A variable structure power supply system and adjustment method suitable for deep space detectors

Abstract

The present invention provides a variable structure power supply system and regulation method adapted to a deep space probe, comprising: a solar cell array, a fully regulated unified bus, a shunt unit, a charging unit, a charging switch, a separated body charging switch, a detector lithium ion battery pack, a separated body lithium ion battery pack, a charging switch, a discharge switch, and a charging and discharging module; the solar cell array supplies power to the fully regulated unified bus through the shunt unit, some charging units are connected to one end of the charging switch or the fully regulated unified bus through the charging switch, and the remaining charging units are connected to one end of the charging switch or the separated body lithium ion battery pack through the separated body charging switch. The variable structure power supply system and regulation method adapted to a deep space probe provided by the present invention improves the output power utilization rate of the solar array and avoids the problem of floating charging of the battery on orbit, which provides great help to greatly improve the on-orbit working life and reliability of the deep space probe battery.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft energy, and in particular to a variable structure power supply system and a regulation method suitable for deep space probes, and in particular to a novel topology of a variable structure power supply system suitable for deep space probes. Background Art

[0002] Deep space probe missions have long flight distances and long durations. There are many unknowns and uncertainties in the space environment, and human intervention is time-sensitive. Therefore, the probes need to have a high degree of autonomous management capabilities. On the way to Mars, the solar radiation is inversely proportional to the square of the distance from the sun (1353W / m per 1AU distance). 2 ). The intensity of solar radiation decreases with increasing distance. After entering the orbit of Mars, the intensity of solar radiation directly irradiated by the Martian atmosphere is 491W / m at the aphelion. 2 and perihelion 715W / m 2 Variations (average value 591W / m 2 ). Therefore, in the process of development, considering the above factors and combining with the needs of the detector, how to design a new topology of the power supply system of deep space detectors to achieve higher utilization of the energy of the entire satellite.

[0003] In the patent document "Partially Self-Reconfigurable Deep Space Exploration Power System" CN201410427811.X, the power system structure of different orbits is realized by transforming the charging control circuit, peak tracking circuit, discharge control circuit and balancing control circuit; in the patent document "A Deep Space Exploration Aircraft Power System" CN201811261951.9, the peak power tracking power supply topology under the dual bus system is optimized to improve the charging efficiency; in the patent document "A Deep Space Exploration Solar Cell System Design Method" CN201910291474.9, the battery cell series and parallel design is determined by judging the flight distance. In the Chinese invention patent document with the publication number CN110148995A, a spacecraft reconfigurable power system architecture is disclosed, including a solar cell array, a battery pack, a source bus, a functional switch module, a DC / DC converter module and a load bus. As the source level, the solar cell array and the battery group are connected to the segmented source bus through the functional switch module, and the source bus is connected to the load bus through the DC / DC converter module to achieve energy conversion. The DC / DC converter has the ability to be reconfigured into MPPT module, battery charging module, battery discharging module and other functional modules, and switches various working modes of the power system through the functional switch module and reconstruction algorithm. Summary of the invention

[0004] In view of the defects in the prior art, the purpose of the present invention is to provide a variable structure power supply system topology and adjustment method suitable for deep space probes.

[0005] According to the present invention, a variable structure power supply system adapted to a deep space detector comprises: a solar cell array, a fully regulated unified bus, a shunt unit, a charging unit, a charging switching switch, a separated body charging switch, a detector lithium ion battery pack, a separated body lithium ion battery pack, a charging switch, a discharge switch and a charging and discharging module; the solar cell array supplies power to the fully regulated unified bus through the shunt unit, the charging units are provided in a plurality and are all connected to the solar cell array, some of the charging units are connected to one end of the charging switch or the fully regulated unified bus through the charging switching switch, the remaining charging units are connected to one end of the charging switch or the separated body lithium ion battery pack through the separated body charging switch, the other end of the charging switch is respectively connected to the discharge regulating module and the detector lithium ion battery pack, the charging switch provides a charging path for the detector lithium ion battery pack, the discharge switch provides a discharge path for the detector lithium ion battery pack, a discharge switch is connected in series between the detector lithium ion battery pack and the other end of the charging switch, and the discharge regulating module outputs the power of the detector lithium ion battery pack to the fully regulated unified bus.

