Reconfigurable power supply control and power distribution system and method for near space low-speed aircraft

Abstract

The invention relates to the technical field of near space aircraft energy systems, and provides a reconfigurable power supply control and power distribution system and method for a near space low-speed aircraft. The system comprises a solar cell array, a lithium battery, an electric load and a reconfigurable power supply control and distribution network. The network connects the solar battery bus, the lithium battery bus and the load bus. The network comprises N bidirectional power converters, N contactors and a reconfiguration controller, the front end of the bidirectional power converter is connected with a solar cell bus or a load bus through a contactor. And the reconfiguration controller is used for controlling the pull-in state of the contactor according to the sampling result of each bus, dynamically configuring the bidirectional power supply converter as a power supply controller or a distributor, and uniformly controlling the pulse width of the bidirectional power supply converter. Flexible configuration of the number of power controllers and distributors in a near space low-speed aircraft is achieved, and the weight of the aircraft is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of energy systems for near-space aircraft, and particularly to a reconfigurable power supply control and power distribution system and method for near-space low-speed aircraft. Background Art

[0002] Near-space low-speed aircraft, such as stratospheric airships, high-altitude balloons, etc., have characteristics such as long endurance and large payload capacity, and have extremely high requirements for the reliability and efficiency of the energy system. A cyclic energy system with solar energy as the energy source is one of the key technologies for near-space low-speed aircraft to achieve long-term flight. This system includes a solar cell array, a lithium battery pack, a power supply controller, a distributor, etc. The power supply controller performs maximum power point tracking (MPPT) on the solar cell array, converts the electrical energy output by the solar cell array, and then controls the charging of the lithium battery pack. The distributor performs power conversion on the output bus of the lithium battery, converts the voltage of the lithium battery output bus into the voltage required by the load, and supplies power to the payload of the near-space low-speed aircraft.

[0003] Existing energy system solutions can realize the power generation, energy storage, and power consumption control of the cyclic energy system of near-space low-speed aircraft, and have been verified by tests. However, in the design and test of the cyclic energy system of near-space low-speed aircraft, it has also been found that the existing technical solutions have a large redundancy in terms of volume and weight, and cannot further meet the requirements for weight reduction of near-space low-speed aircraft. Summary of the Invention

[0004] The present invention provides a reconfigurable power supply control and power distribution system and method for near-space low-speed aircraft to solve the problem that the existing technology has a large redundancy in terms of volume and weight and cannot further meet the requirements for weight reduction of near-space low-speed aircraft, and to realize the flexible configuration of the number of power supply controllers and distributors in near-space low-speed aircraft, so as to reduce the weight of near-space low-speed aircraft. The technical solutions proposed by the present invention are as follows: In a first aspect, the present invention provides a reconfigurable power supply control and power distribution system for near-space low-speed aircraft, including: A solar cell array; A lithium battery; An electrical load; A reconfigurable power supply control and power distribution network, connecting the solar cell bus, the lithium battery bus, and the load bus; wherein, the solar cell bus is the bus led out from the solar cell array, the lithium battery bus is the bus led out from the lithium battery, and the load bus is the bus for supplying power to the electrical load; The reconfigurable power supply control and power distribution network includes N bidirectional power converters, N contactors, and a reconfiguration controller; The back end of the bidirectional power converter is connected to the lithium battery bus, and the front end is connected to the solar cell bus or the load bus through the contactor. The reconstruction controller is used to sample the solar cell bus, the load bus, and the lithium battery bus to obtain sampling results. According to the sampling results of the solar cell bus, the load bus, and the lithium battery bus, it controls the suction state of the contactor, dynamically configures the bidirectional power converter as a power controller or a power distributor, and uniformly controls the pulse width of the bidirectional power converter to achieve maximum power tracking control, lithium battery charging control, and load power supply control in the cyclic energy system of the near-space low-speed aircraft.

