Device for simulating potential state of spacecraft structure

Abstract

According to the device for simulating the potential state of the spacecraft structure, the potential state of the spacecraft structure running in different orbits and in a complex space environment is simulated through an electron injection mode and an electron extraction mode, and the device is an efficient and controllable space environment simulation tool; the device has the characteristics of adjustable electron flow, simple equipment, high integration level, compact structure and wide application range, is an important bridge for connecting space environment theory, material science and aerospace engineering practice, and can be applied to potential simulation experiments of different spacecrafts; the platform is an indispensable key ground verification platform for ensuring high-reliability and long-life operation of a spacecraft in orbit.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of space environment simulation and space plasma physics engineering, and particularly relates to a device for simulating the potential state of a spacecraft structure. BACKGROUND

[0002] In the field of space engineering, accurately predicting and verifying the potential state of a spacecraft in a complex space plasma environment is a key to ensuring its long-term safe and stable operation in orbit, and an electron injection and extraction device plays an indispensable role in ground simulation tests, and its application is directly related to the success or failure of the overall spacecraft electrical design.

[0003] With the rapid development of space technology, the reliability and durability of spacecraft in extreme environments have become a key challenge. When a spacecraft structure is in orbit, it is exposed to high-energy electron radiation, plasma environment, and accumulation of space charges for a long time, which causes changes in the potential of the spacecraft structure, and even system failures. Therefore, simulating these space environment effects on the ground is crucial for the design and verification of spacecraft structures and their electronic systems.

[0004] However, spacecraft in orbit will accumulate different electrically charged particles on their structure surface due to different orbits and space environments, causing the potential to rise or fall, which seriously threatens the safe operation of the spacecraft. In existing spacecraft potential simulation devices, they all have complex structures, heavy equipment, or cannot produce a stable enough electron current. SUMMARY

[0005] To solve the above problems, the application provides a device for simulating the potential state of a spacecraft structure, which simulates the potential state of a spacecraft structure in different orbits and complex space environments through two modes of electron injection and extraction.

[0006] A device for simulating the potential state of a spacecraft in orbit, comprising a vacuum emission electron tube, a constant current heating power supply, and a high-voltage pulse power supply, wherein the vacuum emission electron tube is internally integrated with a heating wire, a cathode, an anode, and a collector, and the cathode and the collector are both connected to the spacecraft structure through connectors; When the potential of the spacecraft surface is higher than the set value, the collector is connected to the spacecraft structure; the constant current heating power supply and the high-voltage pulse power supply are turned on; the constant current heating power supply heats the heating wire, which heats the cathode by thermal radiation, causing the cathode to produce hot electrons; then the high-voltage pulse power supply is adjusted, a positive high-voltage electric field is formed between the cathode and the anode, and the hot electrons are accelerated under the action of the positive high-voltage electric field, forming a controllable electron current of a certain density. The controllable electron current finally falls on the collector through the anode hole, and is injected into the spacecraft surface through the connecting device, realizing electron injection and reducing the potential of the spacecraft structure. When the potential of the spacecraft surface is lower than the set value, the cathode is connected with the spacecraft structure, the electrons on the surface of the spacecraft structure finally fall on the collector through the anode hole, the extraction of the electrons is realized, and the potential of the spacecraft structure is improved.

[0007] Further, the micro-processing unit, the DSP power supply control circuit, the communication device and the sensing device for monitoring the fluctuation of the running environment in real time are further included, when the running environment of the spacecraft changes, the sensing device measures the corresponding environmental fluctuation signal, and then the environmental fluctuation signal is sent to the micro-processing unit through the communication device, the micro-processing unit determines whether the spacecraft structure is connected to the collector or the cathode according to the environmental fluctuation signal, then calculates the electron change amount, and finally controls the opening of the constant-current heating power supply, the output voltage of the constant-current heating power supply, the opening of the high-voltage pulse power supply and the output voltage of the high-voltage pulse power supply according to the electron change amount.

[0008] Further, the device for simulating the potential state of the spacecraft in orbit operation further includes a safety protection module. The safety protection module is used to limit the potential of the constant-current heating power supply and the high-voltage pulse power supply, so that they work in a safe range.

[0009] Further, the device for simulating the potential state of the spacecraft in orbit operation further includes a ground simulation device. The ground simulation device is used to simulate the orbit operation state of the spacecraft.

[0010] Further, the spacecraft performs electron extraction when operating in a high orbit and performs electron injection when operating in a low orbit.

