Detection device for testing aircraft

Abstract

The invention relates to a detection device for testing an aircraft, which comprises a machine table, an air duct shell, a motor located at one end of the air duct shell and fan blades arranged on a rotating shaft of the motor, the air duct shell comprises an inner shell, a plurality of through holes are formed in the radial inner wall of the inner shell, and the machine table is provided with a placing table for placing the aircraft and located in the inner shell. The fan blades can be driven by the motor to enable airflow to be generated in the inner shell, one axial end of the inner shell is an air inlet end, the other axial end of the inner shell is an air outlet end, the through holes are distributed between the air inlet end and the air outlet end, the fan blades are located at the air outlet end, and the containing table is located between the air inlet end and the air outlet end. Air outside the inner shell can enter the inner shell from the air inlet end and the through hole under the action of the fan blades, the airflow direction at the air inlet end is different from the airflow direction at the through hole, and the device has the function of testing the flight capability of the aircraft under the influence of airflow in different flow directions.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft detection, and in particular to a detection device for testing aircraft. Background Art

[0002] In daily life, with the advancement of science and technology, various small aircraft, such as drones, are widely used in various industries and fields. In order to enable aircraft to better cope with various possible flight conditions, environmental simulation tests are carried out on the flight capabilities of aircraft during the production process.

[0003] There is a small wind tunnel test device, which is mainly used to test the wind resistance of drones during flight. It includes a machine platform, which is provided with a wind tube shell and a placement platform for placing the aircraft. The placement platform is located inside the wind tube shell. A motor is arranged at one end of the wind tube shell, and fan blades are fixed on the motor shaft. When conducting the test, the drone is placed on the placement platform, then the drone is started and suspended in the air, and then the motor is started to rotate the fan blades to generate airflow, and then the flight parameters of the drone under airflow disturbance are observed.

[0004] Regarding the above solution, the inventor believes that the airflow generated by the fan blades has a relatively single direction, making it difficult to test the flight conditions of the aircraft facing airflows in different directions. Summary of the Invention

[0005] In order to test the flight conditions of an aircraft under different wind directions, the present application provides a detection device for testing an aircraft.

[0006] The present application provides a detection device for testing an aircraft using the following technical solution.

[0007] A detection device for testing an aircraft, comprising a machine platform, a wind cylinder shell, a motor located at one end of the wind cylinder shell, and fan blades arranged on a rotating shaft of the motor, the wind cylinder shell comprising an inner shell, a radial inner wall of the inner shell having a plurality of through holes, the machine platform being provided with a placement platform for placing the aircraft, the placement platform being located inside the inner shell, the fan blades being driven by the motor to generate airflow inside the inner shell, one axial end of the inner shell being an air inlet end, the other axial end of the inner shell being an air outlet end, the through holes being distributed between the air inlet end and the air outlet end, the fan blades being located at the air outlet end, the placement platform being located between the air inlet end and the air outlet end, the air outside the inner shell being able to enter the interior of the inner shell from the air inlet end and the through holes under the action of the fan blades, and the airflow direction at the air inlet end is different from the airflow direction at the through holes.

[0008] Optionally, the placement platform includes a placement plate, which is used to place the aircraft, and the placement plate is located in the through-hole area.

[0009] The cam is fixedly mounted on the support frame, and the cam is fixedly mounted on the support frame, wherein the cam is fixedly mounted on the support frame, and the cam is fixedly mounted on the support frame.

[0010] Optionally, the sliding rod can slide away from the carrying plate.

[0011] Optionally, an outer shell is provided on the outer wall of the inner shell, the outer shell is slidably connected to the machine platform, and the outer shell can move axially along the inner shell to block or disengage from the through hole.

[0012] The cam is fixedly mounted on the support frame, and the cam is fixedly mounted on the support frame, wherein the cam is fixedly mounted on the support frame, wherein the cam is fixedly mounted on the support frame.

[0013] Optionally, the machine is provided with a first return spring, one end of the first return spring is fixed to the outer shell, and the other end of the first return spring is fixed to the machine, the first return spring can drive the outer shell to move to cover the through hole, and the inner wall of the second slide groove is provided with a second return spring, one end of the second return spring is fixed to the inner wall of the second slide groove, and the other end of the second return spring is fixed to the second connecting rod, and the second return spring can drive the second connecting rod to move radially along the inner shell close to the supporting plate.

