Three-in-one carrier rocket power supply and distribution energy management system and method

Abstract

The invention discloses a three-in-one carrier rocket power supply and distribution energy management system, and the system comprises a first-stage power management module which is used for managing the first-stage power supply and distribution energy management of a rocket; the second-stage power management module is used for managing second-stage power supply and distribution energy of the rocket; the power supply and distribution energy management comprises control single machine management, measurement single machine management and load management; the ground launch control module is used for respectively controlling the first-stage power supply management module and the second-stage power supply management module, and is respectively connected with the first-stage power supply management module and the second-stage power supply management module through RS422 or Ethernet interfaces; and the ground power supply module is used for providing electric energy for the first-stage power supply management module and the second-stage power supply management module respectively, and is electrically connected with the first-stage power supply management module and the second-stage power supply management module respectively.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of power supply and distribution devices of space vehicles, and particularly relates to a three-electricity-in-one launch vehicle power supply and distribution energy management system and method. BACKGROUND

[0002] A new generation of launch vehicles faces complex flight tasks such as landing area control and vertical take-off and landing, and puts forward higher requirements for the reliability, intelligence and emergency response capability of the power supply and distribution system. However, the traditional power supply and distribution system adopts a solidified electromechanical design, and the control, measurement, timing load and other subsystems are powered separately, resulting in a large number of batteries and power distributors on the rocket, a complex cable network, and a lack of flexible switching control capability after the power distributor is powered on, which makes it difficult to adapt to complex task requirements. At the same time, ground operation relies on human intervention, batteries need to be charged multiple times and rely on special charging power sources and cables, and battery warming needs to be controlled by ground measurement and control systems and special warming power sources. The ground power supply is large in scale, has many rocket-ground interfaces and complex control processes, and has low test efficiency. Although the description of invention patents CN106428589A and CN106428589A involves power supply and distribution control, fault monitoring, state self-checking and other functions based on solid-state power control technology, no systematic solution is proposed for the integration of the three-electricity-in-one of the launch vehicle's hierarchical energy management, ground power supply, warming and charging, and the rocket's autonomous management, which still has a gap with the task requirements of the new generation of rockets. SUMMARY

[0003] To solve the above problems, the present application provides a three-electricity-in-one launch vehicle power supply and distribution energy management system and method, which realizes the generalization and simplification of the power supply and distribution system, provides a method for simplifying the ground power supply configuration, realizes online automatic warming and automatic charging on the rocket, and reduces the dependence on the ground launch control system. The power management center and battery configuration of the first and second level power supply and distribution systems on the rocket are completely the same, which simplifies the single machine type and reduces the number, effectively reduces the development cost and shortens the development cycle, and makes up for the technical gap and architectural gap of the existing service type. In addition, the real-time residual energy management method provided by the present application can improve the tolerance of electrical system faults during rocket flight and improve the safety of flight.

[0004] The first aspect of the present application provides a three-electricity-in-one launch vehicle power supply and distribution energy management system, comprising: a first power management module for managing the power supply and distribution energy management of the first level of the rocket; a second power management module for managing the power supply and distribution energy management of the second level of the rocket; the power supply and distribution energy management includes control single machine management, measurement single machine management and load management; The ground control module is used to control the first-level power management module and the second-level power management module respectively, and is connected to the first-level power management module and the second-level power management module respectively via RS422 or Ethernet interface; The ground power module is used to provide electrical energy to the first-level power management module and the second-level power management module respectively, and is electrically connected to the first-level power management module and the second-level power management module respectively.

[0005] Preferably, the first-level power management module and the second-level power management module each include an unprotected module, a protected module, a battery module, a CPU module, and a power module. The unprotected module is used to control the power supply to the rocket system unit and corresponding load. The protected module is used to control the power supply to the rocket's measurement system unit. The battery module is electrically connected to the unprotected module, the protected module, and the power module respectively. The power module is electrically connected to the CPU module. The CPU module is connected to the unprotected module, the protected module, the battery module, and the power module via signals.

