Airplane control surface angle measuring instrument

Abstract

The invention belongs to the technical field of measuring devices, and particularly relates to an aircraft control surface angle measuring instrument, which comprises an observation part, a control surface angle measuring part and a control surface angle measuring part, the rudder sleeve is used for being connected to the outer surface of a rudder in a sleeving mode; the deflection angle components are arranged on the upper side and the lower side of the rudder sleeve and used for measuring the deflection angle of the rudder sleeve. According to the device, the laser transmitters on the upper side and the lower side are driven to synchronously deflect through the arranged adaptive outer sleeve, so that the actual deflection angle of the steering engine is obtained by the analyzer and is compared with deflection angle data in the engine body, and whether the deflection angle of the control surface in the engine body is accurate or not is detected; and the sleeved adaptive jacket cannot be separated from the rudder along with the deflection of the rudder, so that the rudder surface cannot slip relative to the deflection angle part, the phenomenon that a large error is generated between the actual deflection of the rudder surface and the deflection angle measured by an analyzer is avoided, and the reliability and the accuracy of a test result are ensured.

Description

Technical Field

[0001] This invention belongs to the field of measuring device technology, specifically an aircraft control surface angle measuring instrument. Background Technology

[0002] Control surfaces are a crucial component of the flight control system; the aircraft's attitude is controlled by manipulating these surfaces. When repairing or inspecting control surfaces, it's essential to check the accuracy of their deflection. Excessive deflection will severely impact the accuracy of aircraft maneuvers and jeopardize flight safety.

[0003] An existing aircraft control surface deflection measuring device (publication number CN218822291U) uses a first and second clamping member to hold the aircraft control surface. During the aircraft's control surface adjustment process, a digital angle measuring instrument at the bottom measures the actual deflection angle of the control surface, calibrating the control surface control instruments inside the aircraft, thereby improving the accuracy of the aircraft's control surface. However, the aircraft control surface is not actually a flat plate. When the first and second clamping members hold the aircraft control surface, the control surface is prone to slippage with the clamping members, resulting in a large error between the actual deflection of the control surface and the deflection angle measured by the digital angle measuring instrument. Therefore, improvements are needed. Summary of the Invention

[0004] To address the problem of existing technologies' inability to effectively clamp aircraft control surfaces, the technical solution adopted in this invention is: an aircraft control surface angle measuring instrument, comprising: The observation component is used to acquire actual deflection data of the rudder. A rudder sleeve is used to fit onto the outer surface of the rudder. The deflection angle component is located on the upper and lower sides of the rudder sleeve and is used to measure the deflection angle of the rudder sleeve. The rudder sleeve includes: The adapter jacket has an inner wall that fits onto the outer surface of the control rudder. The adapter jacket can be customized according to the control surface of the aircraft to ensure that the adapter jacket can fit completely onto the control surface. The external plugs are symmetrically arranged on the upper and lower sides of the outer surface of the adapter jacket, and the inner wall of the external plugs has adapter slots, so that the external plugs can be installed on the customized adapter jackets. The deflection component includes: A spherical container, wherein a photosensitive sensor is provided in the middle of the inner cavity of the spherical container through an annular groove, and a photosensitive strip is uniformly provided on the inner wall of the photosensitive sensor. The photosensitive sensor is located in the middle of the spherical container and senses the deflection angle of light through the photosensitive strip on the inner wall, and outputs data to the corresponding external component. The polarizing device, located at the axis of the spherical shape, is used to emit laser light into the light-sensitive strip; The correction fixed rod is arranged at the axis of the upper surface of the spherical container and used for correcting the polarizing equipment.

[0005] Further, the observation component comprises, The fixed base is arranged on the ground, and the top of the inner cavity of the fixed base is provided with a propelling slide plate; The outer surface of the connecting sleeve shell is fixedly connected with the side of the propelling slide plate away from the fixed base, the propelling slide plate can drive the connecting sleeve shell to horizontally slide, and the position of the adaptive sleeve is adjusted; The number of the analyzers is two groups, and the outer surface of the analyzer is fixedly connected with the outer surface of the connecting sleeve shell, the inner cavity of the analyzer is connected with the wiring head of the polarizing equipment through connecting wires, the analyzer presents data from the light sensor to the panel for the operator to analyze and correct.

