Mother-child satellite wireless energy and information synchronous transmission system and control method

Abstract

The invention discloses a master-slave satellite wireless energy and information synchronous transmission system and a control method, the master-slave satellite wireless energy and information synchronous transmission system comprises a master satellite power supply system and a slave satellite power supply system, and the master satellite power supply system and the slave satellite power supply system are connected through an energy and information synchronous transmission channel. According to the method, the energy profit and loss state of the mother satellite and the energy profit and loss state of the child satellite in the wireless transmission information flow are used as input criteria, existence and magnitude of wireless transmission power between the two satellites are decided by adopting a digital closed-loop feedback algorithm, peak-load shifting type dynamic balance supply between energy of the mother satellite and energy of the child satellite is realized, and energy transmission between the mother satellite and the child satellite is realized. The reliability and safety of power supply between the mother satellite and the child satellite and the accuracy of information transmission are improved.

Description

Technical Field

[0001] The present invention relates to the fields of satellite power supply and distribution and control, and satellite inter-satellite energy and information transmission technology, and in particular to a mother-child satellite wireless energy and information synchronous transmission system and a control method. Background Art

[0002] The mother and child satellites carry different payloads respectively. When flying in orbit, the two satellites can dock and separate freely to independently perform different in-orbit tasks, such as in-orbit fuel filling and space particle sampling. This can adapt to the diversified characteristics of current spacecraft in-orbit tasks and become one of the hot directions of spacecraft. Figure 1 Shown is a schematic diagram of the traditional mother-child satellite power system architecture, which includes two parts: the mother satellite power system and the child satellite power system. Both of them use the topology of solar array power generation and battery group energy storage.

[0003] At present, the parent and child satellites in orbit are connected by power cables and information cables. Generally speaking, the parent satellite has a large power generation capacity, while the child satellite is short of energy due to transportation restrictions. When the child satellite is short of energy, such as when the solar array has not yet been deployed and cannot generate electricity at the beginning of the satellite launch, or when the attitude changes during the mission in the orbital stage cause the solar array of the child satellite to be blocked by light and the power generation capacity decreases, the power supply system of the parent satellite can not only supply power to the mother satellite's own power units, but also turn on the power switch to supply power to the power units of the child satellite through the power switch and power supply cable. Intersatellite information cables generally use buses such as 1553B and CAN, which are used to transmit information such as the health status of each satellite unit and circuit between the two satellites. This system solves the energy and information interaction between the two satellites in the form of a wired power cable, but has the following disadvantages:

[0004] (1) The intelligence level is low, and the orderly autonomous control of the local energy and remote energy of the sub-satellite cannot be achieved. The energy utilization rate is low and the system failure is prone to occur. The interaction of the two satellite energies is achieved by turning the power switch on and off. When the power switch of the mother satellite is connected, the mother satellite can supply power to the sub-satellite; when the power switch is disconnected, the bus cannot supply power to the sub-satellite. The sub-satellite cannot make an autonomous and real-time decision on whether to draw energy from the remote mother satellite to supply power to it based on the local energy shortage and the remote mother satellite energy shortage, resulting in unnecessary energy waste. More importantly, excessive energy extraction may cause insufficient energy for the mother satellite, resulting in a system-level failure mode where both local and remote energy are insufficient.

[0005] (2) The reliability of wired power cables is low and the failure rate is high. When the two satellites are relatively displaced, the connecting cables between the mother satellite and the satellite may be accidentally pulled by external forces and damaged. In addition, since the power supply cables are exposed outside the cabin for a long time, they are easily affected by space charged electron radiation, etc., which causes the insulation strength of the cable surface insulation sheet to decrease, affecting the power supply safety.

[0006] (3) Safety issues such as sparks are prone to occur during the in-orbit assembly of the satellite. When the satellite is performing a mission in the outer space orbit, there are different working conditions between the two satellites, such as "merge" and "separation". During this process, the power receiving plug and the power transmission socket at the end of the power supply cable need to be frequently plugged and unplugged, and the plugging and unplugging operation is unattended throughout the process. Although the power supply switch can be turned off before plugging and unplugging to prevent live operation, the pinholes in the power receiving plug and the power transmission socket may be damaged or misaligned due to the limited plugging and unplugging accuracy of the robotic arm. When the power switch is turned on again, sparks or even short circuits may occur. At the very least, the power supply path between the mother and the satellite is damaged, and the energy transmission between the two satellites cannot be realized again. At worst, it affects the power supply safety of the mother satellite, causing the mother satellite to fail and cause huge economic losses.

[0007] Some studies have proposed using wireless energy transmission to replace power cables and wireless communications such as Wifi or Zigbee to replace wired buses, as shown in the attached Figure 2 As shown in FIG. 1 , two independent wireless transmission channels for information and energy are used to transmit information flow and energy flow respectively between the two satellites. Although this can solve the above problems (2) and (3), it still has the disadvantages of low intelligence level as mentioned in (1). In addition, the following disadvantages limit its application in spacecraft:

[0008] (1) Information and energy use independent transmission channels, and their operating frequencies, signal amplitudes, etc. are inconsistent. When the energy transmission power between the two satellites is very high, the electromagnetic radiation of the energy transmission power transformer is serious, and its multiple harmonics will be superimposed on the effective signal of the information transmission channel, resulting in a high bit error rate of information transmission and even transmission interruption. Therefore, it is not suitable for medium and high power transmission occasions;

[0009] (2) The space environment is relatively harsh due to on-orbit radiation and single particles. Wireless communication methods such as Wifi or Zigbee currently have no aerospace-grade device solutions, making it difficult to achieve high-reliability and long-life applications. Summary of the invention

[0010] The main purpose of the present invention is to propose a mother-child satellite wireless energy and information synchronous transmission system and control method, aiming to improve the reliability, safety of power supply and accuracy of information transmission between the mother and child satellites.

[0011] To achieve the above objectives, the present invention provides a mother-satellite wireless energy and information synchronous transmission system, including a mother satellite power system and a sub-satellite power system, wherein the mother satellite power system and the sub-satellite power system are connected via an energy and information synchronous transmission channel.

[0012] A further technical solution of the present invention is that the mother satellite power supply system includes a mother satellite power supply controller PPCU, a solar array PSAW, a mother satellite battery PBAT, a mother satellite power unit and a primary coil, and the mother satellite power supply controller PPCU includes a wireless primary power supply conversion module PPC, a mother satellite telemetry and remote control module PTMTC and a signal demodulation circuit;

[0013] The mother star controller PPCU is responsible for coordinating the power balance of the mother star solar array PSAW, the mother star battery PBAT, and the mother star power unit, and generating a fully regulated bus Vr; the mother star telemetry and remote control module PTMTC is used to collect the mother star's own working status, the mother star's energy profit and loss status, and the sub-satellite wireless transmission information output by the signal demodulation circuit, and control the power on and off status of each power module through remote control commands;

[0014] The power input end of the wireless primary power supply conversion module PPC is connected to the fully regulated busbar Vr, the power output end and the signal output end are respectively connected to the primary coil and the signal demodulation circuit, and the output end of the signal demodulation circuit is connected to the mother satellite telemetry and remote control module PTMTC;

[0015] The sub-satellite power supply system includes a sub-satellite power supply controller CPCU, a solar array CSAW, a sub-satellite battery CBAT, a sub-satellite power unit and a secondary coil. The sub-satellite power supply controller CPCU includes a wireless secondary power supply conversion module SPC, i bus adapters CBCR, a sub-satellite telemetry and remote control module CTMTC and a signal modulation circuit;