[0006] Preferably, the partial charging unit is connected to one end of the charging switch or the fully-regulated unified bus through a charging switching switch. When the detector lithium-ion battery pack is connected to the charging switch to provide a path for charging, the charging switching switch is gradually switched from connecting to one end of the charging switch to connecting to the fully-regulated unified bus according to the charging voltage and charging current power required by the detector lithium-ion battery pack.

[0007] Preferably, the partial charging unit is connected to one end of the charging switch or the fully regulated unified bus through a charging switching switch. When the detector lithium-ion battery pack is fully charged and the energy of the entire star is in short supply, all charging switching switches are switched to connect to the fully regulated unified bus.

[0008] Preferably, the partial charging unit is connected to one end of the charging switch or the fully regulated unified bus through a charging switching switch. When the entire star has abundant energy and the detector lithium-ion battery pack is low on power, different numbers of charging switching switches are selected according to the energy abundance of the entire star to switch to connect the detector lithium-ion battery pack and turn on the charging switch. The higher the energy abundance of the entire star, the more charging switching switches are connected to the detector lithium-ion battery pack.

[0009] Preferably, the other part of the charging unit is connected to one end of the charging switch or the separated lithium-ion battery pack through a separated charging switch. When all the charging switching switches are connected to the fully regulated unified bus and the energy of the entire star is still tight, the separated charging switch is connected to one end of the charging switch.

[0010] Preferably, the other part of the charging unit is connected to one end of the charging switch or the separated lithium-ion battery pack through a separated charging switch. When all the charging switching switches are connected to one end of the charging switch to charge the detector lithium-ion battery pack, and the charging speed of the detector lithium-ion battery pack needs to be increased, some or all of the separated charging switches are connected to one side of the charging switch, and the remaining charging unit power is output to the detector lithium-ion battery pack.

[0011] Preferably, the remaining charging unit is connected to one end of the charging switch or the detachable lithium-ion battery pack through the detachable charging switch. When the detachable lithium-ion battery pack needs to be charged before the detector is separated, different numbers of detachable charging switches are selected to be connected to the detachable lithium-ion battery pack according to the remaining time before separation. The shorter the remaining time, the more detachable charging switches are connected to the detachable lithium-ion battery pack, and the number of detachable charging switches connected shall not exceed two.

[0012] Preferably, the partial charging unit is connected to one end of the charging switch or the fully-regulated unified bus through a charging switching switch. When the spacecraft is in an illumination period for a long time during space flight, different numbers of charging switching switches are connected to the fully-regulated unified bus according to the power demand of the entire satellite and the power of the solar cell array, thereby reducing the number of charge and discharge times of the detector lithium-ion battery pack.

[0013] Preferably, the fully-adjustable unified bus includes a fully-adjustable unified bus positive line and a fully-adjustable unified bus return line, and a bus capacitor is connected between the fully-adjustable unified bus positive line and the fully-adjustable unified bus return line.

[0014] According to the present invention, a variable structure power system adjustment method adapted to a deep space probe comprises the following steps:

[0015] Step S1: Before the probe is launched, the charging switch and the discharging switch are turned on, and the charging switch and the discharging switch are kept on during the in-orbit flight phase. The discharge switch is turned on to ensure the stable output voltage on the fully regulated unified bus.

[0016] Step S2: Control the charging switching switch according to the specific situation of the detector and the earth. In the near-earth stage, the solar cell array has a large output power margin and the detector lithium-ion battery pack has a small charging power demand. Some charging switching switches are selected to be connected to one side of the charging switch to charge the detector lithium-ion battery pack. When the detector lithium-ion battery pack is full, zero or one charging switching switch is selected to be connected to one side of the charging switch to charge the detector lithium-ion battery pack.

[0017] Step S3: In the remote stage, the output power margin of the solar cell array is small and the battery charging power demand is small. Select some or all of the charging switching switches to be connected to one side of the charging switch to charge the detector lithium-ion battery pack. When the detector lithium-ion battery pack is full, select one or two charging switching switches to be connected to one side of the charging switch to charge the detector lithium-ion battery pack.

