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

Abstract

The application discloses a kind of mother and child satellite wireless energy and information synchronous transmission system and control method, the mother and child satellite wireless energy and information synchronous transmission system includes mother star power supply system and substar power supply system, and the mother star power supply system and substar power supply system are connected by energy and information synchronous transmission channel.This application takes the surplus and deficit state of mother star energy and the surplus and deficit state of substar energy in wireless transmission information flow as input criterion, adopts digital closed-loop feedback algorithm to decide the existence and size of wireless transmission power between two satellites, realizes the dynamic balance supply of "peak clipping and valley filling" between mother and child satellite energy, energy transmission between mother star and substar, improves the reliability, security of power supply between mother and child satellite and the accuracy of information transmission.

Description

Technical Field

[0001] This invention relates to the fields of satellite power supply and distribution and control, and inter-satellite energy and information transmission technology, and particularly to a mother-daughter satellite wireless energy and information synchronization transmission system and control method. Background Technology

[0002] The mother and daughter satellites carry different payloads, and during their flight in orbit, they can freely dock and separate to independently perform different on-orbit tasks, such as on-orbit refueling and space particle sampling. This approach adapts to the diverse nature of current spacecraft on-orbit missions and has become one of the popular directions in spacecraft development. Figure 1 The diagram shows a traditional mother-daughter satellite power system architecture, which includes two parts: the mother satellite power system and the daughter satellite power system. Both of them adopt a topology of solar cell array power generation and battery pack energy storage.

[0003] Currently, both parent and child satellites in orbit are connected via power and information cables. Generally, the parent satellite has a high power output, while the child satellite may experience energy shortages due to launch limitations. When the child satellite's energy is insufficient, such as during the initial launch phase when its solar arrays are not yet deployed and unable to generate power, or during its mission phase when attitude changes cause the solar arrays to be blocked by sunlight, reducing power output, the parent satellite's power system, in addition to supplying power to its own individual units, can also connect a power switch to supply power to the child satellite's individual units via the power switch and power cable. Inter-satellite information cables typically use buses such as 1553B and CAN for transmitting information such as the health status of individual units and circuits between the two satellites. This system effectively solves the energy and information exchange between the two satellites through wired power cables, but it has the following drawbacks:

[0004] (1) The level of intelligence is low, making it impossible to achieve orderly and autonomous control of local and remote energy sources for the satellite. This results in low energy utilization and a high risk of system failures. The interaction of energy between the two satellites is achieved by switching the power supply on and off. When the power supply switch of the mother satellite is connected, the mother satellite can supply power to the satellite; when the power supply switch is disconnected, the bus cannot supply power to the satellite. The satellite cannot make autonomous, real-time decisions on whether to draw energy from the remote mother satellite to supply power based on the scarcity of local and remote energy sources, resulting in unnecessary energy waste. More importantly, excessive energy drawbacks may lead to insufficient energy from the mother satellite, resulting in a system-level failure mode where both local and remote energy are insufficient.

[0005] (2) Wired power supply cables have low reliability and a high failure rate. When the two satellites are in relative displacement, the connecting cable between the mother and daughter satellites may be accidentally pulled by external forces and damaged. In addition, since the power supply cable is exposed to the outside of the cabin for a long time, it is easily affected by the radiation of charged electrons in space, which leads to a decrease in the insulation strength of the cable surface insulation sheet and affects the safety of power supply.

[0006] (3) Safety issues such as arcing are prone to occur during the on-orbit assembly of satellites. When satellites are performing missions in outer space orbit, there are different operating conditions such as "merging" and "separating" between the two satellites. During this process, the power receiving plug and power supply socket at the end of the power supply cable need to be frequently plugged and unplugged. The plugging and unplugging actions are unattended throughout the process. Although the power supply switch can be turned off to prevent live operation before plugging and unplugging, due to the limitation of the plugging and unplugging accuracy of the robotic arm, there is a possibility that the pinholes in the power receiving plug and power supply socket may be damaged or misaligned. When the power supply switch is turned on again, arcing or even short circuit may occur. At best, it will damage the power supply path between the parent and satellites, making it impossible to transfer energy between the two satellites again. At worst, it will affect the power supply safety of the parent satellite, causing the parent satellite to fail and resulting in huge economic losses.

[0007] Some studies have proposed replacing power cables with wireless power transfer and replacing wired buses with wireless communication such as Wi-Fi or Zigbee, as shown in the attached document. Figure 2 As shown, the two satellites use two independent wireless transmission channels for information and energy to transmit information and energy flows respectively. Although this can solve the problems mentioned in (2) and (3) above, it still has the disadvantages of low intelligence level mentioned in (1). In addition, the following disadvantages limit its application on spacecraft:

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

[0009] (2) The space environment, such as on-orbit irradiation and single particles, is relatively harsh. There are currently no aerospace-grade device solutions for wireless communication methods such as Wifi or Zigbee, making it difficult to achieve high reliability and long lifespan applications. Summary of the Invention

[0010] The main objective of this invention is to propose a wireless power and information synchronization transmission system and control method for mother and child satellites, which aims to improve the reliability, security and accuracy of power supply and information transmission between mother and child satellites.

[0011] To achieve the above objectives, the present invention provides a mother-daughter satellite wireless energy and information synchronization transmission system, comprising a mother satellite power system and a daughter satellite power system, wherein the mother satellite power system and the daughter satellite power system are connected through an energy and information synchronization transmission channel.

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

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

[0014] The power input terminal of the wireless primary-side power supply conversion module PPC is connected to the fully adjustable bus Vr, and the power output terminal and signal output terminal are respectively connected to the primary-side coil and the signal demodulation circuit. The output terminal of the signal demodulation circuit is connected to the mother satellite telemetry and remote control module PMTC.