[0016] The sub-satellite power controller CPCU is responsible for coordinating the operation of the solar array CSAW, the sub-satellite battery CBAT, the bus adapter CBCR, and the sub-satellite power unit, and generating an unregulated bus Vu; the sub-satellite telemetry and remote control module CTMTC is responsible for collecting the sub-satellite's own power module working status CTM, the sub-satellite energy profit and loss status, converting the relevant information into a high-frequency digital signal and outputting it to the signal modulation circuit to generate a high-frequency AC information signal, and is responsible for controlling the power on and off status of each power module through the remote control command CTC;

[0017] The power input end of the wireless secondary power supply conversion module SPC is connected to the secondary coil, and the power output end is connected to the bus adapter CBCR. The signal input end of the wireless secondary power supply conversion module SPC is connected to the sub-satellite telemetry and remote control module CTMTC through the signal modulation circuit; the bus adapter CBCR takes the output voltage Vspc of the wireless secondary power supply conversion module SPC as input and converts it into the voltage required by the unregulated bus Vu;

[0018] The energy and information synchronous transmission channel includes the mother satellite telemetry and remote control module PTMTC, a signal demodulation circuit, a wireless primary power supply conversion module PPC, a primary coil, a daughter satellite telemetry and remote control module CTMTC, a signal modulation circuit, a wireless secondary power supply conversion module SPC and the secondary coil; the primary coil and the secondary coil transmit an AC mixed signal in an LC resonance manner, and the AC mixed signal includes an AC energy signal and an AC information signal, wherein the information signal uses the energy signal as a carrier signal.

[0019] A further technical solution of the present invention is that the wireless primary power supply conversion module PPC includes an energy inverter circuit, a primary energy compensation network and an information extraction circuit. The energy inverter circuit inverts the stable DC full-regulated bus Vr to generate an AC energy signal, which is connected to the primary coil through the primary energy compensation network and the inductor of the information extraction circuit. The switching frequency fs and duty cycle Dppc of the AC energy signal are both set by the mother satellite telemetry and remote control module PTMTC; the AC mixed signal transmitted by the primary coil is loaded with the high-frequency AC information signal transmitted by the secondary coil, and the information extraction circuit extracts the effective components of the high-frequency AC signal using the LC resonance principle and restores the energy profit and loss status information transmitted therein after being processed by the signal demodulation circuit, and finally sends it to the mother satellite telemetry and remote control module PTMTC for collection.

[0020] A further technical solution of the present invention is that the wireless secondary power supply conversion module SPC includes a secondary compensation network, an information loading circuit and an energy rectification circuit. The AC energy signal transmitted by the secondary coil is connected to the energy rectification circuit through the secondary compensation network and the inductor of the information loading circuit. After rectification and filtering, a stable DC voltage Vspc is generated and sent to the unregulated bus Vu through the bus adapter CBCR to realize the transmission of energy between satellites; the amplitude of Vspc is determined by the switching frequency fs and the duty cycle Dppc of the wireless primary power supply conversion module PPC, and the high-frequency AC information signal generated by the sub-satellite telemetry and remote control module CTMTC and the signal modulation circuit is injected into the AC energy signal through the high-frequency resonance of the information loading circuit LC to form an AC mixed signal, which is transmitted to the wireless primary power supply conversion module PPC of the mother satellite through coil coupling.

[0021] A further technical solution of the present invention is that the primary coil is installed on the surface of the mother star, the secondary coil is installed on the surface of the daughter star, and the installation surfaces of the primary coil and the secondary coil are adjacent surfaces of the mother star and the daughter star.

[0022] A further technical solution of the present invention is that both the primary coil and the secondary coil include a high magnetic permeability magnetic core, a winding conductor and a shell support device.

[0023] A further technical solution of the present invention is that the mother star power controller PPCU also includes i solar array power regulators PAPR, i battery chargers PBCR, i battery dischargers PBDR and a bus error amplifier MEA, the power input end of the solar array power regulator PAPR is connected to the mother star solar array PSAW, and the power output end is connected to the full regulation bus Vr, the power input end of the battery charger PBCR is connected to the full regulation bus Vr, and the power output end is connected to the mother star battery PBAT, the power input end of the battery discharger PBDR is connected to the mother star battery PBAT, and the power output end is connected to the full regulation bus Vr.

[0024] A further technical solution of the present invention is that the sub-satellite power controller CPCU also includes n solar array power regulators CAPR, a battery power interface unit BCI and a battery charging manager BCM;

[0025] The power input end of the solar array power regulator CAPR is connected to the sub-satellite solar array CSAW, and the power output end is connected to the unregulated bus Vu. The power input end of the battery power interface unit BCI is connected to the unregulated bus Vu, and the power output end is connected to the sub-satellite battery CBAT.

[0026] A further technical solution of the present invention is that the battery charging manager BCM adopts a dual-stage control mode of a local power supply segment and a local remote combined power supply segment, and internally contains two closed-loop PID control loops. The first PID control loop is a remote energy control loop, and the output signal Vbcmrmt controls the output current Icbcr of the bus adapter CBCR; the second PID loop is called a local energy control loop, and the output signal Vbcmlocal controls the output current Icapr of the solar array power regulator CAPR.

[0027] To achieve the above object, the present invention also proposes a control method for a mother-child satellite wireless energy and information synchronous transmission system, the method comprising the following steps:

[0028] The energy profit and loss status of the mother star and the satellite is collected through the mother star remote control module PTMTC;

[0029] According to the energy surplus and deficit status of the mother star and the sub-star, the switching frequency fs and the duty cycle Dppc of the wireless primary power supply conversion module PPC are adjusted to control the working mode of the inter-satellite energy and information transmission synchronous transmission channel. The working mode includes the inter-satellite normal energy transmission mode and the inter-satellite standby energy transmission mode. The inter-satellite normal energy transmission mode includes the sub-satellite local power supply section and the sub-satellite local remote joint power supply section.

[0030] The beneficial effects of the mother-child satellite wireless energy and information synchronous transmission system of the present invention are:

[0031] The present invention adopts the design of the primary and secondary coils in conjunction with the primary and secondary wireless power conversion module, modulation and demodulation and telemetry remote control module in the power supply system of the mother and child satellites, and utilizes the principle of near-field electromagnetic LC resonance coupling induction. Through the method of signal loading and extraction, the non-contact intersatellite energy and information synchronous transmission is realized, the intersatellite cable is omitted, and the satellite "combination" and "separation" are convenient. It has the characteristics of being simple and reliable, flexible in combination, high in safety, and strong in anti-interference ability, and solves the problems of low safety of on-orbit plugging and unplugging of intersatellite wired cables, high bit error rate of existing wireless transmission technology, and inability to realize aerospace engineering. The combination of PTMTC digital software closed-loop feedback control and sub-satellite "BCM two-stage control" is adopted, so that the mother and child satellites give priority to using local energy. When the mother star has surplus energy and the sub-satellite lacks energy, the energy transmission between the mother star and the sub-satellite is started, and the "peak shaving and valley filling" type dynamic balance supply between the energy of the mother and child satellites is realized, thereby improving the energy utilization rate and autonomous management capability.

