Self-adaptive space energy system

Abstract

The invention discloses a self-adaptive space energy system, and the system comprises a power management unit which controls an electromagnetic induction type wireless charging device, a graphene battery pack or a ground power supply to supply power to a spacecraft through transmitting a power control signal to a power distribution module according to the working mode information transmitted by an external main control computer, charging and discharging of the graphene battery pack are controlled; wake-up control of the graphene battery pack is carried out through a wake-up instruction sent by the wake-up module or an internal timing wake-up signal; detecting a power supply state according to the working state information fed back by the power distribution module; the electromagnetic induction type wireless charging device charges the graphene battery pack in a wireless charging mode; the wake-up module is used for performing signal conversion on the external light wake-up signal, generating a wake-up instruction and sending the wake-up instruction to the power management unit; the power distribution module supplies power to equipment needing power supply; and the working state information is fed back to the power management unit. According to the invention, the reliability problem of a single wake-up mode in a long-time sleep mode is solved.

Description

Technical Field

[0001] The invention relates to an adaptive space energy system, belonging to the technical field of spacecraft energy systems. Background Art

[0002] There is a big temperature difference between lunar day and lunar night (up to 20 days) on the lunar surface. During the lunar night, the temperature can reach as low as -196°C, and electronic equipment needs to use thermal control methods to maintain operation. In addition, spacecraft use hibernation mode in the lunar night environment to save energy.

[0003] It supports the continuous normal operation of the spacecraft during the lunar day for several years, low-power operation in emergency mode, lunar night sleep and lunar day wake-up mode. Since the spacecraft has no solar cell array, it has the ability to supplement the power supply through wireless energy transmission (not less than 500W), and can distribute power to branches as needed. The internally designed energy management unit has functions such as charge and discharge management, battery balancing, information monitoring and real-time transmission, which meets the system's autonomous health monitoring and provides reliability to ensure the smooth completion of various missions of the spacecraft on the lunar surface.

[0004] It mainly involves three technologies: wireless energy transmission, high power density battery and wake-up.

[0005] At present, lithium batteries are widely used in domestic spacecraft (including lunar and Mars probes), but spacecraft still have higher requirements for high energy density, long cycle life, and wide environmental adaptability of batteries. There is an urgent need for battery technology with higher indicators to promote the improvement of the overall performance of spacecraft. Graphene batteries have obvious advantages over existing technologies in energy density, power density, environmental adaptability, cycle life and discharge depth. Foreign graphene batteries are in the stage of space exploration and application, while domestic graphene batteries have started model application in space, leading the world in related fields.

[0006] Wireless energy transmission technologies mainly include: electromagnetic radiation (including microwave radiation, laser radiation), electric field coupling, electromagnetic induction and ultrasonic. Each wireless energy transmission technology has its own advantages, disadvantages and applicable occasions.

[0007] The advantage of microwave radiation is long transmission distance, while the disadvantages are high transmission power, low transmission efficiency, and poor anti-deviation performance. It is suitable for long-distance and high-power occasions with strong electromagnetic radiation. The advantage of laser radiation is long transmission distance, while the disadvantages are high transmission power, low transmission efficiency, and poor anti-deviation performance. It is suitable for long-distance and high-power occasions. The advantage of electric field coupling is no eddy current loss and low coupler cost. The disadvantages are short transmission distance, low transmission power, and high device voltage. It is suitable for short distance and medium power occasions. The advantages of electromagnetic induction are high transmission power, high transmission efficiency, and simple implementation. The disadvantage is short transmission distance. It is suitable for short distance, full power range, and high efficiency requirements. For spatial near-field wireless energy transmission with transmission distance of meters and power of kW, domestic and foreign scholars generally use electromagnetic induction wireless energy transmission.

[0008] Wireless power transmission technology has irreplaceable advantages in unmanned space charging due to its maintenance-free, high spatial fault tolerance and high reliability. Focusing on the research of wireless energy transmission system for lunar robots, it requires high transmission power, high transmission efficiency, simple and reliable system structure, and electromagnetic induction wireless energy transmission technology has the best performance.

