Silencer

Abstract

To provide a noise suppressor which conducts tests of an airframe properly and is easily implemented with an existing noise suppressor.SOLUTION: A noise suppressor includes: an airframe housing part which forms a housing chamber for housing an airframe with a floor part on which the airframe of an aircraft having an engine is disposed, a wall part surrounding front, rear, left, and right sides of the airframe, and a ceiling part disposed above the airframe and in which a suction port is formed in front of the airframe and an exhaust port is formed behind the airframe; and airflow adjustment members which are provided at the housing chamber and can be respectively arranged at use positions, located between the suction port and the engine in a front-rear direction, so as to cover the airframe side while clearing a center part as seen in at least one of a vertical direction and a lateral direction when viewed from the front of the airframe.SELECTED DRAWING: Figure 1

Description

[Technical field]

[0001] The present disclosure relates to a sound deadening device. [Background technology]

[0002] A noise suppression device for conducting operational tests of an aircraft body is known (see, for example, Patent Document 1). Such a noise suppression device has an aircraft housing section for housing the aircraft body, and is configured such that an intake port for taking in air when the engine is running and an exhaust port for discharging gas discharged from the engine are provided in the aircraft housing section. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Publication No. 11-152095 Summary of the Invention [Problem to be solved by the invention]

[0004] In the above-mentioned noise suppression device, the aircraft housing is formed to be large enough so that the wings do not interfere with the walls or the ceiling when the entire aircraft is stored. In this configuration, a large space is formed between the aircraft and the left and right walls and ceiling of the aircraft housing. In this case, air taken in from the intake port when the engine is running flows through this space along the aircraft, the walls and the ceiling, forming a swirling flow. Depending on the type of aircraft, the swirling flow may cause the engine operation to become unstable.

[0005] The silencer described in Patent Document 1 is configured to gradually narrow the rear of the engine by inclining the aircraft housing section toward the center in the left-right direction, thereby suppressing the generation of swirling flow. However, although this configuration makes it possible to properly test the aircraft, it is necessary to implement this configuration in advance when installing a new silencer, and it is difficult to install it by modifying an existing silencer.

[0006] The present disclosure has been made in consideration of the above, and aims to provide a noise suppression device that enables appropriate testing of an aircraft and can be easily implemented on existing noise suppression devices. [Means for solving the problem]

[0007] The noise reduction device of the present disclosure comprises an aircraft accommodation section which defines a storage compartment for accommodating the aircraft, the storage compartment being made up of a floor section on which the fuselage of an aircraft having an engine is placed, walls which surround the front, rear, left and right sides of the fuselage, and a ceiling section which is arranged above the fuselage, the storage compartment having an air intake port formed at the front of the fuselage and an exhaust port formed at the rear of the fuselage, and an airflow adjustment member which is provided in the storage compartment and can be arranged at a usage position between the air intake port and the engine in the front-to-rear direction so as to cover the aircraft side, leaving a central portion in at least one of the up-down and left-right directions when viewed from the front of the aircraft empty. Effect of the Invention

[0008] According to the present disclosure, it is possible to provide a noise suppression device that enables proper testing of an aircraft and can be easily implemented on an existing noise suppression device. [Brief description of the drawings]

[0009] [Figure 1] FIG. 1 is a diagram showing an example of a noise suppressor according to the present embodiment. [Diagram 2] FIG. 2 is a diagram showing an example of a noise suppressor according to the present embodiment. [Diagram 3] FIG. 3 is a diagram showing an example of a noise suppressor according to the present embodiment. [Figure 4] FIG. 4 is a diagram showing the operation of the noise suppressor according to the comparative example. [Diagram 5] FIG. 5 is a diagram showing the operation of the noise suppressor according to the comparative example. [Figure 6] FIG. 6 is a diagram showing an example of the operation of the noise suppressor according to this embodiment. [Figure 7] FIG. 7 is a diagram showing an example of the operation of the noise suppressor according to this embodiment. [Figure 8]FIG. 8 is a diagram showing a noise suppressor according to another example. [Figure 9] FIG. 9 is a diagram showing a noise suppressor according to another example. [Figure 10] FIG. 10 is a diagram showing a noise suppressor according to another embodiment. [Figure 11] FIG. 11 is a diagram showing a noise suppressor according to another embodiment. [Figure 12] FIG. 12 is a diagram showing a noise suppressor according to another example. [Figure 13] FIG. 13 is a diagram showing a noise suppressor according to another example. [Figure 14] FIG. 14 is a diagram showing a noise suppressor according to another example. [Figure 15] FIG. 15 is a diagram showing another example of the noise suppressor according to the present embodiment. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0010] Hereinafter, an embodiment of the noise suppression device according to the present disclosure will be described with reference to the drawings. Note that the present invention is not limited to this embodiment. In addition, the components in the following embodiments include those that are replaceable and easy for a person skilled in the art, or those that are substantially the same.