[0014] Optionally, the machine is provided with a limit slot, a limit rod is provided in the limit slot, a driving spring is provided between the limit rod and the bottom of the limit slot, the driving spring can drive the limit rod to move out of the limit slot, the limit slot is located on the moving path of the shell, and the shell can open or close the notch of the limit slot.

[0015] Optionally, the through hole is funnel-shaped, and a diameter of the through hole at one end close to the machine platform is smaller than a diameter of the through hole at one end away from the machine platform.

[0016] Optionally, an indicator light is provided on the outer wall of the movable sleeve, and a spring button switch is fixed to one end of the baffle facing the retaining ring. The spring button switch is electrically connected to the indicator light, and the spring button switch can be turned on under the squeezing action of the baffle and the retaining ring. When the spring button switch is turned on, the indicator light is on.

[0017] In summary, this application has at least one of the following beneficial effects: When the fan blades rotate, they generate suction on the inside of the inner shell, and the air flows into the inner shell from the air inlet end and the through hole respectively. The air flow entering from the air inlet end acts on the aircraft along the axial direction of the inner shell, and the air flow entering from the through hole acts on the aircraft along the radial direction of the inner shell, which is convenient for testing the flight conditions of the aircraft under the interference of air flow in different directions.

[0018] When only the flight condition of one wind direction needs to be tested, the outer shell covers the inner shell, thereby shielding the through-holes. At this time, the aircraft is only disturbed by the airflow entering from the air inlet end. When the flight conditions of multiple wind directions need to be tested, the kinetic energy output of the aircraft is reduced so that the aircraft moves under the influence of the airflow. At this time, the aircraft drives the sliding rod to move through the placement plate, so that the sliding rod squeezes the first wedge plate along the inclined surface of the first wedge plate to move. The first wedge plate drives the second connecting rod through the first connecting rod to move radially along the inner shell away from the load-bearing plate. The second connecting rod drives the second wedge plate to move radially along the inner shell away from the outer shell. At this time, the outer shell is not restricted by the second wedge plate, and moves under the action of the first return spring, thereby gradually opening the through-holes of the inner shell, so that the aircraft is disturbed by the airflow from the through-holes, thereby providing multiple options for the testing process.

[0019] When it is necessary to test the aircraft's load-bearing flight capability, the aircraft's power output is reduced, allowing the airflow to blow the aircraft to move, thereby driving the slide bar to move away from the load plate. At this time, under the influence of gravity, the slide bar slides down, driving the baffle to move toward the retaining ring, thereby squeezing the spring button switch and turning on the indicator light. The indicator light is turned on to determine whether the aircraft can fly normally under the load. When the indicator light is on, it proves that the aircraft can be suspended normally. When the indicator light is off, it proves that the aircraft has descended, causing the slide bar to contact the machine or the ground, thereby moving the baffle away from the retaining ring and closing the spring button switch. This makes it easier for testers to observe when further testing the aircraft's load-bearing flight capability. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the overall structure of an embodiment of the present application; Figure 2 This is a schematic diagram of the placement table structure of this embodiment; Figure 3 Schematic diagram of other angles of this embodiment as a whole.

[0021] Explanation of the accompanying reference numerals: 1. machine platform; 2. air cylinder shell; 201. inner shell; 202. outer shell; 3. fan blades; 4. motor; 5. air inlet end; 6. air outlet end; 7. through hole; 8. placement table; 801. placement plate; 802. bearing plate; 803. slide rod; 804. movable sleeve; 9. retaining ring; 10. baffle; 11. baffle; 12. first wedge plate; 13. second wedge plate; 14. first connecting rod; 15. second connecting rod; 16. first return spring; 17. limit rod; 18. indicator light; 19. spring button switch; 20. through hole. DETAILED DESCRIPTION

[0022] The following is combined with Figure 1-3 The present application is further described with reference to the following specific examples: First of all, it should be noted that in the description of this application, if the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside" and other directional words appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the accompanying drawings, which is only for the convenience of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of this application; in addition, if the terms "first", "second", "third" and other numerical quantifiers appear, they are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. In addition, in this application, unless otherwise clearly specified and limited, if the terms "installed", "connected", and "connected" appear, they should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, an interference fit, a transition fit and other limited connection, or an integral connection; it can be directly connected or indirectly connected through an intermediate medium; therefore, for ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to the specific circumstances.

