A high-altitude particle pollutant detection and sampling device

Abstract

The present invention relates to the field of air pollution monitoring technology, and the present invention discloses a high-altitude particle pollutant detection sampling device, which includes a fuselage shell, a hanging bracket, an air intake assembly and a sampling assembly, wherein the fuselage shell is cylindrical, an air intake assembly is arranged at one end, a sampling assembly is arranged at the other end, a flow measurement assembly is arranged inside the fuselage shell, a hanging bracket is arranged at the top, and the top of the hanging bracket is connected to the belly or wing of the high-altitude aircraft. The advantages of the present invention compared with the prior art are: it can separate the pollutants to be detected from the high-altitude gas through a comprehensive sampling method and bring them back to the ground, without the need for a large-capacity gas sampling container, and can be adapted to most fixed-wing high-altitude aircraft. Fixed-wing high-altitude aircraft have a faster flight speed, which can improve the sampling and collection efficiency of pollutants, and adopt a comprehensive sampling method for sample collection, which is convenient for subsequent sample processing and analysis.

Description

Technical Field

[0001] The invention relates to the technical field of air pollution monitoring, and in particular to a high-altitude particle pollutant detection and sampling device. Background Art

[0002] The detection of high-altitude particulate pollutants requires the collection and testing of high-altitude air. Commonly used methods for gas sampling include direct sampling, concentrated sampling, and comprehensive sampling. For the sampling of high-altitude gases, a high-altitude hot air balloon is often used to carry a sampling container and move it to the airspace to be sampled. The gas at that location is collected and then the hot air balloon is returned to the ground to recover the gas sample for subsequent processing and analysis. This gas sampling method can be considered a direct sampling method. Due to the low density of high-altitude gases, the total content of particulate pollutants to be detected is small, and the sensitivity of the instruments and equipment used in the subsequent sample processing and analysis process is limited, making the detection difficult.

[0003] If you want to use concentrated sampling method or comprehensive sampling method, you need to carry the adsorption device to high altitude to adsorb pollutants, and you need to record the mass of the gas filtered by the adsorption device. The current gas adsorption sampling device and its supporting mass metering components usually use volume flow recording method. For high-altitude working conditions, the gas density at high altitude is lower than that on the ground. The data obtained after collection by the existing device needs to be converted according to the gas density, which increases the difficulty of data processing. Summary of the invention

[0004] The technical problem to be solved by the present invention is that the existing gas particle pollutant detection device is difficult to cope with the working condition of high-altitude collection, and a high-altitude particle pollutant detection sampling device is provided.

[0005] In order to solve the above technical problems, the technical solution provided by the present invention is: a high-altitude particulate pollutant detection and sampling device, which includes a fuselage shell, a hanging bracket, an air intake assembly and a sampling assembly. The fuselage shell is cylindrical, with an air intake assembly at one end, a sampling assembly at the other end, and a hanging bracket at the top. The top of the hanging bracket is hoisted and connected to the belly or wing of the high-altitude aircraft.

[0006] A flow measurement assembly is arranged in the fuselage shell, and the flow measurement assembly includes a shaft, a first shaft sleeve and a second shaft sleeve. The first shaft sleeve and the second shaft sleeve are respectively arranged at two ends of the shaft, and the middle part of the shaft is rotatably sleeved with an active eccentric rotor, and the two ends are rotatably sleeved with a passive eccentric rotor. The active eccentric rotor includes an inner eccentric cylinder and an outer eccentric cylinder, and an annular eccentric flow channel is arranged between the inner eccentric cylinder and the outer eccentric cylinder. The geometric centers of the inner eccentric cylinder and the annular eccentric flow channel are eccentrically arranged relative to the fuselage shell, and the inner eccentric cylinder is provided with an inner extension shaft at the axis center of the fuselage shell, and an inner shaft hole matching the shaft is arranged in the inner extension shaft. The passive eccentric rotor includes an inner eccentric cone and an outer eccentric cone ring, and an annular cone is arranged between the inner eccentric cone and the outer eccentric cone ring. The inner eccentric cone and the annular cone eccentric flow channel have a larger cone area and the geometric center of the end thereof is eccentrically arranged relative to the fuselage shell, and the geometric center of the other end is concentrically arranged relative to the fuselage shell, the inner eccentric cone is provided with an outer extension shaft at the axis center of the fuselage shell, and an outer shaft hole matching the inner extension shaft is provided in the outer extension shaft, the lower bottom surface of the cone of the passive eccentric rotor is fitted with the end of the active eccentric rotor, the end of the cone of the passive eccentric rotor is fitted with the end of the active eccentric rotor, and the eccentric distance of the annular cone eccentric flow channel and the annular eccentric flow channel are equal, the annular cone eccentric flow channel in the measuring component is connected with the intake component, and the annular cone eccentric flow channel in the passive eccentric rotor at the other end is connected with the sampling component.