[0005] Optionally, the contactor includes: A first port connected to the solar cell bus; A second port connected to the load bus; A third port connected to the bidirectional power converter; The contactor controls the third port to be connected to the first port or the second port through a wire coil. Wherein, when the third port is connected to the first port, the bidirectional power converter is configured as a power controller for power conversion between the solar cell bus and the lithium battery bus; when the third port is connected to the second port, the bidirectional power converter is configured as a power distributor for power conversion between the lithium battery bus and the load bus.

[0006] Optionally, the control logic of the reconstruction controller includes: The contactor array control logic is used to dynamically adjust the number of power controllers and power distributors according to the maximum power generation of the solar cell array and the power consumption of the load bus. The lithium battery charging control logic is used to control the bidirectional power converter configured as a power controller to perform maximum power tracking and constant voltage or constant current charging of the lithium battery. The load power supply control logic is used to control the bidirectional power converter configured as a power distributor to perform constant voltage control and constant current protection of the load bus.

[0007] Optionally, the sampling results include the real-time time and position information of the aircraft and the power consumption of the load bus; the contactor array control logic includes: A first thread for calculating the maximum power generation of the solar cell array according to the real-time time and position information of the aircraft, determining the required number of power controllers N1 according to the maximum power generation of the solar cell array and the rated power of the bidirectional power converter, and configuring the remaining bidirectional power converters as power distributors, and the number of power distributors is N - N1; A second thread, and the second thread works synchronously and quasi-parallel with the first thread; The second thread is used to monitor the power consumption of the load bus in real time. When the power consumption of the load bus exceeds the first preset multiple of the total rated power of the power distributor, the first thread is paused and the number of power distributors is increased until the power consumption of the load bus is lower than the second preset multiple of the total rated power of the power distributor, and then the first thread is resumed.

[0008] Optionally, the sampling result includes the lithium battery voltage and the lithium battery charging current; the lithium battery charging control logic is as follows: In the first working state, if the lithium battery voltage reaches the constant voltage point, the power supply controller enters the constant voltage working mode and calculates the duty ratio of the next cycle according to the constant voltage control method. In the second working state, if the lithium battery voltage does not reach the constant voltage point and the lithium battery charging current reaches the constant current point, the power supply controller enters the constant current working mode and calculates the duty ratio of the next cycle according to the constant current control method. If the above first working state or second working state is not satisfied, the power supply controller enters the maximum power tracking mode and calculates the duty ratio of the next cycle according to the maximum power tracking control method. The duty ratios of all power supply controllers are uniformly configured by the reconstruction controller.

[0009] Optionally, the sampling result includes the load bus current; the load power supply control logic includes: If the load bus current exceeds the total rated current of the power distributor, the power distributor enters the constant current protection mode and calculates the duty ratio of the next cycle according to the output constant current method. If the load bus current does not exceed the total rated current of the power distributor, the power distributor enters the constant voltage working mode and calculates the duty ratio of the next cycle according to the output constant voltage method. The duty ratios of all power distributors are uniformly configured by the reconstruction controller.

[0010] In a second aspect, the present invention provides a reconfigurable power supply control and power distribution method for a near-space low-speed aircraft, using the reconfigurable power supply control and power distribution system for a near-space low-speed aircraft as described in the first aspect. The method includes: Sampling the solar cell bus, the load bus and the lithium battery bus through the reconstruction controller to obtain sampling results; Controlling the suction state of the contactor according to the sampling results of the solar cell bus, the load bus and the lithium battery bus through the reconstruction controller, dynamically configuring the bidirectional power converter as a power supply controller or a power distributor, and uniformly controlling the pulse width of the bidirectional power converter to achieve maximum power tracking control, lithium battery charging control and load power supply control in the near-space low-speed aircraft cyclic energy system.

[0011] Optionally, the sampling results include the real-time time and position information of the aircraft, and the power consumption of the payload bus; the contactor array control is achieved through the following methods: The first thread calculates the maximum power generation of the solar cell array based on the real-time time and position information of the aircraft, determines the required number N1 of power controllers based on the maximum power generation of the solar cell array and the power of the bidirectional power converter, and configures the remaining bidirectional power converters as distributors, with the number of distributors being N - N1; The second thread works synchronously and quasi-parallel with the first thread; The second thread monitors the power consumption of the payload bus in real time. When the power consumption of the payload bus exceeds the first preset multiple of the total rated power of the distributors, the first thread is paused and the number of distributors is increased until the power consumption of the payload bus is lower than the second preset multiple of the total rated power of the distributors, and then the first thread is resumed.