[0006] Further, the observation component further comprises, The outer surface of the distance adjusting component is connected with the axis of the inner wall of the connecting sleeve shell, the upper and lower ends of the distance adjusting component are symmetrically provided with horizontal traction plates through slide rods, and the end of the horizontal traction plate away from the distance adjusting component is connected with the outer surface of the correction fixed rod, the distance adjusting component is composed of a barrel body in the middle and rod bodies on two sides, the motor pulley in the barrel body can drive the rod bodies on two sides to slide, so that the height of the two side angle adjusting components is adjusted.

[0007] Further, the polarizing equipment comprises, The inner cavity of the planar disc shell is provided with a laser emitter at the axis, the outer surface of the laser emitter is uniformly provided with ray ends, and the ray ends extend to the outside of the planar disc shell; The bottom end of the hollow compression pipe is fixedly connected with the axis of the upper surface of the planar disc shell, The top end of the connecting bottom rod is fixedly connected with the axis of the lower surface of the planar disc shell, and the bottom end of the connecting bottom rod is inserted into the inner cavity of the external plug.

[0008] Further, the polarizing equipment further comprises, The outer surface of the counterweight balance rod is uniformly provided with metal pressing rods, the bottom end of the counterweight balance rod is rotationally connected with the axis of the bottom of the inner wall of the connecting bottom rod through a spherical joint, the counterweight balance rod is located at the axis position under normal circumstances, and the metal pressing rods on the outer surface of the counterweight balance rod are not in contact with the other components; The inner cavity of the winding drum is connected with the axis of the top of the counterweight balance rod through a traction rope, the winding drum drives the traction rope to wind and unwind through the roller shaft inside, when the traction rope is taut, the counterweight balance rod is always located at the axis position in the connecting bottom rod; The built-in power box is uniformly provided with pressure-sensitive gaskets at the axis of the inner wall, the top of the built-in power box is connected with the inner cavity of the laser emitter through wires, and the built-in power box mainly plays a power supply function; when any one of the pressure-sensitive gaskets inside is pressed, the circuit of the inner cavity is connected, thereby supplying power to the outside; The outer alarm is fixedly connected with the lower part of the connecting bottom rod inner cavity, and the bottom end of the built-in power box is connected with the inner cavity of the outer alarm through wires; The lower part of the outer surface of the connecting bottom rod is sleeved with a limiting gasket, the limiting gasket mainly isolates the inside and outside of the spherical container, and prevents the connecting bottom rod from separating from the spherical container; since the limiting gasket itself is elastic, the connecting bottom rod can compress the limiting gasket, and the outer side of the limiting gasket is connected with the opening at the bottom of the spherical container.

[0009] Further, the correction fixing rod comprises, The pressurizing shell is provided with a fixed cover at the top, the bottom end of the pressurizing shell is an arc surface, and the bottom of the outer surface of the pressurizing shell is fixedly connected with the outer surface of the spherical container; The built-in air pump is fixedly connected with the axis of the inner wall of the pressurizing shell; The butt joint pipe is inserted into the top of the inner cavity of the hollow compression pipe and the air inlet of the built-in air pump.

[0010] The beneficial effects of the present application are as follows: 1. The device is provided with an adaptive sleeve, so that when the rudder is deflected, the upper and lower laser emitters are deflected synchronously, so that the actual deflection angle of the rudder is obtained by the analyzer, and the deflection angle data inside the machine body are compared to realize the work of detecting whether the deflection angle of the rudder surface inside the machine body is accurate. Since the adaptive sleeve can be customized according to the actual shape of the rudder, and the adaptive sleeve after sleeving will not separate from the rudder with the deflection of the rudder, the rudder surface will not slip with the deflection component, thereby avoiding the phenomenon that the actual deflection of the rudder surface and the deflection angle measured by the analyzer have a large error, and ensuring the reliability and accuracy of the test results.

[0011] 2. After the adaptive sleeve is sleeved on the outer surface of the rudder, the adaptive sleeve uniformly bears the stress of the rudder, does not produce a large extrusion force on a certain point of the outer surface of the rudder during the deflection movement of the rudder, and does not cause the rudder to appear extrusion deformation. It can also effectively protect the outer surface of the rudder, avoiding the problem that the outer surface is easily dirty due to static electricity absorption during deflection.