[0023] An embodiment of the present application discloses a detection device for testing an aircraft.

[0024] A detection device for testing an aircraft, referring to Figure 1 , including a machine 1, a wind cylinder shell 2, a motor 4 located at one end of the wind cylinder shell 2 and a fan blade 3 arranged on the rotating shaft of the motor 4, the wind cylinder shell 2 includes an inner shell 201, the radial inner wall of the inner shell 201 has a plurality of through holes 7, the machine 1 is provided with a placement table 8 for placing the aircraft, the placement table 8 is located inside the inner shell 201, the fan blade 3 can be driven by the motor 4 to generate airflow inside the inner shell 201, one axial end of the inner shell 201 is the air inlet end 5, the other axial end of the inner shell 201 is the air outlet end 6, the through holes 7 are distributed between the air inlet end 5 and the air outlet end 6, the fan blade 3 is located at the air outlet end 6, the placement table 8 is located between the air inlet end 5 and the air outlet Between the wind ends 6, the air outside the inner shell 201 can be affected by the fan blades 3 to enter the inner shell 201 from the air inlet end 5 and the through hole 7. The airflow direction at the air inlet end 5 is different from the airflow direction at the through hole 7. When the fan blades 3 rotate, the fan blades 3 generate suction on the inside of the inner shell 201, and the airflow enters the inner shell 201 from the air inlet end 5 and the through hole 7 respectively. The airflow entering from the air inlet end 5 acts on the aircraft along the axial direction of the inner shell 201, and the airflow entering from the through hole 7 acts on the aircraft along the radial direction of the inner shell 201, which is convenient for testing the flight condition of the aircraft under the interference of airflow in different directions.

[0025] Reference Figure 1-Figure 3 The placement platform 8 includes a placement plate 801, which is used to place the aircraft. The placement plate 801 is located in the through hole 7 area, which reduces the probability of placing the aircraft in an area beyond the through hole 7 where the airflow cannot act.

[0026] Reference Figure 1-Figure 3 The machine 1 also includes a supporting plate 802, a slide bar 803 and a movable sleeve 804. The supporting plate 802 is fixed to the machine 1. One end of the slide bar 803 is slidably connected to the supporting plate 802. A baffle 10 is fixed to the other end of the slide bar 803. The movable sleeve 804 is movably sleeved on the slide bar 803. A baffle 9 is fixed on the end of the movable sleeve 804 facing the machine 1. The inner diameter of the baffle 10 is smaller than the diameter of the baffle 10. There is a gap between the inner wall of the baffle 9 and the side wall of the slide bar 803. A baffle 11 is fixed on the end of the movable sleeve 804 facing away from the machine 1. The inner wall of the movable sleeve 804 is connected to the slide bar 803. There is a gap between the side walls 3, and the baffle 10 is located between the retaining ring 9 and the baffle 11. The placement plate 801 is fixedly set at the end of the baffle 11 away from the machine 1. The placement plate 801 is fixed to the aircraft. During the test, the aircraft is fixed to the placement plate 801, and then the motor 4 is started to rotate the fan blades 3 to generate airflow, and the aircraft rises. At this time, the placement plate 801 drives the movable sleeve 804 to move until the baffle 10 abuts the retaining ring 9, limiting the aircraft from continuing to take off, thereby reducing the probability of the aircraft colliding with the outer wall of the inner shell 201 due to excessive initial kinetic energy.

[0027] Reference Figure 1-Figure 3 The slide bar 803 can slide away from the support plate 802. When it is necessary to test the aircraft's ability to fly with load under airflow interference, the tester actively reduces the aircraft's output kinetic energy so that the thrust generated by the airflow is greater than the aircraft's power. At this time, the aircraft moves axially along the inner shell 201 under the action of the airflow, thereby driving the slide bar 803 to move away from the support plate 802. At this time, the placement plate 801, the movable sleeve 804 and the slide bar 803 become the aircraft's load, which is convenient for testing the aircraft's load-bearing capacity.