[0012] Optionally, the sampling results include the lithium battery voltage and the lithium battery charging current; the lithium battery charging control is achieved through the following methods: In the first working state, if the lithium battery voltage reaches the constant voltage point, the power controller enters the constant voltage working mode and calculates the duty cycle of the next cycle according to the constant voltage control method; In the second working state, if the lithium battery voltage does not reach the constant voltage point and the lithium battery charging current reaches the constant current point, the power controller enters the constant current working mode and calculates the duty cycle of the next cycle according to the constant current control method; If the above first working state or second working state is not satisfied, the power controller enters the maximum power tracking mode and calculates the duty cycle of the next cycle according to the maximum power tracking control method; The duty cycles of all power controllers are uniformly configured by the reconstruction controller.

[0013] Optionally, the sampling results include the payload bus current; the payload power supply control is achieved through the following methods: If the payload bus current exceeds the total rated current of the distributors, the distributors enter the constant current protection mode and calculate the duty cycle of the next cycle according to the output constant current method; If the payload bus current does not exceed the total rated current of the distributors, the distributors enter the constant voltage working mode and calculate the duty cycle of the next cycle according to the output constant voltage method; The duty cycles of all distributors are uniformly configured by the reconstruction controller.

[0014] Based on the above technical solutions, the beneficial effects of the present invention compared with the prior art are as follows: The reconfigurable power control and distribution system and method for near-space low-speed aircraft provided by the present invention. The reconfigurable power control and distribution network consists of N bidirectional power converters, N contactors, and a reconfiguration controller. This modular design enables each component to have an independent function and can be flexibly configured according to actual requirements. The backend of the bidirectional power converter is uniformly connected to the lithium battery bus, and the front end is connected to the solar cell bus or the load bus through a contactor. This architecture allows the reconfiguration controller to dynamically adjust the suction state of the contactor according to different working scenarios and energy states, and flexibly configure the bidirectional power converter as a power controller or a distributor. The reconfigurable design of the present invention enables the system to dynamically adjust the working state of the device according to actual requirements, avoiding unnecessary device redundancy. Through the intelligent control of the reconfiguration controller, the system can accurately adjust the working quantity of the bidirectional power converter and the contactor according to the real-time states of the solar cell bus, the load bus, and the lithium battery bus. The reconfiguration controller uniformly controls the pulse width of the bidirectional power converter, realizing the highly integrated functions such as maximum power tracking control, lithium battery charging control, and load power supply control in the near-space low-speed aircraft cyclic energy system. This centralized control method not only improves the control accuracy and efficiency of the system, but also reduces the need to configure a separate controller for each function, further reducing the weight of the near-space low-speed aircraft.

[0015] Other features and advantages of the present invention will be described in the following specification, and, in part, will be obvious from the specification, or will be understood by practicing the present invention. The objectives and other advantages of the present invention are achieved and obtained by the structures specifically pointed out in the specification, the claims, and the drawings.

[0016] To make the above objectives, features, and advantages of the present invention more obvious and understandable, the following specific preferred embodiments are given, and in conjunction with the accompanying drawings, the detailed description is as follows. Brief Description of the Drawings

[0017] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0018] Figure 1 It is a schematic diagram of the architecture of the existing mainstream near-space low-speed aircraft cyclic energy system.

[0019] Figure 2 It is a schematic diagram of the architecture of the cyclic energy system using a three-port converter.

[0020] Figure 3It is a graph showing the power generation of solar cells of a near-space low-speed aircraft over time.

[0021] Figure 4 It is a schematic diagram of the architecture of a reconfigurable power supply control and power distribution system for a near-space low-speed aircraft provided by the present invention.

