Downward-looking electric field sounding system and detection method

Abstract

The present application relates to a kind of atmospheric electric field detection equipment and detection method, including electric field sounding instrument, carrying aircraft, ground receiving system.Electric field sounding instrument is transported to predetermined position and height and falls, rotates under the drive of tail wing, centrifugal force generates airflow rectification effect, keep stable posture, tail wing is subjected to air resistance, keep electric field sounding instrument uniform speed fall.Electric field sounding instrument detects the horizontal direction atmospheric electric field in the falling process, data is returned to ground, can obtain the horizontal electric field intensity and direction on sounding track in combination with geomagnetic sensor, realize the horizontal electric field detection at different heights on sounding path.Electric field sounding instrument is installed with charge sensor, positioning sensor, gyroscope and geomagnetic sensor, temperature sensor, atmospheric electric field is detected simultaneously, and position and height, geomagnetic and instrument itself rotation speed, temperature are synchronously detected, realize the synchronous comprehensive detection rate of electric field, temperature and other physical quantities in the air.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of atmospheric physical detection, and in particular to a downward-projection type electric field sounding system and a detection method. BACKGROUND

[0002] Lightning disaster seriously threatens human life and property safety, and due to the great randomness of the time and space of lightning, lightning hazards are huge and disasters are rapid, which brings many difficulties to the research, prediction and prevention of lightning. Atmospheric electric field detection is an important parameter for understanding thunderstorm clouds, and the intensity and its change can be used to represent thunderstorm activities, atmospheric convection activities, etc. Real-time detection of atmospheric electric field, detection of charge structure, charge density distribution in thunderstorm cloud, and evolution research with the development of thunderstorm process have important scientific significance for revealing the physical mechanism of lightning occurrence and development process.

[0003] Electric field detection can be divided into ground atmospheric electric field detection, cloud electric field detection and space electric field detection according to the object of detection. At present, the ground atmospheric electric field is mainly detected, so as to monitor the whole process of thunderstorm cloud in the sky of the detected area. However, it is limited to analyze the electric field measurement value obtained by the ground atmospheric average electric field instrument for the charge distribution, the position of the charge center, the polarity and the electrification mechanism in the cloud layer, and the measurement of the atmospheric electric field in the cloud can make up for this defect to some extent.

[0004] The existing technology of thunderstorm cloud electric field detection mainly adopts a rotating vane type, a double ball type and the like as a charge sensor detection method. The electric field detector sets a rotating vane or a double ball as a sensor. The electric field detector is carried by a corresponding carrier tool, and the vector electric field component in the air is detected during the ascending process through the thunderstorm cloud. Two metal conductor electrodes with the same size are symmetrically installed on the rotating shaft as charge sensors, and the two electrodes are connected with a charge amplification circuit. In the external environmental electric field, the two electrodes generate equal charges with opposite polarities due to polarization. In the case that the external electric field does not change, the polarization charges are transferred by rotating the two electrodes. The amount of transferred charges between the two electrodes can be measured through the charge amplification circuit connected with the two electrodes. Considering safety and other factors, the electric field sounding instrument usually adopts a balloon carrier. However, the sounding path of the balloon is uncontrollable due to the influence of the airflow in the thunderstorm cloud, and the sounding path is difficult to pass through the center of the thunderstorm cloud, so that the region with the most intense convection activity in the thunderstorm cloud cannot obtain direct electric field detection data, which cannot meet the needs of the research on thunderstorm charge structure in the field of atmospheric electricity.

[0005] Therefore, it is necessary to develop a downward-projection type electric field sounding system and a detection method to solve the above problems. SUMMARY

[0006] The purpose of the present application is to design a downward-projection type electric field sounding system and a detection method to solve the above problems.

[0007] The present application achieves the above-mentioned purpose by the following technical solutions:

[0008] The lower-throwing electric field sounding system comprises:

[0009] At least one throwing assembly provided on the carrier aircraft for throwing the electric field sonde downward;

[0010] At least one electric field sonde for atmospheric electric field detection; the electric field sonde is placed in the throwing assembly when it is not thrown;

[0011] A ground receiving system; the electric field sonde is communicatively connected with the ground receiving system.

[0012] The electric field sonde comprises:

[0013] A tail wing assembly for maintaining the electric field sonde falling at a constant speed;

[0014] A charge sensor; the charge sensor is installed on the tail wing assembly;

[0015] A charge amplification circuit;

[0016] An operation unit; the charge sensor is electrically connected with the charge amplification circuit;

[0017] A transmitting unit for signal transmission;

[0018] A transmitting antenna; the transmitting unit is electrically connected with the transmitting antenna, and the transmitting antenna is communicatively connected with the ground receiving system;

[0019] A positioning sensor;

[0020] A positioning processing module; the positioning sensor is electrically connected with the positioning processing module;

[0021] A three-axis attitude sensor;

[0022] A three-axis attitude processing circuit; the three-axis attitude sensor is electrically connected with the three-axis attitude processing circuit;

[0023] A temperature sensor;

[0024] A temperature sensing processing circuit; the temperature sensor is electrically connected with the temperature sensing processing circuit;

[0025] A particle charge amount sensor;

[0026] A particle charge amount amplification circuit; the particle charge amount sensor is electrically connected with the particle charge amount amplification circuit; the operation unit is electrically connected with the charge amplification circuit, the transmitting unit, the positioning processing module, the three-axis attitude processing circuit, the temperature sensing processing circuit, and the particle charge amount amplification circuit.

[0027] Specifically, the tail wing assembly comprises at least one pair of tail wings, and electrodes are arranged on the tail wings, and two electrodes on a pair of tail wings form a pair of charge sensors.

[0028] Specifically, the throwing assembly comprises an unhooker, and the unhooker is an electronic unhooker; a ring is arranged on the electric field sonde, and the ring is hung on the unhooker.

[0029] Specifically, the throwing assembly comprises a throwing barrel, the unhooker is arranged at the top of the throwing barrel, the tail wings are arranged in the throwing barrel after being folded, the inner ends of the tail wings are rotatably arranged on the upper end of the tail of the electric field sonde through tail wing shafts, a tail wing spring is sleeved on the tail wing shaft, one end of the tail wing spring is connected with the tail, and the other end of the tail wing spring is connected with the tail wing, and the tail wing spring is in a compressed state when the tail wings are arranged in the throwing barrel.

