Interplanetary transfer detector energy system and operation method

Abstract

The invention provides an interplanetary detector energy transfer system and an operation method. The interplanetary detector energy transfer system comprises a power generation device, a power transformation device, a power storage device, a full-adjustment bus and a non-adjustment bus, the power generation device is connected with the input end of a shunt circuit of the power transformation device through a direct current transmission cable, the output end of the power transformation device is connected to a fully-adjustable bus and an unadjustable bus respectively, the power storage device is in bidirectional connection with the power transformation device through a charging and discharging loop, and the fully-adjustable bus and the unadjustable bus supply power to corresponding loads respectively. According to the invention, the flow direction of the energy is controlled through the elastic change-over switch, so that on one hand, the difference of the generated power of the solar cell array caused by the light intensity change of the space environment in the interplanetary transfer process can be adapted, and on the other hand, the change of the power demand of the interplanetary detector in each task stage can be met; the utilization efficiency of the generated power of the solar cell array is improved; and on the other hand, the design complexity and the overhead of weight and volume resources of the power supply controller are reduced.

Description

Technical Field

[0001] This invention relates to the field of interplanetary transfer probe technology, and more specifically, to an interplanetary transfer probe energy system and operating method. Background Technology

[0002] Compared to Earth-orbiting spacecraft, interplanetary exploration missions may encounter much harsher space environments, such as extreme temperatures, radiation, corrosive atmospheres, and cosmic dust. Coupled with the long lifespan of interplanetary missions, the space environment poses a serious threat to the reliability of interplanetary probes, directly affecting the achievement of their objectives. The JUICE probe carries large-area solar panels; despite being far from the sun, the extensive solar array can still provide sufficient energy to support its mission. Design experience with this probe indicates that for deep-space probes within Jupiter's range, solar energy can be a preferred power source. Compared to nuclear power, solar energy remains a highly efficient and low-cost energy source.

[0003] For the power system of a probe on an interplanetary transfer flight, the complex interplanetary environment encountered during cruise flight is mainly manifested in the large-scale variation of solar intensity with the probe's distance from the sun, for example, 1347 W / m² near Earth. 2 The minimum strength was only 491 W / m² when traversing Martian space. 2 This has led to a series of challenges, including excess power generation from near-Earth space solar arrays, heat dissipation issues in power controllers, and the environmental adaptability of components and raw materials under drastic changes in external heat flow.

[0004] Patent document CN107579587B discloses an energy system and control method suitable for LEO satellites, comprising a solar cell array, an MPPT circuit unit, a battery bank, a capacitor array, a satellite platform load, and a telemetry and remote control unit. The MPPT circuit unit uses three parallel DC-DC converter modules to perform peak power point tracking (MPPT) on the solar cell array in a triple-redundant hot-backup manner. The MPPT circuit unit employs a majority voting control circuit for closed-loop control. Each control circuit generates a drive signal based on the output voltage and current signals of the solar cell array module and the voltage and current signals of the battery bank to perform closed-loop control on its corresponding MPPT circuit, thereby achieving maximum power point tracking of the solar cell array module and charging management of the battery bank.

[0005] Patent document CN110450979B discloses a multi-energy, multi-instrument combined Jupiter system and planetary transit probe, including a Jupiter system probe and a planetary transit probe. The Jupiter system probe and the planetary transit probe are connected via an inter-instrument connection unlocking device. The Jupiter system probe is powered by a solar cell array and a battery, while the planetary transit probe is powered by a radioisotope thermoelectric power source. The Jupiter system probe and the planetary transit probe are respectively equipped with a first high-gain antenna and a second high-gain antenna. The Jupiter system probe and the planetary transit probe work together to complete a cruise flight from Earth to Jupiter. Before reaching Jupiter, the probes separate. After separation, the Jupiter system probe performs a braking capture ignition at Jupiter's perihelion to complete its orbital exploration of Jupiter. The planetary transit probe continues its flight and planetary transit exploration after using Jupiter's gravity.

[0006] Patent document CN109065777B discloses a lightweight lithium-ion battery pack for launch vehicles, including a base plate, support rods, a battery stack, electrical connectors, a cover plate, countersunk screws for the support rods, and fixing screws for the electrical connectors. The base plate and cover plate have several protruding small support platforms around them, each with countersunk holes matching the outer diameter of the support rods. The support rods are inserted into these countersunk holes and secured with countersunk screws to form the outer shell structure. The battery stack is installed within the space formed between the base plate and the cover plate.

