A high-altitude charged particle detection system and method

Abstract

A high-altitude charged particle detection system and method are disclosed. Specifically, the high-altitude charged particle detection system is characterized by comprising: a launch unit, a conductive cable, a signal reading module, a wireless communication module, and a ground control station; the number of launch units is at least two, and the launch unit is either a balloon unit or a rotating launch unit. Two adjacent launch units form a closed conductive loop through the conductive cable. The signal reading module and the wireless communication module are respectively located in the launch unit. The signal reading module is used to read the induced current signal generated in the closed conductive loop due to charged particles passing through it. Based on the above, this invention proposes a high-altitude charged particle detection system and method, solving the problems of limited detection area, high cost, difficulty in achieving large-scale three-dimensional collaborative detection, and limited measurement capability of charged particle velocity in existing technologies.

Description

Technical Field

[0001] This invention relates to the field of space environment detection technology, and in particular to a high-altitude charged particle detection system and method. Background Technology

[0002] High-altitude charged particles mainly include high-energy charged particles in cosmic rays, solar wind particles, and high-energy electrons and protons in the Earth's magnetosphere. Detecting these charged particles is of great significance for space weather research, cosmic ray detection, and aerospace safety.

[0003] Currently, the detection of charged particles in the upper atmosphere mainly employs the following three types of technical means: the first type is satellite payload detection, which involves carrying particle detectors on satellites; the second type is high-altitude balloon detector, which involves launching detection equipment into the air via high-altitude balloons; and the third type is ground-based detection array, which involves indirect detection by deploying large-area detection arrays on the ground.

[0004] However, the existing technologies mentioned above have the following shortcomings: (1) Limited detection area. Whether it is a satellite payload or a high-altitude balloon detector, its effective detection area is strictly limited by the volume and weight of the payload, making it difficult to achieve large-scale coverage detection. (2) High cost. Satellite launch and operation and maintenance costs are expensive, and the cost of a single detection by a high-altitude balloon detector is also high. Ground detection arrays require large areas of land resources and infrastructure construction. (3) Difficulty in achieving large-scale three-dimensional collaborative detection. Existing detection methods are mostly single-point or local detection, lacking effective means to achieve three-dimensional detection on a large spatial scale. (4) Limited ability to measure the velocity of charged particles. Existing technologies cannot simultaneously obtain comprehensive information such as the spatial distribution and velocity of charged particles. Summary of the Invention

[0005] The purpose of this invention is to propose a high-altitude charged particle detection system and method to solve the problems of limited detection area, high cost, difficulty in achieving large-scale three-dimensional collaborative detection, and limited ability to measure charged particle velocity in the existing technology.

[0006] To achieve this objective, the present invention adopts the following technical solution: A high-altitude charged particle detection system includes an ascent unit, a conductive cable, a signal reading module, a wireless communication module, and a ground control station; The number of launch units is at least two. Each launch unit is a balloon unit or a rotating launch unit. Two adjacent launch units form a closed conductive loop through the conductive cable. The signal reading module and the wireless communication module are respectively located in the launch units. The signal reading module is used to read the induced current signal generated by charged particles passing through the closed conductive loop. The wireless communication module is used to send the induced current signal to the ground control station. The ground control station is used to receive and process the induced current signal.

[0007] Furthermore, the conductor cable is a twisted pair cable made of conductive material, and the outer layer of the conductor cable assembly is covered with a polyethylene fiber protective sleeve.

[0008] Specifically, the balloon unit includes an air bladder and a basket. The basket is equipped with the signal reading module, the wireless communication module, the positioning module, a battery, and a control system. The control system is electrically connected to the signal reading module, the wireless communication module, and the positioning module, respectively. The battery is used to supply power to the signal reading module, the wireless communication module, the positioning module, and the control system.