[0007] The sampling component includes a sampling shell, a sampling inner cone and an annular sampling bracket. The inlet end of the sampling component is connected to the flow measurement component, and the outlet end is convergent. An annular boosting chamber is arranged between the inlet ends of the sampling shell and the sampling inner cone, and an annular decompression flow channel is arranged between the outlet ends. One end of the annular boosting chamber is connected to the annular cone eccentric flow channel in the passive eccentric rotor at one end of the flow measurement component, and the other end is connected to the annular decompression flow channel. An annular exhaust port connected to the outside of the sampling component is arranged at the end of the annular decompression flow channel. The annular sampling bracket is slidably connected to the sampling shell, and the annular sampling bracket can be moved to the connection point between the annular boosting chamber and the annular decompression flow channel.

[0008] Furthermore, the air intake assembly includes an air intake duct housing, an air intake cone and an air intake cone base, an air intake duct is provided between the air intake duct housing, the air intake cone and the air intake cone base, the end of the air intake cone base is sleeved with the first shaft sleeve, the air intake cone is slidingly sleeved on the air intake cone base, an inwardly converging air inlet is provided at the end of the air intake duct housing, a throttling electric cylinder is provided in the air intake cone base, and the free end of the throttling electric cylinder is connected to the air intake cone.

[0009] Furthermore, the outer extension shaft of the passive eccentric rotor at one end of the flow measurement component extends into the first sleeve, and the outer extension shaft of the passive eccentric rotor at the other end extends into the second sleeve. The first sleeve and the second sleeve are both provided with a first encoder for measuring the rotation speed of the outer extension shaft, the inner extension shaft of the active eccentric rotor extends into the second sleeve, and the second sleeve is provided with a second encoder for measuring the rotation speed of the inner extension shaft. A gear ring is provided at the end of the second sleeve, a reducer is provided outside the second sleeve, the output shaft of the reducer extends into the second sleeve and a gear is provided to mesh with the gear ring, the sampling inner cone is provided with a flow measurement motor and a transmission shaft, and the flow measurement motor is connected to the reducer input shaft through the transmission shaft.

[0010] Furthermore, the annular sampling bracket is provided with a plurality of detachable sampling boxes around it, a filter cloth is provided in the sampling box, a plurality of guide rods are provided at one end of the annular sampling bracket, a plurality of guide holes matching the guide rods are provided in the sampling housing, a plurality of sampling electric cylinders are provided in the sampling housing, and the free ends of the sampling electric cylinders pass through the guide holes and are connected to the end of the guide rods.

[0011] Furthermore, a plurality of operating windows are arranged around the sampling housing, and the sampling electric cylinder displaces the annular sampling bracket between the operating window and the connection point between the annular pressurization chamber and the annular decompression flow channel. The operating window is connected to the outside of the sampling housing and is provided with a detachable operating window cover.

[0012] The advantages of the present invention compared with the prior art are:

[0013] It is able to separate the pollutants to be tested from the high-altitude gas through comprehensive sampling methods and bring them back to the ground, without the need for large-capacity gas sampling containers.

[0014] Separating the pollutants to be detected from the high-altitude gas can ensure that more pollutants can be collected, which is convenient for subsequent analysis and processing by instruments.

[0015] The flow measurement component can directly record the mass flow of the gas separated by the device for subsequent concentration data calculation.

[0016] It can be adapted to most fixed-wing high-altitude aircraft, which have a faster flight speed and can improve the efficiency of pollutant sampling and collection. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural schematic diagram of the present invention.

[0018] Figure 2 It is a half-section structural schematic diagram of the flow measurement component of the present invention.

[0019] Figure 3 It is a schematic diagram of the half-section structure of the sampling assembly of the present invention.

[0020] Figure 4It is a schematic cross-sectional structural diagram of the flow measurement assembly of the present invention.