[0007] Patent document CN110277522B discloses a lightweight lithium-ion battery module for underwater devices and its manufacturing method. The module has an overall open structure with single-sided adhesive suspension support, including a panel, a first insulating plate, a battery stack, a second insulating plate, guide supports, side supports, bottom supports, top supports, and electrical connectors. The first insulating plate and the panel are coated with silicone rubber, bonded together, and cured for more than one day. The battery stack and the first insulating plate are coated with silicone rubber, bonded together, and cured for more than five days. The second insulating plate is installed on the other side of the battery stack for insulation and does not provide support. The guide supports, side supports, bottom supports, and top supports are not in contact with the battery stack.

[0008] The paper "Design and Implementation of Mars Orbiter Interplanetary Flight" (Shanghai Aerospace (Chinese and English) SHHT2022S1014) addresses the requirements of accurately adjusting solar cell energy distribution and fully utilizing solar cell power to achieve system energy balance under complex operating conditions in Mars orbit. The orbiter's power system is designed with a power conversion module. Through a comprehensive processing circuit, the module centrally judges the battery pack voltage and MEA (Main Error Amplifier), and controls the power conversion module to autonomously switch between power supply and charging in real time. This achieves dynamic autonomous energy switching control and variable charging array switching, ensuring the overall energy safety of the spacecraft.

[0009] However, the aforementioned patents and documents cannot completely solve the existing technical problems, nor can they meet the needs of this invention. Summary of the Invention

[0010] In view of the deficiencies in the prior art, the purpose of this invention is to provide an interplanetary transfer probe energy system and operation method.

[0011] The interplanetary transfer probe energy system provided by the present invention includes: a power generation device, a power transformation device and a power storage device, as well as a fully regulated bus and a non-regulated bus; The power generation device is connected to the input terminal of the shunt circuit of the transformer via a DC transmission cable. The output terminal of the transformer is connected to the fully regulated bus and the unregulated bus respectively. The energy storage device is bidirectionally connected to the transformer via a charging and discharging circuit. The fully regulated bus and the unregulated bus respectively supply power to the corresponding load. The substation includes a shunt circuit, a flexible switching switch, a charging switch, a discharging switch, and a discharging circuit. The output of the shunt circuit is connected through the flexible switching switch. The charging switch is connected between the shunt circuit and the energy storage device. The discharging switch is connected between the energy storage device and the non-regulating bus. The discharging circuit is connected between the non-regulating bus and the fully regulated bus.

[0012] Preferably, the substation has a built-in telemetry and remote control unit that receives control commands from the detector's integrated electronic system via a digital signal bus and feeds back voltage, current, and temperature data.

[0013] Preferably, the power generation device is a triple-junction gallium arsenide solar cell circuit, comprising multiple solar cell arrays, which are independently connected to the shunt circuit in the power transformer through the array configuration. The array is configured as a power supply array and a charging array according to its purpose, wherein the power supply array directly supplies power to the detector, and the charging array supplies power to the detector and / or charges the energy storage device.

[0014] Preferably, the power distribution unit is an S3R type power controller.

[0015] Preferably, the drive signals for each switch are generated by the control logic unit of the power controller. The voltage and current sampling signals are transmitted to the control logic unit for processing via analog signal lines. The control logic unit communicates with the detector's main control system through a digital interface, receives control commands, and uploads status information. A portion of the shunt circuit is directly connected to the busbar. After meeting the detector's basic power requirements, excess energy will be directly shunted. The remaining shunt circuit is connected to the flexible switching switch to power the detector, and excess energy will be directly shunted. If the flexible switching switch contacts switch, and the charging switch is on, excess energy will charge the energy storage device. Once the energy storage device is fully charged, the excess energy will be shunted.

[0016] Preferably, the energy storage device is a lithium-ion battery pack consisting of individual cells connected in parallel and then in series.

[0017] Preferably, the flexible switching switch is a single-pole double-throw mechanical or electronic switch, with one end connected to the shunt circuit and the other end connected to the fully adjustable bus and the non-adjustable bus respectively. It is switched by remote control command from the ground or by the detector according to the real-time telemetry status on the device.

[0018] Preferably, the fully adjustable bus is a high-quality bus with preset low ripple and anti-interference, which provides power for the detector's integrated electronics, measurement and control, attitude and orbit control and individual units.