[0032] In the mother-subsatellite power system architecture of wireless energy transmission, by introducing PTMTC digital closed-loop control and the "BCM two-stage control" method of the subsatellite charger manager, it is possible to independently determine the energy shortage of the two satellites and decide whether to carry out energy transfer between the two satellites. Since there are many links in inter-satellite energy transmission, its transmission efficiency is lower than that of the local power system. In order to improve energy utilization, when the subsatellite energy is relatively abundant, the subsatellite internal power system is preferred to independently provide the energy it needs; when the busbar energy is surplus and the subsatellite energy is scarce, and the local energy cannot meet the use requirements, the wireless energy transmission device is autonomously enabled to dispatch the remote mother satellite power system to replenish energy, thus realizing the orderly control of local energy and remote energy. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0034] Figure 1 This is a schematic diagram of the traditional energy and information connection relationship between mother and child satellites;

[0035] Figure 2 It is a schematic diagram of the improved relationship between wireless transmission of energy and information between mother and child satellites;

[0036] Figure 3 It is a structural schematic diagram of the mother-child satellite wireless energy and information synchronous transmission system of the present invention;

[0037] Figure 4 This is the PPC diagram of the wireless primary power conversion module;

[0038] Figure 5 This is the SPC diagram of the wireless secondary power supply conversion module;

[0039] Figure 6 The design block diagram of the battery charging manager BCM proposed in the present invention;

[0040] Figure 7 This is a schematic diagram of the dual-loop two-stage control proposed by the present invention;

[0041] Figure 8 This is a diagram of the power topology architecture used by the bus adapter CBCR in the present invention.

[0042] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0043] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0044] The present invention proposes a wireless energy and information synchronous transmission system for mother-child satellites. On the basis of the traditional mother-child satellite power system architecture, the primary coil and the secondary coil are used to replace the power receiving plug, the power transmission socket and the power supply cable, and the wireless primary power supply conversion module PPC is used to replace the power supply switch. The signal modulation, signal demodulation and other circuits are configured to merge the inter-satellite information flow and the power flow. The information flow uses the power flow as the carrier signal, and the wireless synchronous transmission of power and information is realized through the resonant coupling between the primary coil and the secondary coil, eliminating the inter-satellite power supply and information cables, and improving the reliability and safety of the power supply and the accuracy of information transmission. The control method of synchronous transmission of wireless energy and information between mother and child satellites is that the mother satellite telemetry and remote control module PTMTC takes the mother satellite energy profit and loss state and the child satellite energy profit and loss state in the wireless transmission information flow as input criteria, and adopts a digital closed-loop feedback algorithm to decide whether there is a wireless transmission power between the two satellites and the size, so as to realize the "peak shaving and valley filling" type dynamic balance supply between the mother and child satellite energy; the child satellite is equipped with a hardware battery charging manager BCM, which adopts a two-stage control method to autonomously control the orderly use of local energy and remote wireless transmission energy according to the demand and supply of local energy; the effect of the joint control of the two is that both satellites give priority to the use of local energy, and when the mother satellite energy is surplus and the child satellite energy is scarce, the wireless energy transmission device is autonomously enabled to realize the energy transmission between the mother satellite and the child satellite.

[0045] For details, please refer to Figure 3 The mother-sub-satellite wireless energy and information synchronous transmission system of the present invention includes a mother-satellite power supply system and a sub-satellite power supply system, and the mother-satellite power supply system and the sub-satellite power supply system are connected through an energy and information synchronous transmission channel.

[0046] Among them, the mother satellite power supply system includes a mother satellite power supply controller PPCU, a solar array PSAW, a mother satellite battery PBAT, a mother satellite power unit and a primary coil. The mother satellite power supply controller PPCU includes a wireless primary power supply conversion module PPC, a mother satellite telemetry and remote control module PTMTC and a signal demodulation circuit.

[0047] The mother star controller PPCU is responsible for coordinating the power balance of the mother star solar array PSAW, the mother star battery PBAT, and the mother star power unit, and generating a fully regulated bus Vr. The mother star telemetry and remote control module PTMTC is used to collect the mother star's own working state PTM, the mother star's energy profit and loss state, and the sub-satellite wireless transmission information output by the signal demodulation circuit (including the sub-satellite energy profit and loss state, voltage, current, and working state of each module), and control the power on and off state of each power module through remote control commands. The built-in digital control software autonomously controls the working mode of the inter-satellite energy and information transmission synchronous transmission channel.

[0048] The power input end of the wireless primary power supply conversion module PPC in the mother star power controller PPCU is connected to the fully regulated bus Vr, the power output end and the signal output end are respectively connected to the primary coil and the signal demodulation circuit, and the output end of the signal demodulation circuit is connected to the mother star telemetry and remote control module PTMTC.

[0049] The sub-satellite power supply system includes a sub-satellite power supply controller CPCU, a solar array CSAW, a sub-satellite battery CBAT, a sub-satellite power unit and a secondary coil. The sub-satellite power supply controller CPCU includes a wireless secondary power supply conversion module SPC, k bus adapters CBCR, a sub-satellite telemetry and remote control module CTMTC and a signal modulation circuit.

[0050] The sub-satellite power controller CPCU is responsible for coordinating the operation of the solar array CSAW, the sub-satellite battery CBAT, the bus adapter CBCR, and the sub-satellite power unit, and generating the unregulated bus Vu. The sub-satellite telemetry and remote control module CTMTC is responsible for collecting the sub-satellite's own power module working status CTM, the sub-satellite energy profit and loss status, converting the relevant information into a high-frequency digital signal and outputting it to the signal modulation circuit to generate a high-frequency AC information signal, and is responsible for controlling the power on and off status of each power module through the remote control command CTC.

[0051] The power input end of the wireless secondary power supply conversion module SPC is connected to the secondary coil, and the power output end is connected to the bus adapter CBCR. The signal input end of the wireless secondary power supply conversion module SPC is connected to the satellite telemetry and remote control module CTMTC through the signal modulation circuit; the bus adapter CBCR has an input undervoltage protection function, and uses the output voltage Vspc of the wireless secondary power supply conversion module SPC as input to convert it into the voltage required by the unregulated bus Vu.

[0052] The energy and information synchronous transmission channel includes the mother satellite telemetry and remote control module PTMTC, a signal demodulation circuit, a wireless primary power supply conversion module PPC, a primary coil, a sub-satellite telemetry and remote control module CTMTC, a signal modulation circuit, a wireless secondary power supply conversion module SPC and the secondary coil, which transmits the energy of the mother satellite to the sub-satellite, and at the same time transmits information such as the working status and energy profit and loss status of the sub-satellite to the mother satellite.

[0053] In order to improve the wireless transmission distance and energy transmission efficiency, the primary coil and the secondary coil transmit an AC mixed signal in an LC resonance mode. The AC mixed signal includes an AC energy signal and an AC information signal, wherein the information signal uses the energy signal as a carrier signal.

[0054] The wireless primary power supply conversion module PPC includes an energy inverter circuit, a primary energy compensation network and an information extraction circuit. The energy inverter circuit inverts the stable DC full-regulated bus Vr to generate an AC energy signal, which is connected to the primary coil through the primary energy compensation network and the inductor of the information extraction circuit. The switching frequency fs and duty cycle Dppc of the AC energy signal are both set by the mother satellite telemetry and remote control module PTMTC; the AC mixed signal transmitted by the primary coil is loaded with the high-frequency AC information signal transmitted by the secondary coil, and the information extraction circuit extracts the effective components of the high-frequency AC signal using the LC resonance principle and restores the energy profit and loss status and other information transmitted therein after being processed by the signal demodulation circuit, and finally sends it to the mother satellite telemetry and remote control module PTMTC for collection.