[0006] Preferably, the battery module includes a first battery and a second battery, and the unprotected module includes a first unprotected module and a second unprotected module. The first battery is electrically connected to the first unprotected module, the protected module, the battery module, and the power module. The second battery is electrically connected to the second unprotected module. The capacity of the first battery and the second battery is 20Ah. The first battery and the second battery are respectively provided with a charging module and a heating module. The charging module is provided with a charging relay, and the heating module is provided with a heating relay and a heating belt. The busbar of the ground power module, the charging relay, and the CPU module are connected. The busbar of the ground power module, the heating belt, the heating relay, and the CPU module are also connected.

[0007] Preferably, the CPU module includes a first CPU and a second CPU, which are connected in parallel, and the charging relay and the heating relay are both dual-redundant switches.

[0008] Preferably, the protection module includes a drive circuit, a solid-state relay, and a resistor. The drive circuit and the solid-state relay are connected in series, and the solid-state relay and the resistor are connected in parallel. The resistance value of the resistor is: In the formula The current protection threshold is preset. If the current of a single unit exceeds the protection threshold, the relay with the protection module will cut off the power supply to the single unit in real time.

[0009] Preferably, the ground power module comprises four DC stabilized power supplies, two of which are electrically connected to the first power management module, and the other two of which are electrically connected to the second power management module, the voltage of the DC stabilized power supply is dynamically adjusted to 24-40V, and the output current of the DC stabilized power supply is 5-20A.

[0010] The second aspect of the application provides a three-in-one launch vehicle power supply and distribution energy management method, applied to the three-in-one launch vehicle power supply and distribution energy management system described in any of the above, comprising: If the rocket is in a state of waiting for launch, the ground launch control module collects data information of the first power management module and the second power management module, and drives the ground power module to supply power to the first power management module and the second power management module based on the data information; If the rocket is in a state of launching, the ground launch control module controls the first power management module and the second power management module to switch from the ground power module to the corresponding battery module, starts a timing task based on the take-off time, and the timing task includes the second power management module driving the second load to supply power to prevent the second load from malfunctioning, and the start time of the timing task is the take-off time delayed by a preset time.

[0011] Preferably, it further comprises a monitoring task: the first power management module and the CPU module of the first power management module collect corresponding battery module data, and the battery module data includes temperature data and voltage data; Based on the battery module data, the CPU module drives the line package to control the opening and closing of the corresponding charging relay and the heating relay to realize temperature management and energy management of the battery module.

[0012] Preferably, based on the battery module data, the CPU module drives the line package to control the opening and closing of the corresponding charging relay and the heating relay, which further comprises: When the rocket is in a state of waiting for launch, if the temperature data of the battery module is less than a preset temperature threshold, the CPU module connected to the battery module drives the heating relay to close to realize power supply from the ground launch control module to the heating belt, otherwise the CPU module drives the heating relay to open, and if the voltage data of the battery module is less than a preset voltage threshold, the CPU module connected to the battery module drives the charging relay to close to realize power supply from the ground launch control module to the corresponding power management module, otherwise the CPU module drives the charging relay to open.

[0013] Preferably, the first power supply management module and the second power supply management module are respectively provided with a diagnosis task if the rocket is in a flight state, and the specific rules are as follows: the residual power of the battery module of the power supply management module is acquired in real time, the corresponding load connected with the protection module is driven to be turned off based on the residual power and a preset power threshold, the turning-off priority is acquired based on the preset important dictionary data and the detected power consumption data, and the protection module is driven to turn off the connection of the corresponding load if the turning-off priority is high.