[0019] Preferably, the voltage of the non-regulating bus varies with the voltage of the battery pack, providing energy for the detector's thermal control heater and individual unit.

[0020] The method for operating an interplanetary transfer probe energy system according to the present invention includes the following steps: Step 1: Calculate the fully regulated bus load power based on the interplanetary transfer probe's requirements for high-quality bus load power. ; Step 2: Calculate the unadjusted bus load power based on the interplanetary transfer probe's power requirements for the non-high-quality bus load. ; Step 3: Calculate the output power of each array based on the default lighting conditions of the interplanetary transfer probe. ; Step 4: Determine the parameter value m to ensure the output power of array 1 to array m-1 is optimal. The sum of these values ​​is greater than the total regulating bus load power. And design margins; Step 5: Determine the parameter value n so that the sum of the output power Pm, Pm+1, ..., Pn-1 of the array m to n is greater than the unadjusted bus load power. And design margins; Step 6: Optimize the distribution of output power from the mth to the nth shunt circuit using the flexible switching switch; by default, the flexible switching switch is connected to the charging switch, and the output power from the mth to the nth shunt circuit is output to the non-regulating bus and the energy storage device, prioritizing the power demand of the non-regulating bus, and charging the energy storage device with excess energy. After the energy storage device is fully charged, the excess energy is then shunted. Step 7: When the lighting conditions of the interplanetary transfer probe change, if the output power of array 1 to array m-1... The sum is less than the load power of the fully regulated bus. By controlling the flexible switching switch via command, subarray m and subarray m+1 are connected to the fully adjustable bus; if the output power of subarray 1 to subarray m+1... The sum is still less than the load power of the fully regulated bus. By controlling the remaining flexible switching switches one by one through commands, the remaining sub-arrays are connected to the fully adjustable bus until the load power of the fully adjustable bus is met. Excess energy will be diverted.

[0021] Compared with the prior art, the present invention has the following beneficial effects: (1) The shunt circuit (m-1) proposed in this invention is directly connected to the bus. After meeting the power requirements of the detector, the excess energy will be directly shunted. The remaining shunt circuit (n-m+1) is connected to the flexible switching switch, which can supply power to the detector. The excess energy will be directly shunted. If the flexible switching switch contacts are switched, and the charging switch is turned on, the excess energy can be preferentially used to charge the energy storage device. After the energy storage device is fully charged, the excess energy will be shunted. (2) The fully adjustable bus proposed in this invention is generally a high-quality bus with low ripple and strong anti-interference capability, which mainly provides energy for important subsystems and individual units such as detector integrated electronics, measurement and control, attitude and orbit control; the voltage of the non-adjustable bus changes with the voltage of the battery pack, which generally provides energy for subsystems and individual units such as detector thermal control heaters that do not have high requirements for bus quality. (3) The single-pole double-throw mechanical or electronic switch proposed in this invention is connected to the shunt circuit at one end and to the fully adjustable bus and the unadjustable bus at the other end respectively. The number of circuits can be adjusted according to the power demand of the fully adjustable bus and the unadjustable bus of the detector. This can avoid the efficiency loss of power supply through the discharge circuit after the power demand of the fully adjustable bus increases, and also avoid the shunt waste caused by the power demand of the fully adjustable bus decreases. (4) The flexible switching switch proposed in this invention generally adopts two sets of switching methods. While avoiding single-point switching failure, it also further reduces the number of flexible switching switches used, and realizes the optimized design of weight and volume. It can be switched by remote control command from the ground, or the detector can intelligently switch according to the real-time telemetry status on the device. (5) The elastic control proposed in this invention can realize the energy flow distribution in various application scenarios such as the initial stage of interplanetary probe entering orbit, the period when the distance between the probe and the sun is constantly increasing and the light weakens, the long light period during interplanetary cruise flight, and the period when the probe is orbiting the target celestial body. Attached Figure Description

[0022] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 A state diagram showing the flexible switching settings for the initial orbital insertion of an interplanetary probe. Figure 2 A diagram showing the state of the flexible switching switch after the light intensity decreases due to the increasing distance between the device and the sun. Figure 3 A state diagram for setting up the flexible switching switch during long periods of illumination during interplanetary cruise flight; Figure 4 This is a diagram showing the state of the flexible switching switch after the interplanetary probe reaches its target celestial body and partially disconnects the electrical load. Detailed Implementation