[0009] Preferably, the airbag includes an air-blocking layer, a pressure-bearing layer, and a radiation-resistant layer. The air-blocking layer is used to prevent leakage of buoyant gas, the pressure-bearing layer is used to withstand the internal and external pressure difference, and the radiation-resistant layer is used to shield against high-altitude radiation. The volume of the airbag is adjustable, and the control system achieves altitude control by releasing or replenishing the buoyant gas in the airbag.

[0010] In some embodiments, the balloon unit operates at an altitude range of 10-30 kilometers above sea level.

[0011] Furthermore, the working orbit altitude range of the rotating launch unit is 200-2000 kilometers above sea level.

[0012] A method for a high-altitude charged particle detection system includes the following steps: Step S1: Release two or more launch units to ascend to the predetermined altitude; Step S2: Control the movement of the lifting unit to tension the conductive cable connecting adjacent lifting units, forming at least one closed conductive loop in the air; Step S3: Collect the current pulse signal induced when charged particles pass through the closed conductive loop, amplify it through the signal reading module, and send it to the ground control station through the wireless communication module; Step S4: The ground control station reconstructs and fuses the collected data to obtain the desired charged particle information.

[0013] Furthermore, in step S4, based on the reconstructed particle motion direction, the angle θ between the incident direction of the charged particle and the direction of the line connecting the detection nodes is obtained. Combined with the equivalent distance d between different closed loops and the arrival time difference Δt of the induced signal, the velocity of a single charged particle is calculated according to the following formula: ; Where d is the equivalent distance between adjacent closed loops, Δt is the arrival time difference of the induced signal, and θ is the angle between the incident direction of the charged particle and the direction of the line connecting the detection nodes.

[0014] Specifically, in step S4, when multiple charged particles continuously pass through the effective detection area of ​​the closed loop, the velocity of the charged particles is calculated according to the following formula: ; Where I is the induced current intensity per unit time, n is the charged particle density, q is the average particle charge, and A is the effective detection area of ​​the closed loop.

[0015] Compared with the prior art, one of the above technical solutions has the following beneficial effects: 1. A closed loop is formed by the conductive cables between multiple launch units. The effective detection area of ​​a single closed loop is much larger than that of a traditional point detector. Multiple closed loops can form a three-dimensional detection network, achieving large-scale coverage detection with a wide detection range. Furthermore, the use of conductive cables to form the detection loop eliminates the need for complex particle detectors, greatly reducing system cost and manufacturing difficulty. The structure is simple and the cost is low. 2. By combining three or more balloon units or rotating launch units, multiple closed loops in different planes can be formed, which intersect to form a three-dimensional detection network, realizing three-dimensional detection of charged particles. It is easy to construct a three-dimensional detection network. Moreover, by analyzing the time difference and signal strength of the sensing signals of different closed loops, the particle trajectory can be reconstructed and the particle velocity can be estimated, realizing comprehensive detection of charged particles and their flow velocity, and possessing the ability to measure the flow velocity of charged particles. 3. The balloon unit can migrate globally with atmospheric flow. The balloon unit is suitable for atmospheric exploration at altitudes of 10 to 30 kilometers. The rotating launch unit can operate at higher orbital altitudes with high signal purity. The rotating launch unit is suitable for space exploration at altitudes of 200 to 2000 kilometers, covering a wide range of exploration areas from the upper atmosphere to near-Earth space. It has both atmospheric and space exploration capabilities. The two modes can adapt to different exploration needs and the working mode is flexible. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of two balloon units according to one embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of multiple balloon units according to one embodiment of the present invention; Figure 3 This is a schematic diagram of the structure of multiple rotating launching units according to one embodiment of the present invention. Detailed Implementation