[0012] 3. The two sets of deflection angle components of the device are symmetrically arranged on the upper and lower sides of the rudder sleeve, so there are self-contrast data, when performing test work, the deflection angle data obtained by the two sets of analyzers should be the same, thereby avoiding the problem of misjudgment caused by system test error, when the rudder deflects, the key components of the polarizing equipment are always inside the spherical container for light shielding protection, so they are not easily disturbed by the external environment, and the anti-interference performance of the device is good.

[0013] 4. In order to reduce the wire connection, the internal laser emitter adopts the form of built-in power box power supply for power transmission work, and triggers the built-in power box by pressing the pressure pad, so that the laser emitter does not perform laser irradiation work in the non-working state, thereby saving the consumed electric energy of the laser, and increasing the endurance of the built-in power box. The external alarm at the bottom will start to emit alarm sound when the rudder deflects, reminding and dispersing irrelevant personnel around the rudder, avoiding the phenomenon that the rudder deflects and causes collision injury to nearby personnel. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 is the front view of the present application; Figure 2 is the sectional view of the present application; Figure 3 is the structural schematic view of the rudder sleeve of the present application; Figure 4 is the sectional view of the deflection angle component of the present application; Figure 5 is the structural schematic view of the observation component of the present application; Figure 6 is the sectional view of the polarizing equipment of the present application; Figure 7 is the sectional view of the pressurizing shell of the present application.

[0015] In the figure: 1, observation component; 2, distance adjusting component; 3, deflection angle component; 4, rudder sleeve; 41, adaptive sleeve; 42, external plug; 31, spherical container; 32, light sensor; 33, light sensing belt; 34, limiting pad; 11, fixed base; 12, propulsion slide plate; 13, connecting sleeve; 14, analyzer; 5, polarizing equipment; 51, flat disc shell; 52, laser emitter; 53, ray end; 54, hollow compression pipe; 55, connecting bottom rod; 56, winding drum; 57, counterweight balance rod; 58, metal pressing rod; 59, built-in power box; 510, pressure pad; 511, external alarm; 6, correction fixing rod; 61, pressurizing shell; 62, built-in air pump; 63, interfacing pipe. DETAILED DESCRIPTION

[0016] The application is further described in detail below with reference to the drawings and specific embodiments. The embodiments of the application are given for illustrative and descriptive purposes only and are not intended to be exhaustive or to limit the application to the forms disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Embodiments are chosen and described in order to best explain the principles of the application and its practical application to thereby enable others skilled in the art to best utilize the application in various embodiments and with various modifications as are suited to the particular use contemplated.

[0017] Embodiment 1, please refer to Figures 1-5 The application provides a technical solution: an aircraft rudder angle measuring instrument, comprising: An observation component 1 is used to obtain actual deflection data of the rudder; A rudder sleeve 4 is used to be sleeved on the outer surface of the rudder; A deflection angle component 3 is arranged on the upper and lower sides of the rudder sleeve 4 and is used to measure the deflection angle of the rudder sleeve 4; The rudder sleeve 4 comprises: An adaptive sleeve 41, the inner wall of the adaptive sleeve 41 is sleeved on the outer surface of the rudder, and the adaptive sleeve 41 can be individually customized according to the rudder surface of the aircraft, so as to ensure that the adaptive sleeve 41 can be completely sleeved on the rudder surface; An external plug 42 is symmetrically arranged on the upper and lower sides of the outer surface of the adaptive sleeve 41, and the inner wall of the external plug 42 is provided with an adaptive slot, and the external plug 42 can be installed on the customized adaptive sleeve 41; The deflection angle component 3 comprises: A spherical container 31, a light sensor 32 is arranged in the middle part of the inner cavity of the spherical container 31 through an annular cutting groove, and the inner wall of the light sensor 32 is uniformly provided with a light sensing strip 33, the light sensor 32 is arranged at the middle position of the spherical container 31, and the deflection angle of the light is sensed through the light sensing strip 33 on the inner wall, and the data is output to the corresponding component outside; A polarized light device 5 is arranged at the axis of the spherical container 31 and is used to emit laser to the light sensing strip 33; A correction fixing rod 6 is arranged at the axis of the upper surface of the spherical container 31 and is used to correct the polarized light device 5.