[0011] 1 to 3 are diagrams showing an example of a silencer 100 according to this embodiment. FIG. 1 is a cross-sectional view seen from above, FIG. 2 is a cross-sectional view seen from the side (cross-sectional view taken along line AA in FIG. 1), and FIG. 3 is a cross-sectional view seen from the front (cross-sectional view taken along line BB in FIG. 2). As shown in FIG. 1 to FIG. 3, the silencer 100 includes an aircraft housing section 10 and an airflow adjustment member 20. The silencer 100 is used as a test device for housing an aircraft body B inside the aircraft housing section 10 and performing a test run of the aircraft B. In this embodiment, when describing the direction of the silencer 100, the front-rear direction, left-right direction, and up-down direction of the aircraft B housed in the aircraft housing section 10 in a housed state are defined as the front-rear direction, left-right direction, and up-down direction of the silencer 100. In this embodiment, the aircraft B has an engine EG. When performing a test run of the aircraft B, the engine EG is driven. The engine EG draws air from the front. The engine EG discharges exhaust gases to the rear.

[0012] The body storage section 10 has a floor 11, a wall 12, and a ceiling 13. The floor 11, the wall 12, and the ceiling 13 form a storage chamber K for storing the body B.

[0013] The floor section 11 is where the fuselage B of the aircraft is placed. The floor section 11 is disposed along a horizontal plane.

[0014] The wall portion 12 is disposed on the floor portion 11. The wall portion 12 is disposed along the four sides of a rectangle in a plan view so as to surround the front, rear, left and right sides of the vehicle body B. At least a part of the wall portion 12 can be provided with a sound absorbing material for absorbing sounds generated during a test run of the vehicle body B. The wall portion 12 has a front wall portion 12a, a rear wall portion 12b, a left wall portion 12c and a right wall portion 12d. The front wall portion 12a is disposed in front of the vehicle body B, i.e., in the front part of the storage room K. The rear wall portion 12b is disposed in the rear of the vehicle body B, i.e., in the rear part of the storage room K. An exhaust port 15 is provided in the rear wall portion 12b. The exhaust port 15 is provided by penetrating the rear wall portion 12b. The left wall portion 12c is disposed on the left side of the vehicle body B, i.e., in the left part of the storage room K. The right wall portion 12d is disposed on the right side of the vehicle body B, i.e., in the right part of the storage room K.

[0015] The ceiling 13 is disposed above the body B, i.e., at the top of the accommodation chamber K. An air intake 14 is provided at the front end of the ceiling 13. The air intake 14 is provided penetrating the ceiling 13. The air intake 14 is rectangular and is formed over the entire left-right direction. The air intake 14 is connected to an air intake duct 17. The air intake duct 17 extends rearward from the air intake 14 and is further bent upward. An open port 18 is provided at the upper end of the air intake duct 17. An internal air intake passage 17a of the air intake duct 17 connects between the open port 18 and the air intake 14. The air intake duct 17 is configured to absorb sound generated by the body B when the body B is test-run in the accommodation chamber K.

[0016] The airflow adjustment member 20 is provided in the storage chamber K. The airflow adjustment member 20 adjusts the flow of air in the storage chamber K. Specifically, the airflow adjustment member 20 blocks a portion of the air taken in from the intake port 14, thereby suppressing air from flowing behind the airflow adjustment member 20.

[0017] The airflow adjustment member 20 is formed, for example, in a rectangular shape. The airflow adjustment member 20 is formed so that the dimension (height) in the up-down direction is approximately the same as that of the wall portion 12. The airflow adjustment member 20 can be formed in a mesh shape. In this case, the airflow adjustment member 20 can be made of a wire mesh of, for example, about 10 mesh. The size of the mesh of the airflow adjustment member 20 is not limited to 10 mesh, and may be other sizes. For example, the size of the mesh may be changed depending on the model of the aircraft B. The airflow adjustment member 20 is not limited to a mesh shape, and may be, for example, a plate shape without mesh.