[0014] Compared with the prior art, the method for simplifying ground power supply configuration has the following advantages and positive effects: online automatic heating and automatic charging on the rocket are realized, the dependence on the ground launch control system is reduced, the power supply management center and the battery configuration of the first and second power supply and distribution systems on the rocket are completely the same, the single structure is simplified and the quantity is reduced, the development cost and period can be effectively reduced, and the technical gap and architecture gap of the existing active model are made up. In addition, the real-time residual energy management method can improve the tolerance of the electrical system fault during the flight of the rocket and improve the safety of the flight. BRIEF DESCRIPTION OF DRAWINGS

[0015] The specific embodiments of the present application will be further described in detail below with reference to the accompanying drawings, in which: Figure 1 FIG. 1 is a schematic diagram of the framework of a three-electricity-in-one launch vehicle power supply and distribution energy management system in the present application; Figure 2 FIG. 2 is a schematic diagram of the framework of online power supply, heating and charging in the three-electricity-in-one in the present application; Figure 3 FIG. 3 is a schematic diagram of the framework of a non-protection module in the present application. DETAILED DESCRIPTION

[0016] The present application will be further described in detail below with reference to the accompanying drawings and specific embodiments. The advantages and features of the present application will be more apparent according to the following description and claims. It should be noted that the drawings are very simplified and non-precise ratios are used, only for the purpose of facilitating and clarifying the purpose of explaining the embodiments of the present application.

[0017] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present application are only used to explain the relative position relationship, movement condition, etc. between the components in a certain specific posture (as shown in the drawings), and if the specific posture changes, the directional indications will also change accordingly.

[0018] First embodiment Referring to Figure 1 , Figure 2 and Figure 3The first aspect of the present application provides a three-in-one launch vehicle power supply and distribution energy management system, comprising: A first-level power management module for managing the power supply and distribution energy management of the first stage of the rocket; A second-level power management module for managing the power supply and distribution energy management of the second stage of the rocket; the power supply and distribution energy management includes single-machine control, measurement single-machine management, and load management; A ground launch control module for controlling the first-level power management module and the second-level power management module, respectively, and connected to the first-level power management module and the second-level power management module through an RS422 or Ethernet interface; A ground power module for providing power energy for the first-level power management module and the second-level power management module, respectively, and electrically connected to the first-level power management module and the second-level power management module.

[0019] The power conversion refers to the conversion from the ground power supply to the battery power supply of the rocket before launching. The power supply and distribution energy management system of the three-in-one launch vehicle includes four modules, namely, the first-stage power management module, the second-stage power management module, the ground launch control module and the ground power module. The first-stage power management module and the second-stage power management module are respectively arranged in the space of the first stage of the rocket and the space of the second stage of the rocket. The ground launch control module is provided with a cable network and a communication interface, acquires data information of the first-stage power management module and the second-stage power management module, and supports the transmission of information to the corresponding power management module. The first-stage power management module and the second-stage power management module are respectively provided with an unprotected module, a protected module, a battery module, a CPU module and a power module. The first-stage power management module and the second-stage power management module respectively include an unprotected module, a protected module, a battery module, a CPU module and a power module. The unprotected module is used for controlling the power supply for the rocket control system single machine and the corresponding load, the protected module is used for controlling the power supply for the measurement system single machine of the rocket, the battery module is electrically connected with the unprotected module, the protected module and the power module, the power module is electrically connected with the CPU module, and the CPU module is connected with the unprotected module, the protected module, the battery module and the power module through a signal connection. The battery module includes a first battery and a second battery, the unprotected module includes a first unprotected module and a second unprotected module, the first battery is electrically connected with the first unprotected module, the protected module, the battery module and the power module, the second battery is electrically connected with the second unprotected module, the capacity of the first battery and the second battery is 20 Ah respectively, the first battery and the second battery are respectively provided with a charging module and a warming module, the charging module is provided with a charging relay, the warming module is provided with a warming relay and a heating belt, the bus of the ground power module, the charging relay and the CPU module are connected, and the bus of the ground power module, the heating belt, the warming relay and the CPU module are connected. The CPU module includes a first CPU and a second CPU, the first CPU and the second CPU are connected in parallel, and the charging relay and the warming relay are respectively provided with a double-redundancy switch. The ground power module includes four identical DC stabilized power supplies, two of which are electrically connected with the first-stage power management module, and the other two of which are electrically connected with the second-stage power management module. The voltage of the DC stabilized power supply is dynamically adjusted to 24-40 V, and the output current of the DC stabilized power supply is 5-20 A. The ground power module has a current limiting capability. The independent power supply strategy of each rocket body stage is realized through the first / second special power management module, the differentiated power consumption demand of different flight stages (including the boost stage and the stage separation) is adapted, and the cross-stage electromagnetic coupling interference is avoided. Dynamic load matching: based on the measurement single machine management and the load management mechanism, the voltage / current data of each stage can be collected in real time, the energy output can be intelligently adjusted, and the stable power supply of the key loads such as the propellant delivery pump and the attitude control engine can be ensured.The ground launch control module adopts a dual communication redundancy design (RS422 industrial bus + Ethernet), synchronously controls two-stage power supply systems, and realizes full-process automatic control such as pre-launch detection, countdown sequence triggering, emergency shutdown, and the like. When an abnormality occurs in a certain stage, the corresponding power management module can be decided by a ground command to make a power-off or power-on decision, thereby improving the system survivability.