[0022] Figure 5 It is a schematic diagram of the architecture of a reconfigurable power supply control and power distribution network provided by the present invention.

[0023] Figure 6 It is a schematic diagram of the ports of a contactor provided by the present invention.

[0024] Figure 7 It is a schematic diagram of the control logic of a contactor array provided by the present invention.

[0025] Figure 8 It is a schematic diagram of the control logic for charging a lithium battery provided by the present invention.

[0026] Figure 9 It is a schematic diagram of the control logic for power supply to a payload provided by the present invention. Detailed implementation manners

[0027] To make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the present invention will be clearly and completely described below with reference to the accompanying drawings in the present invention. Apparently, the described embodiments are some but not all of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present invention without making creative efforts shall fall within the protection scope of the present invention.

[0028] An existing energy recycling system solution includes a solar cell array, a power controller, a lithium battery, a power distributor and an electrical load. In this solution, the power controller and the power distributor are configured separately. Referring to Figure 1 as shown, the power controller and the power distributor work independently, each performing its own functions, and jointly supporting the power generation, charging and power consumption requirements of a near-space low-speed aircraft.

[0029] There is also an energy recycling system solution using a three-port converter. Referring to Figure 2 as shown, the solar cell array, the lithium battery and the electrical load are respectively connected to the corresponding interfaces of the three-port converter. The three-port converter can achieve maximum power tracking of the solar cell, charging control of the lithium battery, and can achieve regulated output of the load port under certain conditions.

[0030] Existing technical solutions can achieve power generation, energy storage, and power consumption control for the cyclic energy system of near-space low-speed aircraft, and have been verified through experiments. However, in the design and testing of the cyclic energy system for near-space low-speed aircraft, it has also been found that the existing technical solutions have a large redundancy in terms of volume and weight, which is caused by the characteristics of the technical solutions. The energy system designed by the existing solutions has a large volume and weight, and cannot further meet the requirements for weight reduction of near-space low-speed aircraft. The reasons are as follows: When a near-space low-speed aircraft is in flight, the sunlight irradiating on the solar cell array changes in a sine law. Correspondingly, referring to Figure 3 as shown, the power generation of the solar cell is the largest at noon, the smallest at sunrise and sunset, and 0 at night. In order to ensure that all the solar energy received by the solar cell throughout the day can be converted into electrical energy. The power capacity of the power supply controller needs to envelope the maximum output power of the solar cell array. This results in a redundancy in the power design of the power supply controller. Only at noon, the power supply controller operates at full power, while in most other periods, the actual power of the power supply controller is less than the rated power. Therefore, designing a power supply controller corresponding to this power value to meet the power at noon is a waste of the volume and weight of the energy system.

[0031] Similarly, there are similar problems at the power distribution end of the energy system. The working conditions of the loads of near-space low-speed aircraft can be divided into full power, medium power, standby, etc. according to the power consumption. The power consumption state of the loads is not stable in the time domain. Generally, the full power state is only turned on in individual periods, and in most periods, it is in the medium power or standby state.

[0032] In the existing energy system solutions, the rated power of the distributor needs to be determined according to the peak power of the load. This causes redundancy for the distributor. Designing a distributor that matches this power value for the short-term peak power of the load is also a waste of the volume and weight of the energy system.

[0033] The reconfigurable power supply control and power distribution system and method for near-space low-speed aircraft proposed by the present invention use a bidirectional power converter network to form a reconfigurable power supply control and power distribution network. Each bidirectional power converter can be configured as a power supply controller or a distributor according to the needs of the system, and can be flexibly switched as needed, which can solve the problem of waste of the volume and weight of the energy system.

[0034] Referring to Figure 4 as shown, the reconfigurable power supply control and power distribution system for near-space low-speed aircraft provided by the present invention includes a solar cell array, a lithium battery, electrical loads, and a reconfigurable power supply control and power distribution network.

[0035] Solar cell array: As the main energy input, it converts solar energy into electrical energy and supplies power to the system through the solar cell busbar.

[0036] Lithium battery: As an energy storage device, it provides electrical energy when there is insufficient light or during peak energy demand, and is connected to the system through the lithium battery busbar.