[0023] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0024] Example This invention provides an interplanetary transfer probe power system, comprising: First, based on the power requirements of different types of loads on interplanetary probes, they are classified into two categories. The first category includes important subsystems and individual units such as integrated electronics, telemetry and control, and attitude and orbit control. These generally use fully adjustable buses, characterized by low ripple, strong anti-interference capabilities, and high quality. The second category includes loads such as probe thermal control heaters, which generally use non-adjustable buses. These are characterized by bus voltage varying with battery pack voltage and provide power to subsystems and individual units with low requirements for bus quality. Secondly, the power demand values ​​of the loads on the fully regulated bus and the non-regulated bus are statistically analyzed. Based on the power generation value of each sub-array, the initial state settings of the flexible switching switch are performed, such as... Figure 1 As shown, the initial settings must ensure the power requirements of both the fully adjustable bus load and the non-adjustable bus load during the initial launch phase, while controlling the charging current of the battery pack below the allowable charging rate to prevent overcharging damage to the battery pack caused by the high power generation of the solar array during the initial orbit insertion phase.

[0025] Third, as the distance between the spacecraft and the sun increases, the intensity of sunlight decreases, and the power generation of the solar array decreases. Based on the variation of sunlight intensity with the distance between the spacecraft and the sun, the flexible switching switch contacts are controlled step-by-step to the non-adjusting bus, such as... Figure 2 As shown, while meeting the power demand of the electrical load on the non-adjustable bus, the excess energy provides sufficient current to charge the battery pack, realizing the switching from power supply array to charging array and the reuse of solar cell array subarrays. Fourth, during long-term sunlight exposure during interplanetary cruise, once the battery pack is fully charged, the control spring switch contacts are switched to the fully regulating bus, such as... Figure 3 As shown, this can effectively avoid the float charging effect on the battery pack and prevent capacity loss; when the battery pack capacity is lower than the set threshold, the flexible switching switch contacts can be re-controlled to the non-adjusting bus for supplementary charging. Fifth, upon reaching the target planet, the power demand of the fully regulated bus is significantly reduced after some of the electrical loads in the probe are disconnected. To avoid wasting power generated by the solar array sub-arrays, based on the probe's basic power demand at this point, the sub-arrays originally on the fully regulated bus are switched to the non-regulated bus via a controllable flexible switching switch. Figure 4 As shown, more energy is provided to the battery bank and the unregulated bus load, so as to achieve flexible distribution of the power generation of the solar cell array under low light intensity based on the existing number of solar cell arrays, improve energy utilization, meet the energy security of the detector, and achieve the purpose of flexible design.

[0026] Specifically, the interplanetary transfer probe's energy system includes: a power generation unit, a power transformation unit, and an energy storage unit, as well as fully regulated and unregulated bus topologies. By setting the contact positions of the flexible switching switches in the power transformation unit, the output power of the power generation unit can be flexibly controlled to flow to the energy storage unit, the fully regulated bus, and the unregulated bus, thus meeting the power needs of different types of loads.

[0027] As interplanetary probes travel from Earth to exoplanets along predetermined transfer orbits, the intensity of sunlight in interplanetary space decreases as the distance increases from one AU to tens or hundreds of AUs, causing drastic changes in the power output of solar arrays. Currently, most interplanetary probes employ a mature power supply system of "solar array + battery pack." However, due to the constraints of launch vehicle capabilities and transfer orbits, interplanetary missions face extremely stringent requirements regarding weight and size. The solution proposed in this invention is to control the energy flow through a flexible switching mechanism. This approach adapts to the variations in solar array power output caused by changes in space environment light intensity during interplanetary transfer, while also meeting the fluctuating power demands of the probe at different mission phases. This solves the problem of power waste caused by mismatch between the two, improving the utilization efficiency of the solar array's power output. Furthermore, it reduces the design complexity of the power controller and the overhead of weight and volume resources, achieving a flexible design for the interplanetary transfer probe's energy system.