[0030] Specifically, the electric field sonde further comprises a parachute and a parachute opening mechanism, the tail is provided with an umbrella compartment with an open end at the tail end, and the parachute and the parachute opening mechanism are arranged in the umbrella compartment; a cover of the umbrella compartment is arranged at the top end of the umbrella compartment, the cover is connected with the middle part of the parachute, a cover locking pin is arranged at the lower part of the cover, and the lower end of the cover locking pin is connected with the acting part of the parachute opening mechanism.

[0031] Specifically, the parachute opening mechanism comprises an opening motor, a sleeve, a rotating shaft, a push rod, a locking rod and a locking rod spring; the opening motor is electrically connected with the operation unit; the rotating shaft is arranged on the output shaft of the opening motor; an internal thread is arranged on the rotating shaft; an external thread is arranged on the push rod; the external thread of the push rod is matched with the internal thread of the rotating shaft; the opening motor is fixedly arranged in the tail; the locking rod is at least one; at least one installation groove is arranged on the inner wall of the sleeve; the middle part of the locking rod is rotatably arranged in the installation groove through a locking rod shaft; the locking rod spring is sleeved on the locking rod shaft; one end of the locking rod spring is connected with the wall of the installation groove; the other end of the locking rod spring is connected with the locking rod; the upper part of the locking rod is a locking hook; the middle part of the locking rod is an opening tenon; the lower part of the locking rod is a locking tenon; an annular groove is arranged on the lower end of the side wall of the cover locking pin; the locking rod spring makes the locking rod in a locking hook locking state in a normal state, and the locking hook is clamped into the annular groove; the upper end of the push rod is connected with the lower end of a push rod table; when the push rod rises, the push rod table moves to the groove between the opening tenon and the locking tenon; the locking tenon is staggered with the push rod table and is no longer limited; the push rod continues to rise; the push rod table pushes the opening tenon; the locking hook is driven to be opened; the push rod continues to rise; the push rod table pushes the cover locking pin; the cover is pushed out; the cover drives the parachute to be popped out.

[0032] Specifically, the electric field sonde further comprises a middle part, and an instrument compartment is arranged in the inside of the middle part; an equipment compartment is further arranged in the inside of the tail; the positioning sensor, the three-axis attitude sensor, the transmitting antenna and the parachute opening motor are arranged in the equipment compartment; the positioning processing module, the three-axis attitude processing circuit, the temperature sensing processing circuit, the particle charge quantity amplification circuit, the operation unit and the transmitting unit are integrated on a PCB board, and the PCB board is arranged in the instrument compartment.

[0033] Specifically, the electric field sonde further comprises a head, an upper portion of the head is provided with a battery compartment, a power supply is installed in the battery compartment, the power supply is electrically connected with the PCB, a heat preservation layer is arranged on the periphery of the battery compartment, a heating cavity is formed between the heat preservation layer and the battery compartment, and a heating agent is arranged in the heating cavity; a lower portion of the head is provided with an airflow compartment, the bottom of the airflow compartment is open, a plurality of air outlets are arranged on the sidewall of the top of the airflow compartment along a circumference thereof, the particle charge sensor comprises an electricity measuring ring, the electricity measuring ring is horizontally installed in the middle portion of the airflow compartment, a temperature sensor is installed on the top of the airflow compartment, and the particle charge amplification circuit is an electricity measuring ring charge amplification circuit.

[0034] The down-throwing electric field sounding method comprises the following steps:

[0035] S1, before the carrying aircraft carrying the electric field sonde ascends, the release position and height of the electric field sonde are preset according to the longitude, latitude and sea level height, and the parachute opening height of the electric field sonde from the ground, the preset data is written into the operation unit, and the wireless communication of the launch unit and the ground receiving system is debugged to be good;

[0036] S2, the head and the middle portion of the electric field sonde are separated, the heating agent is filled into the heating cavity, the power switch is turned on, and the head and the middle portion are combined;

[0037] S3, the electric field sonde is folded and loaded into the throwing barrel of the carrying aircraft, and the hanging ring is hung on the unhooking device;

[0038] S4, the carrying aircraft carrying the electric field sonde ascends, when the positioning sensor detects that the position and height meet the preset position and height, the operation unit sends a release instruction, and the electric field sonde is unhooked and falls;

[0039] S5, the electric field sonde falls under the action of the tail wing assembly, in the falling process, the airflow flows into the airflow compartment from the bottom opening, passes through the electricity measuring ring, and then flows out through the air outlets, the electricity measuring ring senses the charge mutation of the charged particles, sends the charge mutation to the electricity measuring ring amplification circuit for amplification, and then sends the charge mutation to the operation unit; the temperature sensor measures the atmospheric temperature in real time, which is used to determine the performance of the battery at different temperatures and the stability of the system at different temperatures, the data detected by the temperature sensor is sent to the temperature sensing processing circuit for processing, and then sent to the operation unit;

[0040] The electrodes installed on the tail wing generate induced charges under the influence of the electric field in the air during the rotation process, the induced charges are transferred at both ends, the transferred charges are measured, the signals are sent to the charge amplification circuit, and then sent to the operation unit;

[0041] The positioning sensor detects the longitude, latitude and height data through the global satellite positioning system, sends the data to the positioning processing module for data processing, and then sends the data to the operation unit;

[0042] The triaxial attitude sensor obtains the geomagnetic field and gravity acceleration of XYZ triaxial vector in real time, so as to obtain the rotation speed, falling speed and triaxial attitude of the electric field sounding instrument, and the data is sent to the triaxial attitude processing circuit for processing and then sent to the operation unit;

[0043] The detected electric field signal, height, three-dimensional attitude and azimuth data, and temperature data are processed by the operation unit, transmitted by the transmitting unit, and received by the ground receiving system;

[0044] S6, when the electric field sounding instrument falls to the preset parachute opening height, the operation unit sends an instruction to the parachute opening mechanism, the parachute opens and the electric field sounding instrument falls slowly, and finally, the electric field sounding instrument is recovered according to the positioning information of the positioning processing module.

[0045] The beneficial effects of the present application are:

[0046] In the present application, the electric field sounding instrument is thrown by a carrier aircraft, the electric field sounding instrument passes through a thunderstorm cloud in a falling manner, the electric field sounding instrument maintains the attitude under the action of the tail wing rotation, the tail wing is subjected to air resistance, the electric field sounding instrument falls at a uniform speed, and is not a free fall, even if subjected to airflow interference, the electric field sounding instrument itself maintains a vertical state and falls along a slant trajectory, or the electric field sounding instrument maintains a certain inclination angle, and is not irregularly swung, the inclination angle can be detected by a triaxial attitude sensor, the measured electric field is corrected, and the horizontal component of the electric field is accurately calculated; therefore, the electric field sounding system can obtain high-precision and high-temporal and spatial resolution electric field detection results, lays a foundation for establishing a thunderstorm sounding system, constitutes a sounding experiment platform, and analyzes the charge structure, charge density distribution and evolution process of the charge with the development of a thunderstorm cloud.

