Space plasma energy collection device and method based on spacecraft surface potential difference

Abstract

The present invention discloses a space plasma energy collection device and collection method based on the potential difference on the surface of a spacecraft, and belongs to the field of spacecraft energy supply technology. In the present invention, each sensor probe is connected to each of the monitoring points to monitor the potential of the monitoring points; the input end of the processor is connected to the output end of the sensor probe; the output end of the processor is connected to the first input end of the voltage regulator; when the potential of a certain monitoring point reaches the discharge threshold, the monitoring point is turned on to charge the battery using the potential difference between the monitoring point potential and the ground reference point; the monitoring point and the ground reference point are connected to the input end of the inverter; the output end of the inverter is connected to the second input end of the voltage regulator and the battery. The present invention can reduce the accumulation of charge on the surface of the spacecraft, reduce the discharge frequency of the plasma contactor, and has a compact structure.

Description

Technical Field

[0001] The present invention belongs to the technical field of spacecraft energy supply, and in particular relates to a space plasma energy collection device and method based on the surface potential difference of a spacecraft. Background Art

[0002] In order to ensure that the spacecraft maintains normal operation in the universe, it needs to be continuously supplied with energy to provide power. At present, the main ways for spacecraft to obtain electricity include: solar panels, radioisotope thermoelectric generators (used by Voyager 1 and Voyager 2 in the United States) and nuclear fission reactors (NASA Kilopower project aims to develop an economical and affordable fission nuclear power system). These methods mainly obtain energy through active supply. At the initial moment of spacecraft design, its energy supply method and energy storage value have been confirmed according to its flight mission and flight path requirements. The energy supply capacity of a spacecraft is crucial to its flight process. Sufficient energy is required during flight to cope with various flight challenges. In order to ensure its safe flight, a certain amount of redundant energy is usually designed, but this redundant capacity cannot be too high so as to increase the mass of the spacecraft. So is it possible to increase the energy source of the external environment for the spacecraft?

[0003] There is a large amount of plasma in the orbital space of a spacecraft. Plasma is a substance composed of a large number of charged ions. If the charged particles in the plasma can be collected, it can provide additional energy for the spacecraft.

[0004] At present, there are several ideas for energy collection using the space plasma environment: plasma electrodynamic tether, magnetohydrodynamic (MHD) generator and plasma thruster with energy collection. Plasma electrodynamic tether concept A space flight system that connects two or more spacecraft together through a flexible conductive tether. When the electrodynamic tether runs in the space orbit, the conductive tether cuts the earth's magnetic field, causing an induced electromotive force in the tether. Then the tether exchanges charged particles with the surrounding space ionosphere, so that the system and the surrounding ionosphere form a closed loop and generate a stable current in the tether. Under the action of the earth's magnetic field, the tether with current generates an Ampere force. By controlling the current in the tether, the magnitude and direction of the Ampere force generated by the electrodynamic tether can be controlled, so as to carry out various space missions. The electrodynamic tether system has been tested in missions such as the Tethered Satellite System (TSS) and is considered a promising technology for future space missions (NASA). The magnetohydrodynamic generator converts the kinetic energy of plasma into electrical energy. Plasma moves in a magnetic field, generating a current perpendicular to the plasma flow and magnetic field. Plasma thrusters with energy collection collect plasma in thrusters to generate electrical energy. Chinese patent document 202311448386.8 discloses a spacecraft electrostatic discharge energy self-collection device and electrostatic collection equipment, in which a charging module and a power control module are designed. The power control module is used to convert the electrostatic discharge energy and output it to the low-energy consumption components of the spacecraft, providing electrical energy for the low-energy consumption components of the spacecraft.