[0037] Electrical load: Various electrical devices on the aircraft obtain electrical energy through the load busbar.

[0038] In the present invention, the busbar led out from the solar cell array is called the solar cell busbar, the busbar led out from the lithium battery is called the lithium battery busbar, and the busbar for supplying power to the electrical load is called the load busbar. The reconfigurable power control and distribution network connects the solar cell busbar, the lithium battery busbar, and the load busbar.

[0039] The reconfigurable power control and distribution network is the core part. Referring to Figure 5 as shown, it includes N bidirectional power converters (bidirectional power converters 1 - N), N contactors, and a reconfiguration controller. The rear end of the bidirectional power converter is connected to the lithium battery busbar, and the front end is connected to the solar cell busbar or the load busbar through the contactor to achieve bidirectional power transmission and conversion.

[0040] When the bidirectional power converter is connected to the solar cell busbar under the control of the contactor, its function is equivalent to a power controller; conversely, when the bidirectional power converter is connected to the load busbar under the control of the contactor, its function is equivalent to a distributor. The bidirectional power converter can achieve bidirectional energy flow. When the input end of the contactor is connected to the solar cell busbar, the bidirectional power converter controls the energy flow to the lithium battery to charge the lithium battery; when the input end of the contactor is connected to the load busbar, the bidirectional power converter controls the energy to flow from the lithium battery to the load busbar, discharges the lithium battery, and provides regulated power supply for the rear - end load.

[0041] The contactor switches the connection state between the bidirectional power converter and the solar cell busbar or the load busbar according to the instruction of the reconfiguration controller (i.e., Figure 5 the control signals 1 - N in it).

[0042] The reconfiguration controller is used to sample the solar cell busbar, the load busbar, and the lithium battery busbar to obtain sampling results. According to the sampling results of the solar cell busbar, the load busbar, and the lithium battery busbar, it controls the on - off state of the contactor, dynamically configures the bidirectional power converter as a power controller or a distributor, and uniformly controls the pulse width of the bidirectional power converter (i.e., Figure 5 the pulse width signals 1 - N in it) to achieve maximum power tracking control, lithium battery charging control, and load power supply control in the near - space low - speed aircraft cyclic energy system.

[0043] The bidirectional converter adopts MOSFET, GaN or SiC power devices, supports the Buck / Boost bidirectional operation mode, and the rated power is designed according to the system reference; the contactor adopts a magnetic latching relay or a solid-state switch, with the characteristics of fast response and long service life; the reconstruction controller is equipped with a processor and a high-precision sampling system to achieve real-time control.

[0044] The working process of the system of the present invention is as follows: 1. Sampling and status monitoring: The reconstruction controller samples the solar cell bus, load bus and lithium battery bus in real time to obtain parameters such as voltage and current, and understand the operating status of each bus.

[0045] 2. Contactor array control: According to the sampling results, the reconstruction controller judges whether the bidirectional power converter should be connected to the solar cell bus or the load bus, and realizes the dynamic configuration of the contactor array by controlling the suction state of the contactor.

[0046] 3. Bidirectional power converter working mode configuration: When the bidirectional power converter is connected to the solar cell bus, it can be used as a power controller to convert the electric energy output by the solar cell array and then charge the lithium battery or supply power to the load. When the bidirectional power converter is connected to the load bus, it can be used as a distributor to distribute the electric energy stored in the lithium battery or directly output by the solar cell array to the load according to the power consumption requirements of the load.

[0047] 4. Maximum power point tracking control: The reconstruction controller uniformly controls the pulse width of the bidirectional power converter to achieve maximum power point tracking of the solar cell array and improve the utilization efficiency of solar energy.

[0048] 5. Lithium battery charging control: According to the charging state of the lithium battery and the output power of the solar cell array, the reconstruction controller adjusts the working parameters of the bidirectional power converter to achieve intelligent charging of the lithium battery, ensure that the lithium battery operates at a normal working point and extend the service life of the lithium battery.