[0020] Preferably, the first-stage power management module and the second-stage power management module each include an unprotected module, a protected module, a battery module, a CPU module, and a power module, the unprotected module is configured to control power supply for a rocket system single machine and a corresponding load, the protected module is configured to control power supply for a measurement system single machine of the rocket, the battery module is electrically connected to the unprotected module, the protected module, and the power module, respectively, the power module is electrically connected to the CPU module, and the CPU module is connected to the unprotected module, the protected module, the battery module, and the power module through a signal connection.

[0021] The protected module is mainly configured to supply power to the measurement single machine and has the ability to automatically cut off the power supply branch of the measurement system in an emergency. The first unprotected module and the second unprotected module supply power to the control system and the time sequence load, respectively. Through modular design and intelligent scheduling strategy, the power supply system of the launch vehicle realizes a technical leap from passive power distribution to active energy management under the premise of ensuring high reliability, and is particularly suitable for new generation reusable launch vehicles, deep space probes, and other space missions that have strict requirements on power supply systems.

[0022] Referring to Figure 2 , preferably, the battery module includes a first battery and a second battery, the unprotected module includes a first unprotected module and a second unprotected module, the first battery is electrically connected to the first unprotected module, the protected module, the battery module, and the power module, the second battery is electrically connected to the second unprotected module, the first battery and the second battery each have a capacity of 20 Ah, the first battery and the second battery are each provided with a charging module and a warming module, the charging module is provided with a charging relay, the warming module is provided with a warming relay and a heating belt, a bus of the ground power module, the charging relay, and the CPU module are connected, and the bus of the ground power module, the heating belt, the warming relay, and the CPU module are connected.

[0023] Optionally, the battery module adopts a lithium battery, has multiple reuse capabilities, and is respectively provided with two batteries, i.e., a first battery and a second battery, the first battery and the second battery are respectively configured to supply power to time sequence loads such as first-stage and second-stage pyrotechnics, solenoid valves, motors, and an inertial measurement unit (IMU) and temperature control.

[0024] Compared with the prior art, the technical scheme of the application does not need to configure a special heating power supply and a heating cable, a temperature sensor of a battery module of a power management center (including a first power management module and a second power management module) collects temperature data, a CPU module is driven to make a decision based on the temperature data and to open a heating relay. When the rocket is in a state of waiting for launching, if the temperature data is less than a preset temperature threshold, the CPU module controls the heating relay to be closed, a ground power supply module passes through a bus to flow through the heating relay, so as to supply power to a heating belt inside the battery module, the lithium battery is heated, when the lithium battery is heated to a specified temperature, the CPU module controls the heating relay to be opened, and the heating belt stops heating. The process can be completely autonomously performed on the rocket or manually controlled by the ground. After power switching, the lithium battery is not heated again, the charging of the battery module does not need to be separately configured with a special ground charging power supply and a charging cable, the power management center collects and uniformly supplies power to the input end of the battery module, if the voltage of the battery module is lower than a set lower limit before power switching, the CPU module controls a charging relay of the corresponding power management center (including the first power management module and the second power management module) to be closed, the ground power supply module passes through the bus to flow through the charging relay, so as to drive the charging port of the battery module to be supplied with power, the battery module is charged, when the voltage of the lithium battery rises to a specified voltage, the CPU module controls the charging relay to be opened, and the charging of the battery is stopped. The process can be completely autonomously performed on the rocket or manually controlled by the ground. After power switching, the lithium battery is not charged again. Through the innovative path of hardware resource pooling and software defined function, the power supply and distribution system of the launch vehicle has a flexible characteristic, provides a high-reliability, lightweight and intelligent energy management solution for a new generation of reusable launch vehicle and deep space exploration mission, and has significant military and economic benefits and technical radiation value.