[0009] In order to enhance its ability to survive in the harsh lunar environment, the "Yutu-2" rover enters the lunar night sleep mode. Except for the relevant thermal control equipment, all other equipment is powered off and no scientific exploration mission is carried out, waiting for the next lunar day to be awakened by light. The "Yutu-2" rover wakes up in the way of autonomous awakening of the whole device. That is, when the power generation of the solar wing during the next lunar day is greater than the threshold, the light awakening circuit is started, the power controller switch is closed, the battery pack discharge switch is closed, the primary power bus switch is closed, the integrated electronic unit, the X-band transponder and the X-band solid-state amplifier are powered on, and then the +Y side solar wing is autonomously unfolded and moved according to the predetermined logic. Summary of the invention

[0010] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and to provide an adaptive space energy system to achieve periodic replenishment of space energy.

[0011] The technical solution of the present invention is:

[0012] The present invention discloses an adaptive space energy system, comprising: an electromagnetic induction wireless charging device, a graphene battery pack, a power management unit, a power distribution module and a wake-up module; wherein:

[0013] The power management unit controls the electromagnetic induction wireless charging device, the graphene battery pack or the ground power supply to supply power to the spacecraft by sending a power control signal to the power distribution module according to the working mode information sent by the external main control computer, and controls the charging and discharging of the graphene battery pack; performs wake-up control of the graphene battery pack through the wake-up command sent by the wake-up module or the internal timed wake-up signal; and detects the power supply status according to the working status information fed back by the power distribution module;

[0014] An electromagnetic induction wireless charging device charges the graphene battery pack by wireless charging;

[0015] A wake-up module, including a photosensitive circuit and a wireless receiving circuit, performs signal conversion on an external optical wake-up signal obtained by the photosensitive circuit or performs signal conversion on an external wireless wake-up signal obtained by the wireless receiving circuit, generates a wake-up instruction and sends it to the power management unit;

[0016] The power distribution module supplies power to the power-requiring devices according to the power control signal of the power management unit and feeds back the working status information to the power management unit.

[0017] Furthermore, in the above system, when the working mode is the ground test mode, the spacecraft is directly powered by the ground power supply or the charging interface; when the working mode is the device power supply mode, the graphene battery pack is controlled to power the spacecraft, and at the same time, the graphene battery pack is charged by the ground power supply; when the working mode is the lunar surface working mode, the graphene battery pack powers the spacecraft, and at the same time, the external energy storage device charges the graphene battery pack through wireless charging.

[0018] Furthermore, in the above system, the wake-up control is specifically: switching the graphene battery pack from the sleep mode to the normal working mode is achieved by turning on the discharge switch of the graphene battery pack.

[0019] Furthermore, in the above system, the charge and discharge of the graphene battery pack is controlled, specifically: when the working mode is the device supply mode, the power management unit adopts S 3 The R circuit charges the graphene battery pack; when the working mode is the lunar surface working mode, the power management unit charges the graphene battery pack through the electromagnetic induction wireless charging device; when the charging reaches the set value, the charging current is gradually reduced to achieve voltage-limited charging; the power management unit controls the discharge of the graphene battery pack through the discharge switch of the graphene battery pack; the discharge capacity of the discharge path is not less than 5A.

[0020] Furthermore, in the above system, a balancing control circuit is provided for each single cell in the graphene battery pack; when the power management unit detects that the voltage difference between the highest single cell voltage and the lowest single cell voltage in the graphene battery pack reaches a set value, the power management unit sends a balancing instruction, connects the balancing control circuit of the highest single cell voltage, reduces its voltage, and achieves the purpose of balanced charging.

[0021] Furthermore, in the above system, a power distribution circuit is provided at the output end of the graphene battery pack, and the power distribution circuit includes a DCDC module, an input protection circuit, an input filter circuit and an output filter circuit; wherein the output voltage of the single cell in the graphene battery pack passes through the input protection circuit, the input filter circuit, the DCDC module and the output filter circuit to reach the input end of the spacecraft.