[0005] The above-mentioned method for space plasma energy collection requires designing a larger-scale structural unit outside the spacecraft, and using the speed of movement, cutting the geomagnetic line or the magnetic field of the configured magnet to collect energy. The additional volume feature is a burden for the spacecraft, so how to reduce the volume of the newly added structural unit and realize space plasma energy collection is a problem that needs to be solved for external energy collection. Summary of the invention

[0006] The present invention aims to address the technical problems existing in the prior art and provides a space plasma energy collection device and method based on the potential difference on the surface of a spacecraft. The source of the potential difference is mainly to use space plasma to charge the space station structure, and to form a loop for energy collection using the potential difference between the charging potential and the ground reference position. This energy collection method can reduce the accumulation of charge on the surface of the spacecraft to a certain extent, and can also reduce the discharge frequency of the plasma contactor, thereby realizing space plasma energy collection using highly integrated tiny structural units.

[0007] The present invention provides a space plasma energy collection device based on the potential difference on the surface of a spacecraft, which is used for collecting charges on the surface of a spacecraft. The device comprises a plurality of sensor probes, a processor, an inverter, a voltage regulator and a battery, and also comprises a plurality of monitoring points selected on the surface of the spacecraft and a selected ground reference point, wherein the ground reference point has a higher potential than the surface of the spacecraft. Due to the existence of space plasma, the surface of the spacecraft will be negatively charged, but there is always a reference point such as grounding at a high potential, so it is selected as the potential difference reference point for energy collection.

[0008] Each sensor probe is connected to each monitoring point to monitor the potential of the monitoring point; the input end of the processor is connected to the output end of the sensor probe; the output end of the processor is connected to the first input end of the voltage regulator; when the potential of a monitoring point reaches the discharge threshold, the monitoring point is turned on to charge the battery using the potential difference between the monitoring point and the ground reference point;

[0009] The monitoring point and the ground reference point are connected to the input end of the inverter; the output end of the inverter is connected to the second input end of the voltage regulator and the battery.

[0010] Preferably, a plurality of sensor probes are arranged at monitoring points selected on the insulation part and the solar cell array of the spacecraft.

[0011] Preferably, a metal electrode is installed at each monitoring point and connected to the ground reference point via a wire.

[0012] Preferably, a diode is connected between the output end of the voltage regulator and the battery.

[0013] Preferably, the battery output end is also sequentially connected to a voltage stabilizer power converter, a spacecraft power distribution system and a load.

[0014] Preferably, the processor turns on the monitoring point by inputting a DC-DC signal to the monitoring point.

[0015] Preferably, the multiple sensor probes and wires are made of high temperature resistant and radiation resistant materials, which can adapt to the temperature conditions of low earth orbit, medium and high orbit and deep space exploration.

[0016] Preferably, a control system is also included to dynamically adjust the acquisition process according to environmental conditions and spacecraft power requirements.

[0017] The present invention provides a method for collecting space plasma energy based on the potential difference on the surface of a spacecraft, which is used in the above-mentioned space plasma energy collection device based on the potential difference on the surface of a spacecraft, and comprises the following steps:

[0018] Step 1, select multiple monitoring points on the surface of the spacecraft, and select a point with a higher potential than the surface of the spacecraft as a grounding reference point;

[0019] Step 2, using the sensor probe to monitor the potential of the monitoring point;

[0020] Step 3, selecting a monitoring point with an optimal potential difference between the monitoring point and the ground reference point for energy collection;

[0021] Step 4, turning on the monitoring point, reversing the surface potential of the spacecraft through an inverter, and then charging the battery.

[0022] Preferably, the processor is used to input a DC-DC signal to the monitoring point to enable the monitoring point to be turned on.

[0023] Preferably, step 4 includes step 5, in which the voltage of the electricity in the battery is stabilized and the power is converted by using a voltage stabilizer power converter, and then the electricity is output to the spacecraft power distribution system, and then the spacecraft power distribution system outputs the electricity to the load.

[0024] Preferably, the voltage regulator power converter performs power conversion according to power parameters required by the load.

[0025] Preferably, the acquisition process is also dynamically adjusted according to environmental conditions and spacecraft power requirements through a control system.

[0026] Compared with the existing technology, the present invention shows remarkable technical effects in terms of efficient energy conversion, adaptability to complex space environment, lightweight design, long-term stable operation, and low maintenance requirements:

[0027] 1. Efficient energy collection: The collection device of the present invention utilizes the potential difference naturally existing in space, and through optimized electrode design and configuration, efficiently collects plasma energy, thereby significantly improving energy conversion efficiency.