[0018] The airflow adjustment members 20 are disposed at both ends in the left-right direction of the storage chamber K. The airflow adjustment members 20 are attached to the left side wall portion 12c and the right side wall portion 12d, for example, via pivot shafts 21. The pivot shafts 21 are disposed parallel to the up-down direction. The airflow adjustment members 20 are provided so as to be rotatable about the pivot shafts 21. The airflow adjustment members 20 are movable between a use position P1 and a standby position P2 by pivoting about the pivot shafts 21.

[0019] The use position P1 is a position between the intake port 14 and the engine EG of the aircraft B in the front-rear direction. The use position P1 is a position for adjusting the airflow that is sucked in from the intake port 14 by the drive of the engine EG and flows rearward during a test run of the aircraft B. The use position P1 can be appropriately set according to the specifications of the engine EG in the aircraft B, such as the position and size, as long as it is a position between the intake port 14 and the engine EG in the front-rear direction. The use position P1 can be set based on the results of, for example, experiments or simulations performed in advance. In this embodiment, the use position P1 is a position where the airflow adjustment member 20 is arranged inclined with respect to the walls 12 on both sides in the left-right direction (the left side wall portion 12c and the right side wall portion 12d). In this embodiment, the use position P1 is a position where the airflow adjustment member 20 is arranged at an angle of 90° with respect to the left side wall portion 12c and the right side wall portion 12d. The use position P1 may be a position in which the airflow adjustment member 20 is inclined at an angle other than 90° with respect to the left side wall portion 12c and the right side wall portion 12d.

[0020] Here, the airflow adjustment member 20 when placed at the use position P1 will be described. At the use position P1, the airflow adjustment member 20 is placed so as to cover the rear of the storage chamber K, leaving the center in the left-right direction open. The airflow adjustment member 20 is placed so as to cover both sides in the left-right direction of the storage chamber K. The airflow adjustment member 20 is placed from both ends of the storage chamber K toward the center in the left-right direction. In other words, the airflow adjustment member 20 is placed so as to cover both ends in the left-right direction of the storage chamber K. The airflow adjustment member 20 is also provided from the upper end to the lower end of the storage chamber K in the up-down direction. The airflow adjustment member 20 is placed so as to be symmetrical in the left-right direction.

[0021] The standby position P2 is a position where the airflow adjustment member 20 waits when not in use. The standby position P2 is a position where the airflow adjustment member 20 is disposed along the walls 12 on both sides in the left-right direction (the left side wall 12c and the right side wall 12d). In other words, when the airflow adjustment member 20 is disposed in the standby position P2, it is disposed along the left side wall 12c and the right side wall 12d, respectively.

[0022] The airflow adjustment member 20 is provided with casters (not shown) at the bottom to move between the use position P1 and the standby position P2. The airflow adjustment member 20 may be provided with stoppers (not shown) that can restrict movement in the rotation direction at the use position P1 and the standby position P2.

[0023] Next, a description will be given of the operation of the noise suppressor 100 configured as above. In describing the operation of the noise suppressor 100, a noise suppressor 200 not provided with the airflow adjustment member 20 described above will be described as a comparative example.

[0024] 4 and 5 are diagrams for explaining the operation of the noise suppression device 200 according to the comparative example. The noise suppression device 200 is not provided with a configuration corresponding to the above-mentioned airflow adjustment member 20. In this configuration, when testing the airframe B, the airframe B of the aircraft is placed on the floor 111 of the airframe storage section 110, and the engine EG of the airframe B is driven.

[0025] When the engine EG is driven, air is drawn into the accommodation chamber K2 of the aircraft housing section 110 through the intake port 114. The air drawn into the accommodation chamber K2 flows rearward toward the engine EG. As shown in Figs. 4 and 5, the air flowing through the accommodation chamber K2 flows along the aircraft B, the walls 112 on both the left and right sides of the accommodation chamber K2, and the ceiling 113, generating a swirling flow. Depending on the model of the aircraft B, the engine EG may suck in the swirling flow, causing the operation to become unstable.

[0026] 6 and 7 are diagrams for explaining the operation of the noise suppression device 100. In the noise suppression device 100, when the aircraft body B is not being tested, the airflow adjustment member 20 is placed in the standby position P2. When the aircraft body B is to be tested from this state, the aircraft body B is placed on the floor 11 of the aircraft body storage section 10, and the airflow adjustment member 20 is moved from the standby position P2 to the usage position P1.

