircraft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B21/00—Common features of fluid actuator systems; Fluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
    • F15B21/008—Reduction of noise or vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B2211/00—Circuits for servomotor systems
    • F15B2211/80—Other types of control related to particular problems or conditions
    • F15B2211/86—Control during or prevention of abnormal conditions
    • F15B2211/8616—Control during or prevention of abnormal conditions the abnormal condition being noise or vibration

Definitions

  • the present invention relates to a noise reduction device and a noise reduction method used for reducing aircraft noise, for example, and further relates to an aircraft equipped with such a device.
  • a solid rectifying plate Solid Fairing
  • a porous plate Porous Plate
  • Patent Documents 1 to 3, Patent Documents. 1 By disposing a solid rectifying plate or a perforated plate in front of the object, the inflow of air downstream is suppressed, the flow velocity is reduced, and the turbulence of the air current is suppressed. As a result, noise generated mainly by downstream objects is reduced.
  • the present inventors have found that a shear layer of air flow is generated behind the end of the solid rectifying plate or perforated plate, which causes noise generation and reduces the amount of noise reduction.
  • an object of the present invention is to provide a noise reduction device, an aircraft, and a noise reduction method capable of increasing the amount of noise reduction.
  • a noise reduction device includes a perforated plate that is disposed so as to face a fluid flow and has a bent region that is bent upstream of the fluid flow.
  • the bent region is provided at an end of the perforated plate. Further, it is preferable that the bent region has a concave shape, for example, a concave R shape, on the upstream side of the fluid flow.
  • the direction of fluid flow is typically deflected outward from the center of the perforated plate, but having a bent region makes it easier for the deflected fluid to pass through the perforated plate. This weakens the shear layer of the fluid flow, reduces the noise induced by the vortex, and increases the amount of noise reduction.
  • the perforated plate may be disposed so as to cover the front part of the space between the leg wheels such as the main legs and front legs of the aircraft, and structural members of the legs such as the main legs and front legs of the aircraft, for example, You may arrange
  • the porous plate may have a plurality of through holes or through grooves, or may be made of a porous material.
  • An aircraft according to an aspect of the present invention covers a front part of a leg structural member such as a main leg or a front leg, for example, a front part of a side brace of the main leg, so as to cover a front part of an inter-legged part such as a main leg or a front leg.
  • a perforated plate disposed along the front edge of the leg storage chamber and having an end bent forward.
  • a noise reduction method is a perforated plate disposed in a fluid flow and opposed to the fluid flow direction upstream of an object that induces noise generated by the fluid flow. And at least part of the region of the perforated plate in which the fluid flow direction is deflected due to the perforated plate is bent toward the upstream side of the fluid flow. Here, it is preferable that the end of the perforated plate bends to the upstream side of the fluid flow.
  • the amount of noise reduction can be increased.
  • FIG. 1 It is a perspective view which shows the noise reduction apparatus which concerns on one Embodiment of this invention. It is a figure for demonstrating the effect
  • FIG. 7 is a partial front view of FIG. 6. It is a perspective view which shows the structure which has arrange
  • FIG. (1) for demonstrating the cause which noise generate
  • FIG. (2) for demonstrating the cause which noise generate
  • FIG. 25 is a partially enlarged perspective view of the porous plate shown in FIG. 24. It is a numerical analysis result of cross-sectional pressure fluctuation distribution when a deflector or a perforated plate is not installed at the front edge of the leg storage chamber.
  • FIG. 1 is a perspective view showing a noise reduction device according to an embodiment of the present invention.
  • the noise reduction device 1 includes a perforated plate 2.
  • the perforated plate 2 typically includes a plurality of through holes or through grooves, or may be made of a porous material such as a sponge.
  • a punching metal can be used as the perforated plate 2.
  • the holes are typically provided in the entire area of the plate, but are not necessarily provided in the entire area of the plate, and may be provided in at least the bending area described later.
  • the perforated plate 2 is arranged on the upstream side of the object 3 so as to cover the object 3 and in contact with the object 3 at a predetermined interval or in contact with the object 3.
  • the object 3 is arranged in a fluid flow that is typically air, and induces noise generated by the fluid flow.
  • the shape of the object 3 is a cylinder, but the shape is not limited.
  • the perforated plate 2 is typically disposed so as to be orthogonal to the fluid flow direction 4, that is, to face each other.
  • the perforated plate according to the present invention is not necessarily prescribed to be strictly orthogonal.