[0015] The subsatellite power system includes a subsatellite power controller CPCU, a solar array CSAW, a subsatellite battery CBAT, a subsatellite power consumption unit, and a secondary coil. The subsatellite power controller CPCU includes a wireless secondary power supply conversion module SPC, i bus adapters CBCR, a subsatellite 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, sub-satellite battery CBAT, bus adapter CBCR, and sub-satellite power consumption units, and generating the non-regulating bus Vu; the sub-satellite telemetry and remote control module CTMTC is responsible for collecting the sub-satellite's own power module operating status CTM and sub-satellite energy surplus and deficit status, converting the relevant information into high-frequency digital signals and outputting them to the signal modulation circuit to generate high-frequency AC information signals, and is responsible for controlling the on / off status of each power module through remote control commands CTC;

[0017] The power input terminal of the wireless secondary power supply conversion module SPC is connected to the secondary coil, and the power output terminal is connected to the bus adapter CBCR. The signal input terminal 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 to the voltage required without adjusting the 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-side power supply conversion module PPC, a primary-side coil, a daughter satellite telemetry and remote control module CTMTC, a signal modulation circuit, a wireless secondary-side power supply conversion module SPC, and the secondary-side coil; the primary-side coil and the secondary-side coil transmit AC mixed signals in an LC resonance manner, the AC mixed signals include AC energy signals and AC information signals, wherein the information signals use the energy signals as carrier signals.

[0019] A further technical solution of the present invention is that the wireless primary-side power supply conversion module (PPC) includes an energy inverter circuit, a primary-side energy compensation network, and an information extraction circuit. The energy inverter circuit inverts a stable DC fully adjustable bus Vr to generate an AC energy signal, which is then connected to the primary-side coil via the inductors of the primary-side energy compensation network and the information extraction circuit. The switching frequency fs and duty cycle Dppc of the AC energy signal are both set by the home satellite telemetry and remote control module (PTMTC). The AC mixed signal transmitted by the primary-side coil is loaded with a high-frequency AC information signal transmitted by the secondary-side coil. The information extraction circuit uses the LC resonance principle to extract the effective components of the high-frequency AC signal and, after processing by the signal demodulation circuit, restores the energy surplus and deficit information transmitted therein. Finally, the signal is sent to the home satellite telemetry and remote control module (PTMTC) for acquisition.

[0020] A further technical solution of the present invention is that the wireless secondary-side power supply conversion module SPC includes a secondary-side compensation network, an information loading circuit, and an energy rectification circuit. The AC energy signal transmitted by the secondary-side coil is connected to the energy rectification circuit through the inductors of the secondary-side compensation network and 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 inter-satellite energy transfer. The amplitude of Vspc is determined by the switching frequency fs and duty cycle Dppc of the wireless primary-side 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-side power supply conversion module PPC of the parent satellite through coil coupling.

[0021] A further technical solution of the present invention is that the primary side coil is mounted on the surface of the parent star, the secondary side coil is mounted on the surface of the daughter star, and the mounting surfaces of the primary side coil and the secondary side coil are adjacent surfaces of the parent 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 permeability magnetic core, winding wires, and a housing support device.

[0023] A further technical solution of the present invention is that the mother satellite power controller PPCU further includes i solar array power regulators PAPR, i battery chargers PBCR, i battery dischargers PBDR, and a bus error amplifier MEA. The power input terminal of the solar array power regulator PAPR is connected to the mother satellite solar array PSAW, and the power output terminal is connected to the fully regulated bus Vr. The power input terminal of the battery charger PBCR is connected to the fully regulated bus Vr, and the power output terminal is connected to the mother satellite battery PBAT. The power input terminal of the battery discharger PBDR is connected to the mother satellite battery PBAT, and the power output terminal is connected to the fully regulated 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 terminal of the solar array power regulator CAPR is connected to the sub-satellite solar array CSAW, and the power output terminal is connected to the unregulated bus Vu. The power input terminal of the battery power interface unit BCI is connected to the unregulated bus Vu, and the power output terminal 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-segment control mode of local power supply segment and local-remote joint 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 magnitude of the output current Icbcr of the bus adapter CBCR. The second PID loop is called the local energy control loop, and the output signal Vbcmlocal controls the magnitude of the output current Icapr of the solar array power regulator CAPR.

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

[0028] The energy balance status of the mother satellite and the energy surplus / deficit status of the daughter satellite are collected through the PTMTC remote control module of the mother satellite.

[0029] Based on the energy surplus / deficit status of the parent satellite and the satellite, the switching frequency fs and duty cycle Dppc of the wireless primary-side power conversion module PPC are adjusted to control the working mode of the inter-satellite energy and information transmission synchronization 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 satellite local power supply segment and the satellite local remote joint power supply segment.

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

[0031] This invention employs a design in the parent-child satellite power system that combines primary and secondary side coils with a primary-secondary side wireless power supply conversion module, modulation / demodulation, and telemetry / remote control module. Utilizing the near-field electromagnetic LC resonant coupling induction principle, it achieves contactless synchronous transmission of energy and information between satellites through signal loading and extraction, eliminating the need for inter-satellite cables and facilitating satellite integration and separation. It features simplicity, reliability, flexible combination, high security, and strong anti-interference capabilities, solving problems such as low on-orbit plugging and unplugging safety of wired inter-satellite cables, high bit error rate of existing wireless transmission technologies, and the inability to implement them in aerospace engineering. By combining PTMTC digital software closed-loop feedback control with the child satellite's "BCM two-stage control," the parent and child satellites prioritize local energy use. When the parent satellite has surplus energy and the child satellite is short of energy, energy transfer between the parent and child satellites is initiated, achieving a dynamic balance of energy supply through "peak shaving and valley filling," thus improving energy utilization and autonomous management capabilities.

[0032] In the wireless power transmission system architecture for both satellites, by introducing PTMTC digital closed-loop control and the satellite charger manager's "BCM two-stage control" method, the system can autonomously determine the energy shortage status of both satellites and decide whether to conduct energy transfer between them. Since inter-satellite energy transfer involves multiple stages, its efficiency is lower than that of the local power system. To improve energy utilization, when the satellite has sufficient energy, it prioritizes using its internal power system to independently provide the energy it needs. When the main power supply has surplus energy and the satellite's energy is insufficient, and local energy cannot meet the requirements, the system autonomously activates the wireless power transmission device to dispatch energy from the remote main satellite power system, thus achieving orderly control of local and remote energy. Attached Figure Description

[0033] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

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

[0035] Figure 2 This is a schematic diagram illustrating an improved energy and information connection relationship for inter-satellite wireless transmission between mother and child satellites.