[0049] 6. Load power supply control: According to the power consumption requirements of the load and the energy status of the system, the reconstruction controller reasonably distributes electric energy to ensure stable power supply to the load.

[0050] In the power control and distribution system of near-space low-speed aircraft in the prior art, due to the limitations of the traditional design architecture, there are large redundancies in terms of volume and weight, making it difficult to meet the increasingly stringent weight reduction requirements. The reconfigurable power control and distribution system proposed by the present invention realizes flexible changes in the number of power controllers and distributors through a unique architecture design, effectively reducing the weight of the aircraft. Specifically, the core reconfigurable power control and distribution network of the system consists of N bidirectional power converters, N contactors, and a reconfiguration controller. This modular design enables each component to have an independent function and can be flexibly configured according to actual needs. The back ends of the bidirectional power converters are uniformly connected to the lithium battery bus, and the front ends are connected to the solar cell bus or the load bus through contactors. This architecture allows the reconfiguration controller to dynamically adjust the closing states of the contactors according to different working scenarios and energy states, and flexibly configure the bidirectional power converters as power controllers or distributors. For example, when the output power of the solar cell array is sufficient, some of the bidirectional power converters are configured as power controllers to store the excess electrical energy into the lithium battery; when the load power demand is large, the bidirectional power converters are configured as distributors to provide additional electrical energy support for the load.

[0051] Traditional power control and distribution systems usually adopt a fixed configuration of power controllers and distributors. Regardless of the actual working conditions, a full set of equipment needs to be carried, resulting in equipment redundancy in many cases. The reconfigurable design of the present invention enables the system to dynamically adjust the working states of the equipment according to actual needs, avoiding unnecessary equipment redundancy.

[0052] Through the intelligent control of the reconfiguration controller, the system can accurately adjust the number of bidirectional power converters used as power controllers and distributors according to the real-time states of the solar cell bus, the load bus, and the lithium battery bus.

[0053] The reconfiguration controller uniformly controls the pulse width of the bidirectional power converters, achieving a high degree of integration of various functions such as maximum power tracking control, lithium battery charging control, and load power supply control in the cyclic energy system. This centralized control method not only improves the control accuracy and efficiency of the system but also reduces the need to configure a separate controller for each function, further reducing the weight of the system.

[0054] The reconfiguration controller can adjust the operating parameters of the system in real time according to factors such as the flight state of the aircraft, the energy reserve situation, and the load power demand. For example, when the aircraft enters the shadow area, the controller can adjust the charging and discharging strategies of the lithium battery in advance to ensure that the aircraft can still operate stably during the period without sunlight, while avoiding overcharging and over-discharging of the lithium battery, extending the service life of the lithium battery, and reducing the additional weight burden caused by battery replacement.

[0055] The reconfigurable power control and distribution system is applicable to near-space low-speed aircraft, such as stratospheric airships, high-altitude balloons, etc. These aircraft have characteristics such as long-term in-air stay and large payload capacity, and have relatively high requirements for the reliability and efficiency of the energy system. This system can effectively solve the problem of energy supply for near-space aircraft, improve the endurance and mission execution ability of the aircraft, and has broad application prospects in the fields of communication, meteorological monitoring, environmental monitoring, etc.

[0056] The control core of the reconfigurable power control and distribution architecture proposed by the present invention is Figure 5 the reconfiguration controller in. Its control logic is divided into three parts: contactor array control logic, lithium battery charging control logic, and load power supply control logic.

[0057] The contactor array control logic is used to configure the number of power controllers and distributors, and improve the utilization rate of the bidirectional power converter; the lithium battery charging control logic is used to control the maximum power tracking process of the solar cell array and the charging process of the lithium battery; the load power supply control logic is used to control the voltage stabilization of the load bus and the current sharing between power modules.

[0058] Specifically, the contactor array control logic is used to dynamically adjust the number of power controllers and distributors according to the maximum power generation of the solar cell array and the power consumption of the load bus. The lithium battery charging control logic is used to control the bidirectional power converter configured as a power controller to perform maximum power tracking, as well as constant voltage or constant current charging of the lithium battery; the load power supply control logic is used to control the bidirectional power converter configured as a distributor to perform constant voltage control and constant current protection of the load bus.