[0018] The observation component 1 comprises, A fixed base 11 is arranged on the ground, and a propelling slide plate 12 is arranged at the top of the inner cavity of the fixed base 11; A connecting sleeve shell 13 is fixedly connected to the side of the propelling slide plate 12 away from the fixed base 11, the propelling slide plate 12 can drive the connecting sleeve shell 13 to slide horizontally, and the position of the adaptive sleeve 41 can be adjusted; The analyzer 14 is two sets, and the outer surface of the analyzer 14 is fixedly connected with the outer surface of the connecting sleeve shell 13, the inner cavity of the analyzer 14 is connected with the connecting head of the polarized device 5 through a connecting wire, and the analyzer 14 presents data from the photosensor 32 on a panel for an operator to analyze and correct.

[0019] The observation component 1 further comprises, The distance adjusting component 2 is sleeved with the axis of the inner wall of the connecting sleeve shell 13 at the middle part of the outer surface of the distance adjusting component 2, the upper and lower ends of the distance adjusting component 2 are symmetrically provided with horizontal traction plates through slide rods, one end of the horizontal traction plate away from the distance adjusting component 2 is sleeved with the outer surface of the correction fixed rod 6, and the distance adjusting component 2 is composed of a barrel body at the middle part and rod bodies at two sides.

[0020] Before the device is used to detect the angle of the rudder, the actual shape of the rudder is used to select a matched adaptive sleeve 41, which is installed in the deflection angle component 3, then the horizontal position of the connecting sleeve shell 13 is adjusted by sliding the sliding plate 12, and the height of the adaptive sleeve 41 is adjusted by the distance adjusting component 2, so that the adaptive sleeve 41 can be sleeved with the outer surface of the rudder, and the preparation work is completed.

[0021] When the test is performed, the aircraft control rudder is deflected, at this time, the control component in the aircraft has the deflection angle data of the rudder, and when the external rudder is deflected, the upper and lower polarized devices 5 are driven to deflect by the adaptive sleeve 41, for example, the upper polarized device 5, under the traction of the external plug 42, the light source of the polarized device 5, i.e. the light emitted by the laser emitter 52, is changed from horizontal emission to oblique emission, at this time, the light receiving point of the photosensor 32 in the spherical container 31 changes, according to the position change of the light before and after, the deflection angle of the light is measured, i.e. the deflection angle of the rudder, then the photosensor 32 synchronously transmits the deflection data to the analyzer 14, and the actual deflection angle of the rudder can be obtained by the panel of the analyzer 14 by an operator, and the reliability of the aircraft internal control rudder deflection device can be detected by comparing the deflection angle obtained by the aircraft body.

[0022] Embodiment 2, please refer to Figures 1-7 The application provides a technical solution: on the basis of embodiment 1, the polarized device 5 comprises, The planar disc shell 51 is provided with a laser emitter 52 at the axis of the inner cavity of the planar disc shell 51, the outer surface of the laser emitter 52 is uniformly provided with a ray end 53, and the ray end 53 extends to the outside of the planar disc shell 51; A hollow compression pipe 54 is fixedly connected to the center of the upper surface of the flat disc shell 51 at the bottom end, A connecting bottom rod 55 is fixedly connected to the center of the lower surface of the flat disc shell 51 at the top end, and the bottom end of the connecting bottom rod 55 is inserted into the inner cavity of the external plug 42.

[0023] The polarization device 5 further comprises, A counterweight balance rod 57 is uniformly provided with metal pressing rods 58 on the outer surface, and the bottom end of the counterweight balance rod 57 is rotatably connected to the center of the inner wall bottom of the connecting bottom rod 55 through a spherical joint. The counterweight balance rod 57 is normally located at the center position, and the metal pressing rods 58 on the outer surface are not in contact with the remaining components; A winding drum 56 is connected to the center of the top of the counterweight balance rod 57 through a traction rope in the inner cavity of the winding drum 56. The winding drum 56 drives the traction rope to wind and unwind through the internal roller shaft. When the traction rope is taut, the counterweight balance rod 57 is always located at the center position in the connecting bottom rod 55; An internal power supply box 59 is uniformly provided with pressure-sensitive washers 510 on the inner wall at the center. The top of the internal power supply box 59 is connected to the inner cavity of the laser emitter 52 through a wire. The internal power supply box 59 mainly serves as a power supply function. When any of the internal pressure-sensitive washers 510 is pressed, the internal circuit is connected, thereby supplying power to the outside; An external alarm 511 is fixedly connected to the lower part of the inner cavity of the connecting bottom rod 55, and the bottom end of the internal power supply box 59 is connected to the inner cavity of the external alarm 511 through a wire. A limiting washer 34 is sleeved on the lower part of the outer surface of the connecting bottom rod 55. The limiting washer 34 mainly separates the inner and outer parts of the spherical container 31 and prevents the connecting bottom rod 55 from separating from the spherical container 31. Since the limiting washer 34 itself has elasticity, the connecting bottom rod 55 can compress the limiting washer 34, and the outer side of the limiting washer 34 is connected to the opening at the bottom of the spherical container 31.