[0028] Reference Figure 1-Figure 3 The outer wall of the inner shell 201 is provided with an outer shell 202, which is slidably connected to the machine 1. The outer shell 202 can move axially along the inner shell 201 to block or disengage from the through hole 7. When it is necessary to measure the flight capability of the aircraft under airflow interference in different directions, the outer shell 202 is driven to move to open the through hole 7. When only the airflow interference in one direction needs to be measured, the outer shell 202 closes the through hole 7, so as to provide the staff with a variety of test scenarios.

[0029] Reference Figure 1-Figure 3The supporting plate 802 is provided with a first sliding groove, and the sliding rod 803 is slidably set in the first sliding groove. The side wall of the first sliding groove is provided with a through opening 20. A first wedge plate 12 is provided in the through opening 20 and moves radially along the inner shell 201. The sliding rod 803 can abut or disengage with the inclined surface of the first wedge plate 12. The machine 1 is provided with a second sliding groove. A first connecting rod 14 is provided between the second sliding groove and the first wedge plate 12. One end of the first connecting rod 14 is fixedly connected to the first wedge plate 12, and the other end of the first connecting rod 14 is slidably set in the second sliding groove. The machine 1 is provided with a second wedge plate 13 for movement. A second connecting rod 15 is provided between the second wedge plate 13 and the first connecting rod 14. The second connecting rod 15 is provided in the second sliding groove for radial movement along the inner shell 201. One end of the second connecting rod 15 is fixed to the first connecting rod 14, and the other end of the second connecting rod 15 is fixed to the second wedge plate 13. The outer shell 20 2 can abut against the inclined surface of the second wedge plate 13. When only the flight condition of one wind direction needs to be tested, the outer shell 202 covers the inner shell 201, thereby shielding the through hole 7. At this time, the aircraft is only disturbed by the airflow entering from the air inlet end 5. When the flight conditions of multiple wind directions need to be tested, the kinetic energy output of the aircraft is reduced, so that the aircraft moves under the influence of the airflow. At this time, the aircraft drives the sliding rod 803 to move through the placement plate 801, so that the sliding rod 803 presses the first wedge plate 12 along the inclined surface to move the first wedge plate 12. The first wedge plate 12 drives the second connecting rod 15 through the first connecting rod 14 to move radially along the inner shell 201 away from the carrying plate 802. The second connecting rod 15 drives the second wedge plate 13 to move radially along the inner shell 201 away from the outer shell 202. At this time, the outer shell 202 is no longer restricted by the second wedge plate 13. Then the outer shell 202 is moved to open the through hole 7, which is convenient and quick.

[0030] Reference Figure 1-Figure 3The machine 1 is provided with a first return spring 16, one end of the first return spring 16 is fixed to the outer shell 202, and the other end of the first return spring 16 is fixed to the machine 1. The first return spring 16 can drive the outer shell 202 to move to cover the through hole 7. The inner wall of the second slide is provided with a second return spring, one end of the second return spring is fixed to the inner wall of the second slide, and the other end of the second return spring is fixed to the second connecting rod 15. The second return spring can drive the second connecting rod 15 to move radially along the inner shell 201 close to the bearing plate 802. The elastic force of the first return spring 16 is less than the elastic force of the second return spring, and the elastic force of the second return spring is less than the wind force of the fan blade 3. When it is necessary to test flight under different wind directions When the flight capability of the aircraft is tested, the aircraft drives the sliding rod 803 to squeeze the first wedge plate 12, and the first wedge plate 12 compresses the second return spring, thereby pushing the second wedge plate 13 to move radially along the shell 202 away from the bearing plate 802. At this time, the shell 202 is not restricted by the inclined surface of the second wedge plate 13, and then the first return spring 16 pulls the shell 202 to move axially, thereby opening the through hole 7. After the test is completed, the sliding rod 803 slides away from the inclined surface of the first wedge plate 12, and the second return spring pulls the second connecting rod 15 to radially slide the shell 202 close to the bearing plate 802. The second wedge plate 13 squeezes the shell 202 through the inclined surface to move and re-cover the through hole 7, which is convenient and quick.