[0036] Figure 3 This is a schematic diagram of the structure of the mother-daughter satellite wireless energy and information synchronization transmission system of the present invention;

[0037] Figure 4 This is a diagram of a wireless primary-side power supply conversion module (PPC).

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

[0039] Figure 6 This is a block diagram of the battery charging manager (BCM) proposed in this invention.

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

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

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

[0043] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0044] This invention proposes a wireless power and information synchronization transmission system for mother-daughter satellites. Based on the traditional mother-daughter satellite power system architecture, it replaces the power receiving plug, power supply socket, and power cable with primary-side coils and secondary-side coils, and replaces the power switch with a wireless primary-side power conversion module (PPC). It configures signal modulation and demodulation circuits to fuse inter-satellite information flow and power flow. The information flow uses the power flow as the carrier signal, and wireless synchronization of power and information is achieved through resonant coupling between the primary and secondary-side coils. This eliminates inter-satellite power supply and information cables, improving the reliability, security, and accuracy of power supply and information transmission. The control method for synchronous wireless energy and information transmission between the mother and daughter satellites involves the mother satellite's telemetry and remote control module (PTMTC) using the mother satellite's energy surplus / deficit status and the daughter satellite's energy surplus / deficit status in the wireless transmission information stream as input criteria. It employs a digital closed-loop feedback algorithm to determine the availability and magnitude of wireless transmission power between the two satellites, achieving a dynamic balance of energy supply between the mother and daughter satellites through "peak shaving and valley filling." The daughter satellite is equipped with a hardware battery charging manager (BCM) that uses a two-stage control method to autonomously control the orderly use of local energy and remote wireless transmission energy based on local energy demand and supply. The combined control of these two systems ensures that both satellites prioritize the use of local energy. When the mother satellite has surplus energy and the daughter satellite lacks energy, the wireless energy transmission device is automatically activated to achieve energy transmission between the mother and daughter satellites.

[0045] Specifically, please refer to Figure 3 The present invention provides a mother-daughter satellite wireless energy and information synchronization transmission system, which includes a mother satellite power system and a daughter satellite power system, and the mother satellite power system and the daughter satellite power system are connected through an energy and information synchronization transmission channel.

[0046] The mothership power system includes a mothership power controller (PPCU), a solar array (PSAW), a mothership battery (PBAT), a mothership power supply unit, and a primary-side coil. The mothership power controller (PPCU) includes a wireless primary-side power supply conversion module (PPC), a mothership telemetry and remote control module (PTMTC), and a signal demodulation circuit.

[0047] The parent satellite controller (PPCU) is responsible for coordinating the power balance among the parent satellite solar array (PSAW), the parent satellite battery (PBAT), and the parent satellite power-consuming units, and generating the fully regulated bus (Vr). The parent satellite telemetry and control module (PTMTC) is used to collect the parent satellite's own operating status (PTM), the parent satellite's energy surplus / deficit status, and the satellite wireless transmission information output by the signal demodulation circuit (including satellite energy surplus / deficit status, voltage, current, and operating status of each module). It controls the on / off status of each power module through remote control commands, and the built-in digital control software autonomously controls the working mode of the inter-satellite energy and information transmission synchronization channel.

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

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

[0050] The subsatellite power controller (CPCU) is responsible for coordinating the operation of the solar array (CSAW), subsatellite battery (CBAT), bus adapter (CBCR), and individual subsatellite power units, and generating the non-regulating bus voltage (Vu). The subsatellite telemetry and control module (CTMTC) is responsible for collecting the subsatellite's own power module operating status (CTM) and energy surplus / deficit status, converting the relevant information into high-frequency digital signals, outputting them to the signal modulation circuit to generate high-frequency AC information signals, and controlling the on / off status of each power module through remote control commands (CTC).

[0051] The power input terminal of the wireless secondary power supply conversion module SPC is connected to the secondary coil, and the power output terminal is connected to the bus adapter CBCR. The signal input terminal of the wireless secondary power supply conversion module SPC is connected to the sub-satellite telemetry and 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 to the voltage required for bus Vu adjustment.

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

[0053] To improve wireless transmission distance and energy transmission efficiency, the primary coil and the secondary coil transmit AC mixed signals in an LC resonance manner. The AC mixed signals include AC energy signals and AC information signals, wherein the information signals use the energy signals as carrier signals.

[0054] The wireless primary-side power supply conversion module (PPC) includes an energy inverter circuit, a primary-side energy compensation network, and an information extraction circuit. The energy inverter circuit inverts the stable DC fully adjustable bus Vr to generate an AC energy signal, which is then connected to the primary-side coil via the inductors of the primary-side energy compensation network and the information extraction circuit. The switching frequency fs and duty cycle Dppc of the AC energy signal are both set by the home satellite telemetry and remote control module (PTMTC). The AC mixed signal transmitted by the primary-side coil is loaded with a high-frequency AC information signal transmitted from the secondary-side coil. The information extraction circuit uses the LC resonance principle to extract the effective components of the high-frequency AC signal and processes it through the signal demodulation circuit to restore the energy surplus and deficit information transmitted within it. Finally, the signal is sent to the home satellite telemetry and remote control module (PTMTC) for acquisition.

[0055] The wireless secondary-side power conversion module (SPC) includes a secondary-side compensation network, an information loading circuit, and an energy rectification circuit. The AC energy signal transmitted by the secondary-side coil is connected to the energy rectification circuit through the inductors of the secondary-side compensation network and 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 inter-satellite energy transfer. The amplitude of Vspc is determined by the switching frequency fs and duty cycle Dppc of the wireless primary-side power conversion module (PPC). The high-frequency AC information signal generated by the sub-satellite telemetry and 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 then transmitted to the wireless primary-side power conversion module (PPC) of the parent satellite through coil coupling.