[0047] In addition, two or more than two downward electric field sounding instruments, a ground data receiving system or a multi-channel receiving and analyzing unit matched in number, and a plurality of ground atmospheric electric field detectors can form an electric field detection network in a thunderstorm cloud, a plurality of downward electric field sounding instruments are released at intervals, the electric field sounding instruments are positioned and time-synchronized by a global satellite positioning system, synchronous observation results of electric fields in different regions and heights in the air are obtained, important observation data are provided for analyzing and researching the charge structure, charge density distribution and evolution process of the charge with the development of a thunderstorm cloud. Through statistical regression analysis of the data, a mathematical model is established, and necessary means are provided for researching the physical mechanism of the electric field in a thunderstorm cloud and the development process of lightning. BRIEF DESCRIPTION OF DRAWINGS

[0048] Figure 1 It is a perspective view of the tail wing of the electric field sounding instrument;

[0049] Figure 2 It is a plan view of the tail wing of the electric field sounding instrument;

[0050] Figure 3 is a vertical section view of the tail wing folding of the electric field sounding instrument;

[0051] Figure 4 is a vertical section view of the internal structure of the tail wing unfolding of the electric field sounding instrument;

[0052] Figure 5 is a structure view of the parachute compartment and parachute opening mechanism;

[0053] Figure 6 is a structure view of the parachute opening mechanism in the locked state of the lock hook;

[0054] Figure 7 is a structure view of the parachute opening mechanism in the unlocked state of the lock hook;

[0055] Figure 8 is a schematic view of the suspension of the electric field sounding instrument;

[0056] Figure 9 is an electrical schematic diagram of the present application.

[0057] In the figure: 100-electric field sounding instrument, 200-carrier spacecraft, 300-ground receiving system, 400-computing unit, 500-power supply, 1-head, 2-middle, 3-tail, 4-tail wing, 5-tail wing shaft, 6-tail wing groove, 7-tail wing spring, 8-electrode, 9-airflow compartment, 10-air outlet, 11-electricity measuring ring, 12-temperature sensor, 13-battery compartment, 14-instrument compartment, 15-equipment compartment, 16-parachute compartment, 17-parachute, 18-parachute compartment cover, 19-hanging ring, 20-parachute compartment cover locking pin, 21-positioning sensor, 22-three-axis attitude sensor, 23-parachute opening mechanism, 24-shielding cover, 25-launching antenna, 26-USB socket, 27-unhooking button, 28-thermal insulation layer, 29-heating cavity, 30-parachute opening motor, 31-sleeve, 32-rotating shaft, 33-push rod, 34-locking rod, 35-locking rod shaft, 36-lock hook, 37-unlocking tenon, 38-locking tenon, 39-locking rod spring, 40-push rod platform, 201-launching cylinder, 202-unhooking device, 203-unhooking signal socket, 204-unhooking signal plug, 401-electricity measuring ring amplification circuit, 402-temperature sensor processing circuit, 403-charge amplification circuit, 404-positioning processing module, 405-three-axis attitude processing circuit, 406-launching unit. DETAILED DESCRIPTION

[0058] To make the purpose, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are some embodiments of the present application, rather than all the embodiments. The components of the embodiments of the present application described and shown in the drawings herein can be arranged and designed in various different configurations.

[0059] Therefore, the following detailed description of the embodiments of the application provided in the accompanying drawings is not intended to limit the scope of the application claimed, but merely represents selected embodiments of the application. Based on the embodiments of the application, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of the application.

[0060] It should be noted that similar reference numbers and letters refer to similar items in the following drawings, and therefore, once an item is defined in one drawing, it need not be further defined and explained in subsequent drawings.

[0061] In the description of the application, it should be understood that the terms "upper", "lower", "inner", "outer", "left", "right", and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship commonly understood by those skilled in the art, and are merely for the convenience of describing the application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the application.

[0062] In addition, the terms "first", "second", and the like are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0063] In the description of the application, it should also be noted that unless otherwise explicitly specified and limited, the terms "provided", "connected" and the like should be broadly understood, for example, "connected" can be fixedly connected, or detachably connected, or integrally connected; can be mechanically connected, or electrically connected; can be directly connected, or indirectly connected through an intermediate medium, or can be internal communication of two elements. For those of ordinary skill in the art, the specific meaning of the above terms in the application can be understood according to the specific circumstances.

[0064] The specific embodiments of the application will be described in detail below with reference to the accompanying drawings.

[0065] As Figures 1-9As shown, the downward thunderstorm cloud electric field sounding system is composed of an electric field sonde, a carrier aircraft and a ground receiving system, the carrier aircraft carries the electric field sonde to fly to a predetermined position and height in the air, releases the electric field sonde, and the electric field sonde detects the electric field in the thunderstorm cloud during the falling process from high altitude. The electric field sonde rotates under the drive of the tail wing, the centrifugal force produces airflow rectification effect, the electric field sonde maintains a stable posture during the falling process, the tail wing is subjected to air resistance, and the electric field sonde maintains a proper falling speed. The charge sensor is affected by the space electric field to generate induced charge, the induced charge is transferred at both ends, the transferred charge is measured and amplified, and then sent into an operation unit to inverse the space electric field. The electric field sonde is provided with a positioning sensor, a three-axis attitude sensor and a temperature sensor, during the detection of the electric field in the thunderstorm cloud, the longitude and latitude and height, the geomagnetic and rotation speed, and the temperature are synchronously detected through the positioning module, the three-axis attitude sensor and the temperature sensor, the horizontal vector electric field, temperature and other physical quantities in the air are synchronously and comprehensively detected, the wireless real-time return storage of the sounding data is realized in combination with the ground receiving system. The calculation and analysis system of the electric field sounding data is used to process and solve the detected electric field results. The electric field sounding system in the thunderstorm cloud is established, the thunderstorm cloud electric field sounding experiment is carried out, in combination with the ground atmospheric electric field instrument, multiple electric field sondes are released at different time intervals, time synchronization is realized, the electric field of the ground and different areas at the same time point is synchronously observed, and a fine electric field structure model in the thunderstorm cloud can be established. The present application solves the uncontrollable problem of the flight path of the existing ascending electric field sonde, the downward electric field detector mainly moves downward under the influence of gravity, the airflow in the cloud has little influence on the falling track of the sounding equipment, and the horizontal electric field at different heights in the vertical direction can be basically detected, high-precision and high-spatial-temporal resolution electric field detection results can be obtained, the thunderstorm cloud sounding system is established, the sounding experiment platform is formed, and important observation data for analyzing the charge structure, charge density distribution and evolution process of the thunderstorm cloud with the development of the thunderstorm cloud are provided.