[0022] Furthermore, in the above system, the external light wake-up signal acquired by the photosensitive circuit is converted into a signal, specifically:

[0023] A silicon photodiode is used as an excitation source to collect light information. When there is light, the silicon photodiode outputs the light information.

[0024] A three-choose-two circuit is used to perform low-pass filtering on the illumination information; wherein the sampling frequency of the low-pass filter is F = 1 to 2 Hz, and the effective time of the low-pass filter is T = 60s to 180s;

[0025] The low-pass filtered illumination information that meets the voltage amplitude and illumination time is converted into a high-level signal and sent to the power management unit as a wake-up command.

[0026] Furthermore, in the above system, the external wireless wake-up signal acquired by the wireless receiving circuit is converted into a signal, specifically:

[0027] The wake-up module uses a wireless receiving circuit to receive the wireless wake-up command forwarded by the main control computer via the CAN bus;

[0028] The wireless wake-up command is converted into a high-level signal and sent to the power management unit as a wake-up command.

[0029] Furthermore, in the above system, the electromagnetic induction wireless charging device includes a wireless energy supply end and a wireless energy receiving end; wherein the wireless energy supply end includes an inverter, a first compensation topology and a primary coil; the wireless energy receiving end includes a second compensation topology, a secondary coil, a rectifier and a power converter; the input voltage reaches the primary coil through the inverter and the first compensation topology to generate an electromagnetic field; the electromagnetic field reaches the output end after passing through the secondary coil, the rectifier, the second compensation topology and the power converter;

[0030] The inverter uses a high-frequency full-bridge inverter to convert the DC input bus voltage at the energy supply end into high-frequency AC power;

[0031] The first compensation topology and the second compensation topology both adopt LCC / S compensation topology to compensate for reactive power in the wireless power transmission system;

[0032] Both the primary coil and the secondary coil use four layers of coils connected in parallel;

[0033] Rectifier, used to convert AC voltage to DC voltage;

[0034] The power converter adopts a step-down conversion circuit to keep the DC voltage constant.

[0035] The beneficial effects of the present invention and the prior art are:

[0036] (1) The present invention provides a high-power density battery for long-term operation in a large temperature difference environment on the lunar surface. Compared with traditional batteries, the battery is lighter in weight.

[0037] (2) The present invention adopts multiple backup modes to solve the reliability problem of a single wake-up mode in a long-term sleep mode.

[0038] (3) Under the premise of no solar wings, the present invention proposes an adaptive design method for magnetic induction wireless energy transmission to achieve periodic replenishment of space energy.

[0039] (4) Compared with traditional lithium-ion batteries, the graphene supercapacitor battery cells of the present invention have higher power density, wider operating temperature range, and greater discharge depth. They are easier to lighten in the large temperature difference environment on the lunar surface and under long-term working requirements.

[0040] (5) The operating temperature range of the graphene supercapacitor battery of the present invention is -30°C to 70°C, while the normal operating temperature range of the lithium battery is 0°C to 60°C, which is more suitable as a power source in the large temperature difference environment on the surface of the moon. The supercapacitor battery can be repeatedly charged and discharged for hundreds of thousands of times, and the discharge depth can reach 98%, which is much greater than that of chemical batteries, and has an ultra-long service life.

[0041] (6) The present invention can adapt to multiple working and power consumption demand modes, and adopts multiple backup modes to improve the reliability of switching. The BMS switches the power distribution circuit according to different power supply requirements, and improves the reliability of moon-day wake-up through three backup modes: light wake-up, timed wake-up and wireless module wake-up.

[0042] (7) The wireless energy transmission method constructed by the method of the present invention has the effects of high power transmission, simple control, small voltage fluctuation, high efficiency and high reliability. The DC input bus voltage is converted into high-frequency AC by a high-frequency full-bridge inverter, and the LCC / S compensation topology is used to ensure high-precision voltage output. The energy is transferred to the secondary side through the electromagnetic field of the four-layer parallel coil. This solution is easy to implement, simple to control, and has a high power utilization rate. It is suitable for larger power occasions.