[0059] Regarding the contactor array control, as Figure 6 shown, each contactor has three ports: the first port is the solar cell bus port, which is connected to the solar cell bus (the output end of the photovoltaic array) and is used to receive the DC input of the solar energy power generation system. The second port is the load bus port, which is connected to the load bus (the load end) and is used to supply power to the aircraft load (such as communication equipment, sensors, etc.). The third port is the converter port, which is connected to the bidirectional power converter (bidirectional DC / DC converter) and serves as the hub of energy transmission.

[0060] The switch inside the contactor is of double-pole double-throw structure, through the wire coil (each contactor corresponds to a wire coil, that is Figure 5The line package 1-N) controls the third port to connect to the first port or the second port. When the third port is connected to the first port, the bidirectional power converter is configured as a power controller for power conversion between the solar cell bus and the lithium battery bus, realizing the energy conversion between the solar cell bus (input) and the lithium battery bus (energy storage). When the third port is connected to the second port, the bidirectional power converter is configured as a distributor for power conversion between the lithium battery bus and the load bus, realizing the energy distribution from the lithium battery bus (energy storage) to the load bus (load).

[0061] The line package control logic is electromagnetic drive. The line package drives the contact switch through electromagnetic force to realize the mechanical connection between the third port and the first port or the second port.

[0062] In the traditional scheme, a power controller and a distributor need to be independently configured. In the present invention, function multiplexing is achieved through contactor switching. The bidirectional power converter can be dynamically configured as a power controller or a distributor, reducing hardware redundancy and system complexity. According to the flight mission phase of the aircraft (such as the illumination period or the shadow period) and the load demand, the working mode is automatically switched: during the illumination period, the solar cell bus charges the lithium battery through the power controller or directly supplies power to the load. During the shadow period, the lithium battery supplies power to the load through the distributor to ensure continuous operation. The bidirectional power converter operates in the high-efficiency area in both modes, improving the overall efficiency of the system. The double-pole double-throw contactor has a short switching time, ensuring power supply continuity and avoiding the risk of load power-off. Through function multiplexing and hardware simplification, the total weight of the contactor and the power converter is reduced, and the launch cost of the aircraft is lowered. The double-pole double-throw contactor realizes the function multiplexing of the power controller and the distributor through mechanical switching, solves the problems of hardware redundancy, large weight, and poor flexibility in the traditional scheme, and significantly improves the energy management efficiency and reliability of the near-space low-speed aircraft. The present invention meets the energy management requirements of day-night cycles, extends the endurance time of the aircraft, and flexibly distributes power through the distributor mode to support the access of multiple types of loads.

[0063] The reconfiguration controller is responsible for controlling the entire reconfigurable power control and distribution network, mainly including two aspects: one is to control the closing state of the contactor array according to the sampling results of the solar cell bus, the load bus, and the lithium battery bus, and configure the number of power controllers and distributors; the other is to uniformly control the pulse width of the bidirectional power converter array according to the working point of the solar cell array, the working point of the lithium battery, and the load working state, ensuring the normal operation of functions such as maximum power tracking, lithium battery charging control, and load power supply in the cyclic energy system.

[0064] In an optional embodiment, the sampling results include the real-time time and position information of the aircraft and the power consumption of the load bus. The real-time time and position information are used to calculate the maximum power generation of the solar cell array. The power consumption of the load bus is used to dynamically adjust the number of distributors.

[0065] Referring to Figure 7 as shown, the contactor array control logic is divided into two threads, called the first thread and the second thread.