[0011] Advantages: 1. The device for simulating the potential state of the spacecraft structure provided by the application simulates the potential state of the spacecraft structure under different orbit operations and complex space environments through two modes of electron injection and extraction, is a high-efficiency and controllable space environment simulation tool, has the characteristics of adjustable electron flow, simple equipment, high integration, compact structure and wide application range, is an important bridge connecting space environment theory, material science and aerospace engineering practice, can be applied to potential simulation experiments of different spacecrafts, and is an indispensable key ground verification platform for ensuring high reliability and long service life of spacecrafts in orbit.

[0012] 2. The device for simulating the potential state of the spacecraft structure provided by the application can be applied to ground simulation experiments in the field of aerospace, reproduces the potential state of the spacecraft structure in different orbits such as geosynchronous orbit or polar orbit, and provides environmental support for space material testing, protective layer evaluation and electron device anti-interference performance testing.

[0013] 3. The application provides a device for simulating the potential state of a spacecraft structure, which has a simple structure, is stable and reliable, easy to carry and operate, and has low manufacturing cost and can be easily integrated. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 A schematic diagram of the device for simulating the potential of a spacecraft structure.

[0015] Figure 2 An electron injection schematic diagram of the application.

[0016] Figure 3 An electron extraction schematic diagram of the application. DETAILED DESCRIPTION

[0017] In order to enable those skilled in the art to better understand the application, the technical solutions in the application will be described clearly and completely below with reference to the drawings in the application embodiments.

[0018] There are generally two methods for controlling the potential of a spacecraft structure, passive control and active control. Passive control is to prevent or reduce the charging and discharging effect from aspects such as shape, material, material and process during design and production, and the disadvantage of this method is that once the spacecraft is launched, it cannot be changed, and it has limited ability to cope with complex space environment. Active control refers to installing an electric particle beam device to control the potential of the spacecraft structure, and this method is more flexible and effective, and has stronger adaptability to complex space environment.

[0019] The application adopts an active control mode. When the space environment of the spacecraft changes, the sensor of the spacecraft will transmit this information to the control center, the control center will send the extraction or injection instructions to the microprocessor unit of the device through the communication device, determine the connection port (cathode or collector) of the spacecraft structure, and then enter the working state. When the potential is low, the electrons on the surface of the spacecraft are extracted, and when the potential is high, the electrons are injected.

[0020] Specifically, as shown in Figure 1 A device for simulating the potential state of a spacecraft structure, which can generate stable and controllable electron flow and accurately simulate the dynamic change of the potential of the spacecraft structure. Specifically, the device comprises a vacuum electron emission tube, a constant-current heating power supply, a high-voltage pulse power supply, a safety protection module and a DSP power control circuit, wherein the vacuum electron emission tube is internally integrated with a heating wire, a cathode, an anode and a collector, and an electron hole exists on the anode.

[0021] When the potential on the surface of the spacecraft is higher than the set value, the spacecraft structure is connected to the collector through the connector, as shown in Figure 2As shown. The micro control unit opens the constant current heating power supply and the high voltage pulse power supply, and the constant current heating power supply heats the heating wire. The heating wire heats the cathode by heat radiation, so that the cathode generates thermal electrons; then the high voltage pulse power supply is adjusted, a positive high voltage electric field is formed between the cathode and the anode, and the thermal electrons are accelerated under the action of the positive high voltage electric field to form a controllable electron flow with a certain density, and the controllable electron flow finally falls on the collector through the anode hole; that is, under the joint action of the cathode and the anode, a certain current density and a certain shape of electron flow will be generated in the vacuum emission electron tube, and the size of the electron flow is controlled by the cathode control voltage. The collector is used for collecting the electrons emitted from the vacuum emission electron tube to avoid the electrons hitting the wall of the electron emission tube. The collector is connected to the surface of the spacecraft through the connecting device, and the electrons are injected into the surface of the spacecraft through the connector to realize the injection of the electrons.

[0022] When the potential of the surface of the spacecraft is lower than the set value, the spacecraft structure is connected to the cathode through the connector, as shown. Figure 3 The electrons of the spacecraft structure will fall on the cathode through the connector, and under the action of the deflection electric field, these electrons finally fall on the collector through the anode hole to realize the extraction of the electrons on the surface of the spacecraft structure.

[0023] The safety protection module is used for limiting the potential of the heating power supply and the two groups of pulse power supplies, so that they work in a safe range, prevent the system from being burned out, and protect the safety of the system test.

[0024] The ground simulation device is used for simulating the on-orbit operation state of the spacecraft.