[0025] Preferably, the CPU module comprises a first CPU and a second CPU, the first CPU and the second CPU are connected in parallel, and the charging relay and the heating relay each adopt a double-redundancy switch.

[0026] The three-layer protection of hardware redundancy, software fault tolerance and process control makes the power supply and distribution system achieve the progressive reliability targets of fault safety, fault containment and fault harmlessness, and is particularly suitable for manned spaceflight, intercontinental missiles and other high-value tasks.

[0027] Referring to Figure 3 Preferably, the protection module comprises a driving circuit, a solid-state relay and a resistor, the driving circuit and the solid-state relay are connected in series, and the solid-state relay and the resistor are connected in parallel, wherein the resistance value of the resistor is: In the formula, The preset current protection threshold is used, and if the single machine current exceeds the protection threshold, the relay with the protection module will cut off the power supply of the single machine in real time.

[0028] The resistance calculation mode is related to the selection of the solid-state relay, and the design calculation can be carried out according to the corresponding product manual, and the application does not make specific limitations. The resistance is adaptively designed in different scenes to meet the main loop current size in real time. Compared with the traditional Hall sensor scheme, the pure resistance sampling has the characteristics of low cost, fast response and controllable temperature drift. The disadvantages of slow response, short service life and non-adjustable of the traditional electromagnetic relay are solved, and the high cost problem of the special IC chip is avoided.

[0029] Preferably, the ground power module includes 4 DC stabilized power supplies, 2 of which are electrically connected with the first power management module, and the other 2 are electrically connected with the second power management module. The voltage of the DC stabilized power supply is dynamically adjusted to 24-40V, and the output current of the DC stabilized power supply is 5A-20A.

[0030] The ground power module and the first and second power management modules form a physically isolated power supply channel; a single power failure does not affect the normal power supply of the corresponding level, improving the system availability. Before launch, if an abnormal power supply is detected at a certain location, the standby unit can be replaced directly without adjusting the overall system architecture.

[0031] Second embodiment The second aspect of the application provides a three-in-one launch vehicle power supply and distribution energy management method, applied to the three-in-one launch vehicle power supply and distribution energy management system of any one of the above, comprising: If the rocket is in a pre-launch state, the ground launch control module collects data information of the first power management module and the second power management module, and drives the ground power module to supply power to the first power management module and the second power management module based on the data information; If the rocket is in a launch state, the ground launch control module controls the first power management module and the second power management module to switch from the ground power module to the corresponding battery module, starts a timing task based on the takeoff time, and the timing task includes the second power management module driving the second load to supply power to prevent the second load from malfunctioning, and the start time of the timing task is the takeoff time delayed by a preset time. Through closed-loop control of execution, feedback and correction, the power supply and distribution system is changed from passive response to active adaptation, and seamless connection is realized by autonomous driving and switching of the CPU module, and fault early warning is realized by full parameter acquisition; Modular design supports rapid reconstruction and upgrading. The preset time in this scheme can be set to 50s or other constants, and this embodiment does not make limitations.

[0032] Preferably, it also includes a monitoring task: the first-level power management module and the CPU module of the first-level power management module collect corresponding battery module data, including temperature data and voltage data; Based on the battery module data, the CPU module drives the line package to control the opening and closing of the corresponding charging relay and heating relay to achieve temperature management and power management of the battery module.

[0033] Through the complete closed loop of perception, decision-making, and execution, battery management is transformed from passive protection to active optimization, especially suitable for reusable launch vehicles, deep space probes, and other scenarios with strict energy system requirements.