[0056] Both the primary and secondary coils include a high-permeability magnetic core, winding wires, and a supporting outer casing. The primary coil is mounted on the surface of the parent star, and the secondary coil is mounted on the surface of the daughter star, with their mounting surfaces adjacent to each other. When the parent and daughter stars are aligned, the primary and secondary coils are placed parallel to each other with their spacing controlled within the design range, enabling synchronous energy and information transmission between them. When the parent and daughter stars separate, the primary and secondary coils are too far apart to form an effective closed electromagnetic path, thus blocking the energy and information transmission path.

[0057] The parent satellite 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 terminal of the solar array power regulator (PAPR) is connected to the parent satellite solar array (PSAW), and the power output terminal is connected to the fully regulated bus (Vr). The power input terminal of the battery charger (PBCR) is connected to the fully regulated bus (Vr), and the power output terminal is connected to the parent satellite battery (PBAT). The power input terminal of the battery discharger (PBDR) is connected to the parent satellite battery (PBAT), and the power output terminal is connected to the fully regulated bus (Vr).

[0058] 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).

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

[0060] The working principle of the mother-daughter satellite wireless energy and information synchronization transmission system of this invention lies in the fact that the mother satellite telemetry and control module PTMTC collects the energy surplus and deficit status of the mother satellite and the daughter satellite, and adjusts the switching frequency fs and duty cycle Dppc of the wireless primary-side power supply conversion module PPC through internal software closed-loop calculation, thereby controlling the working mode of the inter-satellite energy and information transmission synchronization channel. Its control logic is as follows: when the mother satellite energy surplus is detected (state 1), the Vspc voltage is automatically increased to 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 power used by the bus adapter CBCR. When the mother satellite energy shortage is detected (state 0), Vspc is automatically decreased. The bus adapter CBCR input is undervoltage and cannot start power conversion. The mother satellite energy cannot be transmitted to the daughter satellite bus, and the inter-satellite energy enters the standby energy transmission mode. In this mode, to ensure the normal transmission of inter-satellite information flow, a very low AC energy signal is still transmitted between the wireless primary-side power supply conversion module PPC and the wireless secondary-side power supply conversion module SPC to provide the necessary carrier signal.

[0061] The Battery Charging Manager (BCM) employs a dual-segment control mode, consisting of a local power supply segment and a combined local and remote power supply segment. Internally, it contains two closed-loop PID control loops. The first PID control loop is the remote energy control loop, whose output signal Vbcmrmt controls the output current Icbcr of the bus adapter CBCR. The second PID loop is the local energy control loop, whose output signal Vbcmlocal controls the output current Icapr of the solar array power regulator CAPR. A dead zone is maintained between the control thresholds of the two loops. Vbcmrmt and Vbcmlocal represent the satellite's energy surplus / deficit status.

[0062] When the satellite has sufficient energy (state 1), Vbcmlocal controls the solar array power conditioner CAPR to output current to the unregulated bus Vu, and Vbcmrmt controls the bus adapter CBCR to not output current to the unregulated bus Vu. At this time, the satellite's energy is primarily generated by the local power supply system and does not require the mother satellite; therefore, this section is called the "local power supply section." When the mother satellite has abundant energy (state 1) and the satellite has insufficient energy (state 0), Vbcmlocal controls the solar array power conditioner CAPR to output current to the unregulated bus Vu. The Vbcmrmt control bus adapter CBCR draws energy from the wireless secondary power supply conversion module SPC and outputs current to the unregulated bus Vu. At this time, the satellite's energy is jointly generated by the local power supply system and the remote mother satellite; this segment is called the "local-remote joint power supply segment." When the mother satellite's energy is insufficient, the mother satellite telemetry and control module PTMTC controls the inter-satellite energy to operate in standby energy transmission mode. Regardless of whether the satellite's energy is insufficient, the bus adapter CBCR module does not output current to the unregulated bus Vu due to input undervoltage, and the satellite operates in the local power supply segment. In summary, this achieves orderly control of local and remote energy.

[0063] The following combination Figures 3 to 8 The working principle of the mother-daughter satellite wireless energy and information synchronization transmission system of the present invention will be further explained in detail.

[0064] The present invention provides a mother-daughter satellite wireless power and information synchronization transmission system, comprising two parts: a mother satellite power system and a daughter satellite power system.

[0065] The mother satellite power system includes the mother satellite solar array PSAW, mother satellite battery PBAT, mother satellite power controller PPCU, mother satellite power-consuming units, and primary-side coils. The mother satellite power controller PPCU includes m solar array power regulators (PAPR), i battery chargers (PBCR), i battery dischargers (PBDR), a bus error amplifier (MEA), a wireless primary-side power conversion module (PPC), a mother satellite telemetry and control module (PTMTC), and a signal demodulation circuit. The power input of the solar array power regulators (PAPR) is connected to the mother satellite solar array PSAW, and the power output is connected to the fully regulated bus (Vr). The power input of the battery chargers (PBCR) is connected to the fully regulated bus (Vr), and the power output is connected to the mother satellite battery PBAT. The power input of the battery dischargers (PBDR) is connected to the mother satellite battery PBAT, and the power output is connected to the fully regulated bus (Vr). The mother satellite adopts a fully adjustable bus architecture. The bus error amplifier (MEA) samples the fully adjustable bus voltage (Vr) and internally uses a PID closed-loop output signal (Vmea) to achieve stable control of the fully adjustable bus voltage (Vr). This coordinates the work of the solar cell power regulator (PAPR), battery charger (PBCR), and battery discharger (PBDR) within the power controller (PPCU) to balance the power output of the mother satellite solar array (PSAW), the power consumption of individual power units, and the energy storage of the mother satellite battery (PBAT). The amplitude of the bus voltage (Vr) can be determined according to the power consumption of individual power units. Generally, 100V is required for power consumption above 5KW, while 42V can be selected for power consumption below 5KW. The signal terminals of the solar array power regulator PAPR, battery charger PBCR, battery discharger PBDR, bus error amplifier MEA, signal demodulation circuit, and wireless primary-side 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 for inter-satellite energy and information transmission. It is used to realize the acquisition of the working status PTM of each power module of the mother satellite, the energy surplus and deficit status of the mother satellite, the acquisition of output information of the signal demodulation circuit, the issuance of remote control commands by PTC, and the autonomous control of the working mode of the inter-satellite energy and information transmission synchronous transmission channel.