[0025] When the operating environment of the spacecraft changes, the sensing device measures the corresponding environmental fluctuation signal, and then sends the environmental fluctuation signal to the micro processing unit and the DSP power supply control circuit through the communication device, and the micro processing unit determines whether the spacecraft structure is connected to the collector or the cathode according to the environmental fluctuation signal, then calculates the electron change amount, and then controls the opening of the constant current heating power supply, the output voltage of the constant current heating power supply, the opening of the high voltage pulse power supply and the output voltage of the high voltage pulse power supply according to the electron change amount.

[0026] It should be noted that the present application adopts 220V-AC power supply, and can be converted into the required DC power supply of each module. The system can realize continuous adjustable electron flow, support local control, external signal control (software writing control logic) and remote communication control.

[0027] Specifically, when the spacecraft is in high orbit, especially during the radiation belt and substorm, it is filled with high-energy electrons with energy up to tens to hundreds of keV. These electrons continue to hit the spacecraft surface, and when their injection rate exceeds the charge dissipation rate, charge accumulation will occur, and the potential can rise to tens of thousands of volts, causing electrostatic discharge that can seriously interfere with or even cause serious damage to the spacecraft.

[0028] The working principle of simulating high-orbit conditions is that a large number of high-energy electrons are accumulated on the surface of the spacecraft structure, which are negatively charged and need to be extracted to raise the potential of the spacecraft structure. At this time, the spacecraft structure is connected to the cathode through the connector. When working, the internal power supply structure converts 220V-AC power into the required DC power for each module. Under the action of the deflection electric field, the high-energy electrons on the surface of the spacecraft structure will eventually fall on the collector through the anode hole, achieving the purpose of extracting high-energy electrons from the surface of the spacecraft structure and raising the potential of the spacecraft structure.

[0029] When the spacecraft is in low orbit (especially the 400-kilometer altitude of the space station), the electrical properties of the spacecraft structure are different from the "high-energy electron radiation" in high orbit, mainly related to ionospheric thermal plasma and photoelectron emission. Especially in the light area, the spacecraft structure surface will accumulate a large number of positive charges, and the potential structure is relatively high.

[0030] The working principle of simulating low-orbit conditions is that the constant-current heating power supply heats the heating wire in the vacuum electron emission tube, and the heating wire heats the cathode by thermal radiation, causing the cathode to generate hot electrons. Then adjust the high-voltage pulse power supply to form a high-voltage electric field between the cathode and the anode, and the hot electrons are accelerated under the action of the positive high-voltage electric field to form a certain density of controllable electron flow, and finally the electron flow passes through the anode hole and finally falls on the collector. The collector is connected to the spacecraft through the connecting device, and the electrons will eventually fall on the spacecraft surface to achieve the purpose of reducing the potential of the spacecraft structure. By controlling the constant-current heating power supply and the high-voltage pulse power supply, the size of the electron flow can be controlled, and the continuous adjustable electron flow can be achieved to achieve the purpose of electron injection, thereby reducing the potential of the spacecraft structure.

[0031] As can be seen, the electron injection and extraction device plays a crucial role in simulating the ground testing of spacecraft structures. Its core application is to accurately reproduce the fluctuations in the surface potential of spacecraft in extreme space environments and the effects of electron radiation. When the operating environment of the spacecraft changes, the sensing device will monitor the environmental fluctuations and inform the microprocessor unit of the corresponding electron change amount, and finally the device will inject or extract the corresponding amount of electrons, thereby providing key data support for the reliability and safety of the spacecraft.

[0032] In summary, the application provides a device for simulating the potential state of a spacecraft structure, which converts a 220V-AC working voltage into the required power supply voltage of each module. Under the joint work of a constant-current heating power supply and a high-voltage pulse power supply, a stable electron current is generated and applied to the spacecraft, which can simulate the on-orbit operation state of the spacecraft. When the spacecraft is in high orbit, a large number of high-energy electrons accumulate on the surface of the spacecraft, and the potential of the spacecraft can reach several thousand volts or even tens of thousands of volts. When the spacecraft is in low orbit, the spacecraft structure is affected by light, and the potential of the spacecraft structure is relatively high. The application creates a "programmable" space charging and discharging environment, converts the on-orbit potential risk that is difficult to capture into a quantifiable ground state, simulates the space high-energy electron environment in the ground laboratory, solves the repeatable engineering problem, greatly improves the maturity and on-orbit survival ability of the spacecraft design, and is an important defense line for protecting the spacecraft from safe navigation in the vast space. It can be used to study the on-orbit charging effect and protection technology of the spacecraft structure and its materials.