[0043] (8) The present invention adopts a loosely coupled transformer, i.e., a primary-secondary coil, and four layers of coils in parallel to transfer electrical energy from the primary to the secondary. Compared with the traditional single-layer coil, this solution has a higher transmission capacity than the traditional single-layer coil and a higher power density. At the same time, the series compensation capacitor of the coil adopts segmented parallel compensation, which further improves the efficiency of the loosely coupled transformer and can suppress uneven current problems and harmonic components.

[0044] (9) The present invention uses parallel coils to reduce the voltage stress of the compensation device and coil by about 10 times, thereby improving the overall system efficiency. The rectifier uses a C filter rectifier to convert the AC voltage into a DC voltage, thereby supplying energy to the DC load. The power converter uses a Buck converter, which can adjust the duty cycle of the switch tube drive signal through voltage information feedback, thereby keeping the output DC voltage constant. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 It is a block diagram of the composition of the adaptive energy system of the present invention;

[0046] Figure 2 It is a block diagram of the BMS CPU module of the present invention;

[0047] Figure 3 It is a block diagram of the design principle of the charging interface of the present invention;

[0048] Figure 4 It is a block diagram of the discharge path principle of the present invention;

[0049] Figure 5 It is a block diagram of the equalization control principle of the battery pack of the present invention;

[0050] Figure 6 It is the +28V power conversion circuit diagram of the present invention;

[0051] Figure 7 It is a principle block diagram of the simulation adopted by the present invention;

[0052] Figure 8 It is the principle diagram of the photosensitive circuit of the present invention;

[0053] Fig. 9 It is a block diagram of the electromagnetic induction wireless charging device of the present invention. DETAILED DESCRIPTION

[0054] The present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0055] like Figure 1 As shown, the present invention discloses an adaptive space energy system, including: an electromagnetic induction wireless charging device, a graphene battery pack, a power management unit, a power distribution module and a wake-up module; wherein,

[0056] The power management unit controls the electromagnetic induction wireless charging device, the graphene battery pack or the ground power supply to supply power to the spacecraft by sending a power control signal to the power distribution module according to the working mode information sent by the external main control computer, and controls the charging and discharging of the graphene battery pack; performs wake-up control of the graphene battery pack through the wake-up command sent by the wake-up module or the internal timed wake-up signal; and detects the power supply status according to the working status information fed back by the power distribution module;

[0057] An electromagnetic induction wireless charging device charges the graphene battery pack by wireless charging;

[0058] A wake-up module, including a photosensitive circuit and a wireless receiving circuit, performs signal conversion on an external optical wake-up signal obtained by the photosensitive circuit or performs signal conversion on an external wireless wake-up signal obtained by the wireless receiving circuit, generates a wake-up instruction and sends it to the power management unit;

[0059] The power distribution module supplies power to the power-requiring devices according to the power control signal of the power management unit and feeds back the working status information to the power management unit.

[0060] Preferably, when the working mode is the ground test mode, the spacecraft is directly powered by the ground power supply or the charging interface; when the working mode is the device power supply mode, the graphene battery pack is controlled to power the spacecraft, and at the same time, the graphene battery pack is charged by the ground power supply; when the working mode is the lunar surface working mode, the graphene battery pack powers the spacecraft, and at the same time, the external energy storage device charges the graphene battery pack through wireless charging.

[0061] Preferably, the wake-up control is specifically: switching the graphene battery pack from the sleep mode to the normal working mode is achieved by turning on the discharge switch of the graphene battery pack.

[0062] Preferably, the charge and discharge of the graphene battery pack is controlled, specifically: when the working mode is the device supply mode, the power management unit adopts S 3The R circuit charges the graphene battery pack; when the working mode is the lunar surface working mode, the power management unit charges the graphene battery pack through the electromagnetic induction wireless charging device; when the charging reaches the set value, the charging current is gradually reduced to achieve voltage-limited charging; the power management unit controls the discharge of the graphene battery pack through the discharge switch of the graphene battery pack; the discharge capacity of the discharge path is not less than 5A.