[0055] The wireless secondary power supply conversion module SPC includes a secondary compensation network, an information loading circuit and an energy rectification circuit. The AC energy signal transmitted by the secondary coil is connected to the energy rectification circuit through the secondary compensation network and the inductor of the information loading circuit. After rectification and filtering, a stable DC voltage Vspc is generated and sent to the unregulated bus Vu through the bus adapter CBCR to realize the transmission of energy between satellites; the amplitude of Vspc is determined by the switching frequency fs and the duty cycle Dppc of the wireless primary power supply conversion module PPC. The high-frequency AC information signal generated by the sub-satellite telemetry and remote control module CTMTC and the signal modulation circuit is injected into the AC energy signal through the high-frequency resonance of the information loading circuit LC to form an AC mixed signal, which is transmitted to the wireless primary power supply conversion module PPC of the mother satellite through coil coupling.

[0056] The primary coil and the secondary coil both include a high-permeability magnetic core, a winding conductor, and a shell support device. The primary coil is installed on the surface of the mother star body, and the secondary coil is installed on the surface of the daughter star body, and the installation surfaces of the primary coil and the secondary coil are adjacent surfaces of the mother star and the daughter star. When the mother star and the daughter star are "merged", the primary coil and the secondary coil are placed in parallel and the spacing is controlled within the design range, so as to realize the synchronous transmission of energy and information between the mother star and the daughter star; when the mother star and the daughter star are separated, the primary coil and the secondary coil are far apart, and an effective closed electromagnetic path cannot be formed, and the energy and information transmission path is blocked.

[0057] The mother star power controller PPCU also includes i solar array power regulators PAPR, i battery chargers PBCR, i battery dischargers PBDR and a bus error amplifier MEA. The power input end of the solar array power regulator PAPR is connected to the mother star solar array PSAW, and the power output end is connected to the full-regulation bus Vr. The power input end of the battery charger PBCR is connected to the full-regulation bus Vr, and the power output end is connected to the mother star battery PBAT. The power input end of the battery discharger PBDR is connected to the mother star battery PBAT, and the power output end is connected to the full-regulation bus Vr.

[0058] The satellite power controller CPCU also includes n solar array power regulators CAPR, a battery power interface unit BCI and a battery charging manager BCM.

[0059] The power input end of the solar array power regulator CAPR is connected to the sub-satellite solar array CSAW, and the power output end is connected to the unregulated bus Vu. The power input end of the battery power interface unit BCI is connected to the unregulated bus Vu, and the power output end is connected to the sub-satellite battery CBAT.

[0060] The working principle of the wireless energy and information synchronous transmission system of the mother-child satellite of the present invention is that the mother satellite telemetry and remote control module PTMTC collects the mother satellite energy profit and loss state and the sub-satellite energy profit and loss state, and adjusts the switching frequency fs and duty cycle Dppc of the wireless primary power supply conversion module PPC through internal software closed-loop calculation, thereby controlling the working mode of the inter-satellite energy and information transmission synchronous transmission channel. Its control logic is: when it is detected that the mother satellite energy is surplus (the state is 1), the Vspc voltage is autonomously increased to meet the power conversion demand of the bus adapter CBCR. At this time, the inter-satellite energy enters the normal energy transmission mode, and the actual transmission power size is determined by the bus adapter CBCR power usage; when it is detected that the mother satellite energy is scarce (the state is 0), Vspc is autonomously lowered, the bus adapter CBCR input is undervoltage and power conversion cannot be started, the mother satellite energy cannot be transmitted to the sub-satellite bus, and the inter-satellite energy enters the standby energy transmission mode. In this mode, in order to ensure the normal transmission of the inter-satellite information flow, there is still an extremely low AC energy signal transmitted between the wireless primary power supply conversion module PPC and the wireless secondary power supply conversion module SPC to provide the necessary carrier signal.

[0061] The battery charging manager BCM adopts a dual-stage control mode of a local power supply segment and a local remote joint power supply segment, and contains two closed-loop PID control loops. The first PID control loop is a remote energy control loop, and the output signal Vbcmrmt controls the output current Icbcr of the bus adapter CBCR; the second PID loop is called a local energy control loop, and the output signal Vbcmlocal controls the output current Icapr of the solar array power regulator CAPR. A certain dead zone interval is left between the control thresholds of the two loops. Vbcmrmt and Vbcmlocal represent the profit and loss status of the sub-satellite energy.

[0062] When the satellite energy is sufficient (state is 1), Vbcmlocal controls the solar array power regulator CAPR to output current to the unregulated bus Vu, and Vbcmrmt controls the bus adapter CBCR not to output current to the unregulated bus Vu. At this time, the satellite energy is basically generated by the local power supply system without the help of the mother satellite, so this section is called the "local power supply section"; when the mother satellite has surplus energy (state is 1) and the satellite energy is insufficient (state is 0), Vbcmlocal controls the solar array power regulator CAPR to output current to the unregulated bus Vu. Current, Vbcmrmt controls the bus adapter CBCR to draw energy from the wireless secondary power supply conversion module SPC to output current to the unregulated bus Vu. At this time, the energy of the sub-satellite is jointly generated by the local power supply system and the remote mother satellite. This section is called the "local remote joint power supply section"; when the mother satellite is short of energy, the mother satellite telemetry and remote control module PTMTC controls the inter-satellite energy to work in the standby energy transmission mode. Regardless of whether the sub-satellite is short of energy or not, the bus adapter CBCR module does not output current to the unregulated bus Vu due to input undervoltage, and the sub-satellite works in the local power supply section. In summary, the orderly control of local energy and remote energy is achieved.

[0063] The following combination Figures 3 to 8 The working principle of the mother-child satellite wireless energy and information synchronous transmission system of the present invention is further elaborated in detail.

[0064] The mother-child satellite wireless energy and information synchronous transmission system of the present invention comprises two parts: a mother satellite power supply system and a child satellite power supply system.

[0065] The mother star power supply system includes the mother star solar array PSAW, the mother star battery PBAT, the mother star power controller PPCU, the mother star power unit and the primary coil, etc. The mother star power controller PPCU includes m solar array power regulators PAPR, i battery chargers PBCR, i battery dischargers PBDR, bus error amplifier MEA, wireless primary power supply conversion module PPC, mother star telemetry and remote control module PTMTC, and signal demodulation circuit. The power input end of the solar array power regulator PAPR is connected to the mother star solar array PSAW, and the power output end is connected to the fully regulated bus Vr. The power input end of the battery charger PBCR is connected to the fully regulated bus Vr, and the power output end is connected to the mother star battery PBAT. The power input end of the battery discharger PBDR is connected to the mother star battery PBAT, and the power output end is connected to the fully regulated bus Vr. The mother star adopts a fully regulated bus architecture. The bus error amplifier MEA samples the fully regulated bus Vr voltage and uses a PID closed-loop output signal Vmea internally to achieve stable control of the fully regulated bus Vr. The solar cell power regulator PAPR, battery charger PBCR, and battery discharger PBDR in the coordinated power controller PPCU work in an orderly manner to adjust the power balance of the mother star solar array PSAW power generation, single-machine power consumption, and mother star battery PBAT power storage. The bus voltage Vr amplitude can be determined according to the power of the single-machine power consumption. Generally, 100V is required for power consumption above 5KW, and 42V is required for power consumption below 5KW. The signal ends of the solar array power regulator PAPR, battery charger PBCR, battery discharger PBDR, bus error amplifier MEA, signal demodulation circuit, and wireless primary power supply conversion module PPC are all connected to the mother satellite telemetry and remote control module PTMTC. The mother satellite telemetry and remote control module PTMTC is the control core of inter-satellite energy and information transmission, which is used to realize the collection of the working status PTM of each power module of the mother satellite, the profit and loss status of the mother satellite energy, the output information collection of the signal demodulation circuit, the issuance of remote control instructions PTC, and the autonomous control of the working mode of the inter-satellite energy and information transmission synchronous transmission channel.