[0066] The down-throw electric field sounding system of the application mainly comprises an electric field sounding instrument 100, a carrier aircraft 200 and a ground receiving system 300. The electric field sounding instrument 100 is mainly composed of a head 1, a middle part 2 and a tail part 3, and a tail wing 4. The head 1, the middle part 2 and the tail part 3 are in a cylindrical shape and are divided into three independent parts for easy manufacturing and internal device installation. The head 1, the middle part 2 and the tail part 3 can be made of plastic injection molding in batch production, and can be made by 3D printing in small quantity. Preferably, the material is Teflon, which has good non-stick properties and can prevent the accumulation of atmospheric moisture in the air, thereby improving the insulation performance. The head 1 and the middle part 2, and the middle part 2 and the tail part 3 are connected by buckles to form a whole. The buckle connection method is that the two connecting parts are provided with tenons and grooves, the tenons are embedded into the grooves when assembling, and the two parts are locked together by rotating a certain angle. If necessary, a bolt can be used for locking to prevent loosening. The tail wing 4 is installed at the end of the tail part 3 and there are four tail wings 4, which are the rotating power components of the electric field sounding instrument. The tail wing 4 is a folding structure and can rotate around the tail wing shaft 5. The tail wing shaft 5 is arranged in the tail wing groove 6 arranged at the end of the tail part 3. If the tail wing 4 is designed to be fixed and opened, it will occupy a large space and is not convenient for storage and transportation, and is easy to cause damage to the tail wing 4. A tail wing spring 7 (torsion spring) is arranged on the tail wing shaft 5. The tail wing spring 7 is sleeved on the tail wing shaft 5, one end of the tail wing spring 7 is connected with the tail part 3, and the other end of the tail wing spring 7 is connected with the tail wing 4. When the tail wing 4 is folded and placed in the throwing cylinder 201, the tail wing spring 7 is in a compressed state. When the electric field sounding instrument 100 is thrown, the tail wing 4 is ejected under the action of the tail wing spring 7, and an electrode 8 is embedded on the tail wing 4. Figure 1 , the tail wing folding elevation view of the electric field sounding instrument is shown in Figure 2 , and the tail wing folding elevation view of the electric field sounding instrument is shown in Figure 3 . As shown in Figure 1 , the angle α between the tail wing 4 and the central axis of the electric field sounding instrument is an inclined angle of 60-75° after the tail wing 4 is ejected, and the cross section of the tail wing 4 is arc-shaped. The inclined tail wing 4 generates a rotating power under the action of air resistance when the electric field sounding instrument 100 falls, drives the electric field sounding instrument 100 to rotate, generates an airflow rectification effect under the action of the rotating centrifugal force, and keeps a stable posture during the falling process. The tail wing 4 is also made of plastic material, and the electrode 8 is embedded on the upper surface of the tail wing 4, as shown in Figure 1 、 Figure 2 . The electrode 8 is made of conductive material, and the electrode 8 is drawn as a straight line in the figure only for illustration and is not limited to a metal wire. The electrode 8 can be a metal wire, a metal foil similar to the shape of the tail wing 4, or a conductive layer attached to the tail wing 4 by a plating process. The electrodes 8 of two opposite tail wings 4 serve as a pair of charge sensors, and there are two pairs of electrodes 8, as shown in Figure 2The electrode 8 is led out by double-core shielded wire, two inner core wires are connected with two corresponding electrodes 8 respectively, and the shielding layer is grounded. In the case that the environmental electric field is unchanged, the two opposite electrodes 8 are rotated, so that the polarization charge of the electrode 8 is changed to generate charge transfer, the size of the transferred charge between the two electrodes 8 is measured, and the strength of the environmental electric field can be calculated.

[0067] The lower part of the head 1 is an airflow bin 9, the bottom of the airflow bin 9 is open, and a plurality of air outlets 10 are uniformly arranged on the top along a circumference, as shown in Figure 3 、 Figure 4 , Figure 3 It is a folded vertical section view of the tail wing of the electric field sonde, the tail wing is folded in the tail wing groove 6, Figure 3 The internal device is not drawn. When the electric field sonde 100 falls, the airflow flows from the bottom and out of the air outlet 10. The inner side of the airflow bin 9 is provided with a current measuring ring 11, which is a Faraday ring, as shown in Figure 4 , Figure 4 It is a vertical section view of the internal structure of the unfolded tail wing of the electric field sonde. The current measuring ring 11 is a coil wound on a ring-shaped magnetic material. The two ends of the coil are connected to an amplification circuit by double-core shielded wire, and the shielding layer is grounded. The atmosphere contains small solid particles, and the particles carry electric charge in the electric field. When the charged particles pass through the current measuring ring 11, the current measuring ring 11 induces a sudden change of electric charge. According to the waveform of the induced sudden change of electric charge, the amount of charge carried by the particles can be judged, which provides parameters for comprehensive detection of the atmosphere. The top of the airflow bin 9 is provided with a temperature sensor 12 for real-time measurement of the atmospheric temperature, which is used to determine the performance of the battery at different temperatures and the stability of the system at different temperatures.

[0068] The upper part of the head 1 is a battery bin 13, the inside of the middle part 2 is an instrument bin 14, the inside of the tail part 3 is a device bin 15, and the center of the end of the tail part 3 is an umbrella bin 16, as shown in Figure 4 The umbrella bin 16 places a parachute 17, the top end of the umbrella bin 16 is an umbrella bin cover 18, the umbrella bin cover 18 and the middle part of the parachute 17 are connected together, the upper part of the umbrella bin cover 18 is provided with a hanging ring 19, and the lower part of the umbrella bin cover 18 is provided with an umbrella bin cover locking pin 20, as shown in Figure 5 .