[0024] The correction fixing rod 6 comprises, A pressurizing shell 61 is provided with a fixed cover at the top, and the bottom end of the pressurizing shell 61 is arc-shaped. The bottom of the outer surface of the pressurizing shell 61 is fixedly connected to the outer surface of the spherical container 31. An internal air pump 62 is fixedly connected to the center of the inner wall of the pressurizing shell 61. A butt joint pipe 63 is inserted into the inner cavity of the hollow compression pipe 54 at the top, and the inner wall of the butt joint pipe 63 is inserted into the air inlet of the internal air pump 62.

[0025] The adaptive sleeve 41 directly drives the connecting bottom rod 55 to deflect, and the connecting bottom rod 55 controls the synchronous deflection of the top plane disc shell 51, but the uppermost hollow compression pipe 54 is bent and deformed due to the torsion at this time. When the rudder deflects, it means that the device needs to be tested. At this time, the counterweight balance rod 57 at the axis of the plane disc shell 51 will tilt towards the position close to the pressure-sensitive gasket 510 due to the shift of its own gravity center, thereby triggering the built-in power box 59 in the form of pressing the pressure-sensitive gasket 510, so that the built-in power box 59 supplies power to the upper laser emitter 52 and the lower external alarm 511. At this time, the laser emitter 52 starts to consume electric energy to emit light, and the external alarm 511 at the bottom starts to emit an alarm sound, reminding and dispersing irrelevant personnel around the rudder, so as to avoid causing safety accidents.

[0026] When the rudder detection is completed, it will reset to the initial state. At this time, the polarizing equipment 5 returns to the vertical state, and then the wire winding drum 56 starts to tighten the rope to make the counterweight balance rod 57 in the vertical state, so as to ensure that the counterweight balance rod 57 will not press any pressure-sensitive gasket 510, thereby terminating the power supply work of the built-in power box 59. The tightened rope will prevent the counterweight balance rod 57 from tilting due to external force collision in the non-working state, thereby avoiding the problem of accidentally touching the pressure-sensitive gasket 510.

[0027] When the rudder sleeve 4 is deflected, the resistance of the rudder comes from the elastic bending stress of the hollow compression pipe 54, so the correction rod 6 can pressurize the inside of the hollow compression pipe 54 through the built-in air pump 62 inside, so that the hollow compression pipe 54 pressurizes the adaptive sleeve 41, thereby increasing the resistance of the rudder, so as to simulate the wind resistance in flight, so as to detect whether the rudder deflection device inside the aircraft body has the problem of false measurement under strong wind resistance. After the rudder detection work is completed, the built-in air pumps 62 on both sides are in the form of pressure extraction, so that the pressure inside the hollow compression pipe 54 is reduced, and the hollow compression pipe 54 is contracted. The hollow compression pipes 54 on both sides are tightened, the adaptive sleeve 41 in the middle is corrected back to the initial horizontal state, and the rudder is quickly reset.

[0028] Obviously, the described embodiments are only part of the embodiments of the present application, not all. Based on the embodiments in the present application, all other embodiments obtained by ordinary skilled in the art and related fields without creative labor should belong to the scope of protection of the present application. The structures, devices and operation methods not specifically described and explained in the present application are implemented according to the conventional means in the art, unless otherwise specified and limited.