[0028] 2. Wide applicability: It is suitable for different space environments, such as low-Earth orbit, medium- and high-orbit, and deep space exploration, and can work under various plasma density and temperature conditions, with broad application prospects.

[0029] 3. Lightweight design: The collection device of the present invention has a compact structure and light weight, which is suitable for weight and volume restrictions in space applications and reduces launch and operating costs.

[0030] 4. Long-term stable operation: The use of high temperature resistant and radiation resistant materials ensures long-term stable operation in extreme environments and extends the service life of the device.

[0031] 5. Low maintenance requirement: The collection device of the present invention has a simple design, high reliability, and low maintenance requirement, and is suitable for long-term unattended space missions.

[0032] 6. Real-time monitoring and regulation: Equipped with an advanced control system, it can monitor the space plasma environment and energy collection efficiency in real time, and perform dynamic regulation to adapt to environmental changes and ensure the best energy collection effect.

[0033] 7. Improve spacecraft performance: By efficiently collecting space plasma energy, additional energy support can be provided to spacecraft, thereby improving the spacecraft's endurance and mission execution capabilities. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 This is a schematic diagram of a space plasma energy collection device based on the surface potential difference of a spacecraft according to an embodiment of the present invention.

[0035] Figure 2 This is a schematic diagram of the selection of the grounding reference point and energy collection of a space plasma energy collection device based on the surface potential difference of a spacecraft according to an embodiment of the present invention.

[0036] Figure 3 The present invention is a method for collecting space plasma energy based on the potential difference on the surface of a spacecraft according to an embodiment of the present invention. DETAILED DESCRIPTION

[0037] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. The described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0038] The present invention provides a space plasma energy collection device based on the potential difference on the surface of a spacecraft, which is used for collecting charges on the surface of a spacecraft, and includes a plurality of sensor probes, a processor, an inverter, a voltage regulator and a battery, and also includes a plurality of monitoring points selected on the surface of the spacecraft and a selected ground reference point, wherein the ground reference point has a higher potential than the surface of the spacecraft;

[0039] Each sensor probe is connected to each monitoring point to monitor the potential of the monitoring point; the input end of the processor is connected to the output end of the sensor probe; the output end of the processor is connected to the first input end of the voltage regulator; when the potential of a monitoring point reaches the discharge threshold, the monitoring point is turned on to charge the battery using the potential difference between the monitoring point and the ground reference point;

[0040] The monitoring point and the ground reference point are connected to the input end of the inverter; the output end of the inverter is connected to the second input end of the voltage regulator and the battery.

[0041] In some specific embodiments of the present invention, a plurality of sensor probes are arranged at selected monitoring points of the insulation part and the solar cell array of the spacecraft.

[0042] In some specific embodiments of the present invention, a metal electrode is installed at each monitoring point and connected to the ground reference point via a wire.

[0043] In some specific embodiments of the present invention, a diode is further connected between the output end of the voltage regulator and the battery.

[0044] In some specific embodiments of the present invention, the battery output end is also sequentially connected to a voltage regulator power converter, a spacecraft power distribution system and a load.

[0045] In some specific embodiments of the present invention, the processor turns on the monitoring point by inputting a DC-DC signal to the monitoring point.

[0046] In certain specific embodiments of the present invention, multiple sensor probes and wires are made of high temperature resistant and radiation resistant materials, which can adapt to the temperature conditions of low earth orbit, medium and high orbit and deep space exploration.

[0047] In some specific embodiments of the present invention, a control system is also included to dynamically adjust the acquisition process according to environmental conditions and spacecraft power requirements.

[0048] The present invention provides a method for collecting space plasma energy based on the potential difference on the surface of a spacecraft, which is used in the above-mentioned space plasma energy collection device based on the potential difference on the surface of a spacecraft, and comprises the following steps:

[0049] Step 1, select multiple monitoring points on the surface of the spacecraft, and select a point with a higher potential than the surface of the spacecraft as a grounding reference point;

[0050] Step 2, using the sensor probe to monitor the potential of the monitoring point;

[0051] Step 3, selecting a monitoring point with an optimal potential difference between the monitoring point and the ground reference point for energy collection;

[0052] Step 4, turning on the monitoring point, reversing the surface potential of the spacecraft through an inverter, and then charging the battery.