[0017] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0018] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "left," "right," "front," "rear," "vertical," "horizontal," "top," "bottom," "inner," "outer," "inner side," "outer side," "inner end," "outer end," "axial," "radial," and "circumferential," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention. Furthermore, features defined with "first" and "second" may explicitly or implicitly include one or more of these features, used to distinguish descriptive features, without any order or emphasis. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0019] In one embodiment of the present invention, such as Figure 1-3As shown, a high-altitude charged particle detection system includes a launch unit, a conductive cable, a signal reading module, a wireless communication module, and a ground control station. The number of launch units is at least two, and each launch unit can be a balloon unit or a rotating launch unit. Two adjacent launch units form a closed conductive loop via the conductive cable. The signal reading module and the wireless communication module are respectively located within the launch unit. The signal reading module reads the induced current signal generated in the closed conductive loop due to charged particles passing through it. The wireless communication module transmits the induced current signal to the ground control station, which receives and processes the induced current signal. In this embodiment, if the launch unit is a balloon unit and there are two of them, only one signal reading module is needed for the two launch units. The two balloon units are connected by two conductive cables to form a closed conductive loop. Specifically, one conductive cable is a straightened structure, which is used for connection and support, while the other conductive cable is a suspended structure, which is used to expand the spatial range of the closed loop. The closed conductive loop collects the current pulse signal induced when charged particles pass through it. After being amplified by the signal reading module, it is sent to the ground control station through the wireless communication module. The ground control station reconstructs and fuses the collected data to obtain the desired charged particle signal. Particle Information: When three or more balloon units are combined, each launch unit is equipped with a signal reading module. Each launch unit only detects the induced current in one closed loop. The straightened and suspended conductive cables between the units form closed loops in different planes. Multiple sets of closed loops in different planes interweave to form a three-dimensional detection network. The three balloon units form a triangular closed loop at an altitude of 10 kilometers. When a charged particle passes through the three closed loops formed by the three balloon units, a transient induced current pulse is generated in the conductive cable. The signal reading modules on the three balloon units record the pulse arrival time, pulse amplitude, and waveform duration, respectively. The ground control station receives and analyzes the data synchronously. Through analysis, the flight trajectory and energy of charged particles in space can be mapped. Furthermore, if the launch unit is a rotating launch unit, two rotating launch units are connected by two conductive cables to form a closed loop. The two rotating launch units and the two conductive cables are folded and stored in a rocket or satellite, and then released after being carried to a predetermined altitude by the rocket or satellite. The working orbit altitude of the rotating launch unit is between 200 km and 2000 km above sea level. Upon release, it gains initial rotational kinetic energy and automatically unfolds in space by centrifugal force, forming a stable rotating closed conductive loop. The closed loop collects the current pulse signal induced when charged particles pass through it. After being amplified by the signal reading module, it is transmitted to the ground control station through the wireless communication module. If there are multiple rotating launch units, the multiple rotating launch units are connected in series by conductive cables.This invention utilizes conductive cables connecting multiple launch units to form a closed loop. The effective detection area of ​​a single closed loop is significantly larger than that of a traditional point detector, and multiple closed loops can form a three-dimensional detection network, achieving large-scale spatial coverage detection with a wide detection range. Furthermore, using conductive cables to form the detection loop eliminates the need for complex particle detectors, greatly reducing system cost and manufacturing difficulty, resulting in a simple and low-cost structure. Moreover, by combining three or more balloon units or rotating launch units, multiple sets of closed loops in different planes can be formed, intersecting to form a three-dimensional detection network, enabling three-dimensional detection of charged particles. This facilitates the construction of a three-dimensional detection network, and by analyzing different closed loops… By combining the time difference and signal strength of the loop sensing signal, the particle trajectory can be reconstructed and the particle velocity estimated, enabling comprehensive detection of charged particles and their flow velocity, and providing the capability to measure the flow velocity of charged particles. The balloon unit can migrate globally with atmospheric flow and is suitable for atmospheric detection at altitudes of 10 to 30 kilometers. The rotating launch unit can operate at higher orbital altitudes with high signal purity and is suitable for space detection at altitudes of 200 to 2000 kilometers, covering a wide detection area from the upper atmosphere to near-Earth space. It has both atmospheric and space detection capabilities, and the two modes can adapt to different detection needs, making the working mode flexible.