[0066] The satellite power system includes the satellite solar array CSAW, satellite battery CBAT, satellite power controller CPCU, satellite power consumption units, and secondary coils. The satellite power controller CPCU includes n solar array power regulators CAPR, battery power interface unit BCI, battery charging manager BCM, wireless secondary power conversion module SPC, k bus adapters CBCR, signal modulation circuit, and satellite telemetry and control module CTMTC. The satellite uses a non-regulated bus architecture, meaning the bus voltage equals the satellite battery CBAT voltage. Generally, the satellite's power consumption is low, and to ensure safe battery operation, Vu can be selected as 36V-45V or 23V-29V. The power input terminal of the solar array power regulator CAPR is connected to the satellite solar array CSAW, and the power output terminal is connected to the non-regulated bus Vu. The power input terminal of the battery power interface unit BCI is connected to the non-regulated bus Vu, and the power output terminal is connected to the satellite battery CBAT. The non-regulated bus Vu also connects to satellite power consumption units 1-1 to supply power to them. The secondary coil connects to the wireless secondary power supply conversion module SPC. The bus adapter CBCR uses the output voltage Vspc of the wireless secondary power supply conversion module SPC as input, converting it to the voltage required for 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, power conversion is started, and the conversion power is controlled by the battery charging manager BCM. The satellite telemetry and control module CTMTC connects to the solar array power regulator CAPR, battery power interface unit BCI, bus adapter CBCR, battery charging manager BCM, and the signal terminal of the signal modulation circuit. It is used to collect the working status of each power module of the satellite and the energy surplus and deficit status of the satellite, issue remote control commands CTC, and is responsible for framing and transmitting the relevant information flow of the satellite to the signal modulation circuit to generate high-frequency AC information signals.

[0067] The wireless primary-side power conversion module (PPC), primary-side coil, mother satellite telemetry and remote control module (PTMTC), and signal demodulation circuit within the mother satellite power system, and the secondary-side coil, wireless secondary-side power conversion module (SPC), mother satellite adapter (CBCR), signal modulation circuit, and daughter satellite telemetry and remote control module (CTMTC) within the daughter satellite power system together constitute a wireless energy and information transmission channel. This channel is responsible for enabling energy and information flow interaction between the mother and daughter satellites. Energy is transferred from the mother satellite to the daughter satellite, and information is transferred from the daughter satellite to the mother satellite. The wireless primary-side power conversion module (PPC), primary-side coil, secondary-side coil, and wireless secondary-side power conversion module (SPC) together form a high-power DC-DC converter, realizing power conversion between the mother satellite's fully regulated bus Vr and the daughter satellite's Vspc. The primary and secondary-side coils are equivalent to transformers. Since transformers can only transmit AC voltage, the wireless primary-side power conversion module (PPC) is responsible for inverting the input fully regulated bus Vr to generate AC energy signals, as shown in the attached diagram. Figure 4 As shown, switches Q1 to Q4 are power switches, forming a full-bridge topology. They are controlled by a digital controller and driver to periodically turn on and off at a certain frequency. When switches Q1 and Q4 are on, switches Q2 and Q3 are off, and the bridge arm output is positive at the top and negative at the bottom, with an output voltage equal to +Vr. When switches Q1 and Q4 are off, switches Q2 and Q3 are on, and the bridge arm output voltage is negative at the top and positive at the bottom, with an output voltage equal to -Vr. Inductor L1, capacitor C1, and capacitor C2 form a resonant compensation network to stabilize the converter gain. Inductor L21 of the information extraction circuit is connected between the primary-side energy compensation network and the primary-side coil. Utilizing the high-frequency resonance principle of inductor L22 and capacitor C3, it extracts the high-frequency AC information signal from the AC mixed signal transmitted by the primary-side coil and sends it to the demodulation circuit to restore it to a valid information signal for acquisition by the PTMTC telemetry and control module of the mother satellite. A mixed signal of alternating energy and information is transmitted between the primary and secondary coils. Within the wireless secondary power supply conversion module (SPC), it passes through a secondary compensation network and an information loading circuit before being rectified by the energy rectifier circuit to output a DC voltage Vspc, as shown in the attached diagram. Figure 5 As shown; the secondary-side compensation network, together with the primary-side compensation network, is used to stabilize the overall converter gain; the information loading circuit utilizes the high-frequency resonance principle of inductor L32 and capacitor C5 to load the high-frequency information signal output from the modulation circuit into the AC energy signal, forming an AC mixed signal. The energy rectification circuit adopts a full-bridge rectification form. When the bridge arm voltage is positive at the top and negative at the bottom, rectifier diodes D1 and D4 are turned on, while rectifier diodes D2 and D3 are turned off; when the bridge arm voltage is negative at the top and positive at the bottom, rectifier diodes D2 and D3 are turned on, while 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 that is related to the turns ratio of the primary and secondary coils, the duty cycle Dppc of Q1 to Q4 in the PPC, the switching frequency fs, and the LC resonant frequency of the primary and secondary compensation networks. 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 and secondary coils consist of a high-permeability magnetic core, winding wires, and a supporting outer casing. The primary coil is mounted on the surface of the parent satellite, and the secondary coil is mounted on the surface of the child satellite. The mounting surfaces of the coils are adjacent to each other. When the parent and child satellites are "united," the two coils are placed parallel to each other with the spacing controlled within the design range. The energy transfer path is as follows (solid lines represent cable connections, and dashed lines represent cableless connections):

[0071] Fully adjustable bus → PPC → Primary coil → Secondary coil → SPC → Vspc

[0072] After being inverted by a PPC, the AC signal output from the parent satellite's fully regulated bus is coupled to the secondary coil of the daughter satellite via near-field electromagnetic coupling through the primary coil. The signal is then rectified by the daughter satellite to form a DC voltage Vspc, enabling energy transfer between the two satellites. When the parent and daughter satellites separate, the primary and secondary coils are too far apart to form an effective closed electromagnetic path, thus blocking the energy transfer. This "cableless" non-contact energy transfer method simplifies the interconnection between the two satellites and improves power supply security.