[0053] In some specific embodiments of the present invention, a processor is used to input a DC-DC signal to the monitoring point to enable the monitoring point to be turned on.

[0054] In certain specific embodiments of the present invention, step 4 is followed by step 5, in which the voltage in the battery is stabilized and the power is converted using a voltage regulator power converter, and then the power is output to a spacecraft power distribution system, and then the spacecraft power distribution system outputs the power to the load.

[0055] In some specific embodiments of the present invention, the voltage regulator power converter performs power conversion according to power parameters required by the load.

[0056] In some specific embodiments of the present invention, the acquisition process is dynamically adjusted according to environmental conditions and spacecraft power requirements through a control system.

[0057] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention are included in the protection scope of the present invention.

Claims

1. A space plasma energy collection device based on the potential difference on the surface of a spacecraft, used for collecting charges on the surface of a spacecraft, characterized in that: The device includes a plurality of sensor probes, a processor, an inverter, a voltage regulator and a battery, and also includes a plurality of monitoring points selected on the surface of the spacecraft and a selected ground reference point, wherein the ground reference point has a higher potential relative to the surface of the spacecraft; Each sensor probe is connected to each of the monitoring points and is used to monitor the potential of the monitoring point; A plurality of sensor probes are arranged at monitoring points selected from the insulating part and the solar cell array of the spacecraft, and a metal electrode is installed at each of the monitoring points, which is connected to the ground reference point through a wire; the input end of the processor is connected to the output end of the sensor probe; the output end of the processor is connected to the first input end of the voltage regulator; when the potential of a certain monitoring point reaches a discharge threshold, the monitoring point is turned on to charge the battery by using the potential difference between the potential of the monitoring point and the ground reference point; The monitoring point and the ground reference point are connected to the input end of the inverter; the output end of the inverter is connected to the second input end of the voltage regulator and the battery.

2. The space plasma energy collection device based on the spacecraft surface potential difference according to claim 1 is characterized in that: A diode is also connected between the output end of the voltage regulator and the battery.

3. The space plasma energy collection device based on the spacecraft surface potential difference according to claim 1 is characterized in that: The battery output end is also sequentially connected to a voltage stabilizer power converter, a spacecraft power distribution system and a load.

4. The space plasma energy collection device based on the spacecraft surface potential difference according to claim 1 is characterized in that: The processor turns on the monitoring point by inputting a DC-DC signal to the monitoring point.

5. A method for collecting space plasma energy based on the potential difference on the surface of a spacecraft, characterized in that: The space plasma energy collection device based on the spacecraft surface potential difference as described in any one of claims 1 to 4 comprises the following steps: Step 1, select multiple monitoring points on the surface of the spacecraft, and select a point with a higher potential than the surface of the spacecraft as a grounding reference point; Step 2, using the sensor probe to monitor the potential of the monitoring point; Step 3, selecting a monitoring point with an optimal potential difference between the monitoring point and the ground reference point for energy collection; Step 4, turning on the monitoring point, reversing the surface potential of the spacecraft through an inverter, and then charging the battery.

6. The method for collecting space plasma energy based on spacecraft surface potential difference according to claim 5, characterized in that: The processor is used to input a DC-DC signal to the monitoring point to enable the monitoring point to be turned on.

7. The method for collecting space plasma energy based on spacecraft surface potential difference according to claim 5, characterized in that: Step 4 includes step 5, which uses a voltage regulator power converter to stabilize the voltage and convert the power of the battery, and then outputs it to the spacecraft power distribution system, and then the spacecraft power distribution system outputs it to the load.

8. The method for collecting space plasma energy based on spacecraft surface potential difference according to claim 7, characterized in that: The voltage regulator power converter performs power conversion according to the power parameters required by the load.

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