[0027] From this state, the engine EG of the aircraft B is driven. By driving the engine EG, air is sucked from the open port 18 into the intake passage 17a inside the intake duct 17, and further sucked into the accommodation chamber K of the aircraft accommodation section 10 from the intake port 14. When air is sucked from the intake port 14 arranged above the accommodation chamber K, a small vortex may be generated, but this vortex does not affect the engine EG. The air sucked into the accommodation chamber K flows backward toward the engine EG. In this embodiment, the airflow adjustment member 20 is arranged at the use position P1 between the intake port 14 and the engine EG in the front-rear direction. Therefore, the air flowing through the accommodation chamber K bypasses the airflow adjustment member 20 and flows backward from the center in the left-right direction. In other words, the air flowing through the accommodation chamber K flows backward from the space between the left and right airflow adjustment members 20. Therefore, the air is prevented from flowing toward the left side wall portion 12c and the right side wall portion 12d of the accommodation chamber K, and the generation of a swirling flow is suppressed. Furthermore, in this embodiment, the airflow adjustment members 20 are arranged symmetrically in the left-right direction, so that turbulence of the airflow is suppressed.

[0028] As described above, the noise reduction device 100 of this embodiment is provided with a floor section 11 on which the fuselage B of an aircraft having an engine EG is placed, walls 12 surrounding the front, rear, left and right sides of the fuselage B, and a ceiling section 13 arranged above the fuselage B, which form a storage compartment K for accommodating the fuselage B, and is equipped with an aircraft storage section 10 in which an air intake 14 is formed at the front of the fuselage B and an exhaust port 15 is formed at the rear of the fuselage B, and an airflow adjustment member 20 which is provided in the storage compartment K and can be positioned at a usage position P1 between the air intake 14 and the engine EG in the fore-and-aft direction so as to cover the fuselage B side, leaving the central portion in the vertical direction when viewed from the front of the aircraft B empty.

[0029] In this configuration, by disposing the airflow adjustment member 20 at the usage position P1, the air flowing through the accommodation chamber K when the engine EG is running flows from the center in the left-right direction rearward, bypassing the airflow adjustment member 20. Therefore, air is prevented from flowing toward the wall portions 12 on both the left and right sides of the accommodation chamber K, and the generation of a swirling flow is suppressed. This makes it possible to prevent the operation of the engine EG from becoming unstable, and makes it possible to properly test the aircraft B. In addition, since this can be achieved by disposing the airflow adjustment member 20 at the usage position P1, it can be easily implemented in existing silencers.

[0030] In the silencer 100 according to this embodiment, the airflow adjustment member 20 is provided so as to be movable between a use position P1 and a standby position P2 along at least one of the wall 12 and the ceiling 13. Therefore, when the airflow adjustment member 20 is used, it is placed at the use position P1, and when not used, it can be kept on standby at the standby position P2. For this reason, when testing different models, such as an aircraft B that is easily affected by a swirling flow and an aircraft B that is not easily affected by a swirling flow, a test environment suitable for each model can be easily realized by switching the position of the airflow adjustment member 20 according to the model.

[0031] In the silencer 100 according to this embodiment, the airflow adjustment member 20 is attached via a rotating shaft 21 and is provided so as to be rotatable about the rotating shaft 21 between a use position P1 and a standby position P2, the standby position P2 being a position where the airflow adjustment member 20 is disposed along the wall portions 12 on both left-right sides or the floor portions 11 and ceiling portion 13 on both up-down sides, and the use position P1 being a position where the airflow adjustment member 20 is disposed at an angle to the wall portions 12 on both left-right sides or the floor portions 11 and ceiling portion 13 on both up-down sides. Therefore, the airflow adjustment member 20 can be easily moved between the use position P1 and the standby position P2.

[0032] In the noise suppression device 100 according to this embodiment, the airflow adjustment members 20 are arranged symmetrically in the left-right direction at the use position P1, which makes it possible to more reliably suppress the occurrence of swirling flows.

[0033] In the noise suppression device 100 according to this embodiment, the airflow adjustment members 20 are disposed on both left and right sides of the accommodation chamber K. Therefore, it is possible to suppress air from flowing to the left side wall portion 12c side and the right side wall portion 12d side of the accommodation chamber K when the engine EG is running.

[0034] In the noise suppression device 100 according to this embodiment, the air intake 14 is provided at the front end of the ceiling portion 13. This allows the aircraft housing portion 10 to have a compact configuration. Furthermore, since the air intake 14 is not provided in the wall portion 12, it is possible to suppress the generation of an air flow caused by the intake of air around the wall portion 12. This allows the area around the wall portion 12 to be used as a passageway or the like.