Claims

1. An aircraft control surface angle measuring instrument, comprising: The observation component (1) is used to acquire the actual deflection data of the rudder; The rudder sleeve (4) is used to fit onto the outer surface of the rudder. The deflection component (3) is set on the upper and lower sides of the rudder sleeve (4) and is used to measure the deflection angle of the rudder sleeve (4); Its characteristic is that the rudder sleeve (4) includes: The inner wall of the adapter jacket (41) is fitted to the outer surface of the rudder; External plugs (42) are symmetrically arranged on the upper and lower sides of the outer surface of the adapter jacket (41), and the inner wall of the external plugs (42) is provided with adapter slots. The deflection component (3) includes: A spherical container (31) has a photosensitive sensor (32) provided in the middle of its inner cavity through an annular groove, and a photosensitive strip (33) is uniformly provided on the inner wall of the photosensitive sensor (32). A polarizing device (5) is set at the center of the spherical container (31) and is used to emit laser light into the light-sensitive strip (33); The correction rod (6) is set at the center of the axis on the upper surface of the spherical container (31) and is used to correct the polarization device (5).

2. The aircraft control surface angle measuring instrument according to claim 1, characterized in that: The observation component (1) includes, A fixed base (11) is provided on the ground, and a push plate (12) is provided on the top of the inner cavity of the fixed base (11). Connecting sleeve (13), the outer surface of which is fixedly connected to the side of the push slide (12) away from the fixed base (11); The analyzer (14) consists of two sets, and the outer surface of the analyzer (14) is fixedly connected to the outer surface of the connecting housing (13). The inner cavity of the analyzer (14) is connected to the terminal of the polarizing device (5) through a connecting wire.

3. The aircraft control surface angle measuring instrument according to claim 2, characterized in that: The observation component (1) also includes, The middle part of the outer surface of the adjusting component (2) is sleeved with the axis of the inner wall of the connecting sleeve (13). Both the upper and lower ends of the adjusting component (2) are symmetrically provided with horizontal traction plates through sliding rods, and the end of the horizontal traction plate away from the adjusting component (2) is sleeved with the outer surface of the straightening rod (6).

4. The aircraft control surface angle measuring instrument according to claim 1, characterized in that: The polarizing device (5) includes, A planar disk shell (51) is provided with a laser emitter (52) at the axial center of the inner cavity of the planar disk shell (51). The outer surface of the laser emitter (52) is uniformly provided with ray tips (53), and the ray tips (53) extend to the outside of the planar disk shell (51). A hollow compression tube (54) is fixedly connected at its bottom end to the center of the upper surface of the flat disk shell (51). The connecting rod (55) is fixedly connected at the top end to the axis of the lower surface of the flat disk shell (51), and the bottom end of the connecting rod (55) is inserted into the inner cavity of the external plug (42).

5. The aircraft control surface angle measuring instrument according to claim 4, characterized in that: The polarizing device (5) also includes, The counterweight balance bar (57) has metal pressure bars (58) evenly arranged on its outer surface. The bottom end of the counterweight balance bar (57) is rotatably connected to the axis at the bottom of the inner wall of the connecting base bar (55) through a spherical joint. The inner cavity of the spool (56) is connected to the center of the top of the counterweight balance bar (57) via a traction rope at the center of the spool (56). Built-in power supply box (59), pressure-sensitive washers (510) are evenly arranged at the axis of the inner wall of the built-in power supply box (59), and the top of the built-in power supply box (59) is connected to the inner cavity of the laser emitter (52) through a wire. An external alarm (511) is fixedly connected to the lower part of the inner cavity of the connecting base rod (55) on its outer surface, and the bottom end of the built-in power supply box (59) is connected to the inner cavity of the external alarm (511) through a wire. A limiting washer (34) is fitted onto the lower part of the outer surface of the connecting bottom rod (55), and the outer side of the limiting washer (34) is connected to the opening at the bottom of the spherical container (31).

6. The aircraft control surface angle measuring instrument according to claim 1, characterized in that: The corrective rod (6) includes, The pressure housing (61) is provided with a fixed cover on the top, the bottom end of the pressure housing (61) is an arc-shaped surface, and the bottom of the outer surface of the pressure housing (61) is fixedly connected to the outer surface of the spherical container (31). Built-in air pump (62), the outer surface of which is fixedly connected to the axial center of the inner wall of the pressurized housing (61); Connecting pipe (63), the bottom end of which is inserted into the top of the inner cavity of hollow compression pipe (54), and the inner wall of connecting pipe (63) is inserted into the air inlet of built-in air pump (62).

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