[0034] Preferably, based on the battery module data, the CPU module drives the line package to control the opening and closing of the corresponding charging relay and heating relay, which further includes: When the rocket is in a pre-launch state, if the temperature data of the battery module is less than the preset temperature threshold, the CPU module connected to the battery module drives the heating relay to close to implement ground launch control module power supply to the heating band, otherwise the CPU module drives the heating relay to open circuit, if the voltage data of the battery module is less than the preset voltage threshold, the CPU module connected to the battery module drives the charging relay to close to implement ground launch control module power supply to the corresponding power management module, otherwise the CPU module drives the charging relay to open circuit.

[0035] By comparing the temperature data with the preset temperature threshold, the CPU module drives the heating relay to open or close circuit, and by comparing the voltage data with the preset voltage threshold, the CPU module drives the heating relay to open or close circuit, ensuring that the battery SOC (state of charge) is stable in the safe interval, preventing lithium dendrite growth caused by direct large current discharge at low temperature (which may cause short circuit).

[0036] Preferably, if the rocket is in flight, the first-level power management module and the second-level power management module are provided with a diagnosis task, the specific rules are: real-time acquisition of the remaining power of the battery module of the power management module, based on the remaining power and the preset power threshold, the corresponding protected module connected load is driven to shut down based on the decision, the specific shutdown rules are based on the preset important dictionary data and the detected power consumption data to obtain the shutdown priority, and the higher the shutdown priority, the higher the drive protected module to shut down the connection of the corresponding load.

[0037] Two-stage power management module collects the residual capacity of the corresponding battery module, and compares with the preset threshold, which can identify the risk early and extrapolate the endurance time combined with the current discharge rate, to provide decision basis for the flight control system. Based on the pre-stored importance dictionary and real-time power consumption data, a load shutdown priority table is dynamically generated. High-power low-value loads are placed in the front row, and core devices (such as GPS receivers) are placed at the end; if a device suddenly has short-time high-power consumption (such as image devices), temporarily lower its priority to avoid false triggering of global power-off. The priority model trained by historical task data improves the survival rate of key devices.

[0038] In the description of the present application, it should be noted that the terms "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship commonly used when the product of the present application is placed, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second" and the like are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0039] It should also be noted that unless otherwise explicitly specified and limited, the terms "set", "connected" should be broadly understood, for example, can be fixedly connected, can be detachably connected, or integrally connected; can be directly connected, or indirectly connected through an intermediate medium; can be internal communication of two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0040] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific implementation of the above-described system and device can refer to the corresponding process in the foregoing method embodiments.

[0041] The embodiments of the present application are described in detail above in combination with the drawings, but the present application is not limited to the above-described embodiments. Even if various changes are made to the present application, as long as these changes fall within the scope of the claims of the present application and their equivalent technologies, they still fall within the protection scope of the present application.

Claims

1. A power supply and distribution energy management system for a launch vehicle integrating three electrical systems, characterized in that, include: The first-level power management module is used to manage the power supply and distribution energy of the rocket's first stage; The second-level power management module is used to manage the power supply and distribution energy of the second stage of the rocket; the power supply and distribution energy management includes control unit management, measurement unit management, and load management; The ground control module is used to control the first-level power management module and the second-level power management module respectively, and is connected to the first-level power management module and the second-level power management module respectively via RS422 or Ethernet interface; The ground power module is used to provide electrical energy to the first-level power management module and the second-level power management module respectively, and is electrically connected to the first-level power management module and the second-level power management module respectively.

2. The integrated power supply and distribution energy management system for launch vehicles according to claim 1, characterized in that, The first-level power management module and the second-level power management module each include an unprotected module, a protected module, a battery module, a CPU module, and a power module. The unprotected module is used to control the power supply to the rocket system unit and corresponding load. The protected module is used to control the power supply to the rocket's measurement system unit. The battery module is electrically connected to the unprotected module, the protected module, and the power module respectively. The power module is electrically connected to the CPU module. The CPU module is connected to the unprotected module, the protected module, the battery module, and the power module via signals.