[0035] In the noise suppression device 100 according to this embodiment, the airflow adjustment member 20 is formed in a mesh shape. This makes it possible to reduce the weight of the airflow adjustment member 20. In addition, the wind pressure that the airflow adjustment member 20 receives can be reduced.

[0036] Fig. 8 to Fig. 10 are diagrams showing a noise suppression device 100A according to another example. Fig. 8 shows a cross-sectional view seen from above, Fig. 9 shows a cross-sectional view seen from the side, and Fig. 10 shows a cross-sectional view seen from the front. As shown in Fig. 8 to Fig. 10, the noise suppression device 100A includes a machine body storage section 10 and an airflow adjustment member 20A. The machine body storage section 10 can have the same configuration as in the above embodiment.

[0037] In the silencer 100A, the airflow adjustment members 20A are disposed on both sides in the up-down direction of the accommodation chamber K. The airflow adjustment members 20A are attached to the floor 11 and the ceiling 13, for example, via pivot shafts 21A. The pivot shafts 21A are disposed parallel to the left-right direction. The airflow adjustment members 20A are provided rotatable about the pivot shafts 21A. The airflow adjustment members 20A are movable between a use position P3 and a standby position P4 by pivoting about the pivot shafts 21A.

[0038] As in the above embodiment, the use position P3 is a position in the front-rear direction between the intake port 14 and the engine EG of the aircraft B. In the noise suppression device 100A, the use position P3 is a position where the airflow adjustment member 20 is disposed at an angle of 90° with respect to the floor 11 and the ceiling 13. Note that the use position P3 may be a position where the airflow adjustment member 20 is disposed at an angle other than 90° with respect to the left side wall 12c and the right side wall 12d.

[0039] When the airflow adjustment member 20 is disposed at the usage position P3, it is disposed so as to cover the rear of the storage chamber K. When the airflow adjustment member 20 is disposed at the usage position P3, it is disposed so as to leave the center in the up-down direction open when viewed from the front. In this embodiment, the airflow adjustment member 20 is disposed so as to cover both sides in the up-down direction of the storage chamber K by the left-right dimension of the storage chamber K, for example. When the airflow adjustment member 20 is disposed at the usage position P3, it is disposed so as to be symmetrical in the left-right direction.

[0040] The standby position P4 is a position along the floor portion 11 and the ceiling portion 13. When the airflow adjustment member 20 is disposed in the standby position P4, the airflow adjustment member 20 is disposed along the floor portion 11 and the ceiling portion 13, respectively.

[0041] When the sound deadening device 100A is used to test the aircraft B, air is drawn into the accommodation chamber K of the aircraft accommodation section 10 from the intake port 14 by driving the engine EG. The air drawn into the accommodation chamber K flows rearward toward the engine EG. In this embodiment, the airflow adjustment member 20A is disposed at the use position P1 between the intake port 14 and the engine EG in the front-rear direction. Therefore, the air flowing through the accommodation chamber K bypasses the airflow adjustment member 20A and flows rearward from the center in the vertical direction. In other words, the air flowing through the accommodation chamber K flows rearward from the space between the upper and lower airflow adjustment members 20A. Therefore, the air is prevented from flowing toward the floor 11 side and the ceiling 13 side of the accommodation chamber K, and the generation of a swirling flow is prevented.

[0042] In this way, in the noise suppression device 100A, the airflow adjustment members 20A are disposed on both sides in the up-down direction of the accommodation chamber K. Therefore, it is possible to suppress air from flowing toward the floor 11 side and the ceiling 13 side of the accommodation chamber K when the engine EG is running. This makes it possible to suppress the operation of the engine EG from becoming unstable, and makes it possible to properly perform the testing of the aircraft B.

[0043] Fig. 11 to Fig. 13 are diagrams showing a noise suppression device 100A according to another example. Fig. 11 shows a cross-sectional view seen from above, Fig. 12 shows a cross-sectional view seen from the side, and Fig. 13 shows a cross-sectional view seen from the front. As shown in Fig. 11 to Fig. 13, the noise suppression device 100B includes a machine body storage section 10 and an airflow adjustment member 20B. The machine body storage section 10 can have the same configuration as in the above embodiment.

[0044] In the silencer 100B, the airflow adjustment member 20B is disposed on both the left and right sides of the accommodation chamber K. The airflow adjustment member 20B is attached to the left wall portion 12c and the right wall portion 12d, for example, via a rotating shaft 21B. The rotating shaft 21B is disposed parallel to the up-down direction. The airflow adjustment member 20B is attached to the rotating shaft 21B via a connecting portion 22B. The airflow adjustment member 20B is provided so as to be rotatable about the rotating shaft 21B. The airflow adjustment member 20B is movable between a use position P5 and a standby position P6 by rotating about the rotating shaft 21B.