[0028] The power generation unit is connected to the input terminal of the shunt circuit of the substation via a DC transmission cable; the output terminal of the substation is connected to the fully regulated bus and the unregulated bus respectively; the energy storage device is bidirectionally connected to the substation via a charging and discharging circuit; the fully regulated bus and the unregulated bus supply power to their respective loads. The signal transmission relationship is as follows: the substation has a built-in telemetry and control unit that receives control commands from the integrated electronic system of the detector via a digital signal bus, and simultaneously feeds back telemetry data such as voltage, current, and temperature to the system; the control signal of the flexible switching switch originates from ground remote control commands or the decision output of the intelligent control algorithm on the device. In this flexible energy topology, the triple-junction gallium arsenide solar cell arrays (power generation units) are connected to the shunt circuit of the S3R system power controller via DC transmission lines, forming independent input channels for the power supply array and the charging array. The power generation units include array 1...array m-1, array m, array m+1...array n-1, array n. The generator set includes a power generation system with output terminals connected to shunt circuit 1, shunt circuit m, and shunt circuit n, providing power to the system. The substation's output terminals are connected to both the fully regulated bus and the unregulated bus. The substation includes shunt circuit 1, shunt circuit m-1, shunt circuit m, shunt circuit m+1, shunt circuit n, flexible switching switches 1-k, a charging switch, a discharging switch, and a discharging circuit. The output terminals of the shunt circuits dynamically switch between the fully regulated bus and the unregulated bus according to real-time power demand via a single-pole double-throw flexible switching switch. When the charging switch is closed, excess power is directed to the energy storage branch. The energy storage device (a lithium-ion battery pack connected in parallel and then in series) absorbs energy through the charging switch and feeds it back to the fully regulated bus via the discharging switch and discharging circuit, enabling continuous power supply under insufficient sunlight or shade conditions. Specifically, the output terminals of the first to nth shunt circuits are connected to the unregulated bus via flexible switching switches 1 to k and a charging switch. The positive terminal of the energy storage device is connected to the unregulated bus via a discharge switch, and the positive terminal of the unregulated bus is connected to the fully regulated bus via a discharge circuit. The positive terminals of the mth and m+1th shunt circuit outputs are respectively connected to two sets of contacts of flexible switching switch 1… the positive terminals of the n-1th and nth shunt circuit outputs are respectively connected to two sets of contacts of flexible switching switch k. The system signal transmission relationship is as follows: the substation has a built-in telemetry and control unit that receives control commands from the integrated electronic system of the detector via a digital signal bus, and simultaneously feeds back telemetry data such as voltage, current, and temperature to the system; the control signals of the flexible switching switches originate from ground remote control commands or the decision output of the intelligent control algorithm on the device. By setting the contact positions of the flexible switching switches in the substation, the output power of the generator can be flexibly controlled to flow to the energy storage device, the fully regulated bus, and the unregulated bus, meeting the power needs of different types of loads. The power generation device is a triple-junction gallium arsenide solar cell circuit, which is independently connected to the shunt circuit in the power transformer through a grid configuration. The grid is configured as a power supply array and a charging array according to its purpose. The power supply array directly supplies power to the detector, while the charging array can supply power to the detector and charge the energy storage device. The substation is an S3R-type power controller, consisting of a shunt circuit, a discharge circuit, flexible switching switches 1-k, a charging switch, and a discharging switch. The connections are as follows: the outputs of the solar array are connected to the corresponding shunt circuit inputs; the outputs of the shunt circuits are selectively connected to either the fully regulated bus or the non-regulated bus via flexible switching switches; the energy storage device is connected to the shunt circuit via a charging switch to achieve charging, and to the discharge circuit via a discharging switch to achieve discharging; the discharge circuit output is connected to the fully regulated bus. The signal transmission is as follows: the drive signals for each switch are generated by the power controller's control logic unit; voltage and current sampling signals are transmitted to the control logic unit for processing via analog signal lines; the control logic unit communicates with the detector's main control system via a digital interface, receiving control commands and uploading status information. A portion of the shunt circuits (m-1) are directly connected to the bus; after meeting the detector's basic power requirements, excess energy is directly shunted. The remaining shunt circuits (n-m+1) are connected to the flexible switching switches to power the detector, and excess energy is directly shunted. If the flexible switching switch contacts switch, and the charging switch is on, the excess energy can be used to charge the energy storage device first. Once the energy storage device is fully charged, the excess energy will be diverted. The energy storage device is a lithium-ion battery pack consisting of individual cells connected in parallel and then in series, and is connected to a discharge switch. When the discharge switch is on, it provides energy to the bus load directly or through the discharge circuit when the solar array's power generation capacity is insufficient or the detector is in a shaded area. The fully adjustable busbar is generally a high-quality busbar with low ripple and strong anti-interference capability, which mainly provides power for important subsystems such as detector integrated electronics, measurement and control, attitude and orbit control, as well as individual units; The non-regulating busbar, whose busbar voltage varies with the battery pack voltage, generally provides energy for subsystems and individual units such as detectors, thermal control heaters, etc., which do not have high requirements for busbar quality. The flexible switching switch is generally a single-pole double-throw mechanical or electronic switch. One end is connected to the shunt circuit, and the other end is connected to the fully adjustable bus and the non-adjustable bus respectively. The number of circuits can be adjusted according to the power demand of the fully adjustable bus and the non-adjustable bus of the detector. This can avoid the efficiency loss of power supply through the discharge circuit when the power demand of the fully adjustable bus increases, and also avoid the shunt waste caused by the power demand of the fully adjustable bus decreases. The flexible switching switch generally adopts a two-set switching method, which can avoid single-point switching failure and further reduce the number of flexible switching switches used, thus achieving optimized design in terms of weight and volume. The flexible switching switch can be switched by remote control commands issued from the ground or by intelligent switching based on the real-time telemetry status of the detector. The aforementioned elastic control can be used to allocate energy flow in various application scenarios, such as the initial stage of interplanetary probe orbiting, the period of decreasing light intensity due to the increasing distance between the probe and the sun, the long period of light intensity during interplanetary cruise, and the period when the probe is orbiting the target celestial body.