  • the fluid flow direction 4 is a direction in which the direction is not deflected by the influence of the perforated plate 2 or the object 3. Taking an aircraft as an example, this fluid flow direction 4 is generally opposite to the flight direction of the aircraft. However, since the airflow is locally bent depending on the shape, the direction opposite to the flight direction of the aircraft is not necessarily the fluid flow direction 4.
  • the perforated plate 2 has a bent region 5 at the end 6 of the perforated plate 2 that is bent upstream of the fluid flow, that is, opposite to the direction 4.
  • the bent region 5 is configured by, for example, bending the end of the perforated plate 2 forward.
  • the bend region 5 typically has a concave R shape upstream of the fluid flow. The radius of curvature of the R shape is preferably determined according to the degree of fluid deflection described later.
  • the bent region 5 is provided at the end 6, but at least a part of the region of the porous plate 2 in which the fluid flow direction is deflected due to the porous plate 2 is located upstream of the fluid flow. It only needs to bend.
  • the fluid flow direction is deflected outward from the center 2 a of the porous plate 2 due to the presence of the porous plate 2 in the fluid flow.
  • the present inventors have obtained that a shear layer of the air flow is generated behind the end of the solid rectifying plate or the perforated plate, which causes noise generation and reduces the amount of noise reduction.
  • This is a finding. In this case, for example, it may be possible to bend the end of the solid rectifying plate or the perforated plate backward, or to make the whole into a convex curved surface, but this still cannot suppress the reduction in the amount of noise reduction. It was.
  • the present invention has the bent region 5 at the end 6 so that the deflected fluid easily passes through the porous plate 2.
  • the difference in velocity between the flow A passing through the end 6 and the flow B outside the end 6 is reduced, and the shear layer itself and the fluctuation of the fluid flow between them are weakened, and the vortex generated by the shear layer Weakens or no vortex is generated. Since the fluid fluctuation is reduced by the weakening of the vortex or no vortex being generated, the noise is reduced and the amount of noise reduction can be increased.
  • FIG. 3A shows a cross-sectional flow velocity distribution, an in-plane streamline (FIG. 3A (1)), and a cross-sectional pressure fluctuation distribution (177 Hz ⁇ ) when a cylinder 3 is placed in the fluid flow from left to right in the figure. 354 Hz) (FIG. 3A (2)) and cross-sectional pressure fluctuation distribution (707 Hz to 1414 Hz) (FIG. 3A (3)).
  • FIG. 3B shows a cross-sectional flow velocity distribution and in-plane streamlines (FIG. 3B (1)) and a cross-sectional pressure fluctuation distribution (177 Hz to 354 Hz) when a flat porous plate is disposed in front of the object 3 (FIG. 3B (2)). And cross-sectional pressure fluctuation distribution (707 Hz to 1414 Hz) (FIG. 3B (3)).
  • FIG. 3C shows a cross-sectional flow velocity distribution and in-plane streamlines (FIG. 3C (1)) and a cross-sectional pressure fluctuation distribution (177 Hz to 354 Hz) in the case where a perforated plate bent at the rear end is disposed in front of the object 3 (FIG. 3C ( 2)) and the cross-sectional pressure fluctuation distribution (707 Hz to 1414 Hz) (FIG. 3C (3)).
  • FIG. 3D shows a cross-sectional flow velocity distribution and in-plane streamlines (FIG. 3D (1)) and cross-sectional pressure fluctuation distribution when a perforated plate (perforated plate according to the present embodiment) bent in front of the end is disposed in front of the object 3. (177 Hz to 354 Hz) (FIG. 3D (2)) and cross-sectional pressure fluctuation distribution (707 Hz to 1414 Hz) (FIG. 3D (3)) are shown.
  • FIG. 3A (1) it can be seen that when the perforated plate is not present in front, the speed around the object is increased. As shown in FIGS. 3B (1) to 3D (1), the presence of the perforated plate in front reduces the speed around the object.
  • FIG. 3B (1) and FIG. 3C (1) and FIG. 3D (1) it can be seen that the velocity gradient of the shear layer behind the end of the perforated plate is smaller in FIG. 3D (1).
  • FIGS. 3A (2) (3) to 3C (2) (3) by using the porous plate according to this embodiment, the end of the porous plate is It turns out that the area
  • Fig. 4 shows the noise level (OASPL) synthesized by summing the levels for each frequency band from 21 Hz to 10.7 kHz with the A-weighted auditory correction around the object 3 (0 ° to 360 °).