[0045] The use position P5 is a position between the intake port 14 and the engine EG of the aircraft B in the front-rear direction, as in the above embodiment. Here, the airflow adjustment member 20B when placed in the use position P5 will be described. In the use position P5, the airflow adjustment member 20B is placed so as to cover a portion in the left-right direction. In the use position P5, the airflow adjustment member 20B is placed so as to leave both ends and the center in the left-right direction open. In addition, the airflow adjustment member 20B is placed so as to leave the upper end and lower end of the storage chamber K open in the up-down direction. The airflow adjustment member 20B is placed so as to be symmetrical in the left-right direction.

[0046] The standby position P6 is a position along the left side wall 12c and the right side wall 12d. When the airflow adjustment member 20B is disposed in the standby position P6, the airflow adjustment member 20B is disposed along the left side wall 12c and the right side wall 12d, respectively.

[0047] When testing the aircraft B using the silencer 100B, air is drawn into the accommodation chamber K of the aircraft accommodation section 10 from the intake port 14 by driving the engine EG. The air drawn into the accommodation chamber K flows rearward toward the engine EG. In this embodiment, the airflow adjustment member 20B is disposed at a usage position P5 between the intake port 14 and the engine EG in the front-rear direction. Therefore, the air flowing through the accommodation chamber K flows rearward, bypassing the airflow adjustment member 20B. In other words, the air flowing through the accommodation chamber K is partially blocked by the airflow adjustment member 20B. By blocking a portion of the air flowing through the accommodation chamber K, the generation of a swirling flow is suppressed.

[0048] Fig. 14 is a diagram showing a noise suppression device 100C according to another example. Fig. 14 shows a cross-sectional view seen from the side. As shown in Fig. 14, the noise suppression device 100C includes a machine body storage section 10 and an airflow adjustment member 20C. The machine body storage section 10 can have the same configuration as in the above embodiment.

[0049] The airflow adjustment member 20C is provided so as to be able to be wound around a winding shaft 21C. The winding shafts 21C are provided, for example, on both the left and right sides of the ceiling portion 13, and are arranged parallel to each other in the left-right direction. By rotating the winding shaft 21C in one direction, the airflow adjustment member 20C is wound around the winding shaft 21C. By rotating the winding shaft 21C in multiple directions, the airflow adjustment member 20C is unwound downward from the winding shaft 21C. The airflow adjustment member 20C is able to move between a use position P7 and a standby position P8 by being wound around the winding shaft 21C and being unwound from the winding shaft 21C.

[0050] As in the above embodiment, the use position P7 is a position between the intake port 14 and the engine EG of the aircraft body B in the front-rear direction. The use position P7 is a position where the airflow adjustment member 20C is unwound from the winding shaft 21C. When placed at the use position P7, the airflow adjustment member 20C can be configured to cover the same range as the above-mentioned airflow adjustment members 20, 20A, and 20B, for example. At the use position P7, the lower end of the airflow adjustment member 20C can be fixed to the floor 11 by a fixing part (not shown).

[0051] The standby position P8 is a position where the airflow adjustment member 20C is wound around the winding shaft 21C. The winding shaft 21C is surrounded by a storage case 22C. The storage case 22C stores the airflow adjustment member 20C that is wound around the winding shaft 21C. At the standby position P8, the airflow adjustment member 20C is wound around the winding shaft 21C and stored in the storage case 22C.

[0052] In the noise suppressor 100C, the airflow adjustment member 20C is provided so as to be able to be wound around a winding shaft 21C, the standby position P8 is a position where the airflow adjustment member 20C is wound around the winding shaft 21C, and the use position P7 is a position where the airflow adjustment member 20C is unwound from the winding shaft 21C. With this configuration, the airflow adjustment member 20C can be moved between the use position P7 and the standby position P8 by a configuration different from the configuration where the airflow adjustment member 20C is rotated around a rotation shaft.

[0053] The technical scope of the present invention is not limited to the above embodiment, and can be modified as appropriate without departing from the spirit of the present invention. For example, in the above embodiment, the inclination of the airflow adjustment member in the front-rear direction is constant in the use position, but the present invention is not limited to this.