[0029] This invention also provides a method for operating an interplanetary transfer probe's power system, comprising the following steps: 1) Calculate the fully regulated bus load power based on the interplanetary transfer probe's requirements for high-quality bus load power. , It is generally the sum of the individual power of the detector's integrated electronics, measurement and control, attitude and orbit control, etc. 2) Calculate the unregulated bus load power based on the interplanetary transfer probe's power requirements for non-high-quality bus loads. , It is generally the sum of the power of individual units such as detectors, thermal controllers, and heaters; 3) Calculate the output power of each array based on the default illumination conditions of the interplanetary transfer probe. ; 4) Determine the parameter value m to ensure the output power of array 1 to array m-1 is... The sum of these values ​​is greater than the total regulating bus load power. And ensure a 5% design margin; 5) Determine the parameter value n so that the sum of the output powers Pm, Pm+1, ..., Pn-1 of array m to array n is greater than the unadjusted bus load power. And ensure a 5% design margin; 6) Flexible switching switches 1~k are used to optimize the distribution of output power from the mth to the nth branch circuit of the shunt circuit. In the default state, flexible switching switches 1~k are connected to the charging switch. The output power from the mth to the nth branch circuit of the shunt circuit is output to the non-regulating bus and the energy storage device, giving priority to meeting the power demand of the non-regulating bus. Excess energy is used to charge the energy storage device. After the energy storage device is fully charged, the excess energy is then shunted. 7) When the lighting conditions of the interplanetary transfer probe change, such as the output power of arrays 1 to m-1... The sum will be less than the load power of the fully regulated bus. By controlling the flexible switching switch 1 via command, subarrays m and m+1 are connected to the fully adjustable bus; if the output power of subarrays 1 to m+1... The sum will still be less than the load power of the fully regulated bus. By controlling the flexible switching switches 2~K one by one via commands, the remaining sub-arrays are connected to the fully adjustable bus until the load power of the fully adjustable bus is met. Excess energy will be diverted; 8) The charging switch and discharge switch of the interplanetary transfer probe are in the ON state by default.

[0030] Those skilled in the art will understand that, in addition to implementing the system, apparatus, and their modules provided by this invention in purely computer-readable program code, the same program can be implemented 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, apparatus, and their modules provided by this invention can be considered a hardware component, and the modules included therein for implementing various programs can also be considered structures within the hardware component; alternatively, modules for implementing various functions can be considered both software programs implementing the method and structures within the hardware component.

[0031] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. An interplanetary transfer probe energy system, characterized by, The application relates to a power generation device, a power transformation device and a power storage device, and a full-regulation bus and an unregulated bus. The power generation device is connected with the input end of a shunt circuit of the power transformation device through a direct-current transmission cable, the output end of the power transformation device is connected with the full-regulation bus and the unregulated bus respectively, the power storage device is bidirectionally connected with the power transformation device through a charge-discharge loop, and the full-regulation bus and the unregulated bus supply power to corresponding loads respectively. The power transformation device comprises a shunt circuit, an elastic switching switch, a charging switch, a discharging switch and a discharging circuit, the output end of the shunt circuit is connected with the elastic switching switch, the charging switch is connected between the shunt circuit and the power storage device, the discharging switch is connected between the power storage device and the unregulated bus, and the discharging circuit is connected between the unregulated bus and the full-regulation bus. The power transformation device is internally provided with a telemetry remote control unit, can receive control instructions of a detector integrated electronic system through a digital signal bus, and can feed back voltage, current and temperature data to the detector integrated electronic system.