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

[0074] CTMTC → Signal Modulation → SPC → Secondary Coil → Primary Coil → PPC → Signal Demodulation → PTMTC

[0075] The satellite telemetry and control module CTMTC outputs information such as satellite energy balance, bus voltage, bus current, and health status of each power module in digital form. After modulation by the signal modulation circuit, a high-frequency AC information signal is generated. This signal is then injected into the secondary coil by the information loading circuit in the wireless secondary power supply conversion module SPC at high frequency to form a mixed AC signal. This signal is wirelessly transmitted to the primary coil. The effective high-frequency AC information signal is extracted by the information extraction circuit of the wireless primary power supply conversion module PPC. After being restored to effective information by the demodulation circuit, it is sent to the satellite telemetry and control module PTMTC.

[0076] The bus adapter CBCR is used to convert the Vspc output from the wireless secondary power supply conversion module SPC to a varying, unregulated bus voltage, as shown in the attached diagram. Figure 8 As shown, it adopts a buck-boost topology internally. When the voltage Vspc meets the operating threshold requirement of the wireless secondary power supply conversion module SPC, the output voltage and current are controlled by adjusting the duty cycle of the four internal switching transistors Q1 to Q4. The bus adapter CBCR outputs power to the unregulated bus, delivering the energy transmitted from 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 operating threshold requirement of the wireless secondary power supply conversion module SPC, the output power of the bus adapter CBCR to the unregulated bus is 0. At this time, even if there is energy transmission between the primary and secondary coils, it will not be delivered to the unregulated bus Vu.

[0077] The operating status of the bus adapter CBCR and the solar array power conditioner CAPR are both centrally controlled by the battery charge manager (BCM), as shown in the attached diagram. 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 consists of proportional operational amplifier A1 and error operational amplifier A2, while the local energy control loop consists of proportional operational amplifier A3 and error operational amplifier A4. The conversion ratios of proportional operational amplifiers A1 and A3 are K1 and K2, respectively. The inverting inputs of error operational amplifiers A2 and A4 are both connected to the reference voltage Vref, and the non-inverting inputs are connected to the outputs of proportional operational amplifiers A1 and A3, respectively. The remote charging termination voltage threshold is defined as VL, and the local charging termination voltage threshold is defined as VH.

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

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

[0080] The error amplifier A2 outputs a signal, Vbcmrmt, which is sent to the CBCR of the host adapter to control the duty cycle of the CBCR switching transistor, thereby controlling the output current Icbcr. The relationship between Icbcr and Vbcmrmt is 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 CBCR of the mothership adapter. The minimum value of Icbcr is 0.

[0083] The output signal of error amplifier A4 is Vbcmlocal, which is sent to the CAPR module of the solar array power regulator to control the magnitude of the CAPR output current Icapr. The relationship between Icapr and VbcmIocal is 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 within the solar array power regulator CAPR. The minimum value of Icapr is 0. Vbcmrmt and Vbcmlocal can be jointly used to characterize the local energy surplus and deficit of a satellite.

[0086] The following is in conjunction with the appendix Figure 6 Appendix Figure 7Appendix 1 introduces the control principle of orderly output of local energy and remote energy, divides the energy transmission mode between parent and child satellites into two types, and divides the working mode of child satellites into two working segments.

[0087] I. Normal Interstellar Energy Transfer Mode

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

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

[0090] When the energy of the satellite is sufficient or low, 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 non-inverting input of error op-amp A2 is VA2+ = Vcabat * K1 (Formula 6)

[0092] Substitute formula 2 into formula 6:

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

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

[0095] Since VA2+ > VA2-, the amplification factor of A2 can be considered infinite. Therefore, its output is the highest level, equal to its supply voltage Vcc, i.e.:

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

[0097] Where H(VA2) is the transfer function of operational amplifier A2;

[0098] Substitute formula 9 into formula 4:

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

[0100] The voltage at the non-inverting input of error op-amp A4 is VA4+ = Vcbat * K2 (Formula 11)

[0101] Substituting Formula 3 into Formula 11:

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

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

[0104] Since VA4+ < VA4-, the output of A4 is at its lowest level, which is 0.

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

[0106] Where H(VA4) is the transfer function of operational amplifier A4;

[0107] Substitute formula 14 into formula 6:

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

[0109] 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 supplies power to the unregulated bus and charges the satellite battery CBAT. At this time, the satellite's energy is generated by the local power supply system and does not require the help of the mother satellite.

[0110] As the CBAT voltage of the Zixing battery gradually increases, it will gradually approach the charging termination voltage threshold VH, i.e.

[0111] Vcbat-VH=ε (Formula 16)

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

[0113] Combining formulas 3, 11, and 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] Substitute formula 17 into formula 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] When the error amplifier A4 enters closed-loop feedback mode, according to the closed-loop feedback principle, the voltage difference between the non-inverting and inverting terminals is amplified, and 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 sub-satellite battery CBAT changes from high-current charging mode to trickle charging mode. The charging current gradually decreases, and the sub-satellite battery CBAT voltage eventually stabilizes at VH and no longer increases. The sub-satellite power system has excess energy, but no excessive energy flows to the sub-satellite battery CBAT to ensure its safety and prevent overcharging.

[0122] (2) Local and remote joint power supply section of sub-star

[0123] When the energy of the satellite is insufficient or the degree of scarcity is high, the discharge of the satellite battery CBAT is large and the voltage of the satellite battery CBAT 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 formulas 2, 6, and 8, we get:

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

[0126] Since VA2+ < VA2-, the amplification factor of the error op-amp A2 can be considered infinite, therefore its output is the lowest level 0, i.e.:

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

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

[0129] Substitute formula 20 into formula 4:

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

[0131] The voltage at the non-inverting input of error amplifier A4 is also lower than the voltage at the inverting input. The calculation process is the same as for the local power supply section. Referring to formulas 11-15, Vbcmlocal is 0.