  • the fluid flows from 180 ° to 0 °.
  • FIG. 5 shows the frequency distribution of noise at the 270 ° position.
  • the object 3 made of a cylinder is placed in the fluid flow as it is (1)
  • a flat plate is placed in front of the object 3 (2)
  • a flat porous plate is placed in front of the object 3
  • a perforated plate bent backward at the end is arranged in front of the object 3
  • a perforated plate bent forward at the end is arranged in front of the object 3.
  • Case (5) is shown. It can be seen that the perforated plate according to this embodiment has a low noise level over a wide band.
  • the noise reduction amount can be increased by the noise reduction device 1 according to the present embodiment.
  • FIG. 6 is a bottom view of the aircraft as seen from below, and FIG. 7 is a partial front view.
  • a pair of main legs 13 are disposed so as to straddle the fuselage 11 and the left and right main wings 12.
  • the main leg 13 is accommodated in the leg storage chamber 14.
  • Each main leg 13 has two tires 20, an axle 16 between them, a pedestal 17 that supports the axle 16, and a side brace (lateral support) 18.
  • a region including the axle 16 and the pedestal 17 is referred to as a main leg inter-car part 19.
  • FIG. 8 is a perspective view showing a configuration in which the perforated plate 21 is disposed in the main leg inter-car space 19.
  • 9 is a perspective view of the porous plate 21
  • FIG. 10 is a front view of the porous plate 21
  • FIG. 11 is a partially enlarged view of FIG.
  • the perforated plate 21 has a shape that covers the front side of the main landing gear part 19 and is disposed at a predetermined distance from the main landing gear part 19.
  • the perforated plate 21 is made of, for example, punching metal.
  • the perforated plate 21 is disposed so as to be slightly inclined from the direction orthogonal to the flight direction of the aircraft 10.
  • the perforated plate 21 is bent toward the flight direction of the aircraft 10 and has a bent region 51 having a concave R shape on the flight direction side over the entire circumference of the end.
  • the bent region 51 is configured, for example, by bending the end of the perforated plate 21 forward.
  • Fig. 12 shows the frequency distribution of noise.
  • a case where a flat perforated plate is disposed (1) and a case where a perforated plate 21 (a perforated plate according to the present embodiment) which is bent forward at the end portion is disposed forward (2) are shown.
  • FIG. 13 shows these differences. It can be seen that the porous plate 21 according to the present embodiment has a low noise level over a wide band as compared with a flat plate-like porous plate.
  • the perforated plate 21 according to the present embodiment can increase the amount of noise reduction in the main-legs inter-car part 19.
  • FIG. 14 is a front view showing a configuration in which the porous plate 22 is arranged on the side brace 18.
  • FIG. 15 is a cross-sectional view of the perforated plate 22 and the side brace 18.
  • the perforated plate 22 has a shape that covers the front side of the side brace 18 and is arranged at a predetermined interval from the side brace 18.
  • the porous plate 22 is made of, for example, punching metal.
  • the perforated plate 22 is arranged at a predetermined angle with the flight direction of the aircraft 10. The arrangement of the perforated plate 22 is also included in the “arrangement so as to face the flow of fluid”.
  • the perforated plate 22 has a curved region 52 having a concave R shape on the flight direction side over the entire circumference of the end.
  • the bent region 52 is configured, for example, by bending the end of the perforated plate 22 forward.
  • the perforated plate 22 may be disposed so as to contact the front side of the side brace 18, as shown in FIG.
  • FIG. 17A to 17E, FIG. 18, FIG. 19, FIG. 20, FIG. 29, and FIG. 30 show the evaluation results by numerical analysis.
  • FIG. 17A is a cross-sectional flow velocity distribution and an in-plane streamline (FIG. 17A (1)) when the side brace 18 is arranged as it is in the fluid flow in which the flow is flowing from the lower left to the upper right at an angle of 12.5 degrees.
  • the cross-sectional pressure fluctuation distribution (891 Hz to 1122 Hz) (FIG. 17A (2)) is shown.
  • FIG. 17B shows the cross-sectional flow velocity distribution and in-plane streamlines (FIG. 17B (1)) and cross-sectional pressure fluctuation distribution (891 Hz to 1122 Hz) (FIG. 17B (2) when a flat plate is placed in front of the side brace 18 )).