[0054] Fig. 15 is a diagram showing another example of the usage mode of the silencer 100. As shown in Fig. 15, the inclination of the airflow adjustment member 20 in the front-rear direction may be adjustable at the usage position P1. In this case, the adjustment may be performed by manually changing the inclination of the airflow adjustment member 20 by an operator, or the adjustment may be performed automatically by changing the inclination of the airflow adjustment member 20 by a driving mechanism (not shown). With this configuration, it is possible to finely adjust the flow of air when the engine EG is running.

[0055] As described above, in the present disclosure, the noise reduction device of the first embodiment comprises an aircraft accommodation section 10 which defines an accommodation chamber K for accommodating the aircraft B, the accommodation chamber K being made up of a floor section 11 on which the aircraft B having the engine EG is placed, walls 12 which surround the front, rear, left and right sides of the aircraft B, and a ceiling section 13 which is arranged above the aircraft B, the intake port 14 being formed at the front of the aircraft B and an exhaust port 15 being formed at the rear of the aircraft B, and airflow adjustment members 20, 20A, 20B, 20C which are provided in the accommodation chamber K and can be arranged at usage positions P1, P3, P5, P7 between the intake port 14 and the engine EG in the fore-and-aft direction so as to cover the aircraft B side, leaving at least one central portion in the up-down and left-right directions when viewed from the front of the aircraft B empty.

[0056] In this configuration, by arranging the airflow adjustment members 20, 20A, 20B, and 20C at the use positions P1, P3, P5, and P7, the air flowing through the accommodation chamber K during the operation of the engine EG flows from the center in the left-right direction to the rear, bypassing the airflow adjustment members 20, 20A, 20B, and 20C. Therefore, the air is prevented from flowing toward the wall portions 12 on both the left and right sides of the accommodation chamber K, and the generation of a swirling flow is prevented. This makes it possible to prevent the operation of the engine EG from becoming unstable, and to appropriately test the aircraft B. In addition, since this can be realized by arranging the airflow adjustment members 20, 20A, 20B, and 20C at the use positions P1, P3, P5, and P7, it can be easily implemented in an existing silencer.

[0057] The noise suppression device according to the second embodiment is the noise suppression device according to the first embodiment, in which airflow adjustment members 20, 20A, 20B, 20C are provided to be movable between use positions P1, P3, P5, P7 and standby positions P2, P4, P6, P8 along at least one of the wall portion 12 and the ceiling portion 13. For example, when testing different models such as an aircraft B that is susceptible to swirling flow and an aircraft B that is not susceptible to swirling flow, the positions of the airflow adjustment members 20, 20A, 20B, 20C can be switched between the use positions P1, P3, P5, P7 and the standby positions P2, P4, P6, P8 according to the model, thereby easily realizing a test environment suitable for each model.

[0058] The noise suppression device of the third embodiment is the noise suppression device of the second embodiment, in which airflow adjustment members 20, 20A, 20B are attached via pivot shafts 21, 21A, 21B, 21D and are arranged to be rotatable around the pivot shaft 21 between use positions P1, P3, P5 and standby positions P2, P4, P6, the standby positions P2, P4, P6 are positions where the airflow adjustment members 20, 20A, 20B are arranged along the wall portions 12 on both left-right sides or the floor portions 11 and ceiling portion 13 on both up-down sides, and the use positions P1, P3, P5 are positions where the airflow adjustment members 20, 20A, 20B are arranged at an angle relative to the wall portions 12 on both left-right sides or the floor portions 11 and ceiling portion 13 on both up-down sides. Therefore, the airflow adjustment members 20, 20A, 20B can be easily moved between the use positions P1, P3, P5 and the standby positions P2, P4, P6.

[0059] The silencer according to the fourth embodiment is the silencer according to the second embodiment, in which the airflow adjustment member 20C is provided so as to be capable of being wound around a winding shaft 21C, the standby position P8 is the position where the airflow adjustment member 20C is wound around the winding shaft 21C, and the use position P7 is the position where the airflow adjustment member 20C is unwound from the winding shaft 21C. With this configuration, the airflow adjustment member 20C can be moved between the use position P7 and the standby position P8 by a configuration different from the configuration where it is rotated around a rotation shaft.

[0060] The noise suppressor according to the fifth aspect is the noise suppressor according to any one of the first to fourth aspects, in which the airflow control members 20, 20A, 20B, and 20C are arranged symmetrically in the left-right direction at the use positions P1, P3, P5, and P7, and therefore the generation of a swirling flow can be more reliably suppressed.