[0069] The device bin 15 is installed with a positioning sensor 21, a three-axis attitude sensor 22, and an umbrella opening mechanism 23. The positioning sensor 21 is a global satellite positioning system sensor, which can be the Chinese Beidou satellite navigation system BDS, or the American satellite navigation system GPS, the Russian satellite navigation system GLONASS, or the European satellite navigation system GALILEO. The positioning sensor 21 is used to determine the latitude, longitude, and height during the falling detection of the electric field sonde 100, to calculate the falling speed, and to provide system time service. The Z-axis of the three-axis attitude sensor 22 coincides with the center of the device bin 15. The three-axis attitude sensor 22 is a high-performance three-dimensional motion attitude measuring device based on MEMS technology, which includes three-axis gyroscopes, three-axis accelerometers, three-axis electronic compasses, and other motion sensors. Through the embedded low-power ARM processor, temperature-compensated three-dimensional attitude and azimuth data are obtained. The sensor can measure the geomagnetic intensity and acceleration, thereby obtaining the geomagnetic field and gravitational acceleration of the XYZ three-axis vector in real time, measuring the attitude and rotation speed of the electric field sonde 100, and correcting the error of the electric field intensity information obtained by inversion.

[0070] Considering the working environment of strong electric field and strong electromagnetic radiation in thunderstorm cloud, the electromagnetic protection of the sounding instrument is needed to ensure its reliability. The instrument bin 14 is installed with a shielding cover 24 to avoid the influence of strong electromagnetic radiation in the discharge process of thunderstorm cloud on the circuit. The shielding cover 24 is installed with an electric ring amplification circuit 401, a temperature sensing processing circuit 402, a charge amplification circuit 403, a positioning processing module 404, a three-axis attitude processing circuit 405 and a transmitting unit 406 controlled by the operation unit 400. The charge amplification circuit 403 is a double-channel amplifier connected with two-channel charge sensors, and different amplification factors can be set. The atmospheric electric field intensity changes greatly, and the two-channel charge sensors and different amplification factors are set to detect electric fields of different intensities, so as to realize high-precision and high-spatial and temporal resolution electric field detection. Considering that the maximum electric field intensity in thunderstorm cloud changes greatly and may exceed 20 kV / m, the electric field sounding instrument 100 is designed to have two electric field detection ranges of ±20 kV / m and ±200 kV / m. When the electric field intensity is weak, ±20 kV / m is used to improve the resolution, and when the electric field intensity is strong, ±200 kV / m is used to meet the maximum electric field detection requirements. The result of the electric field sounding experiment can also be adjusted. The sounding instrument measures the signal output by the electric field sensor with a 16-bit measurement resolution. The minimum resolution of two-channel electric field measurement is 0.6 V / m and 6.1 V / m, and the signal sampling rate is 100 Hz. The operation unit 400 is a programmable single-chip microcomputer integrated with the above-mentioned circuits on a PCB board, which is packaged with heat preservation and waterproof and installed in the shielding cover 24 of the instrument bin 14. The transmitting antenna 25 of the transmitting unit is installed in the equipment bin 15 to avoid the shielding of the transmitting signal, and is connected with the transmitting unit 406 by a coaxial cable. The USB socket 26 and the unhooking button 27 are installed on the outer wall of the middle part 2. The USB socket 26 is used to connect a computer to write programs and preset parameters for the operation unit 400, and the unhooking button 27 is used to load the electric field sounding instrument 100 into the carrier vehicle 200.

[0071] Considering that lithium battery cannot work normally in low temperature environment, and lithium battery generates low heat during discharging, and the design working temperature of the sonde can reach-50℃, therefore, the heat preservation material is installed in the battery compartment, and the space for placing auxiliary heat source is reserved. The outer periphery of the battery compartment 13 is provided with a heat preservation layer 28, and a heating cavity 29 is formed between the heat preservation layer 28 and the battery compartment 13 for placing the heating agent. The ferrous oxide material is added into the heating cavity 29 as an auxiliary heat source before the sonde is launched. The ferrous oxide can react with oxygen in the air to become ferric oxide to release heat, and the process is slow and lasting, which can meet the need of maintaining the temperature in the battery compartment. The heating device is light in weight, and does not need to consume additional power, which is suitable for use in the electric field sonde. The power supply 500 is placed in the battery compartment 13, and the power supply 500 adopts two groups of double-core lithium batteries to form a double-path power supply of ±7.2V for supplying power to the sensor and the control circuit. The lithium battery is installed on the outside of the bottom of the middle part 2 and fixed with the bottom of the middle part 2. The power switch is arranged beside the lithium battery. When the head part 1 is separated from the middle part 2, the heating cavity 29 presents a ring-shaped groove, and the heating cavity 29 is filled with the heating agent. When the head part 1 is connected with the middle part 2, the lithium battery is embedded in the battery compartment 13, and the heating cavity 29 is blocked by the middle part 2. See Figure 4 .

[0072] The parachute opening mechanism 23 includes a parachute opening motor 30, a sleeve 31, a rotating shaft 32, a push rod 33, and a lock rod 34. The parachute opening motor 30 is provided with a reduction gear box, and the rotating shaft 32 is installed on the output shaft. The rotating shaft 32 is provided with internal threads, and the push rod 33 is provided with external threads. The external threads of the push rod 33 are matched with the internal threads of the rotating shaft 32, and the rotating shaft 32 drives the push rod 33 to ascend and descend in the sleeve 31 when the rotating shaft 32 rotates. Four installation grooves are uniformly arranged on the inner wall of the sleeve 31, and the middle part of the lock rod 34 is rotatably installed in the installation grooves through a lock rod shaft 35. The lock rod 34 is provided with four lock hooks 36, four opening tenons 37, and four locking tenons 38. The lock rod 34 is provided with a lock rod spring 39, which is a torsion spring. The lock rod spring 39 is sleeved on the lock rod shaft 35, one end of the lock rod spring 39 is connected with the wall of the installation groove, and the other end of the lock rod spring 39 is connected with the lock rod 34. A ring-shaped groove is arranged on the lower end of the side wall of the parachute compartment cover locking pin 20. The lock rod spring 39 makes the lock rod 34 in the locked state of the lock hook 36 in the normal state, and the lock hook 36 is clamped into the ring-shaped groove. The parachute 17 is folded and placed in the parachute compartment 16, the parachute compartment cover locking pin 20 is inserted into the sleeve 31, the groove of the parachute compartment cover locking pin 16 is hooked by the lock hook 36 under the action of the lock rod spring 39, the upper part of the push rod 33 is provided with a push rod table 40, the diameter of the push rod table 40 is greater than the diameter of the push rod 33, the side of the push rod table 40 abuts against the locking tenon 38, the lock rod 34 is locked and cannot rotate around the lock rod shaft 35, and the lock hook 36 is prevented from being unlocked and opening the parachute by mistake. See Figure 6 .