[0033] Of course, the application can have other various embodiments. Those skilled in the art can certainly make various corresponding changes and modifications according to the application without departing from the spirit and essence of the application. However, these corresponding changes and modifications should all belong to the protection scope of the claims attached to the application.

Claims

1. An apparatus for simulating on-orbit potential conditions of a spacecraft, characterized by, The device comprises a vacuum emission electron emission tube, a constant current heating power supply, and two groups of high-voltage pulse power supplies, wherein the vacuum emission electron tube is internally integrated with a heating wire, one two-group cathode, one anode, and one collector electrode pair, and each group of cathode-anode pairs is connected with one group of pulse power supplies; meanwhile, the cathode in the first group of cathode-anode pairs is directly opposite to the heating wire, and the cathode in the second group of cathode-anode pairs is connected with the surface of a spacecraft to be simulated through a connecting device; the anode in each group of cathode-anode pairs is provided with an anode hole, and the two anodes are opposite to each other; and the cathode and the collector electrode can be connected with the spacecraft structure through connectors. When the potential of the surface of the spacecraft is higher than a set value, the collector electrode is connected with the spacecraft structure, the constant current heating power supply and the high-voltage pulse power supply are turned on, and the pulse power supply connected with the first group of cathode-anode pairs is adjusted; the constant current heating power supply heats the heating wire, the heating wire heats the cathode through heat radiation, the cathode generates hot electrons, the heating wire generates free electrons, the high-voltage pulse power supply is adjusted to form a forward high-voltage electric field between the cathode and the anode of the first group of cathode-anode pairs, the hot electrons are accelerated under the action of the forward high-voltage electric field to form a controllable electron current, the anode hole generates a controllable electron current, the free electrons fall on the cathode of the second group of cathode-anode pairs through the anode hole under the driving of the forward high-voltage electric field, the controllable electron current finally falls on the collector electrode through the anode hole, and the electron injection is realized by injecting the electron current into the surface of the spacecraft through the connecting device to reduce the potential of the spacecraft structure. When the potential of the surface of the spacecraft is lower than a set value, the cathode is connected with the spacecraft structure, the electrons on the surface of the spacecraft finally fall on the collector electrode through the anode hole, the pulse power supply connected with the second group of cathode-anode pairs is turned on, a reverse high-voltage electric field opposite to the injection direction is formed between the cathode and the anode of the second group of cathode-anode pairs, and the electrons on the surface of the spacecraft fall on the cathode of the first group of cathode-anode pairs through the anode hole under the driving of the reverse high-voltage electric field to realize the extraction of the electrons and improve the potential of the spacecraft structure.

2. A device for simulating the on-orbit potential conditions of a spacecraft according to claim 1, characterized in that, The device further comprises a micro-processing unit, a DSP power supply control circuit, a communication device, and a sensing device for monitoring the fluctuation of the running environment in real time. When the running environment of the spacecraft changes, the sensing device measures the corresponding environmental fluctuation signal, sends the environmental fluctuation signal to the micro-processing unit through the communication device, and determines whether the spacecraft structure is connected with the collector electrode or the cathode according to the environmental fluctuation signal. Then, the micro-processing unit calculates the electron change amount and controls the opening of the constant current heating power supply, the output voltage of the constant current heating power supply, the opening of the high-voltage pulse power supply, and the output voltage of the high-voltage pulse power supply according to the electron change amount. The greater the output voltage of the heating power supply, the more free electrons the heating wire generates, the greater the output voltage of the pulse power supply, the greater the field strength of the high-voltage electric field, and the faster the driving speed of the electrons.

3. A device for simulating potential conditions of on-orbit spacecraft operation as claimed in claim 1, characterized in that, The device further comprises a safety protection module. The safety protection module is used to limit the potential of the constant current heating power supply and the two groups of high-voltage pulse power supplies to make them work in a safe range.

4. The device for simulating the potential state of an on-orbit spacecraft of claim 1, wherein, The device further comprises a ground simulation device. The ground simulation device is used to simulate the on-orbit running state of the spacecraft.

5. The device for simulating the potential state of an on-orbit spacecraft of claim 1, wherein, The spacecraft performs electron injection extraction when operating in a high orbit and electron extraction injection when operating in a low orbit. The spacecraft performs electron injection extraction when operating in a high orbit and electron extraction injection when operating in a low orbit.

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