[0061] The noise suppressor according to the sixth aspect is the noise suppressor according to any one of the first to fifth aspects, in which the airflow adjustment members 20, 20B, 20C are arranged on both sides in the left-right direction of the accommodation chamber K. Therefore, it is possible to suppress air from flowing to the left side wall portion 12c side and the right side wall portion 12d side of the accommodation chamber K when the engine EG is running.

[0062] The noise suppressor according to the seventh aspect is the noise suppressor according to any one of the first to fifth aspects, in which airflow adjustment members 20A are disposed on both sides of the accommodation chamber K in the up-down direction.

[0063] The noise suppression device according to the eighth aspect is the noise suppression device according to any one of the first to seventh aspects, in which the air intake 14 is provided at the front end of the ceiling 13. This allows the aircraft housing section 10 to have a compact configuration. Also, since the air intake 14 is not provided in the wall 12, it is possible to suppress the generation of an air flow caused by the intake of air around the wall 12. This allows the area around the wall 12 to be used as a passage or the like.

[0064] The noise suppressor according to the ninth aspect is the noise suppressor according to any one of the first to eighth aspects, in which the inclination of the airflow adjustment member 20D in the front-rear direction is adjustable. With this configuration, it is possible to finely adjust the airflow when the engine EG is running.

[0065] The noise suppressor according to the tenth aspect is the noise suppressor according to any one of the first to ninth aspects, in which the airflow adjustment members 20, 20A, 20B, and 20C are formed in a mesh shape. This makes it possible to reduce the weight of the airflow adjustment members 20, 20A, 20B, and 20C. In addition, the wind pressure that the airflow adjustment member 20 receives can be suppressed. [Explanation of symbols]

[0066] 10,110 Aircraft housing section 11,111 Floor section 12 Wall 12a Front wall 12b Rear wall 12c Left side wall 12d Right side wall 13 Ceiling 14,114 Air intake 15 Exhaust port 17 Intake duct 17a Intake passage 18 Open mouth 20, 20A, 20B, 20C, 20D Airflow adjustment members 21, 21A, 21B, 21D Rotating shaft 21C Winding shaft 22B Connecting part 22C Storage Case 100,100A,100B,100C,200 Silencer B Aircraft EG Engine K,K2 Containment Room P1,P3,P5,P7 Usage position P2,P4,P6,P8 Standby position

Claims

1. an aircraft accommodation section that defines a storage room for accommodating an aircraft having an engine, the storage room being made up of a floor section on which an aircraft body having an engine is placed, walls surrounding the aircraft body on the front, rear, left and right sides, and a ceiling section that is placed above the aircraft body, the airframe accommodation section having an intake port formed at a front end of the ceiling section at the front of the aircraft body and an exhaust port formed at a rear of the aircraft body; an airflow adjustment member that is provided in the accommodation chamber and can be arranged at a usage position between the intake port and the engine in the front-rear direction so as to cover the aircraft side, leaving a central portion in the left-right direction as viewed from the front of the aircraft open; The airflow adjustment member is attached to the wall portions on both sides in the left-right direction via a pivot shaft, the airflow adjustment member is provided to be rotatable about the rotation axis between a use position in which the airflow adjustment member is disposed at an angle with respect to the wall portions on both sides in the left-right direction and a standby position in which the airflow adjustment member is disposed along the wall portions on both sides in the left-right direction; the pivot shaft is disposed forward of a nose of the aircraft to be tested using the airflow adjustment member; The position of the airflow adjustment member is changed depending on the type of aircraft being tested. Silencer.

2. The airflow adjustment members are disposed symmetrically in the left-right direction in the use position.

2. The noise suppressor according to claim 1.

3. A floor portion on which an aircraft body having an engine is placed, walls surrounding the aircraft body on the front, rear, left and right sides, and a front A ceiling portion disposed above the aircraft body forms a storage chamber for storing the aircraft body, a body housing section having an intake port formed in a front portion and an exhaust port formed in a rear portion of the body; The intake port is provided in the accommodation chamber at a position between the intake port and the engine in the front-rear direction. When viewed from the front of the aircraft, the center of the vertical direction is left empty, and the and an airflow adjustment member that can be arranged to cover the The airflow adjustment members are disposed on both sides of the storage chamber in the up-down direction. Silencer.

4. The airflow adjustment member is capable of adjusting the inclination in the front-rear direction.

2. The noise suppressor according to claim 1.

5. The airflow adjustment member is formed in a mesh shape.

2. The noise suppressor according to claim 1.

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