[0021] Figure 5 It is a structural schematic diagram of the passive eccentric rotor of the present invention.

[0022] Figure 6 It is a structural schematic diagram of the active eccentric rotor of the present invention.

[0023] Figure 7 It is a structural schematic diagram of the position relationship of the eccentric shaft of the eccentric rotor of the present invention.

[0024] Figure 8 It is a schematic diagram of the half-section structure of the second shaft sleeve of the present invention.

[0025] Fig. 9 It is a schematic diagram of the structure of the sampling component of the present invention in the sampling state.

[0026] Fig.10 It is a schematic diagram of the structure of the sampling assembly of the present invention in the recovery state.

[0027] Fig.11 It is a structural schematic diagram of the annular exhaust port of the present invention.

[0028] Fig.12 It is a structural schematic diagram of the operating window of the present invention.

[0029] Fig.13 It is a structural schematic diagram of the side equipment cabin of the present invention.

[0030] Fig.14 It is a structural schematic diagram of the annular sampling support of the present invention.

[0031] Fig.15 It is a structural schematic diagram of the air intake assembly of the present invention.

[0032] Fig.16 It is a schematic diagram of the airflow direction of the present invention.

[0033] Fig.17 It is a schematic diagram of the working principle of the flow measurement component of the present invention.

[0034] As shown in the figure: 1. Fuselage shell; 2. Hoisting bracket; 3. Intake assembly; 4. Sampling assembly; 5. Flow measurement assembly; 6. Intake duct shell; 7. Intake cone; 8. Intake cone base; 9. First fixed grille; 10. First shaft sleeve; 11. Passive eccentric rotor; 12. Active eccentric rotor; 13. Second shaft sleeve; 14. Second fixed grille; 15. Side equipment compartment; 16. Sampling shell; 17. Annular pressurization chamber; 18. Sampling inner cone; 19. Annular sampling bracket; 20. Annular decompression flow channel; 21. Axis equipment compartment; 22. Tail cone; 23. Annular exhaust port; 24. Operation window; 25. Guide hole; 26. Sampling electric cylinder; 27. Shaft; 28. Reducer; 29. ​​First encoder; 30. The second encoder; 31. inner eccentric cone; 32. outer eccentric cone ring; 33. first fixed rod; 34. annular cone eccentric flow channel; 35. outer shaft hole; 36. outer extension shaft; 37. first counterweight; 38. inner eccentric cylinder; 39. outer eccentric cylinder; 40. second fixed rod; 41. annular eccentric flow channel; 42. inner extension shaft; 43. inner shaft hole; 44. second counterweight; 45. gear ring; 46. gear; 47. transmission shaft hole; 48. flow measurement motor; 49. transmission shaft; 50. third fixed grid; 51. operating window cover; 52. side equipment compartment cover; 53. guide rod; 54. sampling box fixing frame; 55. sampling box; 56. filter cloth; 57. throttling electric cylinder; 58. air inlet; 59. air inlet. DETAILED DESCRIPTION

[0035] The present invention is further described in detail below in conjunction with the accompanying drawings.

[0036] Combined with Figure 1 A high-altitude particle pollutant detection and sampling device includes a fuselage shell 1, a hanging bracket 2, an air intake assembly 3 and a sampling assembly 4. The fuselage shell 1 is cylindrical, with an air intake assembly 3 at one end and a sampling assembly 4 at the other end. The hanging bracket 2 is arranged on the top, and the top of the hanging bracket 2 is connected to the belly or wing of the high-altitude aircraft. The whole device is powered by the high-altitude aircraft.

[0037] The airflow diagram of the present invention when working can refer to the attached Fig.16 , where m refers to the airflow entering the device and n refers to the airflow on the surface of the device.

[0038] Combined with Figure 2 , Attachment Figure 3 and attached Figure 4A flow measurement assembly 5 is arranged in the fuselage shell 1, and the flow measurement assembly 5 includes a shaft 27, a first shaft sleeve 10 and a second shaft sleeve 13. The first shaft sleeve 10 and the second shaft sleeve 13 are respectively arranged at both ends of the shaft 27. A first fixed grid 9 is arranged around the outside of the first shaft sleeve 10 and is fixedly connected to the air inlet shell 6. A second fixed grid 14 is arranged around the outside of the second shaft sleeve 13 and is fixedly connected to the sampling shell 16. The middle part of the shaft 27 is rotatably sleeved with an active eccentric rotor 12, and the two ends are rotatably sleeved with a passive eccentric rotor 11.