2. The interplanetary transfer probe energy system of claim 1, wherein, The power generation device is a three-junction gallium arsenide solar cell circuit, and comprises a plurality of solar cell subarrays which are independently connected with the shunt circuit in the power transformation device through a subarray mode.

3. The interplanetary transfer probe energy system of claim 1, wherein, The subarrays are arranged into power supply subarrays and charging subarrays according to use, wherein the power supply subarrays directly supply power to the detector, and the charging subarrays supply power to the detector and / or charge the power storage device. The power transformation device is an S3R system power controller.

4. The interplanetary transfer probe energy system of claim 1, wherein, The driving signals of the switches are generated by a control logic unit of the power controller, voltage and current sampling signals are transmitted to the control logic unit through analog signal lines for processing, the control logic unit communicates with a detector master control system through a digital interface, receives control commands and uploads state information, a part of the shunt circuit is directly connected with the bus, after the basic power demand of the detector is met, the excess energy is directly shunted, the remaining shunt circuit is connected with the elastic switching switch to supply power to the detector, and the excess energy is directly shunted, if the elastic switching switch is switched, under the condition that the charging switch is turned on, the excess energy charges the power storage device, and after the power storage device is fully charged, the excess energy is shunted.

5. The interplanetary transfer probe energy system of claim 4, wherein, The power storage device is a single-cell-parallel-and-multi-cell-series lithium ion battery pack.

6. The interplanetary transfer probe energy system of claim 1, wherein, The elastic switching switch is a single-pole double-throw mechanical or electronic switch, one end of which is connected with the shunt circuit, and the other end of which is connected with the full-regulation bus and the unregulated bus respectively, and the elastic switching switch is switched through a ground remote control instruction or is switched according to real-time telemetry states of the detector.

7. The interplanetary transfer probe energy system of claim 1, wherein, The full-regulation bus is a preset small-ripple anti-interference high-quality bus, and provides energy for the detector integrated electronic system, the measurement and control system, the attitude and orbit control system and the single machine.

8. The interplanetary transfer probe energy system of claim 1, wherein, The voltage of the unregulated bus changes with the voltage of the battery pack, and the unregulated bus provides energy for the heater of the detector thermal control system and the single machine.

9. The interplanetary transfer probe energy system of claim 1, wherein, The application further discloses a power supply control method.

10. A method of operating an interplanetary transfer probe energy system according to any one of claims 1 to 9, characterized in that, ​ Step 1: Calculate the total regulated bus load power according to the requirement of the interplanetary transfer probe for high-quality bus load power ; Step 2: Calculate the unregulated bus load power based on the power requirement of the interplanetary transfer probe for non-high quality bus loads ; Step 3: Calculate the output power of each subarray according to the default illumination condition of interplanetary transfer probe ; Step 4: Determine parameter value m, such that the sum of the output power of subarray 1 to subarray m-1 is greater than the load power of the fully adjusted bus , and design margin . Step 5: Determine the parameter value n, such that the sum of the output power Pm, Pm+1...Pn-1, Pn of the sub-array m~sub-array n is greater than the unregulated bus load power and design margin; Step 6: The distribution of the output power of the mth shunt circuit and the nth shunt circuit is optimized through the elastic switch; in the default state, the elastic switch is connected to the charging switch, and the output power of the mth shunt circuit and the nth shunt circuit is output to the unregulated bus and the power storage device, the power demand of the unregulated bus is preferentially met, the excess energy is used to charge the power storage device, and after the power storage device is fully charged, the excess energy is shunted; Step 7: When the lighting conditions of the interplanetary transfer probe change, if the output power of array 1 to array m-1... The sum will be less than the load power of the fully regulated bus. By controlling the flexible switching switch via command, subarray m and subarray m+1 are connected to the fully adjustable bus; if the output power of subarray 1 to subarray m+1... The sum will still be less than the load power of the fully regulated bus. By controlling the remaining flexible switching switches one by one through commands, the remaining sub-arrays are connected to the fully adjustable bus until the load power of the fully adjustable bus is met. Excess energy will be diverted.

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