[0018] Step S4: During the detector separation stage, the solar cell array output power margin is small, and different numbers of separation body charging switches are selected to be connected to the separation body lithium-ion battery pack according to the remaining time before separation. The shorter the remaining time, the more separation body charging switches are connected to the separation body lithium-ion battery pack.

[0019] Step S5: After the detector is separated, all the separated body charging switches are connected to one end of the charging switch.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1. The present invention greatly improves the utilization rate of the output power of the solar cell array and reduces the waste of energy;

[0022] 2. The present invention avoids the problem of on-orbit floating charge of the detector lithium-ion battery pack, thereby increasing the on-orbit service life of the detector lithium-ion battery pack;

[0023] 3. This power system topology has the advantage of high stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0025] Figure 1 This is a topology diagram of a variable structure power supply system suitable for deep space probes according to the present invention. DETAILED DESCRIPTION

[0026] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0027] A variable structure power supply system adapted to a deep space detector includes: a solar cell array, a fully regulated unified bus, a shunt unit, a charging unit, a charging switch, a separated body charging switch, a detector lithium ion battery pack, a separated body lithium ion battery pack, a charging switch, a discharging switch, and a charging and discharging module. In this embodiment, the number of shunt units is 14, the number of charging switches is 2, the number of discharging switches is 2, the number of charging units is 6, the number of charging switches is 4, the number of separated body charging switches is 2, and the fully regulated unified bus includes a fully regulated unified bus positive line and a fully regulated unified bus return line.

[0028] The solar cell array supplies power to the fully regulated unified busbar through the shunt unit, and the 14 charging units are connected to the solar cell array and then connected in parallel to the fully regulated unified busbar. One end of the charging unit is connected to the solar cell array, and the other ends of four charging units are connected to one end of the charging switch or the fully regulated unified busbar through four charging switching switches, respectively. The remaining two charging units are connected to one end of the charging switch or the separated lithium-ion battery pack through two separated charging switches, respectively. A protection capacitor is connected to one end of the charging switch, and the other end of the protection capacitor is connected to the charging switching switch and the separated charging switch. The other end of the charging switch is respectively connected to the discharge regulation module and the detector lithium-ion battery pack. A discharge switch is connected in series between the detector lithium-ion battery pack and the other end of the charging switch, and the discharge regulation module outputs the power of the detector lithium-ion battery pack to the fully regulated unified busbar. A bus capacitor is connected between the positive line of the fully regulated unified busbar and the return line of the fully regulated unified busbar.

[0029] The charging switch is controlled according to the distance of the probe from the earth, but the charging switch and the discharging switch remain on during the whole mission phase. In the near-Earth phase, the output power margin of the solar cell array is relatively large, and the charging power demand of the probe lithium-ion battery pack is relatively small. Two or three of the charging switches can be switched to charge the probe lithium-ion battery pack, and after the charging of the separated lithium-ion battery pack is completed, the two separated charging switches are switched to charge the probe lithium-ion battery pack; when the probe lithium-ion battery pack is full, 0 or 1 of the charging switches can be switched to the probe lithium-ion battery pack, and the two separated charging switch switches can remain unchanged, so that the probe lithium-ion battery pack is in a state of not charging or discharging with a small current; the number of switching paths of the charging switch is mainly based on the output power of the solar cell array and the load power demand, so that the probe lithium-ion battery pack has a smaller discharge current and a smaller discharge current under different charging switch states;

[0030] In the remote stage, the output power margin of the solar cell array is relatively small, and the charging power demand of the detector lithium-ion battery pack is relatively small. Three or four of the charging switches can be switched to charge the detector lithium-ion battery pack, and the separation body charging switch can be switched to charge the detector lithium-ion battery pack. When the detector lithium-ion battery pack is full, one or two of the charging switches can be switched to the detector lithium-ion battery pack, so that the detector lithium-ion battery pack is in a state of small current discharge, which not only ensures that the detector lithium-ion battery pack is not floating charged but also ensures that the charging path is uninterrupted;

[0031] During the separation stage, the output power margin of the solar cell array is relatively small. The separation body lithium-ion battery pack is required to be fully charged 2 days before separation. Then the detector program controls one separation body charging switch to the separation body lithium-ion battery pack. If the actual project time is tight, two separation body charging switches can be switched to the separation body lithium-ion battery pack to achieve fast charging.