[0073] The opening control mode of the parachute 17 is that the height from the ground is detected by the positioning processing module 404, when the preset opening height is reached, the operation unit 400 sends an instruction to the opening mechanism 23, the opening motor 30 rotates to drive the rotating shaft 32 to rotate, the push rod 33 rises, the push rod table 40 moves to the groove between the opening tenon 37 and the locking tenon 38, the locking tenon 38 is staggered with the push rod table 40 and is no longer limited, the push rod 33 continues to rise, the push rod table 40 pushes the opening tenon 37, drives the locking hook 36 to open, the push rod 33 continues to rise, the push rod table 40 pushes the canopy locking pin 20, and the canopy cover 18 is pushed out, the canopy cover 18 drives the parachute 17 to pop out, see Figure 7 .

[0074] The carrier aircraft 200 can be a fixed-wing aircraft, a helicopter, a drone, or a rocket, a sounding balloon. The bottom of the carrier aircraft 200 is provided with a throwing cylinder 201, and the throwing cylinder 201 is provided with an unhooking device 202. The unhooking device 202 is electromagnetic, and the control signal is provided by the operation unit 400. The top of the electric field sonde 100 is provided with an unhooking signal socket 203, the unhooking device 202 is connected with an unhooking signal plug 204 through a wire, the unhooking signal socket 203 and the unhooking signal plug 204 are plug-in type, the unhooking signal plug 204 is inserted into the unhooking signal socket 203, and a sealing rubber ring is arranged on the unhooking signal plug 204 to avoid that humid air enters the unhooking signal socket 203 and the unhooking signal plug 204 to affect the electrical connection performance. The tail fin 4 of the electric field sonde 100 is folded and loaded into the throwing cylinder 201, the unhooking button 27 is pressed, the hook of the unhooking device 202 is opened, the hanging ring 19 is hung on the unhooking device 202, the unhooking button 27 is released, the hook of the unhooking device 202 is closed, and the tail fin 4 is constrained by the throwing cylinder 201 and cannot pop out, see Figure 8 When the carrier aircraft 200 flies to the predetermined position and height, the operation unit 400 sends an unhooking instruction, the unhooking device 202 opens the hanging ring 19 to be separated, the electric field sonde 100 is released to fall, the unhooking signal plug 204 is pulled out of the unhooking signal socket 203 to be separated, the tail fin 4 is separated from the constraint of the throwing cylinder 201 and pops out, and the tail fin 4 is subjected to air resistance to keep the electric field sonde 100 falling at a constant speed.

[0075] The electrical principle of each sensor, corresponding amplification circuit, and the transmitting unit and the control unit of the application is shown in the following figure: Figure 9The electric ring 11 is connected with the electric ring amplification circuit 401, the electric ring amplification circuit 401 is connected with the operation unit 400; the temperature sensor 12 is connected with the temperature sensor processing circuit 402, the temperature sensor processing circuit 402 is connected with the operation unit 400; two pairs of electrodes 8 are divided into two paths and connected with the charge amplification circuit 403 respectively, the charge amplification circuit 403 is connected with the operation unit 400; the positioning sensor 21 is connected with the positioning processing module 404, the positioning processing module 404 is connected with the operation unit 400; the gyroscope and geomagnetic sensor 22 are connected with the three-axis attitude processing circuit 405, the three-axis attitude processing circuit 405 is connected with the operation unit 400; the parachute opening mechanism 23 is connected with the operation unit 400; the unhooker 202 is connected with the operation unit 400; the transmitting unit 406 is connected with the operation unit 400. Shielded wires are used for connecting all the sensors and amplification processing circuits, and the shielding layer of the shielded wires is connected with the power supply ground.

[0076] The ground receiving system 300 is composed of a signal receiving, demodulating, storing, calculating and analyzing unit. The receiving unit adopts a high-sensitivity radio receiver, cooperates with a high-gain antenna to receive the signal returned by the sounding instrument, decodes the signal into a digital signal through an FSK demodulation module, and stores the digital signal by a data receiving and storing unit. In order to reduce the bit error rate of long-distance data transmission, the transmission baud rate is designed to be 4800bps, which can ensure the reliability of signal transmission and meet the needs of data return rate. The calculating and analyzing unit adopts a specially developed thunderstorm cloud electric field sounding data analysis and processing system. According to the three-axis magnetic field data and acceleration data detected synchronously with the electric field signal, the attitude information of the sounding instrument is obtained by analysis, the influence of the tilt of the electric field sounding instrument 100 on the electric field measurement result is corrected, and the measurement accuracy of the electric field detection result is improved. The sounding data analysis and processing system performs vector decomposition on the detection data to obtain the horizontal electric field information on the falling trajectory. By taking advantage of the characteristics that the falling trajectory of the downward sounding instrument is mainly affected by gravity and the falling speed is fast, the consistency of the electric field sounding instrument electric field detection data at different heights is greatly improved, and the vertical distribution profile of the electric field in the thunderstorm cloud is obtained with high accuracy and high spatial and temporal resolution.

[0077] The method comprises the following steps: when a thunderstorm cloud electric field sounding experiment is carried out, real-time detection data of a meteorological radar is used to extrapolate and predict a thunderstorm cloud development trend, a thunderstorm cloud occurrence area is identified, and a suitable electric field sounding balloon release opportunity is determined.

[0078] The head 1 and the middle 2 of the electric field sounding instrument 100 are separated, a heating agent is filled into the heating cavity 29, a power switch is turned on, and the head 1 and the middle 2 are combined together. The folding tail wing 4 is loaded into the throwing barrel 201 of the carrier aircraft 200, the unhooking button 27 is pressed to open the unhooking device 202, the hanging ring 19 is hung on the unhooking device 202, the unhooking button 27 is released to close the unhooking device 202, the carrier aircraft 200 carries the electric field sounding instrument 100 to ascend, reaches the preset position and height, the positioning sensor 21 detects that the preset position and height are met, the operation unit 400 sends a release instruction, and the electric field sounding instrument 100 is unhooked and falls.

[0079] In the rotating falling process of the electric field sounding instrument 100, airflow flows through the airflow bin 9, and charged particles in the atmosphere pass through the electric measuring ring 11. The electric measuring ring 11 senses a charge mutation of the charged particles, sends the charge mutation to the electric measuring ring amplification circuit 401 for amplification, and then sends the charge mutation into the operation unit 400. The temperature sensor 12 installed in the airflow bin 9 measures the atmospheric temperature in real time, is used to determine the performance of the battery at different temperatures and the stability of the system at different temperatures, and sends the detected data to the temperature sensor processing circuit 402 for processing and then to the operation unit 400.