[0063] Preferably, each single cell in the graphene battery pack is provided with a balancing control circuit; when the power management unit detects that the voltage difference between the highest single cell voltage and the lowest single cell voltage in the graphene battery pack reaches a set value, the power management unit sends a balancing instruction, connects the balancing control circuit of the highest single cell voltage, reduces its voltage, and achieves the purpose of balanced charging.

[0064] Preferably, the balancing control circuit includes a MOS tube switch, a bypass resistor, a battery cell and a comparator voltage sampling circuit; wherein, during the charging process, the battery cell voltage is sampled, and when balancing is allowed and the voltage difference between the cells is greater than a set value, the MOS tube switch is turned on, and the charging current is reduced through the bypass resistor, and the maximum bypass current is 50mA.

[0065] Preferably, a power distribution circuit is provided at the output end of the graphene battery pack, and the power distribution circuit includes a DCDC module, an input protection circuit, an input filter circuit and an output filter circuit; wherein the output voltage of the single cell in the graphene battery pack reaches the input end of the spacecraft through the input protection circuit, the input filter circuit, the DCDC module and the output filter circuit.

[0066] Preferably, the external light wake-up signal acquired by the photosensitive circuit is converted into a signal, specifically:

[0067] A silicon photodiode is used as an excitation source to collect light information. When there is light, the silicon photodiode outputs the light information.

[0068] A three-choose-two circuit is used to perform low-pass filtering on the illumination information; wherein the sampling frequency of the low-pass filter is F = 1 to 2 Hz, and the effective time of the low-pass filter is T = 60s to 180s;

[0069] The low-pass filtered illumination information that meets the voltage amplitude and illumination time is converted into a high-level signal and sent to the power management unit as a wake-up command.

[0070] Preferably, the external wireless wake-up signal acquired by the wireless receiving circuit is converted into a signal, specifically:

[0071] The wake-up module uses a wireless receiving circuit to receive the wireless wake-up command forwarded by the main control computer via the CAN bus;

[0072] The wireless wake-up command is converted into a high-level signal and sent to the power management unit as a wake-up command.

[0073] Preferably, the electromagnetic induction wireless charging device comprises a wireless energy supply end and a wireless energy receiving end; wherein the wireless energy supply end comprises an inverter, a first compensation topology and a primary coil; the wireless energy receiving end comprises a second compensation topology, a secondary coil, a rectifier and a power converter; the input voltage reaches the primary coil through the inverter and the first compensation topology to generate an electromagnetic field; the electromagnetic field reaches the output end after passing through the secondary coil, the rectifier, the second compensation topology and the power converter;

[0074] The inverter uses a high-frequency full-bridge inverter to convert the DC input bus voltage at the energy supply end into high-frequency AC power;

[0075] The first compensation topology and the second compensation topology both adopt LCC / S compensation topology to compensate for reactive power in the wireless power transmission system;

[0076] Both the primary coil and the secondary coil use four layers of coils connected in parallel;

[0077] Rectifier, used to convert AC voltage to DC voltage;

[0078] The power converter adopts a step-down conversion circuit to keep the DC voltage constant.

[0079] Example

[0080] The adaptive space energy system provided in this embodiment is mainly composed of an electromagnetic induction wireless charging device, a graphene battery pack, a power management unit, a power distribution module and a wake-up module.

[0081] The power management unit (BMS) is responsible for power charging and discharging control. During ground testing, the ground supply test mode directly powers the spacecraft through the ground power / charging interface; the device supply mode powers the spacecraft through the graphene battery pack and charges the graphene battery through the ground power supply. During lunar surface work, the graphene battery pack powers the spacecraft, and other energy storage devices supplement the graphene battery pack with electricity through wireless charging. The electromagnetic induction wireless charging device is the implementation device of this method.

[0082] BMS receives the main control computer command through the CAN bus to realize the on-off control of the power distribution branch; it receives external commands through the wireless receiving circuit to realize the on-off control of the power distribution branch by remote control;

[0083] BMS controls the internal charging and discharging circuits to achieve the charging and discharging management function of the adaptive energy system.