[0031] Reference Figure 1-Figure 3 The machine 1 is provided with a limit slot, in which a limit rod 17 is provided, and a driving spring is provided between the limit rod 17 and the bottom of the limit slot, and the driving spring can drive the limit rod 17 to move out of the limit slot, and the limit slot is located on the moving path of the shell 202, and the shell 202 can open or close the notch of the limit slot. When the shell 202 moves to open the through hole 7, the notch of the limit slot is not covered by the shell 202, and then the limit rod 17 is extended by the driving spring and abuts against one end of the shell 202 axially away from the first return spring 16, thereby limiting the shell 202 from closing the through hole 7 again when the slide rod 803 is separated from the load plate 802, so as to facilitate the testing of the aircraft in different wind directions when the aircraft is loaded.

[0032] Reference Figure 1-Figure 3 The through hole 7 is funnel-shaped, and the diameter of the through hole 7 at one end close to the machine 1 is smaller than the diameter of the through hole 7 at one end away from the machine 1 , so as to accelerate the airflow from the through hole 7 into the inner shell 201 and generate a greater force.

[0033] Reference Figure 1-Figure 3The outer wall of the movable sleeve 804 is provided with an indicator light 18, and a spring button switch 19 is fixed to one end of the baffle 10 facing the retaining ring 9. The spring button switch 19 is electrically connected to the indicator light 18. The spring button switch 19 can be opened under the squeezing action of the baffle 10 and the retaining ring 9. When the spring button switch 19 is turned on, the indicator light 18 is on. When it is necessary to test the load-bearing flight capability of the aircraft, the power output of the aircraft is reduced, so that the airflow blows the aircraft to move, thereby driving the slide bar 803 to move away from the bearing plate 802. At this time, under the influence of gravity, the slide bar 803 The slide 803 moves downward, driving the baffle 10 toward the retaining ring 9, thereby squeezing the spring button switch 19 and turning on the indicator light 18. The light of the indicator light 18 is used to judge whether the aircraft can normally hover in the air under the load. When the indicator light 18 is on, it proves that the aircraft can hover in the air normally. When the indicator light 18 is off, it proves that the aircraft has descended, causing the slide bar 803 to contact the machine 1 or the ground, thereby moving the baffle 10 away from the retaining ring 9 and closing the spring button switch. This makes it easier for testers to observe when further testing the aircraft's load-bearing flight capability.

[0034] It should be noted that the above embodiments are only used to illustrate the present application and are not intended to limit the technical solutions described in the present application. Although this specification has described the present application in detail with reference to the above embodiments, ordinary technicians in this field should understand that technicians in the relevant technical field can still modify or replace the present application with equivalents, and all technical solutions and improvements that do not depart from the spirit and scope of the present application should be included in the scope of the claims of the present application.

Claims

1. A detection device for testing an aircraft, comprising a machine (1), a wind tube housing (2), a motor (4) located at one end of the wind tube housing (2), and a fan blade (3) arranged on a rotating shaft of the motor (4), characterized in that: The wind tube shell (2) includes an inner shell (201), the radial inner wall of the inner shell (201) has a plurality of through holes (7), the machine (1) is provided with a placement platform (8) for placing the aircraft, the placement platform (8) is located inside the inner shell (201), the fan blade (3) can be driven by the motor (4) to generate airflow inside the inner shell (201), one axial end of the inner shell (201) is an air inlet end (5), and the other axial end of the inner shell (201) is an air outlet end (6) The through holes (7) are distributed between the air inlet end (5) and the air outlet end (6), the fan blades (3) are located at the air outlet end (6), and the placement platform (8) is located between the air inlet end (5) and the air outlet end (6). The air outside the inner shell (201) can enter the inner shell (201) from the air inlet end (5) and the through holes (7) under the action of the fan blades (3), and the air flow direction at the air inlet end (5) is different from the air flow direction at the through holes (7).

2. The detection device for testing an aircraft according to claim 1, characterized in that: The placement platform (8) comprises a placement plate (801), the placement plate (801) is used to place the aircraft, and the placement plate (801) is located in the area of ​​the through hole (7).