[0080] The electrode 8 installed on the tail wing 4 generates induced charges in the rotating process under the influence of the electric field in the thunderstorm cloud, the induced charges are transferred at both ends, the transferred charges are measured, the signal is sent to the charge amplification circuit 403 and then to the operation unit 400, and the spatial electric field can be inverted.

[0081] The positioning sensor 21 detects longitude, latitude and height data through a global satellite positioning system, sends the data to the positioning processing module 404 for data processing, and then sends the data to the operation unit 400 to obtain electric field intensity at different heights.

[0082] The tri-axial attitude sensor 22 falls with the electric field sounding instrument 100, and obtains the XYZ tri-axial magnetic field and gravity acceleration in real time, so as to obtain the rotation speed, falling speed and tri-axial attitude of the electric field sounding instrument 100, and the data is sent to the tri-axial attitude processing circuit 405 for processing, and then sent to the operation unit 400 to obtain the falling speed and rotation speed, which are used for correcting the electric field intensity error.

[0083] The detected electric field signal, height, three-dimensional attitude and azimuth data, temperature and other data are processed by the operation unit 400, converted into digital signals by the A / D converter, modulated by the signal modulator, and transmitted by the transmitting unit 406. The ground receiving system 300 receives and further processes the data.

[0084] When the electric field sounding instrument 100 falls to the preset parachute opening height, the operation unit 400 sends a command to the parachute opening mechanism 23, and the parachute 17 opens to slowly descend with the electric field sounding instrument 100, so as to avoid too fast speed to cause injury to ground personnel and building damage. According to the longitude and latitude obtained by the positioning processing module 404 at the time of opening the parachute, the electric field sounding instrument 100 can be recovered under certain conditions.

[0085] The electric field sounding system is used for detecting the electric field in thunderstorm clouds. Two or more electric field sounding instruments 100 are carried by the carrier aircraft 200, and the ground receiving system 300 or the multi-channel receiving and analyzing unit is matched with the number of the electric field sounding instruments 100. In combination with multiple ground atmospheric electric field detectors, a thunderstorm cloud electric field detection network can be formed. Multiple electric field sounding instruments 100 are released at intervals, so that the electric field sounding instruments 100 are distributed at different heights of thunderstorm clouds. Through the global satellite positioning system, the electric field sounding instruments 100 are positioned and time-synchronized, and the synchronous observation results of the electric field in different regions of the thunderstorm cloud at the same time point are obtained, so as to establish a fine thunderstorm cloud charge structure model. Important observation data are provided for analyzing and researching the thunderstorm cloud charge structure, charge density distribution and evolution process thereof with the development of thunderstorm clouds. A thunderstorm cloud sounding system is established, an electric sounding experiment platform is constructed, a mathematical model is established through statistical regression analysis of data, and the physical mechanism of the occurrence and development process of lightning is revealed and researched.

[0086] The above only describes the preferred embodiments of the present application. It should be noted that those skilled in the art can make some improvements and refinements without departing from the technical principles of the present application, and these improvements and refinements should also be considered as the protection scope of the present application.

Claims

1. A downcast electric field sounding system, characterized by, The application relates to an atmospheric electric field sounding system. The atmospheric electric field sounding system comprises: at least one throwing assembly arranged on a carrier aircraft (200) and used for throwing an electric field sonde (100) downward; at least one electric field sonde (100) used for atmospheric electric field detection; the electric field sonde (100) is arranged in the throwing assembly when not thrown; and a ground receiving system (300); the electric field sonde (100) is in communication connection with the ground receiving system (300). The electric field sonde (100) comprises: a head (1); a middle part (2); a tail (3); a tail wing assembly used for keeping the electric field sonde (100) falling at a constant speed; the tail wing assembly comprises at least one pair of tail wings (4), an electrode (8) is arranged on each tail wing (4), and two electrodes (8) on a pair of tail wings (4) form a pair of charge sensors; inner ends of the tail wings (4) are rotatably arranged on an upper end of the tail (3) of the electric field sonde (100) through a tail wing shaft (5), a tail wing spring (7) is sleeved on the tail wing shaft (5), one end of the tail wing spring (7) is connected with the tail (3), and the other end of the tail wing spring (7) is connected with the tail wing (4); the tail wing spring (7) is in a compressed state when the tail wing (4) is folded and arranged in a throwing barrel (201); a charge sensor; the charge sensor is arranged on the tail wing assembly; a charge amplification circuit (403); an operation unit (400); the charge sensor is in electric connection with the charge amplification circuit (403); a transmitting unit (406) used for signal transmission; a transmitting antenna (25); the transmitting unit (406) is in electric connection with the transmitting antenna (25), and the transmitting antenna (25) is in communication connection with the ground receiving system (300); a positioning sensor (21); a positioning processing module (404); the positioning sensor (21) is in electric connection with the positioning processing module (404); a three-axis attitude sensor (22); a three-axis attitude processing circuit (405); the three-axis attitude sensor (22) is in electric connection with the three-axis attitude processing circuit (405); a temperature sensor (12); a temperature sensing processing circuit (402); the temperature sensor (12) is in electric connection with the temperature sensing processing circuit (402); a particle charge amount sensor; a particle charge amount amplification circuit; the particle charge amount sensor is in electric connection with the particle charge amount amplification circuit; the operation unit (400) is in electric connection with the charge amplification circuit (403), the transmitting unit (406), the positioning processing module (404), the three-axis attitude processing circuit (405), the temperature sensing processing circuit (402) and the particle charge amount amplification circuit respectively; an airflow bin (9) is arranged in a lower part of the head (1), a bottom of the airflow bin (9) is open, a plurality of air outlet holes (10) are arranged on a side wall of a top of the airflow bin (9) along a periphery of the top, the particle charge amount sensor comprises a current measuring ring (11), the current measuring ring (11) is horizontally arranged in a middle part of the airflow bin (9), the temperature sensor (12) is arranged on a top of the airflow bin (9), and the particle charge amount amplification circuit is a current measuring ring amplification circuit (401).

2. The downcast electric field radiosonde system of claim 1, wherein, The throwing assembly comprises a throwing barrel (201) and a unhooking device (202), the unhooking device (202) is an electronic unhooking device, the unhooking device (202) is installed at the top of the throwing barrel (201), the tail wing (4) is folded and placed in the throwing barrel (201), and the electric field sonde (100) is provided with a hanging ring (19) which is hung on the unhooking device (202).