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

[0133] According to the calculation results of Formulas 21 and 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 satellite is jointly provided by the local power supply system and the mother satellite, and the energy transfer power between the mother and satellite is relatively large.

[0134] II. Inter-satellite standby power transfer mode

[0135] When the parent satellite is energy-depleted, forcing it to transfer energy to the satellite will exacerbate the energy shortage, potentially leading to energy imbalances and serious malfunctions such as satellite power outages. To prevent this, the PTMTC digital control software is designed with the following logic:

[0136] When the mother satellite's energy is low (state 0), the switching frequency fs and duty cycle Dppc are adjusted to make the value of α in Formula 1 lower, specifically αL (αL << αn). According to Formula 1, the amplitude of Vspc is αL * Vr. This voltage cannot meet the power conversion requirements of the mother satellite adapter CBCR. At this time, the two satellites operate in inter-satellite energy standby power transmission mode, and the actual transmission power is basically zero, but information flow still occurs. When αL is 0, there will be no AC energy signal transmission between the primary and secondary coils, which cannot provide a signal carrier for AC information signals, leading to interruption of information flow transmission. Therefore, αL should be greater than 0. In standby power transmission mode, the mother satellite adapter CBCR will not output energy to the unregulated bus Vu. It can only rely on the daughter satellite's local solar array power regulator CAPR to supply power to the unregulated bus and charge the battery pack. At this time, the daughter satellite operates in the local power supply segment, and all energy is generated by the local power supply system, without consuming the mother satellite's energy, ensuring the power supply safety of both satellites.

[0137] Appendix 1

[0138]

[0139] Appendix Table 1 is a schematic diagram showing the relationship between the energy supply and system operating mode matrix of the mother-daughter satellite wireless energy and information synchronization transmission system of the present invention.

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

[0141] This invention employs a design in the parent-child satellite power system that combines primary and secondary side coils with a primary-secondary side wireless power supply conversion module, modulation / demodulation, and telemetry / remote control module. Utilizing the near-field electromagnetic LC resonant coupling induction principle, it achieves contactless synchronous transmission of energy and information between satellites through signal loading and extraction, eliminating the need for inter-satellite cables and facilitating satellite integration and separation. It features simplicity, reliability, flexible combination, high security, and strong anti-interference capabilities, solving problems such as low on-orbit plugging and unplugging safety of wired inter-satellite cables, high bit error rate of existing wireless transmission technologies, and the inability to implement them in aerospace engineering. By combining PTMTC digital software closed-loop feedback control with the child satellite's "BCM two-stage control," the parent and child satellites prioritize local energy use. When the parent satellite has surplus energy and the child satellite is short of energy, energy transfer between the parent and child satellites is initiated, achieving a dynamic balance of energy supply through "peak shaving and valley filling," thus improving energy utilization and autonomous management capabilities.

[0142] In the wireless power transmission system architecture for both satellites, by introducing PTMTC digital closed-loop control and the satellite charger manager's "BCM two-stage control" method, the system can autonomously determine the energy shortage status of both satellites and decide whether to conduct energy transfer between them. Since inter-satellite energy transfer involves multiple stages, its efficiency is lower than that of the local power system. To improve energy utilization, when the satellite has sufficient energy, it prioritizes using its internal power system to independently provide the energy it needs. When the main power supply has surplus energy and the satellite's energy is insufficient, and local energy cannot meet the requirements, the system autonomously activates the wireless power transmission device to dispatch energy from the remote main satellite power system, thus achieving orderly control of local and remote energy.

[0143] To achieve the above objectives, the present invention also proposes a control method for a mother-daughter satellite wireless energy and information synchronization transmission system, characterized in that the method includes the following steps:

[0144] The energy balance status of the mother satellite and the daughter satellite are collected by the PTMTC remote control module of the mother satellite.

[0145] Based on the energy surplus / deficit status of the parent satellite and the satellite, the switching frequency fs and duty cycle Dppc of the wireless primary-side power conversion module PPC are adjusted to control the working mode of the inter-satellite energy and information transmission synchronization 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 satellite local power supply segment and the satellite local remote joint power supply segment.

[0146] For the specific working principle of the control method of the mother-daughter satellite wireless energy and information synchronization transmission system of the present invention, please refer to the above introduction of the working principle of the mother-daughter satellite wireless energy and information synchronization 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 transformations made under the concept of the present invention using the contents of the present invention specification and drawings, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