  • FIG. 17C shows the cross-sectional flow velocity distribution and in-plane streamlines (FIG. 17C (1)) and cross-sectional pressure fluctuation distribution (891 Hz to 1122 Hz) when a flat porous plate is disposed in front of the side brace 18 (FIG. 17C (2)). ).
  • FIG. 17D shows a case where a perforated plate (a perforated plate 22 according to the present embodiment) bent in front of an end of a plate on a flat plate is disposed in front of the side brace 18, that is, an end of the plate on the flat plate in FIG. 17B.
  • the cross-sectional flow velocity distribution and the in-plane streamline (FIG. 17D (1)) and the cross-sectional pressure fluctuation distribution (891 Hz to 1122 Hz) (FIG. 17D (2)) in a form in which the portion is perforated and bent forward are shown.
  • FIG. 17E shows a case where a perforated plate (a perforated plate 22 according to the present embodiment) bent forward at the end is disposed in front of the side brace 18, that is, the end of the perforated plate on the flat plate of FIG.
  • the cross-sectional flow velocity distribution and the in-plane streamline (FIG. 17E (1)) and the cross-sectional pressure fluctuation distribution (891 Hz to 1122 Hz) (FIG. 17E (2)) in a bent form are shown.
  • FIG. 17C (1), FIG. 17D (1), and FIG. 17E (1) compared to the case where no flat plate is present in the front as shown in FIG. 17A (1) and FIG. ),
  • the flow speed around the side brace 18 becomes slow due to the presence of the porous plate in the front.
  • FIG. 17B (1) and FIG. 17D (1), and FIG. 17C (1) and FIG. 17E (1) are compared, the perforated plate is bent forward by the perforated plate (the perforated plate 22 according to this embodiment). The difference in speed behind the end of is reduced, and the shear layer is weakened.
  • FIG. 17B (2), FIG. 17D (2), and FIG. 17C (2) with FIG. 17E (2) the pressure fluctuation behind the end of the perforated plate is caused by using the perforated plate according to this embodiment. It can be seen that the large area has been drastically reduced.
  • FIG. 29 shows the frequency distribution of noise.
  • FIG. 17A shows the case (1)
  • FIG. 17B shows the case (2)
  • FIG. 17C shows the case (3)
  • FIG. 17D shows the case (4)
  • FIG. 30 shows these differences, that is, (2)-(1), (3)-(1), (4)-(1) and (5)-(1) in FIG. From these results, it is understood that the noise level is low over a wide band by using the porous plate 22 according to the present embodiment.
  • FIG. 18 shows the frequency distribution of the noise as a result of the three-dimensional numerical analysis using the three-dimensional shape of the side brace and the leg storage portion in the form shown in FIG.
  • the side brace 18 is disposed in the fluid flow as it is (1), and when the perforated plate (the perforated plate 22 according to the present embodiment) in front of the side brace 18 is disposed in contact with the front end of the side brace 18 (2) shows a case (3) in which a perforated plate (a perforated plate 22 according to the present embodiment) that is bent forward at the end is disposed in front of the side brace 18.
  • FIG. 19 shows these differences, that is, (2)-(1) in FIG. 18 and (3)-(1) in FIG. From these results, it is understood that the noise level is low over a wide band by using the porous plate 22 according to the present embodiment.
  • FIG. 20 shows the noise level (OASPL) synthesized by adding the A characteristic audibility correction around the side brace 18 and summing the levels for each frequency band from 38 Hz to 10.7 kHz.
  • the angle in the graph indicates the angle formed by the fluid flow.
  • 21A and 21B are diagrams for explaining the cause of noise generated in the leg storage chamber 14.
  • FIG. 21A when the air flow passes through the leg storage chamber 14, a strong shear layer is generated due to a speed difference (pressure difference) with the air in the leg storage chamber 14, and a vortex is gradually generated. Will grow.
  • the grown vortex continuously hits, for example, the rear edge region 14a of the leg storage chamber 14, and the pressure fluctuation propagates upstream to form a feedback loop that induces the vortex vibration to generate a narrow band sound. .
  • the pressure fluctuation increases, and noise is generated therefrom.
  • FIG. 21B a vortex hits the pedestal 17 of the leg storage chamber 14, and noise is generated therefrom.
  • FIG. 22 is a view showing an example in which the deflector 24 is arranged along the front edge 14b of the leg storage chamber 14.
  • the deflector 24 is a member having a slope whose height gradually increases from the front toward the leg storage chamber 14.