[0084] The wake-up module and the internal timing circuit of the BMS realize the switching from the sleep mode to the normal working mode by turning on the discharge switch, among which the wireless wake-up has the highest priority.

[0085] The power distribution module directly outputs to the equipment that needs power supply, and the BMS controls whether to output, and at the same time feeds back its own status information to the BMS.

[0086] (1) BMS solution design

[0087] 1) CPU core circuit

[0088] BMS is based on CPU and equipped with necessary peripheral circuits to realize battery sampling, analog quantity acquisition, level command control, and dual-channel high-speed dual-redundant communication functions. It completes data acquisition and processing internally and transmits data with the spacecraft via the high-speed dual-redundant CAN bus, reducing the number of connecting cables between BMS and other spacecraft equipment. Figure 2 shown.

[0089] The CPU uses a microcontroller chip with rich internal functions, including ADC module, IO interface, support for CAN2.0 B controller, UART controller, and a maximum speed of 25MIPS.

[0090] The analog measurement parameters are mainly current and voltage, which are converted into standard voltage values ​​for output. The current conversion circuit samples the current through the sampling resistor, and amplifies it into a standard voltage conversion value through the analog circuit; the voltage conversion circuit divides the voltage through the resistor, and then converts it into a standard voltage conversion value for output through the analog circuit. The voltage range is 0~5V, and the remote control command is powered by 12V and is divided into OC command (command width 160ms) and level command (normally high or normally low).

[0091] The watchdog reset chip uses an external watchdog chip to monitor the CPU status.

[0092] like Figure 2 Analog quantity measurement uses analog switches for channel selection, and a 16-to-1 analog switch chip is selected, which has the characteristics of low on-resistance, low off-leakage current and internal address decoding. At the same time, within the normal input signal range, the on-resistance can be relatively stable.

[0093] The OC instruction and level instruction driver chip conforms to the standard TTL, with the highest withstand voltage value up to 95V, large current collection, wide application range, sufficient aerospace verification, effective electrical isolation, and pulse width instruction or level instruction through program control.

[0094] The CAN driver chip supply voltage is +3.3V, which can directly match the CPU internal CAN controller voltage.

[0095] 2) BMS main peripheral circuit

[0096] Charging design: For unregulated busbars, the S3R circuit is responsible for realizing the battery charging function. The charging adopts the voltage-limited charging mode. When charging reaches the final charging voltage, the charging current is gradually reduced to realize voltage-limited charging. Figure 3 shown.

[0097] Discharge design: The system is designed to be unregulated during discharge. The battery pack directly outputs energy to the back end without power regulation and conversion in the middle, achieving the highest efficiency of discharge. The battery is designed with an independent discharge switch. The discharge capacity of the battery discharge path is not less than 5A. The discharge MOS tube adopts a parallel design and adopts Class I derating. Figure 4 shown.

[0098] Balance function design: In order to balance the voltage between cells, balance control is adopted. When the voltage difference between the highest cell voltage and the lowest cell voltage reaches the set value, the balance command will connect the cell balance control circuit with higher cell voltage to reduce its voltage and achieve the purpose of balanced charging. Figure 5 shown.

[0099] Power distribution design: The DCDC module realizes the conversion of the secondary power supply of the spacecraft and is equipped with corresponding protection circuits and filtering circuits to ensure the quality of the power supply and the reliability of the circuit operation. Figure 6 shown.

[0100] Analog quantity sampling: Voltage measurement outputs 0~4.5V analog quantity after impedance transformation; current telemetry uses sampling resistor as sensor, and outputs 0~4.5V analog quantity after impedance transformation; temperature and switch (including expansion indication and travel switch) telemetry outputs 0~5V analog quantity after pulling up 5V power supply. Figure 7 shown.

[0101] Command control: It can receive external OC commands or level pulse signals from the internal CPU through the IO port to control components such as relays. The maximum withstand voltage of the command driver chip is 95V, with internal electrical isolation, and pulse width commands or level commands can be realized through program control.