3. The downcast electric field radiosonde system of claim 1, wherein, The electric field sonde (100) further comprises a parachute (17) and a parachute opening mechanism (23), the tail (3) is provided with an open-ended parachute compartment (16) at the tail end, the parachute (17) and the parachute opening mechanism (23) are both installed in the parachute compartment (16), the top end of the parachute compartment (16) is provided with a parachute compartment cover (18), the parachute compartment cover (18) is connected with the middle part of the parachute (17), and the lower part of the parachute compartment cover (18) is provided with a parachute compartment cover locking pin (20), and the lower end of the parachute compartment cover locking pin (20) is connected with the acting part of the parachute opening mechanism (23).

4. The downcast electric field radiosonde system of claim 3, wherein, The parachute opening mechanism (23) comprises a parachute opening motor (30), a sleeve (31), a rotating shaft (32), a push rod (33), a locking rod (34) and a locking rod spring (39), the parachute opening motor (30) is electrically connected with the operation unit (400), the rotating shaft (32) is installed on the output shaft of the parachute opening motor (30), the rotating shaft (32) is provided with an internal thread, the push rod (33) is provided with an external thread, the external thread of the push rod (33) is matched with the internal thread of the rotating shaft (32), the parachute opening motor (30) is fixedly installed in the tail (3), the locking rod (34) is at least one, at least one installation groove is formed in the inner wall of the sleeve (31), the middle part of the locking rod (34) is rotatably installed in the installation groove through a locking rod shaft (35), the locking rod spring (39) is sleeved on the locking rod shaft (35), one end of the locking rod spring (39) is connected with the wall of the installation groove, the other end of the locking rod spring (39) is connected with the locking rod (34), the upper part of the locking rod (34) is a locking hook (36), the middle part is an opening tenon (37), and the lower part is a locking tenon (38); an annular groove is formed in the lower end of the side wall of the parachute compartment cover locking pin (20), the locking rod spring (39) makes the locking rod (34) in a locking state of the locking hook (36) in a normal state, and the locking hook (36) is clamped into the annular groove; the upper end of the push rod (33) is connected with the lower end of a push rod table (40), when the push rod (33) rises, the push rod table (40) moves to the groove between the opening tenon (37) and the locking tenon (38), the locking tenon (38) is disengaged from the push rod table (40) and is no longer limited, the push rod (33) continues to rise, the push rod table (40) pushes the opening tenon (37) and drives the locking hook (36) to open, the push rod (33) continues to rise, the push rod table (40) pushes the parachute compartment cover locking pin (20) and pushes out the parachute compartment cover (18), the parachute compartment cover (18) drives the parachute (17) to pop out.

5. The downcast electric field radiosonde system of claim 1, wherein, The middle part (2) is internally provided with an instrument bin (14); the tail part (3) is internally further provided with an equipment bin (15), the positioning sensor (21), the three-axis attitude sensor (22), the transmitting antenna (25) and the parachute opening motor (30) are all arranged in the equipment bin (15), the positioning processing module (404), the three-axis attitude processing circuit (405), the temperature sensing processing circuit (402), the electric ring measuring amplification circuit (401), the operation unit (400) and the transmitting unit (406) are all integrated on a PCB board, and the PCB board is arranged in the instrument bin (14).

6. The downcast electric field radiosonde system of claim 1, wherein, The head part (1) is internally provided with a battery bin (13), the battery bin (13) is internally provided with a power supply (500), the power supply (500) is electrically connected with the PCB board, the battery bin (13) is externally provided with a heat preservation layer (28), a heating cavity (29) is arranged between the heat preservation layer (28) and the battery bin (13), and the heating cavity (29) is internally provided with a heating agent.

7. A downlight electric field sounding method characterized by The method comprises the following steps: S1, before the carrying aircraft (200) carrying the electric field sonde (100) ascends, according to the longitude and latitude and the sea level height, the release position and height of the electric field sonde (100) and the parachute opening height of the electric field sonde (100) from the ground are preset, the preset data is written into the operation unit (400), the transmitting unit (406) and the ground receiving system (300) are debugged to be in good wireless communication; S2, the head part (1) and the middle part (2) of the electric field sonde (100) are separated, the heating agent is filled into the heating cavity (29), the power supply (500) switch is turned on, and the head part (1) and the middle part (2) are combined; S3, the electric field sonde (100) is folded and loaded into the throwing barrel (201) of the carrying aircraft (200), and the hanging ring (19) is hung on the unhooking device (202); S4, the carrying aircraft (200) carrying the electric field sonde (100) ascends, when the positioning sensor (21) detects that the position and height meet the preset position and height, the operation unit (400) sends a release instruction, and the electric field sonde (100) is unhooked and falls; S5, the electric field sonde (100) rotates and falls under the action of the tail wing assembly, in the falling process, the airflow flows into the airflow bin (9) from the bottom opening, passes through the electric ring and flows out through the air outlet (10), the electric ring (11) senses the charge mutation of the charged particles, sends the charge mutation to the electric ring amplification circuit (401) for amplification, and then sends the charge mutation into the operation unit (400); the temperature sensor (12) measures the atmospheric temperature in real time, and is used for judging the performance of the battery at different temperatures and the stability of the system at different temperatures, the data detected by the temperature sensor (12) is sent to the temperature sensing processing circuit (402) for processing, and then sent to the operation unit (400); The electrode (8) arranged on the tail wing (4) generates induced charges under the influence of the air electric field in the rotating process, the induced charges are transferred at both ends, the transferred charges are measured, the signal is sent to the charge amplification circuit (403), and then sent to the operation unit (400); The positioning sensor (21) detects longitude, latitude and height data through a global satellite positioning system, sends the data to a positioning processing module (404) for data processing, and then sends the data to an operation unit (400); The three-axis attitude sensor (22) acquires the geomagnetic field and gravitational acceleration of XYZ three-axis vectors in real time, thereby acquiring the rotation speed, falling speed and three-axis attitude of the electric field sounding instrument (100), and sends the data to a three-axis attitude processing circuit (405) for processing, and then sends the data to the operation unit (400); The detected electric field signal, height, three-dimensional attitude and azimuth data, and temperature data are processed by the operation unit (400), transmitted by a transmitting unit (406), and received by a ground receiving system (300); S6, when the electric field sounding instrument (100) falls to a preset parachute opening height, the operation unit (400) sends an instruction to the parachute opening mechanism (23), the parachute (17) opens and the electric field sounding instrument (100) falls slowly, and finally, the electric field sounding instrument (100) is recovered according to the positioning information of the positioning processing module (404).

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