Claims

1. A mother and child satellite wireless energy and information synchronous transmission system, characterized in that, The power supply system comprises a parent satellite power supply system and a child satellite power supply system, which are connected through an energy and information synchronous transmission channel; The parent satellite power supply system comprises a parent satellite power supply controller PPCU, a solar array PSAW, a parent satellite battery PBAT, a parent satellite power consumer and a primary coil, the parent satellite power supply controller PPCU comprises a wireless primary side power conversion module PPC, a parent satellite telemetry and remote control module PTMTC and a signal demodulation circuit; The parent satellite controller PPCU is responsible for coordinating the power balance of the parent satellite solar array PSAW, the parent satellite battery PBAT and the parent satellite power consumer, and generating a fully regulated bus Vr; the parent satellite telemetry and remote control module PTMTC is used to collect the working state of the parent satellite itself, the energy gain and loss state of the parent satellite and the output of the signal demodulation circuit, and control the on-off state of each power module through a remote control instruction; The power input end of the wireless primary side power conversion module PPC is connected to the fully regulated bus Vr, and the power output end and the signal output end are connected to the primary coil and the signal demodulation circuit respectively, and the output end of the signal demodulation circuit is connected to the parent satellite telemetry and remote control module PTMTC; The child satellite power supply system comprises a child satellite power supply controller CPCU, a solar array CSAW, a child satellite battery CBAT, a child satellite power consumer and a secondary coil, the child satellite power supply controller CPCU comprises a wireless secondary side power conversion module SPC, i bus adaptors CBCR, a child satellite telemetry and remote control module CTMTC and a signal modulation circuit; The child satellite power supply controller CPCU is responsible for coordinating the working of the solar array CSAW, the child satellite battery CBAT, the bus adaptor CBCR and the child satellite power consumer, and generating an unregulated bus Vu; the child satellite telemetry and remote control module CTMTC is responsible for collecting the power module working state CTM of the child satellite itself, the energy gain and loss state of the child satellite, converting the relevant information into a high-frequency digital signal and outputting it to the signal modulation circuit to generate a high-frequency alternating current information signal, and controlling the on-off state of each power module through a remote control instruction CTC; The power input end of the wireless secondary side power conversion module SPC is connected to the secondary coil, and the power output end is connected to the bus adaptor CBCR, the signal input end of the wireless secondary side power conversion module SPC is connected to the child satellite telemetry and remote control module CTMTC through the signal modulation circuit; the bus adaptor CBCR takes the output voltage Vspc of the wireless secondary side power conversion module SPC as input and converts it into the required voltage of the unregulated bus Vu; The energy and information synchronous transmission channel comprises the parent satellite telemetry and remote control module PTMTC, the signal demodulation circuit, the wireless primary side power conversion module PPC, the primary coil, the child satellite telemetry and remote control module CTMTC, the signal modulation circuit, the wireless secondary side power conversion module SPC and the secondary coil; the primary coil and the secondary coil transmit an alternating current mixed signal in an LC resonance mode, the alternating current mixed signal comprises an alternating current energy signal and an alternating current information signal, and the information signal takes the energy signal as a carrier signal; The control method of the mother and daughter satellite wireless energy and information synchronous transmission system comprises the following steps: The mother star energy surplus and deficiency state and the daughter star energy surplus and deficiency state are collected by a mother star telemetry remote control module PTMTC; According to the mother star energy surplus and deficiency state and the daughter star energy surplus and deficiency state, the switching frequency fs and the duty cycle Dppc of a wireless primary side power conversion module PPC are adjusted, and then the working mode of an inter-satellite energy and information transmission synchronous transmission channel is controlled, the working mode comprising an inter-satellite normal energy transmission mode and an inter-satellite standby energy transmission mode, and the inter-satellite normal energy transmission mode comprising a daughter star local power supply section and a daughter star local remote joint power supply section.

2. The mother-child satellite wireless energy and information synchronous transmission system according to claim 1, characterized in that, The wireless primary side power conversion module PPC comprises an energy inverter circuit, a primary side energy compensation network and an information extraction circuit, the energy inverter circuit inverts a stable direct current full-regulation bus Vr to generate an alternating current energy signal, the primary side coil is connected to the inductor of the primary side energy compensation network and the information extraction circuit through the alternating current energy signal, and the switching frequency fs and the duty cycle Dppc of the alternating current energy signal are set by the mother star telemetry remote control module PTMTC; the alternating current mixed signal transmitted by the primary side coil is loaded with the high-frequency alternating current information signal transmitted by the secondary side coil, the information extraction circuit extracts the effective component of the high-frequency alternating current signal by using the LC resonance principle, and the energy surplus and deficiency state information transmitted in the information extraction circuit is restored after being processed by the signal demodulation circuit, and finally sent to the mother star telemetry remote control module PTMTC for collection.

3. The mother-child satellite wireless energy and information synchronous transmission system according to claim 2, characterized in that, The wireless secondary side power conversion module SPC comprises a secondary side compensation network, an information loading circuit and an energy rectifier circuit, the alternating current energy signal transmitted by the secondary side coil is connected to the energy rectifier circuit through the inductor of the secondary side compensation network and the information loading circuit, and a stable direct current voltage Vspc generated after rectification and filtering is sent to the non-regulation bus Vu through the bus adapter CBCR to realize the transmission of inter-satellite energy; the amplitude of Vspc is determined by the switching frequency fs and the duty cycle Dppc of the wireless primary side power conversion module PPC, the high-frequency alternating current information signal generated by the daughter star telemetry remote control module CTMTC and the signal modulation circuit is injected into the alternating current energy signal by the information loading circuit LC high-frequency resonance to form an alternating current mixed signal, and the alternating current mixed signal is transmitted to the wireless primary side power conversion module PPC of the mother star through coil coupling.

4. The mother-child satellite wireless energy and information synchronous transmission system according to claim 1, characterized in that, The primary side coil is installed on the surface of the mother star, the secondary side coil is installed on the surface of the daughter star, and the installation surfaces of the primary side coil and the secondary side coil are adjacent surfaces of the mother star and the daughter star.

5. The mother-child satellite wireless energy and information synchronous transmission system according to claim 4, characterized in that, The primary side coil and the secondary side coil each comprise a high magnetic permeability magnetic core, a winding wire and a shell support device.

6. The mother-child satellite wireless energy and information synchronous transmission system according to claim 5, characterized in that, The parent star power controller PPCU further comprises 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 parent 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 parent star battery PBAT; the power input end of the battery discharger PBDR is connected to the parent star battery PBAT, and the power output end is connected to the full-regulation bus Vr.

7. The mother-child satellite wireless energy and information synchronous transmission system according to claim 6, characterized in that, The sub-star power controller CPCU further comprises n solar array power regulators CAPR, a battery power interface unit BCI and a battery charge manager BCM; The power input end of the solar array power regulator CAPR is connected to the sub-star solar array CSAW, and the power output end is connected to the non-regulation bus Vu; the power input end of the battery power interface unit BCI is connected to the non-regulation bus Vu, and the power output end is connected to the sub-star battery CBAT.

8. The mother-child satellite wireless energy and information synchronous transmission system according to claim 7, characterized in that, The battery charge manager BCM adopts a double-section control mode of a local power supply section and a local remote joint power supply section, internally contains two closed-loop PID control loops, a first PID control loop is a remote energy control loop, an output signal Vbcmrmt controls the size of an output current Icbcr of the bus adapter CBCR; a second PID loop is a local energy control loop, an output signal Vbcmlocal controls the size of an output current Icapr of the solar array power regulator CAPR.

Images