[0066] The sub-satellite power supply system includes the sub-satellite solar array CSAW, the sub-satellite battery CBAT, the sub-satellite power controller CPCU, the sub-satellite power unit and the secondary coil. The sub-satellite power controller CPCU includes n solar array power regulators CAPR, battery power interface unit BCI, battery charging manager BCM, wireless secondary power supply conversion module SPC, k bus adapters CBCR, signal modulation circuit and sub-satellite telemetry and remote control module CTMTC. The sub-satellite adopts an unregulated bus architecture, that is, the bus voltage is equal to the voltage of the sub-satellite battery CBAT. Generally, the sub-satellite power consumption is low. At the same time, to ensure the safe operation of the battery, Vu can be selected from 36V~45V or 23V~29V. The power input end of the solar array power regulator CAPR is connected to the sub-satellite solar array CSAW, and the power output end is connected to the unregulated bus Vu. The power input end of the battery power interface unit BCI is connected to the unregulated bus Vu, and the power output end is connected to the sub-satellite battery CBAT. The unregulated bus Vu is also connected to the sub-satellite power units 1~I to power them. The secondary coil is connected to the wireless secondary power supply conversion module SPC, and the bus adapter CBCR uses the output voltage Vspc of the wireless secondary power supply conversion module SPC as input to convert it into the voltage required by the unregulated bus Vu. The bus adapter CBCR has an input voltage undervoltage protection function. When the Vspc voltage is low, the module does not work and cannot supply power to the unregulated bus; when the Vspc voltage is high, the power conversion is started, and the conversion power size is controlled by the battery charging manager BCM. The sub-satellite telemetry and remote control module CTMTC is connected to the solar array power regulator CAPR, the battery power interface unit BCI, the bus adapter CBCR, the battery charging manager BCM, and the signal end of the signal modulation circuit. It is used to realize the working status of each power module of the sub-satellite, the collection of the sub-satellite energy profit and loss status, and the issuance of the remote control command CTC, and is responsible for framing the sub-satellite related information stream and transmitting it to the signal modulation circuit to generate a high-frequency AC information signal.

[0067] The wireless primary power supply conversion module PPC, primary coil, mother satellite telemetry and remote control module PTMTC, signal demodulation circuit in the mother satellite power system and the secondary coil, wireless secondary power supply conversion module SPC, mother satellite adapter CBCR, signal modulation circuit, and sub-satellite telemetry and remote control module CTMTC in the sub-satellite power system together constitute a wireless energy and information transmission channel, which is responsible for realizing the interaction of energy flow and information flow between the mother and sub-satellites. The direction of energy transmission is from the mother satellite to the sub-satellite, and the direction of information transmission is from the sub-satellite to the mother satellite. Among them, the wireless primary power supply conversion module PPC, primary coil, secondary coil and wireless secondary power supply conversion module SPC together constitute a high-power DCDC converter to realize the power conversion of the mother satellite fully regulated bus Vr and the sub-satellite Vspc. The primary coil and the secondary coil are equivalent to a transformer. Since the transformer can only transmit AC voltage, the wireless primary power supply conversion module PPC is responsible for inverting the input fully regulated bus Vr to generate an AC energy signal, as shown in the attached figure. Figure 4 As shown, the switch tubes Q1 to Q4 are power switches, forming a full-bridge topology, which are controlled by a digital controller and a driver to periodically open and close at a certain frequency. When the switch tubes Q1 and Q4 are turned on, the switch tubes Q2 and Q3 are turned off, and the bridge arm output is positive at the top and negative at the bottom, and the output voltage is equal to +Vr; when the switch tubes Q1 and Q4 are turned off, the switch tubes Q2 and Q3 are turned on, and the bridge arm output voltage is negative at the top and positive at the bottom, and the output voltage is equal to -Vr. The inductor L1, the capacitor C1 and the capacitor C2 form a resonant compensation network for stabilizing the converter gain; the inductor L21 of the information extraction circuit is connected between the primary energy compensation network and the primary coil, and the high-frequency resonance principle of the inductor L22 and the capacitor C3 is used to extract the high-frequency AC information signal from the AC mixed signal transmitted by the primary coil, and send it to the demodulation circuit to restore it to an effective information signal for collection by the mother satellite telemetry and remote control module PTMTC. The mixed signal of AC energy and information is transmitted between the primary coil and the secondary coil, and is output to the energy rectifier circuit in the wireless secondary power supply conversion module SPC after being rectified by the secondary compensation network and the information loading circuit, and then outputs the DC voltage Vspc. Figure 5 As shown; the secondary compensation network and the primary compensation network are used together to stabilize the gain of the entire converter; the information loading circuit uses the high-frequency resonance principle of inductor L32 and capacitor C5 to load the high-frequency information signal output by the modulation circuit into the AC energy signal to form an AC mixed signal. The energy rectifier circuit adopts a full-bridge rectifier form. When the bridge arm voltage is positive at the top and negative at the bottom, the rectifier diodes D1 and D4 are turned on, and the rectifier diodes D2 and D3 are turned off; when the bridge arm voltage is negative at the top and positive at the bottom, the rectifier diodes D2 and D3 are turned on, and the rectifier diodes D1 and D4 are turned off. After smoothing and filtering by capacitor C1, the output DC voltage Vspc is obtained. The relationship between Vspc and the input voltage Vr can be expressed as:

[0068] Vspc=α*Vr (Formula 1)

[0069] αα is a preset coefficient, which is related to the turns ratio of the primary coil and the secondary coil, the duty cycle Dppc of Q1~Q4 in PPC, the switching frequency fs, the LC resonant frequency of the primary and secondary compensation network, etc. The Q value can be set by adjusting Dppc and fs in the software of the PTMTC digital controller of the mother satellite telemetry and remote control module.

[0070] Both the primary coil and the secondary coil are composed of a high permeability magnetic core, winding wires and a shell support device. The primary coil is installed on the surface of the mother satellite, and the secondary coil is installed on the surface of the daughter satellite. The coil installation surface is the adjacent surface of the two satellites. When the mother and daughter satellites are "combined", the two coils are placed in parallel and the spacing is controlled within the design range. The energy transfer path is as follows (the solid line is a cable connection, and the dotted line is a cable-free connection):

[0071] Fully regulated busbar → PPC → primary coil → secondary coil → SPC → Vspc

[0072] After the mother satellite's fully regulated bus is inverted by PPC, the output AC signal is coupled to the sub-satellite's secondary coil through the primary coil in a near-field electromagnetic coupling manner, and then rectified by the sub-satellite to form a DC voltage Vspc, realizing the energy transmission between the two satellites; when the mother and sub-satellites are separated, the primary coil and the secondary coil are far apart, and an effective closed electromagnetic path cannot be formed, and the energy transfer path is blocked. This "cableless" non-contact energy transmission method simplifies the interconnection between the two satellites and improves the safety of power supply.

[0073] The information transmission path is as follows (solid lines represent cable connections, and dotted lines represent non-cable connections):

[0074] CTMTC→Signal modulation→SPC→Secondary coil→Primary coil→PPC→Signal demodulation→PTMTC

[0075] The sub-satellite telemetry and remote control module CTMTC will output the sub-satellite energy profit and loss status, bus voltage, bus current, health status of each power module and other information in digital form, and generate a high-frequency AC information signal after modulation by the signal modulation circuit. The high-frequency resonant coupling of the information loading circuit in the wireless secondary power supply conversion module SPC is injected into the secondary coil to form an AC mixed signal, which is wirelessly transmitted to the primary coil. The effective high-frequency AC information signal is taken out by the information extraction circuit of the wireless primary power supply conversion module PPC, and is restored to effective information by the demodulation circuit and transmitted to the mother satellite telemetry and remote control module PTMTC.