[0020] The conductive cable is a twisted-pair cable made of conductive material, and the outer layer of the conductive cable assembly is covered with a polyethylene fiber protective sheath. In this embodiment, the conductive cable adopts a twisted-pair structure, consisting of two conductive core wires twisted together, and is covered with an ultra-high molecular weight polyethylene fiber protective sheath. Ultra-high molecular weight polyethylene fiber has the characteristics of high strength, wear resistance, corrosion resistance, ultraviolet resistance, low density, good insulation and wind resistance. It can maintain long-term stable mechanical and electrical properties in harsh high-altitude environments. The conductive cable not only undertakes the mechanical connection function between adjacent ascending units, but also undertakes the electrical signal transmission function of closed conductive circuits.

[0021] like Figure 1-2As shown, the balloon unit includes an airbag and a basket. The basket is equipped with a signal reading module, a wireless communication module, a positioning module, a battery, and a control system. The control system is electrically connected to the signal reading module, the wireless communication module, and the positioning module. The battery powers the signal reading module, the wireless communication module, the positioning module, and the control system. In this embodiment, the basket is equipped with a wireless communication module, a positioning module (such as GPS / BeiDou), a battery, a signal reading module, and a control system. The signal reading module reads and amplifies the current pulse signal induced in the closed loop of the conductor cable. The wireless communication module transmits the processed data to a ground control station. The balloon array migrates globally with atmospheric flow. The control system can adjust the relative positions of the balloon units, changing the geometry or spatial position of the detection network to achieve coverage measurement of different areas, environments, and directions. Furthermore, the control system can adjust the relative positions of each balloon unit, changing the geometry or spatial position of the three-dimensional detection network.

[0022] The airbag comprises a gas-blocking layer, a pressure-bearing layer, and a radiation-resistant layer. The gas-blocking layer prevents leakage of rising gas, the pressure-bearing layer withstands the internal and external pressure difference, and the radiation-resistant layer shields against high-altitude radiation. The volume of the airbag is adjustable, and the control system achieves altitude control by releasing or replenishing the rising gas within the airbag. In this embodiment, the airbag is made of a multi-layer composite material, including a gas-blocking layer, a pressure-bearing layer, and a radiation-resistant layer. The gas-blocking layer prevents leakage of rising gases such as helium, the pressure-bearing layer withstands the internal and external pressure difference, and the radiation-resistant layer shields against strong ultraviolet radiation and particle radiation at high altitudes. The airbag volume can be adjusted according to the target altitude, and the control system achieves altitude control by releasing or replenishing the rising gas (helium) within the airbag.

[0023] In this embodiment, three balloon units form a triangular closed loop at an altitude of 10 kilometers. When a charged particle passes through the three closed loops formed by the three balloon units, a transient induced current pulse is generated in the conductive cable. Signal reading modules installed on the three balloon units record the pulse arrival time, pulse amplitude, and waveform duration, respectively. The ground control station receives the data and analyzes it synchronously. Through analysis, the flight trajectory and energy of the charged particle in space can be plotted. At the same altitude, when only two balloon units form a closed loop, only a single current pulse signal can be detected. It can only be known that a particle has passed through and the magnitude of the particle flux, but the trajectory of the charged particle cannot be analyzed from the data of multiple closed loops. At different altitudes, the same type of closed loop will produce different results. At 10 kilometers, the atmosphere is still relatively thick, and some high-energy particles have already collided with the air and produced secondary particles. The background noise in the detection signal is relatively large, the detected signal pulse frequency is high, but the energy of a single pulse is low. The detected charged particles are mostly secondary cosmic ray particles (muons, electrons, photons, etc.). At 30 kilometers, the detected signal pulse frequency is low, but the energy of a single pulse is high. The detected charged particles are mostly primary high-energy particles (high-energy protons, alpha particles) and a small number of secondary particles.