[0039] Combined with Figure 5 and attached Figure 6 The active eccentric rotor 12 includes an inner eccentric cylinder 38 and an outer eccentric cylinder 39, an annular eccentric flow channel 41 is provided between the inner eccentric cylinder 38 and the outer eccentric cylinder 39, a second fixing rod 40 is provided between the inner eccentric cylinder 38 and the outer eccentric cylinder 39 for fixing, the geometric centers of the inner eccentric cylinder 38 and the annular eccentric flow channel 41 are eccentrically arranged relative to the fuselage shell 1, the inner eccentric cylinder 38 is provided with an inner extension shaft 42 at the axis center of the fuselage shell 1, and an inner shaft hole 43 matching the shaft rod 27 is arranged in the inner extension shaft 42.

[0040] The passive eccentric rotor 11 includes an inner eccentric cone 31 and an outer eccentric cone ring 32, an annular cone eccentric flow channel 34 is arranged between the inner eccentric cone 31 and the outer eccentric cone ring 32, a first fixing rod 33 is arranged between the inner eccentric cone 31 and the outer eccentric cone ring 32 for fixing, the geometric center of the inner eccentric cone 31 and the annular cone eccentric flow channel 34 at the end with a larger frustum bottom area is eccentrically arranged relative to the fuselage shell 1, and the geometric center of the other end is concentrically arranged relative to the fuselage shell 1, the end with a larger frustum bottom area of ​​the passive eccentric rotor 11 is fitted with the end of the active eccentric rotor 12, the end of the annular eccentric flow channel 41 is equal to the geometric size of the end with a larger frustum bottom area of ​​the annular cone eccentric flow channel 34, one end of the flow measurement component 5 is connected to the annular cone eccentric flow channel 34 in the passive eccentric rotor 11 and is connected to the intake component 3, and the other end of the annular cone eccentric flow channel 34 in the passive eccentric rotor 11 is connected to the sampling component 4.

[0041] Reference Figure 7 and attached Fig.17 , wherein the x-axis refers to the axis of the fuselage shell 1 , which is also the rotation axis of the active eccentric rotor 12 and the passive eccentric rotor 11 , and the y-axis refers to the geometric axis of the annular eccentric flow channel 41 and the annular cone eccentric flow channel 34 .

[0042] A first counterweight 37 is provided at a position of the outer eccentric cone ring 32 away from the y-axis, and a second counterweight 44 is provided at a position of the outer eccentric cylinder 39 away from the y-axis.

[0043] Combined with Figure 4 and attached Figure 8The outer extension shaft 36 of the passive eccentric rotor 11 at one end of the flow measurement component 5 extends into the first sleeve 10, and the outer extension shaft 36 of the passive eccentric rotor 11 at the other end extends into the second sleeve 13. The first sleeve 10 and the second sleeve 13 are both provided with a first encoder 29 for measuring the rotation speed of the outer extension shaft 36. The inner extension shaft 42 of the active eccentric rotor 12 extends into the second sleeve 13, and the second sleeve 13 is provided with a second encoder 30 for measuring the rotation speed of the inner extension shaft 42. A gear ring 45 is provided at the end of the second sleeve 13, and a reducer 28 is provided outside the second sleeve 13. The output shaft of the reducer 28 extends into the second sleeve 13 and a gear 46 is provided to mesh with the gear ring 45. The sampling inner cone 18 is provided with an axial device cabin 21, and a flow measurement motor 48 is provided in the axial device cabin 21. The axial device cabin 21 is provided with a transmission shaft hole 47, and a transmission shaft 49 is provided in the transmission shaft hole 47. The flow measurement motor 48 is connected to the input shaft of the reducer 28 through the transmission shaft 49.