  • FIG. 23 is a view showing an example in which the porous plate 23 according to the present embodiment is arranged along the front edge 14b of the leg storage chamber 14. As shown in FIG. FIG. 24 is a perspective view thereof, and FIG. 25 is a partially enlarged perspective view of the porous plate 23.
  • the perforated plate 23 has a long shape along the front edge 14 b of the leg storage chamber 14.
  • the perforated plate 23 is made of, for example, punching metal.
  • the perforated plate 23 has a curved region having a concave R shape on the flight direction side.
  • the bent region 52 is configured by, for example, bending the perforated plate 23 forward.
  • the direction of fluid flow is deflected from the bottom to the top of the perforated plate 23 in the figure. It becomes easy to pass through the porous plate 23.
  • the difference in velocity between the air A passing through the bent region 52 and the air B outside the end thereof becomes small, the shear layer itself of the fluid flow between them and the fluctuation thereof are weakened, and the vortex generated by the shear layer Weakens or no vortex is generated.
  • the shear layer can be shifted away from the cavity like the deflector 24. Therefore, the pressure fluctuation in the rear edge region 14a of the leg storage chamber 14 is reduced, and the noise generated therefrom is reduced. Further, noise generated from the pedestal 17 in FIG. 21B is also reduced.
  • FIG. 26A shows a cross-sectional pressure fluctuation distribution when the deflector 24 and the porous plate 23 are not installed.
  • FIG. 26B shows a cross-sectional pressure fluctuation distribution when the deflector 24 is installed.
  • FIG. 26C shows the cross-sectional pressure fluctuation distribution when the porous plate 23 according to the present embodiment is installed.
  • FIG. 27 shows the frequency distribution of noise.
  • the case where the deflector 24 and the porous plate 23 are not installed (1), the case where the deflector 24 is installed (2), and the case where the porous plate 23 according to the present embodiment is installed (3) are shown.
  • FIG. 28 shows these differences, that is, (1)-(2) in FIG. 24 and (1)-(3) in FIG. From these results, it is understood that the noise level is low over a wide band by using the porous plate 23 according to the present embodiment.
  • the present invention is not limited to the above-described embodiment, and can be applied to various fields.
  • the scope of application also belongs to the technical scope of the present invention.
  • the porous plate according to the present invention is arranged on the side brace of the main leg of the aircraft, but the porous plate according to the present invention is arranged not only on the main leg but also on the side brace of the other leg. May be. Moreover, you may arrange
  • the present invention can be applied to each part of an aircraft, it can be applied to various fields such as automobiles, buildings, wind power generation facilities, and the like.
  • Noise reduction device 2 Perforated plate 3: Object 4: Direction 5: Bending area 6: End 10: Aircraft 13: Main leg 14: Leg storage room 14a: Area 14b: Front edge 15: Main leg inter-car part 18: Side brace 19: main pedestal space 21: perforated plate 22: perforated plate 23: perforated plate 51: bent region 52: bent region

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Engineering & Computer Science (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
  • Tires In General (AREA)
PCT/JP2019/002065 2018-02-26 2019-01-23 騒音低減装置、航空機及び騒音低減方法 Ceased WO2019163379A1 (ja)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP19756790.2A EP3760882B1 (en) 2018-02-26 2019-01-23 Noise reducing device, aircraft, and noise reduction method
US16/976,020 US11577823B2 (en) 2018-02-26 2019-01-23 Noise reduction apparatus, aircraft, and noise reduction method

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2018031578A JP6631977B2 (ja) 2018-02-26 2018-02-26 騒音低減装置、航空機及び騒音低減方法
JP2018-031578 2018-02-26

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US (1) US11577823B2 (enExample)
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WO (1) WO2019163379A1 (enExample)

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EP3992079A1 (en) * 2020-10-28 2022-05-04 Airbus Defence and Space GmbH Flow body for a vehicle and method for manufacturing a flow body
US11485471B2 (en) * 2017-08-25 2022-11-01 United States Of America As Represented By The Administrator Of Nasa Application of leading edge serration and trailing edge foam for undercarriage wheel cavity noise reduction

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* Cited by examiner, † Cited by third party
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EP3560826B1 (en) * 2018-04-25 2022-11-30 Safran Landing Systems UK Ltd Noise reduction fairing
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US11577823B2 (en) 2023-02-14
US20210039773A1 (en) 2021-02-11
EP3760882A1 (en) 2021-01-06
EP3760882B1 (en) 2025-08-27
JP6631977B2 (ja) 2020-01-15
JP2019148266A (ja) 2019-09-05

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