[0032] In the post-separation stage, the two separation body charging switches are switched to charge the detector lithium-ion battery pack, or the charging switch is connected to switch the state of the separation body lithium-ion battery pack to realize the charging and discharging of the battery detector lithium-ion battery pack.

[0033] Through the above process, the charging switch and the separated charging switch are controlled to put the detector lithium-ion battery pack in a state of small current charging and small current discharging (or no charging); the number of switching paths of the charging switch is mainly based on the output power of the solar cell array and the load power requirement, so that the detector lithium-ion battery pack has a smaller discharge current and a smaller discharge current under different charging switch states, which realizes the improvement of the solar array output power utilization rate and avoids the problem of battery floating charge on orbit, and greatly improves the on-orbit working life of the deep space detector lithium-ion battery and provides great help for reliability.

[0034] According to the special requirements of deep space exploration for power supply and the advantages of the commonly used S3R and S4R topological structures of power supply, the present invention makes partial changes to the circuit structure, which not only ensures the maturity of the original technology but also ensures the safety of project implementation, while improving the output power utilization rate of the solar array and avoiding the problem of floating charge of the battery on orbit, greatly improving the on-orbit working life of the lithium-ion battery of the deep space probe and providing great help to the reliability.

[0035] Those skilled in the art know that, in addition to realizing the system and its various devices, modules, and units provided by the present invention in a purely computer-readable program code, it is entirely possible to realize the same functions in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a hardware component, and the devices, modules, and units included therein for realizing various functions can also be regarded as structures within the hardware component; the devices, modules, and units for realizing various functions can also be regarded as both software modules for realizing the method and structures within the hardware component.

[0036] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A variable structure power supply system adapted to deep space probes, characterized in that: include: A solar cell array, a fully regulated unified bus, a shunt unit, a charging unit, a charging switch, a separated body charging switch, a detector lithium ion battery pack, a separated body lithium ion battery pack, a charging switch, a discharging switch and a discharging regulating module; the solar cell array supplies power to the fully regulated unified bus through the shunt unit, the charging units are provided in a plurality and are all connected to the solar cell array, wherein some charging units are connected to the input end of the charging switch, the first output end of the charging switch is connected to one end of the charging switch, and the second output end of the charging switch is connected to the fully regulated unified bus; the remaining charging units are connected to the input end of the separated body charging switch, the first output end of the separated body charging switch is connected to one end of the charging switch, the second output end of the separated body charging switch is connected to the separated body lithium ion battery pack, the other end of the charging switch is respectively connected to the discharging regulating module and the detector lithium ion battery pack, the charging switch provides a charging path for the detector lithium ion battery pack, the discharging switch provides a discharging path for the detector lithium ion battery pack, a discharging switch is connected in series between the detector lithium ion battery pack and the other end of the charging switch, and the discharging regulating module outputs the power of the detector lithium ion battery pack to the fully regulated unified bus.

2. The variable structure power supply system adapted to deep space probes according to claim 1 is characterized in that: The partial charging unit is connected to one end of the charging switch or the fully regulated unified bus through the charging switching switch. When the detector lithium-ion battery pack is connected to the charging switch to provide a path for charging, the charging switching switch is gradually switched from connecting to one end of the charging switch to connecting to the fully regulated unified bus according to the charging voltage and charging current power required by the detector lithium-ion battery pack.

3. The variable structure power supply system adapted to deep space probes according to claim 1 is characterized in that: The partial charging unit is connected to one end of the charging switch or the fully regulated unified busbar through the charging switching switch. When the lithium-ion battery pack of the detector is fully charged and the energy of the deep space detector is in short supply, all the charging switching switches are switched to connect to the fully regulated unified busbar.