[0044] The principle of the flow measurement component 5 to measure the airflow mass flow is:

[0045] When the airflow enters the device to form a stable flow field, the flow measurement motor 48 is started to rotate the active eccentric rotor 12 around the x-axis through the above-mentioned transmission structure. At this time, for the gas in the annular eccentric flow channel 41, the center of mass of the gas as a whole is located on the y-axis. Since the annular eccentric flow channel 41 rotates around the x-axis as a whole, the center of mass of the gas in the annular eccentric flow channel 41 is forced to rotate around the x-axis synchronously. For the gas in the annular conical eccentric flow channel 34, since the passive eccentric rotor 11 has no external power drive, there is a deviation between the cross-section of the annular conical eccentric flow channel 34 and the annular eccentric flow channel 41, and the gas flows from the annular conical eccentric flow channel 34 to the annular conical eccentric flow channel 41. When the airflow enters the annular eccentric flow channel 41 or enters the annular conical eccentric flow channel 34 from the annular eccentric flow channel 41, it will be deflected. The deflected airflow contacts the inner wall surface of the inner eccentric cone 31 and the outer eccentric cone ring 32 to generate a force, forcing the annular conical eccentric flow channel 34 to align with the cross section of the annular eccentric flow channel 41. As the annular eccentric flow channel 41 rotates continuously, the airflow indirectly drives the passive eccentric rotor 11 to rotate synchronously. Due to the inertia of the airflow, there is a certain phase difference in the rotation of the passive eccentric rotors 11 on both sides of the active eccentric rotor 12, and this phase difference is proportional to the mass flow rate of the fluid in the flow channel.

[0046] When a particle in a rotating system moves toward or away from the center of rotation, an inertial force will be generated. When a particle with a mass of δm moves axially at a uniform speed u in a flow channel rotating around the rotation axis x at an angular velocity ω, the particle will obtain two acceleration components:

[0047] Normal acceleration (centripetal acceleration) is equal to 2ωr and points toward the x-axis.

[0048] The tangential acceleration (Coriolis acceleration) is equal to 2ωu and its direction is perpendicular to the normal acceleration.

[0049] In order to make the particle have tangential acceleration, a force equal to 2ωuδm needs to be added in the direction of the tangential acceleration. This force comes from the wall of the flow channel. The force acting on the wall of the flow channel is the Coriolis force exerted by the fluid on the flow channel.

[0050] When a fluid with a density of ρ flows along a channel at a constant velocity u, any length of the flow channel will be subject to a tangential Coriolis force:

[0051] A is the cross-sectional area of ​​the flow channel. Since the mass flow rate qm=ρuA, then:

[0052] As long as the Coriolis force exerted on the rotating flow channel by the fluid flowing in the flow channel can be measured directly or indirectly, the mass flow rate of the fluid passing through the flow channel can be measured.

[0053] The present application can measure the rotational speed of the passive eccentric rotor 11 through the first encoder 29. At the same time, the entire device is hoisted on a high-altitude aircraft. The airflow velocity in the flow measurement component 5 can be obtained from the aircraft airspeed. The mass flow rate of the airflow in the flow measurement component 5 can be known by comparing the phase difference between the two passive eccentric rotors 11.

[0054] Combined with Figure 3 , Attachment Fig. 9 , Attachment Fig.10 and attached Fig.11 The sampling assembly 4 includes a sampling shell 16, a sampling inner cone 18 and an annular sampling bracket 19. The inlet end of the sampling assembly 4 is connected to the flow measurement assembly 5, and the outlet end is convergent. An annular pressurization chamber 17 is arranged between the inlet ends of the sampling shell 16 and the sampling inner cone 18, and an annular decompression flow channel 20 is arranged between the outlet ends. A third fixed grid 50 is arranged between the sampling shell 16 and the sampling inner cone 18 for fixing. One end of the annular pressurization chamber 17 is connected to the annular cone-shaped eccentric flow channel 34 in the passive eccentric rotor 11 at one end of the flow measurement assembly 5, and the other end is connected to the annular decompression flow channel 20. An annular exhaust port 23 connected to the outside of the sampling assembly 4 is arranged at the end of the annular decompression flow channel 20. A detachable tail cone 22 is arranged at the tail of the sampling inner cone 18. The annular sampling bracket 19 is slidably connected to the sampling shell 16, and the annular sampling bracket 19 can be moved to the place where the annular pressurization chamber 17 and the annular decompression flow channel 20 are connected.

[0055] The flow cross-sectional area formed by the annular pressurizing chamber 17 is larger than the annular cone-shaped eccentric flow channel 34 , and the flow cross-sectional area formed by the annular decompression flow channel 20 is smaller than the annular pressurizing chamber 17 .