[0076] The bus adapter CBCR is used to convert the Vspc output by the wireless secondary power conversion module SPC into a variable unregulated bus voltage, as shown in the attached Figure 8 As shown, it adopts Buck-Boost topology internally. When the voltage Vspc meets the SPC working threshold requirements of the wireless secondary power supply conversion module, the output voltage and current are controlled by controlling the duty cycle of the four internal switch tubes Q1~Q4. The bus adapter CBCR outputs power to the unregulated bus and transmits the energy transmitted by the secondary coil to the unregulated bus Vu. The bus adapter CBCR has an input undervoltage protection function. When the voltage Vspc is low and cannot meet the SPC working threshold requirements of the wireless secondary power supply conversion module, the bus adapter CBCR outputs power to the unregulated bus to 0. At this time, even if there is energy transmission between the primary coil and the secondary coil, it will not be transmitted to the unregulated bus Vu.

[0077] The working status of the bus adapter CBCR and the solar array power regulator CAPR are uniformly controlled by the battery charging manager BCM, as shown in the attached Figure 6As shown, the battery charging manager BCM includes two closed-loop PID control loops: a remote energy control loop and a local energy control loop. The remote energy control loop is composed of a proportional op amp A1 and an error op amp A2, and the local energy control loop is composed of a proportional op amp A3 and an error op amp A4. The conversion ratios of the proportional op amp A1 and the proportional op amp A3 are divided into K1 and K2. The inverting terminals of the error op amp A2 and the error op amp A4 are both connected to the reference voltage Vref, and the non-inverting terminals are respectively connected to the outputs of the proportional op amp A1 and the proportional op amp A3. The remote charging termination voltage threshold is defined as VL, and the local charging termination voltage threshold is defined as VH, where

[0078] VL=Vref / K1 (Formula 2)

[0079] VH=Vref / K2 (Formula 3)

[0080] The output signal of the error amplifier A2 is Vbcmrmt, which is sent to the mother star adapter CBCR to control the duty cycle of the mother star adapter CBCR switch tube, thereby realizing the control of the output current Icbcr. The relationship between Icbcr and Vbcmrmt is characterized as follows:

[0081] I cbcr =max[I Hcbcr -β*V bcmrmt ,0] (Formula 4)

[0082] Icbcr is inversely proportional to Vbcmrmt. The maximum value of Icbcr is IHcbcr, which is limited by the selection of power devices in the mother star adapter CBCR. The minimum value of Icbcr is 0.

[0083] The output signal of the error amplifier A4 is Vbcmlocal, which is sent to the solar array power regulator CAPR module to control the output current Icapr of the solar array power regulator CAPR. The relationship between Icapr and VbcmIocal is characterized as follows:

[0084] I capr =max[I Hcapr -δ*V bcmlocal ,0] (Formula 5)

[0085] Icapr is inversely proportional to Vbcmlocal. The maximum value of Icapr is IHcapr, which is limited by the selection of power devices in the solar array power regulator CAPR. The minimum value of Icapr is 0. Vbcmrmt and Vbcmlocal can jointly characterize the local energy profit and loss state of the satellite.

[0086] The following is combined with Figure 6 , Attachment Figure 7, Appendix 1 introduces the control principle of orderly output of local energy and remote energy, divides the inter-satellite energy transmission mode between the mother and child satellites into two types, and divides the child satellite working mode into two working sections.

[0087] 1. Normal energy transmission mode between satellites

[0088] The mother satellite telemetry and remote control module PTMTC collects the mother satellite energy surplus and deficit status and the sub-satellite energy surplus and deficit status transmitted by the information wireless transmission channel, and performs closed-loop control through the digital control software: when the mother satellite energy surplus state (state is 1) is collected, the switching frequency fs and duty cycle Dppc are adjusted autonomously so that α in formula 1 takes the normal value αn. According to formula 1, the Vsp amplitude is αn*Vr. This voltage amplitude is relatively high and can meet the power conversion requirements of the bus adapter CBCR. At this time, the inter-satellite energy enters the normal energy transmission mode, and the actual transmission power is determined by the bus adapter CBCR using power, as follows:

[0089] (1) Sub-satellite local power supply section

[0090] When the satellite energy is sufficient or low in deficiency, the battery pack does not discharge or discharges less, and the battery pack voltage is high. At this time, the battery voltage is between the remote charging termination voltage threshold VL and the local charging termination voltage threshold VH, that is, VL<Vcbat<VH;

[0091] The voltage at the in-phase terminal of the error amplifier A2 is VA2+ = Vcabat*K1 (Formula 6)

[0092] Substituting Equation 2 into Equation 6:

[0093] VA2+=Vcabat*K1>VL*K1=Vref (Formula 7)

[0094] The voltage at the inverting terminal of error amplifier A2 is VA2-=Vref (Formula 8)

[0095] Since VA2+>VA2-, the amplification factor of A2 can be regarded as infinite, so its output is the highest level, equal to its supply voltage Vcc, that is:

[0096] VA2out=Vbcmrmt=max[H(VA2)*(VA2+-VA2-),0]=Vcc (Formula 9)

[0097] Where H(VA2) is the transfer function of op amp A2;

[0098] Substituting Equation 9 into Equation 4:

[0099] I cbcr =max[I Hcbcr -β*Vcc,0]=0 (Formula 10)

[0100] The voltage at the in-phase terminal of the error amplifier A4 is VA4+ = Vcbat*K2 (Formula 11)

[0101] Substituting Equation 3 into Equation 11:

[0102] VA4+=Vcbat*K2<VH*K2=Vref (Formula 12)

[0103] The voltage at the inverting terminal of error amplifier A4 is VA4-=Vref (Formula 13)

[0104] Since VA4+<VA4-, the output of A4 is the lowest level equal to 0, that is:

[0105] VA4out=Vbcmlocal=max[H(VA4)*(VA4+-VA4-), 0]=0 (Formula 14)

[0106] Where H(VA4) is the transfer function of op amp A4;

[0107] Substituting Equation 14 into Equation 6:

[0108] I capr =max[I Hcapr -δ*0,0]=I Hcapr (Formula 15)

[0109] That is, in the local power supply section, the bus adapter CBCR outputs a current Icbcr of 0 to the unregulated bus Vu, and the solar array power regulator CAPR's maximum current IHcapr supplies power to the unregulated bus and charges the sub-satellite battery CBAT. At this time, the sub-satellite energy is generated by the local power supply system without the help of the mother satellite.

[0110] As the voltage of the satellite battery CBAT gradually increases, it will gradually approach the charge termination voltage threshold VH, that is,

[0111] Vcbat-VH=ε (Formula 16)

[0112] Where ε is a value that is infinitely close to 0;

[0113] Combining Formula 3, Formula 11, and Formula 16:

[0114] VA4out=Vbcmlocal=max[H(VA4)*(VA4+-VA4-),0]

[0115] =max[H(VA4)*(Vcbat*K2-Vref), 0]

[0116] =max[H(VA4)*(Vcbat*K2-VH*K2), 0]

[0117] =H(VA4)*K2*ε (Formula 17)

[0118] Substituting Equation 17 into Equation 5

[0119] I capr =max[I Hcapr -δ*H(V A4 )*K2*ε,0]=I Hcapr -δ*H(V A4 )*K2*ε

[0120] (Formula 18)

[0121] That is, the error amplifier A4 enters the closed-loop feedback state. According to the closed-loop feedback principle, the voltage difference between the in-phase terminal and the inverting terminal is amplified, the amplitude of Vbcmlocal gradually increases from 0, the output current Icapr of the solar array power regulator CAPR gradually decreases, and the charging mode of the satellite battery CBAT changes from the high-current charging mode to the trickle charging mode. The charging current gradually decreases, and the voltage of the satellite battery CBAT finally maintains at VH and no longer increases. The energy of the satellite power system is in a surplus state, but there will not be too much energy flowing to the satellite battery CBAT to ensure the safety of the satellite battery CBAT and prevent overcharging.