4. The variable structure power supply system adapted to deep space probes according to claim 1 is characterized in that: Some charging units are connected to one end of the charging switch or the fully regulated unified bus through the charging switching switch. When the energy of the entire satellite is abundant and the detector lithium-ion battery pack is low on power, different numbers of charging switching switches are selected according to the energy abundance of the entire satellite to switch to connect the detector lithium-ion battery pack and turn on the charging switch. The higher the energy abundance of the entire satellite, the more charging switching switches are connected to the detector lithium-ion battery pack.

5. The variable structure power supply system adapted to deep space probes according to claim 1 is characterized in that: Some charging units are connected to one end of the charging switch or the separated lithium-ion battery pack through the separated charging switch. When all charging switching switches are connected to the fully regulated unified bus and the energy of the entire star is still tight, the separated charging switch is connected to one end of the charging switch.

6. The variable structure power supply system adapted to deep space probes according to claim 1 is characterized in that: Some charging units are connected to one end of the charging switch or the separated lithium-ion battery pack through the separated charging switch. When all the charging switching switches are connected to one end of the charging switch to charge the detector lithium-ion battery pack, and the charging speed of the detector lithium-ion battery pack needs to be increased, some or all of the separated charging switches are connected to one side of the charging switch, and the remaining charging unit power is output to the detector lithium-ion battery pack.

7. The variable structure power supply system adapted to deep space probes according to claim 1 is characterized in that: The residual charging unit is connected to one end of the charging switch or the detachable lithium-ion battery pack through the detachable charging switch. When the detachable lithium-ion battery pack needs to be charged before the detector is separated, different numbers of detachable charging switches are selected to be connected to the detachable lithium-ion battery pack according to the remaining time before separation. The shorter the remaining time, the more detachable charging switches are connected to the detachable lithium-ion battery pack, and the number of detachable charging switches connected shall not exceed two.

8. The variable structure power supply system adapted to deep space probes according to claim 1 is characterized in that: The partial charging unit is connected to one end of the charging switch or the fully-regulated unified busbar through the charging switching switch. When the spacecraft is in an illumination period for a long time during space flight, different numbers of charging switching switches are connected to the fully-regulated unified busbar according to the power demand of the entire satellite and the power of the solar cell array, thereby reducing the number of charge and discharge times of the detector lithium-ion battery pack.

9. The variable structure power supply system adapted to deep space probes according to claim 1 is characterized in that: The fully-adjustable unified bus includes a fully-adjustable unified bus positive line and a fully-adjustable unified bus return line, and a bus capacitor is connected between the fully-adjustable unified bus positive line and the fully-adjustable unified bus return line.

10. A method for adjusting a variable structure power supply system for a deep space probe, using the variable structure power supply system for a deep space probe as claimed in claim 1, characterized in that: The following steps are involved: Step S1: Before the launch of the probe, the charging switch and the discharging switch are turned on, and the charging switch and the discharging switch are kept on during the on-orbit flight stage. The discharge switch is turned on to ensure the stable output of the voltage on the fully regulated unified bus; Step S2: Control the charging switch according to the distance between the detector and the earth. In the near-earth phase, the output power margin of the solar cell array is large, and the charging power demand of the detector lithium-ion battery pack is small. Select some charging switches to connect to one side of the charging switch to charge the detector lithium-ion battery pack. When the detector lithium-ion battery pack is full, stop charging or connect a charging switch to one side of the charging switch. Step S3: In the remote stage, the output power margin of the solar cell array is small, and the battery charging power demand is small. Some or all of the charging switching switches are selected to be connected to one side of the charging switch to charge the detector lithium-ion battery pack. When the detector lithium-ion battery pack is full, one or two charging switching switches are selected to be connected to one side of the charging switch to charge the detector lithium-ion battery pack. Step S4: During the detector separation stage, the output power margin of the solar cell array is small, and different numbers of separation body charging switches are selected to be connected to the separation body lithium-ion battery pack according to the remaining time before separation. The shorter the remaining time, the more separation body charging switches are connected to the separation body lithium-ion battery pack; Step S5: After the detector is separated, all the separated body charging switches are connected to one end of the charging switch.

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