[0056] Combined with Fig.12 , Attachment Fig.13 and attached Fig.14 The annular sampling bracket 19 is provided with a plurality of sampling box fixing frames 54 around the periphery, and the sampling box fixing frames 54 connect the inner circle of the annular sampling bracket 19 with the outer circle, and a detachable sampling box 55 is provided in the sampling box fixing frame 54, and a filter cloth 56 is provided in the sampling box 55, and the filter cloth 56 is perpendicular to the channel formed by the sampling box fixing frame 54, and a plurality of guide rods 53 are provided at one end of the annular sampling bracket 19, and a plurality of guide holes 25 matching the guide rods 53 are provided in the sampling housing 16, and a plurality of side equipment compartments 15 are provided in the sampling housing 16, and a sampling electric cylinder 26 is provided in the side equipment compartment 15, and the free end of the sampling electric cylinder 26 passes through the guide hole 25 and is connected to the end of the guide rod 53, and the side equipment compartment 15 is provided with a detachable side equipment compartment cover 52.

[0057] Combined with Fig.12 and attached Fig.13 The sampling housing 16 is provided with a plurality of operation windows 24 around a circle, and the sampling electric cylinder 26 displaces the annular sampling bracket 19 between the operation window 24 and the connection point between the annular pressurization chamber 17 and the annular decompression flow channel 20. The operation window 24 is connected to the outside of the sampling housing 16 and is provided with a detachable operation window cover 51.

[0058] The working principle of the above structure is as follows: after the airflow enters the device to form a stable flow field, the airflow enters the annular boost chamber 17. Due to the increase in the flow cross-sectional area, the airflow here is decelerated and pressurized. Then the airflow enters the annular decompression flow channel 20. Due to the decrease in the flow cross-sectional area, the airflow here is accelerated and decompressed, so that there is a pressure difference between the annular boost chamber 17 and the annular decompression flow channel 20. In addition, for the airflow attached to the outer wall of the device, it is deflected when passing through the convergence of the sampling shell 16 and forms a detached vortex at the annular exhaust port 23. The detached vortex continues to flow backward along the surface of the tail cone 22, forming a low-pressure area outside the annular exhaust port 23, and forming a pressure difference with the annular decompression flow channel 20. When the annular sampling bracket When 19 is pushed by the sampling electric cylinder 26 to the connection point between the annular boost chamber 17 and the annular decompression flow channel 20, the pressure difference between the annular boost chamber 17 and the annular boost chamber 17 will force the air flow to flow through the filter cloth 56 and be discharged through the annular exhaust port 23. The filter cloth can be fully impregnated with the required impregnation reagent filter material in advance, and the objects to be detected in the high-altitude gas will react with the impregnation reagent and remain in the pores of the filter cloth 56. After sampling is completed, the sampling electric cylinder 26 pulls the annular sampling bracket 19 back to the operating window 24 to stop sampling. When the aircraft returns to the ground, the staff opens the operating window cover 51 to recover the sampling box 55, and dissolves and separates the objects to be detected in the filter cloth 56 for subsequent detection operations.

[0059] Combined with Fig.15The air intake assembly 3 includes an air intake duct housing 6, an air intake cone 7 and an air intake cone base 8. An air intake duct 58 is provided between the air intake duct housing 6, the air intake cone 7 and the air intake cone base 8. The end of the air intake cone base 8 is sleeved with the first shaft sleeve 10. The air intake cone 7 is slidably sleeved on the air intake cone base 8. An inwardly converging air inlet 59 is provided at the end of the air intake duct housing 6. A throttling electric cylinder 57 is provided in the air intake cone base 8. The free end of the throttling electric cylinder 57 is connected to the air intake cone 7.

[0060] The operation of the sampling component 4 and the flow measurement component 5 requires a stable airflow, and the flow rate of the airflow entering the device needs to be adjusted in real time. When the air intake cone 7 in the air intake component 3 is pushed by the throttling electric cylinder 57, the cross-sectional area formed by the air intake cone 7 and the inwardly converging air inlet 59 will change, thereby adjusting the flow rate of the airflow. When the throttling electric cylinder 57 pushes the air intake cone 7 outward so that the cone surface fits the inner surface of the air inlet 59, the air intake duct 58 can be closed.