[0122] (2) Sub-satellite local remote joint power supply section

[0123] When the sub-satellite energy is insufficient or the deficiency is high, the sub-satellite battery CBAT discharges a large amount and the sub-satellite battery CBAT voltage is low. At this time, the battery voltage is lower than the remote charging termination voltage threshold VL and the local charging termination voltage threshold VH, that is, Vcbat<VL<VH;

[0124] Combining Formula 2, Formula 6, and Formula 8, we get:

[0125] VA2+=Vcabat*K1<VL*K1=Vref=VA2- (Formula 19)

[0126] Since VA2+<VA2-, the error amplifier A2 gain can be regarded as infinite, so its output is the lowest level 0, that is:

[0127] VA2out=Vbcmrmt=max[H(VA2)*(VA2+-VA2-),0]=0 (Formula 20)

[0128] Where H(VA2) is the transfer function of the error amplifier A2;

[0129] Substituting Equation 20 into Equation 4:

[0130] I cbcr =max[I Hcbcr -β*0,0]=I Hcbcr (Formula 21)

[0131] The voltage at the non-inverting terminal of the error amplifier A4 is also lower than the voltage at the inverting terminal. The calculation process is the same as that of the local power supply stage. Referring to formulas 11 to 15, it can be seen that Vbcmlocal is 0.

[0132] I capr =max[I Hcapr -δ*0,0]=I Hcapr (Formula 22)

[0133] According to the calculation results of Formula 21 and Formula 22, in the local remote joint power supply section, the bus adapter CBCR draws energy from the secondary coil, and supplies power to the unregulated bus and charges the battery pack with the maximum current IHcbcr. At this time, the energy of the sub-satellite is jointly provided by the local power supply system and the mother satellite, and the energy transmission power between the mother and sub-satellites is relatively large.

[0134] 2. Intersatellite standby energy transmission mode

[0135] When the mother star is short of energy, if the mother star is forced to transfer energy to the daughter star, the degree of energy shortage of the mother star will be aggravated. In severe cases, it will lead to energy imbalance and cause serious faults such as satellite power failure. To prevent this fault from happening, the PTMTC digital control software design logic is as follows:

[0136] When the mother star energy is scarce (state is 0), the switching frequency fs and duty cycle Dppc are adjusted to make the value of α in formula 1 lower, αL (αL<<αn). According to formula 1, the amplitude of Vspc is αL*Vr, which cannot meet the power conversion requirements of the mother star adapter CBCR. At this time, the two satellites work in the inter-satellite energy standby energy transmission mode, and the actual transmission power is basically 0, but there is still information flow transmission. When αL is 0, there will be no AC energy signal transmission between the primary coil and the secondary coil, and the signal carrier cannot be provided for the AC information signal, which will cause the information flow transmission to be interrupted. Therefore, αL should be greater than 0. In the standby energy transmission mode, the mother star adapter CBCR will not output energy to the unregulated bus Vu, and can only rely on the sub-satellite local solar array power regulator CAPR to supply power to the unregulated bus and charge the battery pack. At this time, the sub-satellite works in the local power supply section, and the energy is generated by the local power supply system, which will not consume the mother star energy, ensuring the safety of the power supply of the two satellites.

[0137] Schedule 1

[0138]

[0139] Appendix 1 is a schematic diagram of the relationship between the energy supply situation and the system working mode matrix of the mother-child satellite wireless energy and information synchronous transmission system of the present invention.

[0140] The beneficial effects of the mother-child satellite wireless energy and information synchronous transmission system of the present invention are:

[0141] The present invention adopts the design of the primary and secondary coils in conjunction with the primary and secondary wireless power conversion module, modulation and demodulation and telemetry remote control module in the power supply system of the mother and child satellites, and utilizes the principle of near-field electromagnetic LC resonance coupling induction. Through the method of signal loading and extraction, the non-contact intersatellite energy and information synchronous transmission is realized, the intersatellite cable is omitted, and the satellite "combination" and "separation" are convenient. It has the characteristics of being simple and reliable, flexible in combination, high in safety, and strong in anti-interference ability, and solves the problems of low safety of on-orbit plugging and unplugging of intersatellite wired cables, high bit error rate of existing wireless transmission technology, and inability to realize aerospace engineering. The combination of PTMTC digital software closed-loop feedback control and sub-satellite "BCM two-stage control" is adopted, so that the mother and child satellites give priority to using local energy. When the mother star has surplus energy and the sub-satellite lacks energy, the energy transmission between the mother star and the sub-satellite is started, and the "peak shaving and valley filling" type dynamic balance supply between the energy of the mother and child satellites is realized, thereby improving the energy utilization rate and autonomous management capability.

[0142] In the mother-subsatellite power system architecture of wireless energy transmission, by introducing PTMTC digital closed-loop control and the "BCM two-stage control" method of the subsatellite charger manager, it is possible to independently determine the energy shortage of the two satellites and decide whether to carry out energy transfer between the two satellites. Since there are many links in inter-satellite energy transmission, its transmission efficiency is lower than that of the local power system. In order to improve energy utilization, when the subsatellite energy is relatively abundant, the subsatellite internal power system is preferred to independently provide the energy it needs; when the busbar energy is surplus and the subsatellite energy is scarce, and the local energy cannot meet the use requirements, the wireless energy transmission device is autonomously enabled to dispatch the remote mother satellite power system to replenish energy, thus realizing the orderly control of local energy and remote energy.

[0143] To achieve the above object, the present invention also proposes a control method for a mother-child satellite wireless energy and information synchronous transmission system, characterized in that the method comprises the following steps:

[0144] The energy profit and loss status of the mother star and the sub-star is collected through the mother star remote control module PTMTC.

[0145] According to the energy surplus and deficit status of the mother star and the sub-star, the switching frequency fs and the duty cycle Dppc of the wireless primary power supply conversion module PPC are adjusted to control the working mode of the inter-satellite energy and information transmission synchronous transmission channel. The working mode includes the inter-satellite normal energy transmission mode and the inter-satellite standby energy transmission mode. The inter-satellite normal energy transmission mode includes the sub-satellite local power supply section and the sub-satellite local remote joint power supply section.

[0146] The specific working principle of the control method of the mother-child satellite wireless energy and information synchronous transmission system of the present invention can be found in the introduction to the working principle of the above-mentioned mother-child satellite wireless energy and information synchronous transmission system, which will not be repeated here.

[0147] The above description is only a preferred embodiment of the present invention, and does not limit the patent scope of the present invention. All equivalent structural changes made by using the contents of the present invention specification and drawings under the concept of the present invention, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. A mother-child satellite wireless energy and information synchronous transmission system, characterized in that: It comprises a mother satellite power supply system and a sub-satellite power supply system, wherein the mother satellite power supply system and the sub-satellite power supply system are connected via an energy and information synchronous transmission channel.