[0102] (2) Construction of the lunar day wake-up plan

[0103] 1) Light wake-up circuit

[0104] The light wake-up circuit uses a photosensor as the circuit input, and a three-choice-two voting circuit to input the IO of the BMS system, which is then filtered internally and transferred to the CPU.

[0105] The three-choose-two circuit is a logic circuit design used to vote among three input signals. If at least two input signals are the same, the output signal will depend on this same signal. A silicon photodiode is used as an excitation source to collect light information. When there is light, the silicon photodiode outputs a 40V voltage; when there is no light, it outputs a 0V voltage. A three-choose-two circuit is used to filter the light information, with a sampling frequency of F=1Hz, and a low-pass filter effective time of T=120s, that is, the wake-up mode is switched after 2 minutes of light exposure, which improves the robustness of obtaining light information and reduces the impact of noise. Figure 8 shown.

[0106] 2) Wireless wake-up

[0107] In sleep mode, the BMS CPU waits for ground or other wireless wake-up commands forwarded by the main control computer via the CAN bus. When the wireless wake-up command arrives, the power system forces the discharge switch to open and power on the entire spacecraft equipment. This wake-up command channel has the highest authority.

[0108] 3) Scheduled wake-up

[0109] The CPU in the BMS pre-binds the moon-night timing instructions obtained by the spacecraft main control system from the ground station in the CPU, establishes a timer interrupt, and counts and accumulates in multiple crystal timers. Set up timing accumulation status monitoring, and when the timing accumulation reaches the threshold, the power system is forced to wake up according to the control program.

[0110] (3) Wireless charging device design

[0111] The electromagnetic induction wireless charging device includes the construction of a wireless energy transmitting end (primary side) and a wireless energy receiving end (secondary side). The wireless energy transmitting end (primary side) mainly includes an inverter, a compensation topology, and a primary coil. The wireless energy receiving end (secondary side) mainly includes a compensation topology, a secondary coil, a rectifier, and a power converter. Fig. 9 shown.

[0112] The inverter uses a high-frequency full-bridge inverter to convert the DC input bus voltage at the energy supply end into high-frequency AC power, and then transfer the energy to the secondary side through the electromagnetic field. The compensation topology adopts the LCC / S compensation topology to compensate for the reactive power in the wireless power transmission system and ensure constant voltage output. The primary and secondary coils use four layers of coils in parallel to transfer electrical energy from the primary side to the secondary side. The rectifier converts the AC voltage into DC voltage to power the DC load. The power converter uses a Buck converter, which can adjust the duty cycle of the drive signal of the switch tube through voltage information feedback, thereby keeping the output DC voltage constant.

[0113] Although the content of the present invention has been described in detail through the above preferred embodiments, it should be appreciated that the above description should not be considered as a limitation of the present invention. After reading the above content, it will be apparent to those skilled in the art that various modifications and substitutions of the present invention will occur. Therefore, the protection scope of the present invention should be limited by the appended claims.

[0114] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. An adaptive space energy system, characterized in that: include: Electromagnetic induction wireless charging device, graphene battery pack, power management unit, power distribution module and wake-up module; wherein, The power management unit controls the electromagnetic induction wireless charging device, the graphene battery pack or the ground power supply to supply power to the spacecraft by sending a power control signal to the power distribution module according to the working mode information sent by the external main control computer, and controls the charging and discharging of the graphene battery pack; performs wake-up control of the graphene battery pack through the wake-up command sent by the wake-up module or the internal timed wake-up signal; and detects the power supply status according to the working status information fed back by the power distribution module; An electromagnetic induction wireless charging device charges the graphene battery pack by wireless charging; A wake-up module, including a photosensitive circuit and a wireless receiving circuit, performs signal conversion on an external optical wake-up signal obtained by the photosensitive circuit or performs signal conversion on an external wireless wake-up signal obtained by the wireless receiving circuit, generates a wake-up instruction and sends it to the power management unit; The power distribution module supplies power to the power-requiring devices according to the power control signal of the power management unit and feeds back the working status information to the power management unit.