[0061] The use process of this device:

[0062] Before sampling, the filter cloth 56 is fully impregnated with the required impregnation reagent filter material, and the entire device is hoisted on the belly or wing of the high-altitude aircraft through the hoisting bracket 2. The sampling electric cylinder 26 is controlled to move the annular sampling bracket 19 to the operating window 24, and the operating window cover 51 is opened. The sampling box 55 is installed on the annular sampling bracket 19. After the installation is completed, the operating window cover 51 is closed, and the throttling electric cylinder 57 is controlled to keep the air inlet 58 closed, waiting for the high-altitude aircraft to take off.

[0063] After the high-altitude aircraft takes off and arrives at the designated airspace to be detected, the throttling electric cylinder 57 is controlled to open the air inlet 58 to a half-open position, and the flow measurement motor 48 is started to rotate the active eccentric rotor 12 at a constant speed. After the airflow enters the device, the passive eccentric rotor 11 is rotated. The rotation speed of the two passive eccentric rotors 11 is read in real time by the first encoder 29 and the phase difference is calculated. After the mass flow rate is stable, the sampling electric cylinder 26 is controlled to move the annular sampling bracket 19 to the position where the annular boost chamber 17 and the annular boost chamber 17 are connected. The airflow passes through the filter cloth 56 to react with the impregnated reagent filter material, and at the same time, the metering mass flow of the airflow is started. The throttling electric cylinder 57 is controlled to continuously adjust the opening of the air inlet 58 to keep the mass flow stable. After the accumulated airflow mass reaches the target value, the sampling electric cylinder 26 is controlled to move the annular sampling bracket 19 to the operating window 24, stop recording the airflow mass flow, and at the same time control the high-altitude aircraft to return to the ground for landing.

[0064] After the high-altitude aircraft lands, the ground staff opens the operating window cover 51 and takes out the sampling box 55 for subsequent sample operations.

[0065] The present invention and its implementation methods are described above, and such description is not restrictive, and the actual structure is not limited thereto. In short, if a person skilled in the art is inspired by it, and does not deviate from the purpose of the invention, and does not creatively design a structure and implementation method similar to the technical solution, they should all fall within the protection scope of the present invention.

Claims

1. A high-altitude particle pollutant detection sampling device, comprising a fuselage shell (1), a hanging bracket (2), an air intake assembly (3) and a sampling assembly (4), wherein the fuselage shell (1) is cylindrical, an air intake assembly (3) is arranged at one end, a sampling assembly (4) is arranged at the other end, a hanging bracket (2) is arranged at the top, and the top of the hanging bracket (2) is hangingly connected to the belly or wing of the high-altitude aircraft, a flow measurement assembly (5) is arranged in the fuselage shell (1), one end of the flow measurement assembly (5) is connected to the air intake assembly (3), and the other end is connected to the sampling assembly (4), characterized in that: The flow measurement assembly (5) comprises a shaft (27), a first shaft sleeve (10) and a second shaft sleeve (13); the first shaft sleeve (10) and the second shaft sleeve (13) are respectively arranged at two ends of the shaft (27); the middle part of the shaft (27) is rotatably sleeved with an active eccentric rotor (12), and the two ends are rotatably sleeved with a passive eccentric rotor (11); The active eccentric rotor (12) comprises an inner eccentric cylinder (38) and an outer eccentric cylinder (39) which are connected to each other, an annular eccentric flow channel (41) is provided between the inner eccentric cylinder (38) and the outer eccentric cylinder (39), and an inner extension shaft (42) is provided on the inner eccentric cylinder (38) at the axis center of the body shell (1); The passive eccentric rotor (11) comprises an inner eccentric cone (31) and an outer eccentric cone ring (32) connected to each other, an annular cone eccentric flow channel (34) is arranged between the inner eccentric cone (31) and the outer eccentric cone ring (32), an outer extension shaft (36) is arranged at the axis center of the inner eccentric cone (31) of the fuselage shell (1), a first encoder (29) for measuring the rotation speed of the outer extension shaft (36) is arranged in the first sleeve (10) and the second sleeve (13), and the annular cone eccentric flow channel (34) at one end of the flow measurement component (5) is connected to the air intake component (3), and the annular cone eccentric flow channel (34) at the other end is connected to the sampling component (4).