[0024] In this embodiment, the predetermined orbital altitude is 200-2000 kilometers above sea level. Within this altitude range, the detection of charged particles is not affected by the atmosphere, and the signal purity is higher than that of the balloon unit's atmospheric detection.

[0025] A method for a high-altitude charged particle detection system includes the following steps: Step S1: Release two or more launch units to ascend to a predetermined altitude; Step S2: Control the launch units to move, causing the conductive cables connecting adjacent launch units to be tensioned, forming at least one closed conductive loop in the air; Step S3: Collect the current pulse signal induced when a charged particle passes through the closed conductive loop, amplify it through a signal reading module, and transmit it to a ground control station through a wireless communication module; Step S4: The ground control station reconstructs and fuses the collected data to obtain the desired charged particle information. In this embodiment, if the launch unit is a balloon unit, multiple balloon units are released and their buoyancy is adjusted (by releasing or replenishing helium) to rise to a predetermined altitude (10 to 30 kilometers above sea level). The movement of the multiple balloon units is controlled to tension the connecting cables, forming a preset closed-loop geometry in the air. The current pulse signal induced when charged particles pass through the closed loop is collected, amplified by the signal reading module, and then transmitted to the ground control station via the wireless communication module. The ground control station reconstructs and fuses the collected data to obtain information such as the spatial distribution, trajectory, and velocity of the charged particles. The positions of the balloon units are adjusted to change the geometry or spatial position of the detection network for large-scale measurements. If the launch unit is a rotating launch unit, the tethered detection unit is folded and stored, mounted on the rocket, and launched to a predetermined orbit (altitude 200 km to 2000 km). At the predetermined altitude, the tethered detection unit is released, and the rotating drive mechanism is activated to give it initial rotational kinetic energy. The rotating launch unit automatically unfolds in the microgravity environment of space by relying on centrifugal force, and the conductive cable is tensioned to form a closed conductive loop. The current pulse signal induced when charged particles pass through the closed loop is collected, amplified by the signal reading module, and then transmitted to the ground control station through the wireless communication module.

[0026] In step S4, based on the reconstructed particle motion direction, the angle θ between the incident direction of the charged particle and the direction of the line connecting the detection nodes is obtained. Combined with the equivalent distance d between different closed loops and the arrival time difference Δt of the induced signal, the velocity of a single charged particle is calculated using the following formula: Where d is the equivalent distance between adjacent closed loops, Δt is the arrival time difference of the induced signal, and θ is the angle between the incident direction of the charged particle and the direction of the line connecting the detection nodes. In this embodiment, when a high-energy charged particle passes through a closed loop composed of a conductive cable, a current pulse will be induced in the loop within a short time. The signal reading module reads the induced current pulse, amplifies it, and sends the data to the ground receiving station through the wireless communication module. When a charged particle passes through a three-dimensional detection network composed of multiple closed loops, different closed loops will generate induced current signals of different intensities. Specifically: when a single charged particle passes perpendicularly through the central region of a closed loop, that closed loop generates a strong induced signal, while the signals of adjacent closed loops are relatively weak; when a charged particle passes through the three-dimensional detection network at an angle, different closed loops will generate induced signals sequentially according to the particle's motion path. By analyzing the time difference and signal intensity distribution of the signals from each loop, the ground control station can deduce the incident direction and spatial trajectory of the charged particle. Based on the reconstructed particle motion direction, the angle θ between the incident direction of the charged particle and the direction of the line connecting the detection nodes can be obtained. Combined with the equivalent distance d between different closed loops and the arrival time difference Δt of the induced signal, the velocity of a single charged particle can be estimated, and the relationship satisfies: Where d is the equivalent distance between adjacent closed loops, Δt is the arrival time difference of the induced signal, and θ is the angle between the incident direction of the charged particle and the direction of the line connecting the detection nodes.