2. The adaptive space energy system according to claim 1, characterized in that: When the working mode is the ground test mode, the spacecraft is directly powered by the ground power supply or charging interface; when the working mode is the device power supply mode, the graphene battery pack is controlled to power the spacecraft, and the graphene battery pack is charged by the ground power supply at the same time; when the working mode is the lunar surface working mode, the graphene battery pack powers the spacecraft, and the external energy storage device charges the graphene battery pack through wireless charging.

3. The adaptive space energy system according to claim 1, characterized in that: The wake-up control is specifically: switching the graphene battery pack from the sleep mode to the normal working mode is achieved by turning on the discharge switch of the graphene battery pack.

4. The adaptive space energy system according to claim 2, characterized in that: The charge and discharge of the graphene battery pack is controlled. Specifically, when the working mode is the device supply mode, the power management unit uses S 3 The R circuit charges the graphene battery pack; when the working mode is the lunar surface working mode, the power management unit charges the graphene battery pack through the electromagnetic induction wireless charging device; when the charging reaches the set value, the charging current is gradually reduced to achieve voltage-limited charging; the power management unit controls the discharge of the graphene battery pack through the discharge switch of the graphene battery pack; the discharge capacity of the discharge path is not less than 5A.

5. The adaptive space energy system according to claim 1, characterized in that: Each single cell in the graphene battery pack is provided with a balancing control circuit; when the power management unit detects that the voltage difference between the highest single cell voltage and the lowest single cell voltage in the graphene battery pack reaches a set value, the power management unit sends a balancing instruction to connect the balancing control circuit of the highest single cell voltage to reduce its voltage and achieve the purpose of balanced charging.

6. The adaptive space energy system according to claim 1, characterized in that: A power distribution circuit is provided at the output end of the graphene battery pack, and the power distribution circuit includes a DCDC module, an input protection circuit, an input filter circuit and an output filter circuit; wherein the output voltage of the single cell in the graphene battery pack reaches the input end of the spacecraft through the input protection circuit, the input filter circuit, the DCDC module and the output filter circuit.

7. The adaptive space energy system according to claim 1, characterized in that: The external light wake-up signal obtained by the photosensitive circuit is converted into a signal, specifically: A silicon photodiode is used as an excitation source to collect light information. When there is light, the silicon photodiode outputs the light information. A three-choose-two circuit is used to perform low-pass filtering on the illumination information; wherein the sampling frequency of the low-pass filter is F = 1 to 2 Hz, and the effective time of the low-pass filter is T = 60s to 180s; The low-pass filtered illumination information that meets the voltage amplitude and illumination time is converted into a high-level signal and sent to the power management unit as a wake-up command.

8. The adaptive space energy system according to claim 1, characterized in that: The external wireless wake-up signal obtained by the wireless receiving circuit is converted into a signal, specifically: The wake-up module uses a wireless receiving circuit to receive the wireless wake-up command forwarded by the main control computer via the CAN bus; The wireless wake-up command is converted into a high-level signal and sent to the power management unit as a wake-up command.

9. The adaptive space energy system according to claim 1, characterized in that: The electromagnetic induction wireless charging device comprises a wireless energy supply end and a wireless energy receiving end; wherein the wireless energy supply end comprises an inverter, a first compensation topology and a primary coil; the wireless energy receiving end comprises a second compensation topology, a secondary coil, a rectifier and a power converter; the input voltage reaches the primary coil through the inverter and the first compensation topology to generate an electromagnetic field; the electromagnetic field reaches the output end after passing through the secondary coil, the rectifier, the second compensation topology and the power converter; The inverter uses a high-frequency full-bridge inverter to convert the DC input bus voltage at the energy supply end into high-frequency AC power; The first compensation topology and the second compensation topology both adopt LCC / S compensation topology to compensate for reactive power in the wireless power transmission system; Both the primary coil and the secondary coil use four layers of coils connected in parallel; Rectifier, used to convert AC voltage to DC voltage; The power converter adopts a step-down conversion circuit to keep the DC voltage constant.

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