3. The detection device for testing an aircraft according to claim 2, characterized in that: The machine (1) further comprises a supporting plate (802), a slide bar (803) and a movable sleeve (804), wherein the supporting plate (802) is fixed to the machine (1), one end of the slide bar (803) is slidably connected to the supporting plate (802), the other end of the slide bar (803) is fixed with a baffle (10), the movable sleeve (804) is movably sleeved on the slide bar (803), and a baffle ring (9) is fixed on one end of the movable sleeve (804) facing the machine (1), and the inner diameter of the baffle ring (9) is smaller than that of the baffle ( 10) diameter, a gap is provided between the inner wall of the retaining ring (9) and the side wall of the slide bar (803), a baffle (11) is fixedly provided at one end of the movable sleeve (804) away from the machine (1), a gap is provided between the inner wall of the movable sleeve (804) and the side wall of the slide bar (803), the baffle (10) is located between the retaining ring (9) and the baffle (11), the placement plate (801) is fixedly provided at one end of the baffle (11) away from the machine (1), and the placement plate (801) is fixed between the aircraft.

4. The detection device for testing an aircraft according to claim 3, characterized in that: The sliding rod (803) is capable of sliding away from the supporting plate (802).

5. The detection device for testing an aircraft according to claim 2, characterized in that: The outer wall of the inner shell (201) is provided with an outer shell (202), the outer shell (202) is slidably connected to the machine (1), and the outer shell (202) can move axially along the inner shell (201) to block or disengage from the through hole (7).

6. The detection device for testing an aircraft according to claim 5, characterized in that: The carrier plate (802) is provided with a first slide groove, the slide rod (803) is slidably arranged in the first slide groove, the side wall of the first slide groove is provided with a through opening (20), a first wedge plate (12) is provided in the through opening (20) and moves radially along the inner shell (201), the slide rod (803) can abut or disengage with the inclined surface of the first wedge plate (12), the machine (1) is provided with a second slide groove, a first connecting rod (14) is provided between the second slide groove and the first wedge plate (12), one end of the first connecting rod (14) is fixedly connected to the first wedge plate (12), the The other end of the first connecting rod (14) is slidably arranged in the second sliding groove, and the machine (1) is movably provided with a second wedge plate (13), and a second connecting rod (15) is provided between the second wedge plate (13) and the first connecting rod (14), and the second connecting rod (15) is radially movable along the inner shell (201) and arranged in the second sliding groove, one end of the second connecting rod (15) is fixed to the first connecting rod (14), and the other end of the second connecting rod (15) is fixed to the second wedge plate (13), and the outer shell (202) can abut against the inclined surface of the second wedge plate (13).

7. The detection device for testing an aircraft according to claim 6, characterized in that: The machine (1) is provided with a first return spring (16), one end of the first return spring (16) is fixed to the outer shell (202), and the other end of the first return spring (16) is fixed to the machine (1), and the first return spring (16) can drive the outer shell (202) to move to cover the through hole (7), and the inner wall of the second slide groove is provided with a second return spring, one end of the second return spring is fixed to the inner wall of the second slide groove, and the other end of the second return spring is fixed to the second connecting rod (15), and the second return spring can drive the second connecting rod (15) to move radially along the inner shell (201) close to the supporting plate (802).

8. The detection device for testing an aircraft according to claim 7, characterized in that: The machine (1) is provided with a limiting slot, a limiting rod (17) is provided in the limiting slot, a driving spring is provided between the limiting rod (17) and the bottom of the limiting slot, the driving spring can drive the limiting rod (17) to move out of the limiting slot, the limiting slot is located on the moving path of the housing (202), the housing (202) can open or close the notch of the limiting slot, and the limiting rod (17) can abut against one end of the housing (202) axially away from the fan blade (3).

9. The detection device for testing an aircraft according to claim 1, characterized in that: The through hole (7) is funnel-shaped, and the diameter of the through hole (7) at one end close to the machine (1) is smaller than the diameter of the through hole (7) at one end away from the machine (1).

10. The detection device for testing an aircraft according to claim 3, characterized in that: An indicator light (18) is provided on the outer wall of the movable sleeve (804); a spring button switch (19) is fixed to one end of the baffle (10) facing the baffle ring (9); the spring button switch (19) and the indicator light (18) are electrically connected; the spring button switch (19) can be turned on under the squeezing action of the baffle (10) and the baffle ring (9); when the spring button switch (19) is turned on, the indicator light (18) is on.

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