3. The integrated power supply and distribution energy management system for a launch vehicle according to claim 2, characterized in that, The battery module includes a first battery and a second battery. The unprotected module includes a first unprotected module and a second unprotected module. The first battery is electrically connected to the first unprotected module, the protected module, the battery module, and the power module. The second battery is electrically connected to the second unprotected module. The capacity of the first battery and the second battery is 20Ah. The first battery and the second battery are respectively provided with a charging module and a heating module. The charging module is provided with a charging relay. The heating module is provided with a heating relay and a heating belt. The busbar of the ground power module, the charging relay, and the CPU module are connected. The busbar of the ground power module, the heating belt, the heating relay, and the CPU module are connected.

4. The integrated power supply and distribution energy management system for a launch vehicle according to claim 3, characterized in that, The CPU module includes a first CPU and a second CPU, which are connected in parallel. The charging relay and the heating relay are both dual-redundant switches.

5. The integrated power supply and distribution energy management system for a launch vehicle according to claim 2, characterized in that, The protection module includes a drive circuit, a solid-state relay, and a resistor. The drive circuit and the solid-state relay are connected in series, and the solid-state relay and the resistor are connected in parallel. The resistance value of the resistor is: In the formula The current protection threshold is preset. If the current of a single unit exceeds the protection threshold, the relay with the protection module will cut off the power supply to the single unit in real time.

6. The integrated power supply and distribution energy management system for a launch vehicle according to claim 1, characterized in that, The ground power module includes four DC regulated power supplies, two of which are electrically connected to the first-level power management module, and the other two are electrically connected to the second-level power management module. The voltage of the DC regulated power supplies is dynamically adjusted from 24 to 40V, and the output current of the DC regulated power supplies is from 5A to 20A.

7. A method for managing the power supply and distribution energy of a three-in-one launch vehicle, applied to the power supply and distribution energy management system of the three-in-one launch vehicle as described in any one of claims 1 to 6, characterized in that, include: If the rocket is in a ready-to-launch state, the ground launch control module collects data information from the first-stage power management module and the second-stage power management module, and drives the ground power module to supply power to the first-stage power management module and the second-stage power management module respectively based on the data information; If the rocket is in launch mode, the ground launch control module controls the first-stage power management module and the second-stage power management module to switch the power supply from the ground power module to the corresponding battery module. Based on the takeoff time, a timed task is started. The timed task includes the second-stage power management module driving the power supply to the secondary load to prevent the secondary load from malfunctioning. The start time of the timed task is a preset time after the takeoff time.

8. The power supply and distribution energy management method for a three-in-one launch vehicle according to claim 7, characterized in that, It also includes monitoring tasks: the first-level power management module and the CPU module of the first-level power management module collect corresponding battery module data, including temperature data and voltage data; Based on the battery module data, the CPU module drives the winding to control the opening and closing of corresponding charging relays and heating relays, thereby realizing the temperature management and power management of the battery module.

9. The power supply and distribution energy management method for a three-in-one launch vehicle according to claim 8, characterized in that, The step of controlling the opening and closing of the corresponding charging relay and heating relay by driving the coil through the CPU module based on the battery module data further includes: When the rocket is in a ready-to-launch state, if the temperature data of the battery module is less than a preset temperature threshold, the CPU module connected to the battery module drives the heating relay to close, so that the ground launch control module supplies power to the heating zone; otherwise, the CPU module drives the heating relay to open. If the voltage data of the battery module is less than a preset voltage threshold, the CPU module connected to the battery module drives the charging relay to close, so that the ground launch control module supplies power to the corresponding power management module; otherwise, the CPU module drives the charging relay to open.

10. The power supply and distribution energy management method for a three-in-one launch vehicle according to claim 7, characterized in that, It also includes diagnostic tasks for the first-stage power management module and the second-stage power management module when the rocket is in flight. The specific rules are as follows: the remaining power of the battery module of the power management module is obtained in real time, and the corresponding load connected to the protection module is shut down based on the remaining power and a preset power threshold. The specific shutdown rules are based on preset important dictionary data and detected power consumption data to obtain the shutdown priority. If the shutdown priority is high, the protection module is driven to shut down the connection of the corresponding load.

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