2. The high-altitude particle pollution detection and sampling device according to claim 1 is characterized in that: The sampling assembly (4) comprises a sampling outer shell (16), a sampling inner cone (18) and an annular sampling bracket (19); the inlet end of the sampling assembly (4) is connected to the flow measurement assembly (5), and the outlet end is convergent; an annular pressurization chamber (17) is provided between the inlet ends of the sampling outer shell (16) and the sampling inner cone (18); an annular decompression flow channel (20) is provided between the outlet ends; one end of the annular pressurization chamber (17) is connected to the annular cone-shaped eccentric flow channel (34) of the flow measurement assembly (5), and the other end is connected to the annular decompression flow channel (20); an annular exhaust port (23) connected to the outside of the sampling assembly (4) is provided at the end of the annular decompression flow channel (20); the annular sampling bracket (19) is slidably connected to the sampling outer shell (16), and the annular sampling bracket (19) can be moved to the point where the annular pressurization chamber (17) and the annular decompression flow channel (20) are connected.

3. The high-altitude particle pollution detection and sampling device according to claim 1 is characterized in that: The geometric centers of the inner eccentric cylinder (38) and the annular eccentric flow channel (41) are eccentrically arranged relative to the fuselage shell (1); the geometric centers of the inner eccentric cone (31) and the annular conical eccentric flow channel (34) at one end with a larger cone area are eccentrically arranged relative to the fuselage shell (1); the geometric centers of the other ends are concentrically arranged relative to the fuselage shell (1); the end with a larger cone area of ​​the passive eccentric rotor (11) is fitted with the end of the active eccentric rotor (12), and the eccentric distances of the annular conical eccentric flow channel (34) and the annular eccentric flow channel (41) are equal.

4. The high-altitude particle pollution detection and sampling device according to claim 1 is characterized in that: The air intake assembly (3) comprises an air intake duct housing (6), an air intake cone (7) and an air intake cone base (8); an air intake duct (58) is provided between the air intake duct housing (6), the air intake cone (7) and the air intake cone base (8); the end of the air intake cone base (8) is sleeved with a first shaft sleeve (10); the air intake cone (7) is slidably sleeved on the air intake cone base (8); an inwardly converging air intake port (59) is provided at the end of the air intake duct housing (6); a throttling electric cylinder (57) is provided in the air intake cone base (8); and the free end of the throttling electric cylinder (57) is connected to the air intake cone (7).

5. The high-altitude particle pollution detection and sampling device according to claim 1 is characterized in that: An inner shaft hole (43) matching the shaft rod (27) is arranged in the inner extension shaft (42), and an outer shaft hole (35) matching the inner extension shaft (42) is arranged in the outer extension shaft (36). The outer extension shaft (36) at one end of the flow measurement component (5) extends into the first shaft sleeve (10), and the outer extension shaft (36) at the other end extends into the second shaft sleeve (13). The inner extension shaft (42) of the active eccentric rotor (12) extends into the second shaft sleeve (13), and a second encoder (30) for measuring the rotation speed of the inner extension shaft (42) is arranged in the second shaft sleeve (13).

6. The high-altitude particle pollution detection and sampling device according to claim 2 is characterized in that: A gear ring (45) is provided at the end of the second sleeve (13), a reducer (28) is provided outside the second sleeve (13), an output shaft of the reducer (28) extends into the second sleeve (13) and a gear (46) is provided to mesh with the gear ring (45), a flow measurement motor (48) and a transmission shaft (49) are provided in the sampling inner cone (18), and the flow measurement motor (48) is connected to the input shaft of the reducer (28) via the transmission shaft (49).

7. The high-altitude particle pollution detection and sampling device according to claim 2 is characterized in that: The annular sampling bracket (19) is provided with a plurality of detachable sampling boxes (55) around its periphery, the sampling boxes (55) are provided with filter cloths (56), one end of the annular sampling bracket (19) is provided with a plurality of guide rods (53), the sampling housing (16) is provided with a plurality of guide holes (25) matching the guide rods (53), the sampling housing (16) is provided with a plurality of sampling electric cylinders (26), and the free ends of the sampling electric cylinders (26) pass through the guide holes (25) and are connected to the ends of the guide rods (53).

8. The high-altitude particle pollution detection and sampling device according to claim 7 is characterized in that: The sampling housing (16) is provided with a plurality of operating windows (24) around its periphery. The sampling electric cylinder (26) moves the annular sampling bracket (19) between the operating window (24) and the connection point between the annular pressurizing chamber (17) and the annular decompression flow channel (20). The operating window (24) is connected to the outside of the sampling housing (16) and is provided with a detachable operating window cover (51).

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