2. The mother-child satellite wireless energy and information synchronous transmission system according to claim 1 is characterized in that: The mother star power supply system includes a mother star power supply controller PPCU, a solar array PSAW, a mother star battery PBAT, a mother star power unit and a primary coil. The mother star power supply controller PPCU includes a wireless primary power supply conversion module PPC, a mother star telemetry and remote control module PTMTC and a signal demodulation circuit. The mother star controller PPCU is responsible for coordinating the power balance of the mother star solar array PSAW, the mother star battery PBAT, and the mother star power unit, and generating a fully regulated bus Vr; the mother star telemetry and remote control module PTMTC is used to collect the mother star's own working status, the mother star's energy profit and loss status, and the sub-satellite wireless transmission information output by the signal demodulation circuit, and control the power on and off status of each power module through remote control commands; The power input end of the wireless primary power supply conversion module PPC is connected to the fully regulated busbar Vr, the power output end and the signal output end are respectively connected to the primary coil and the signal demodulation circuit, and the output end of the signal demodulation circuit is connected to the mother satellite telemetry and remote control module PTMTC; The sub-satellite power supply system includes a sub-satellite power supply controller CPCU, a solar array CSAW, a sub-satellite battery CBAT, a sub-satellite power unit and a secondary coil. The sub-satellite power supply controller CPCU includes a wireless secondary power supply conversion module SPC, i bus adapters CBCR, a sub-satellite telemetry and remote control module CTMTC and a signal modulation circuit; The sub-satellite power controller CPCU is responsible for coordinating the operation of the solar array CSAW, the sub-satellite battery CBAT, the bus adapter CBCR, and the sub-satellite power unit, and generating an unregulated bus Vu; the sub-satellite telemetry and remote control module CTMTC is responsible for collecting the sub-satellite's own power module working status CTM, the sub-satellite energy profit and loss status, converting the relevant information into a high-frequency digital signal and outputting it to the signal modulation circuit to generate a high-frequency AC information signal, and is responsible for controlling the power on and off status of each power module through the remote control command CTC; The power input end of the wireless secondary power supply conversion module SPC is connected to the secondary coil, and the power output end is connected to the bus adapter CBCR. The signal input end of the wireless secondary power supply conversion module SPC is connected to the sub-satellite telemetry and remote control module CTMTC through the signal modulation circuit; the bus adapter CBCR takes the output voltage Vspc of the wireless secondary power supply conversion module SPC as input and converts it into the voltage required by the unregulated bus Vu; The energy and information synchronous transmission channel includes the mother satellite telemetry and remote control module PTMTC, a signal demodulation circuit, a wireless primary power supply conversion module PPC, a primary coil, a daughter satellite telemetry and remote control module CTMTC, a signal modulation circuit, a wireless secondary power supply conversion module SPC and the secondary coil; the primary coil and the secondary coil transmit an AC mixed signal in an LC resonance manner, and the AC mixed signal includes an AC energy signal and an AC information signal, wherein the information signal uses the energy signal as a carrier signal.

3. The mother-child satellite wireless energy and information synchronous transmission system according to claim 2 is characterized in that: The wireless primary power supply conversion module PPC includes an energy inverter circuit, a primary energy compensation network and an information extraction circuit. The energy inverter circuit inverts the stable DC full-regulated bus Vr to generate an AC energy signal, which is connected to the primary coil through the primary energy compensation network and the inductor of the information extraction circuit. The switching frequency fs and duty cycle Dppc of the AC energy signal are both set by the mother satellite telemetry and remote control module PTMTC; the AC mixed signal transmitted by the primary coil is loaded with the high-frequency AC information signal transmitted by the secondary coil, and the information extraction circuit extracts the effective components of the high-frequency AC signal by using the LC resonance principle and restores the energy profit and loss status information transmitted therein after being processed by the signal demodulation circuit, and finally sends it to the mother satellite telemetry and remote control module PTMTC for collection.

4. The mother-child satellite wireless energy and information synchronous transmission system according to claim 3 is characterized in that: The wireless secondary power supply conversion module SPC includes a secondary compensation network, an information loading circuit and an energy rectification circuit. The AC energy signal transmitted by the secondary coil is connected to the energy rectification circuit through the secondary compensation network and the inductor of the information loading circuit. After rectification and filtering, a stable DC voltage Vspc is generated and sent to the unregulated bus Vu through the bus adapter CBCR to realize the transmission of energy between satellites; the amplitude of Vspc is determined by the switching frequency fs and the duty cycle Dppc of the wireless primary power supply conversion module PPC. The high-frequency AC information signal generated by the sub-satellite telemetry and remote control module CTMTC and the signal modulation circuit is injected into the AC energy signal through the high-frequency resonance of the information loading circuit LC to form an AC mixed signal, which is transmitted to the wireless primary power supply conversion module PPC of the mother satellite through coil coupling.

5. The mother-child satellite wireless energy and information synchronous transmission system according to claim 2 is characterized in that: The primary coil is installed on the surface of the mother star, the secondary coil is installed on the surface of the daughter star, and the installation surfaces of the primary coil and the secondary coil are adjacent surfaces of the mother star and the daughter star.

6. The mother-child satellite wireless energy and information synchronous transmission system according to claim 5 is characterized in that: The primary coil and the secondary coil both include a high magnetic permeability magnetic core, a winding conductor and a shell supporting device.

7. The mother-child satellite wireless energy and information synchronous transmission system according to claim 6, characterized in that: The mother star power controller PPCU also has i solar array power regulators PAPR, i battery chargers PBCR, i battery dischargers PBDR and a bus error amplifier MEA. The power input end of the solar array power regulator PAPR is connected to the mother star solar array PSAW, and the power output end is connected to the full-regulation bus Vr. The power input end of the battery charger PBCR is connected to the full-regulation bus Vr, and the power output end is connected to the mother star battery PBAT. The power input end of the battery discharger PBDR is connected to the mother star battery PBAT, and the power output end is connected to the full-regulation bus Vr.

8. The mother-child satellite wireless energy and information synchronous transmission system according to claim 7 is characterized in that: The satellite power controller CPCU also includes n solar array power regulators CAPR, a battery power interface unit BC1 and a battery charging manager BCM; The power input end of the solar array power regulator CAPR is connected to the sub-satellite solar array CSAW, and the power output end is connected to the unregulated bus Vu. The power input end of the battery power interface unit BC1 is connected to the unregulated bus Vu, and the power output end is connected to the sub-satellite battery CBAT.

9. The mother-child satellite wireless energy and information synchronous transmission system according to claim 8, characterized in that: The battery charging manager BCM adopts a dual-stage control mode of a local power supply segment and a local remote combined power supply segment, and internally includes two closed-loop PID control loops. The first PID control loop is a remote energy control loop, and the output signal Vbcmrmt controls the output current lcbcr of the bus adapter CBCR; the second PID loop is called a local energy control loop, and the output signal Vbcmlocal controls the output current lcapr of the solar array power regulator CAPR.

10. A control method for a mother-child satellite wireless energy and information synchronous transmission system, characterized in that: The method comprises the following steps: The energy profit and loss status of the mother star and the satellite is collected through the mother star remote control module PTMTC; According to the energy surplus and deficit status of the mother star and the sub-star, the switching frequency fs and the duty cycle Dppc of the wireless primary power supply conversion module PPC are adjusted to control the working mode of the inter-satellite energy and information transmission synchronous transmission channel. The working mode includes the inter-satellite normal energy transmission mode and the inter-satellite standby energy transmission mode. The inter-satellite normal energy transmission mode includes the sub-satellite local power supply section and the sub-satellite local remote joint power supply section.

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