[0027] In step S4, when multiple charged particles continuously pass through the effective detection area of ​​the closed loop, the velocity of the charged particles is calculated according to the following formula: Where I is the induced current intensity per unit time, n is the charged particle density, q is the average particle charge, and A is the effective detection area of ​​the closed loop. In this embodiment, when multiple charged particles continuously pass through the effective detection area of ​​the closed loop, the induced current intensity generated per unit time is related to the charged particle density, the average particle charge, the particle velocity, and the effective detection area of ​​the closed loop, and the relationship is expressed as follows: Where n is the charged particle density, q is the average charge of the particle, A is the effective detection area of ​​the closed loop, and v is the particle velocity.

[0028] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0029] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A high-altitude charged particle detection system, characterized in that: It includes the launch unit, conductor cable, signal reading module, wireless communication module, and ground control station; The number of launch units is at least two. Each launch unit is a balloon unit or a rotating launch unit. Two adjacent launch units form a closed conductive loop through the conductive cable. The signal reading module and the wireless communication module are respectively located in the launch units. The signal reading module is used to read the induced current signal generated by charged particles passing through the closed conductive loop. The wireless communication module is used to send the induced current signal to the ground control station. The ground control station is used to receive and process the induced current signal.

2. The high-altitude charged particle detection system according to claim 1, characterized in that: The conductor cable is a twisted pair cable made of conductive material, and the outer layer of the conductor cable assembly is covered with a polyethylene fiber protective sleeve.

3. The high-altitude charged particle detection system according to claim 1, characterized in that: The balloon unit includes an airbag and a basket. The basket is equipped with a signal reading module, a wireless communication module, a positioning module, a battery, and a control system. The control system is electrically connected to the signal reading module, the wireless communication module, and the positioning module, respectively. The battery is used to power the signal reading module, the wireless communication module, the positioning module, and the control system.

4. The high-altitude charged particle detection system according to claim 3, characterized in that: The airbag includes a gas-blocking layer, a pressure-bearing layer, and a radiation-resistant layer. The gas-blocking layer is used to prevent the leakage of buoyant gas, the pressure-bearing layer is used to withstand the internal and external pressure difference, and the radiation-resistant layer is used to shield against high-altitude radiation. The volume of the airbag is adjustable, and the control system achieves altitude control by releasing or replenishing the buoyant gas in the airbag.

5. The high-altitude charged particle detection system according to claim 1, characterized in that: The working altitude range of the balloon unit is 10-30 kilometers above sea level.

6. The high-altitude charged particle detection system according to claim 1, characterized in that: The working orbit altitude range of the rotating launch unit is 200-2000 kilometers above sea level.

7. A method using a high-altitude charged particle detection system as described in any one of claims 1-6, characterized in that, Includes the following steps: Step S1: Release two or more launch units to ascend to the predetermined altitude; Step S2: Control the movement of the lifting unit to tension the conductive cable connecting adjacent lifting units, forming at least one closed conductive loop in the air; Step S3: Collect the current pulse signal induced when charged particles pass through the closed conductive loop, amplify it through the signal reading module, and send it to the ground control station through the wireless communication module; Step S4: The ground control station reconstructs and fuses the collected data to obtain the desired charged particle information.

8. The method for a high-altitude charged particle detection system according to claim 7, characterized in that: In step S4, based on the reconstructed particle motion direction, the angle θ between the incident direction of the charged particle and the direction of the line connecting the detection nodes is obtained. Combined with the equivalent distance d between different closed loops and the arrival time difference Δt of the induced signal, the velocity of a single charged particle is calculated using the following formula: ； Where d is the equivalent distance between adjacent closed loops, Δt is the arrival time difference of the induced signal, and θ is the angle between the incident direction of the charged particle and the direction of the line connecting the detection nodes.

9. The method for a high-altitude charged particle detection system according to claim 7, characterized in that: In step S4, when multiple charged particles continuously pass through the effective detection area of ​​the closed loop, the velocity of the charged particles is calculated according to the following formula: ； Where I is the induced current intensity per unit time, n is the charged particle density, q is the average particle charge, and A is the effective detection area of ​​the closed loop.

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