[0066] The first thread is used to calculate the maximum power generation P1 of the solar cell array according to the real-time time and position information of the aircraft, and determine the required number of power controllers N1 according to the maximum power generation of the solar cell array and the rated power P of the bidirectional power converter, N1 = P1 / P DC . Configure the remaining bidirectional power converters as distributors, and the number of distributors N2 is N - N1. Configure the control signals 1 - N in DC . Then, configure the power controllers and the number of distributors through the relay status. Figure 5

[0067] The second thread works synchronously and quasi-parallel with the first thread; The second thread is used to monitor the power consumption of the payload bus in real time. When the power consumption of the payload bus exceeds the first preset multiple α of the total rated power of the distributors, that is, P L > α × N2 × P DC , it is considered that the priority of the payload bus is higher than that of the solar cell bus at this time. First, pause the operation of the first thread and increase the number of distributors (N2 = N2 + 1) until the power consumption of the payload bus is lower than the second preset multiple β of the total rated power of the distributors (P L < β × N2 × P DC ), and then the first thread resumes operation.

[0068] The calculation method of the maximum power generation of the solar cell array can refer to the description in the prior art and will not be elaborated here.

[0069] The present invention combines the maximum power generation of the solar cell array and the real-time power consumption of the payload bus to dynamically optimize the number of power controllers and distributors. The first thread configures the number of power controllers in real time according to the power generation of the solar cell array to ensure the maximum utilization of energy. The second thread dynamically adjusts the number of distributors according to the payload demand to avoid system crashes caused by overload. Through the dynamic configuration of the bidirectional power converter, the number of independent power controllers and distributors is reduced, and the system weight is reduced. The dual-thread architecture ensures that the system can still recover stable operation through dynamic adjustment in case of overload. The reconstruction controller coordinates all devices uniformly to achieve global optimization of MPPT, lithium battery charging, and payload power supply.

[0070] In an optional embodiment, regarding the charging control of a lithium battery, the lithium battery charging control logic controls a bidirectional power converter configured as a power controller to achieve maximum power tracking and constant voltage or constant current charging control functions for the lithium battery. The above sampling results include the lithium battery voltage and the lithium battery charging current; referring to Figure 8 As shown, the lithium battery charging control logic is as follows: First, sample and judge the lithium battery voltage. If the lithium battery voltage reaches the constant voltage point (referred to as the first working state), the power controller enters the constant voltage working mode and calculates the duty cycle of the next cycle according to the constant voltage control method to obtain the duty ratio value duty3. The duty cycle is adjusted through closed-loop feedback to maintain a constant output voltage and prevent overcharging. Ensure safe charging of the battery in the fully charged stage and avoid electrolyte decomposition or thermal runaway caused by too high voltage.

[0071] If the lithium battery voltage does not reach the constant voltage point and the lithium battery charging current reaches the constant current point (referred to as the second working state), the power controller enters the constant current working mode and calculates the duty cycle of the next cycle according to the constant current control method to obtain the duty ratio value duty2. The current can be controlled to be constant through PWM modulation to quickly supplement the power. Achieve efficient fast charging when the battery capacity is low and shorten the charging time.

[0072] If the above first working state or second working state is not satisfied, that is, the constant voltage and constant current conditions are not satisfied, the power controller enters the maximum power tracking mode (MPPT mode) and calculates the duty cycle of the next cycle according to the maximum power tracking control method to obtain the duty ratio value duty1; The duty cycles of all power controllers are uniformly configured by the reconstruction controller to ensure multi-channel collaborative work. To ensure the stability and current sharing of the control process, the reconstruction controller simultaneously configures the duty cycles of all power controllers as duty1 or duty2 or duty3, and all power controllers perform power conversion according to duty1 or duty2 or duty3.

[0073] The control period of this control logic is T1. After reaching T1, the reconstruction controller resamples the lithium battery bus and conducts the next control.

[0074] The calculation process of the duty cycle in the constant voltage working mode is as follows: 1. Sample the lithium battery bus voltage: Obtain the current bus voltage V in real time bus .

[0075] 2. Calculate the error: The difference ΔV from the preset constant voltage value V ref :

[0076] 3. PI controller calculation: Calculate the duty cycle adjustment amount ΔD through a proportional-integral (PI) controller:

[0077] Wherein, K p is the proportionality coefficient, which controls the response speed. K i is the integral coefficient, which eliminates the steady-state error.

[0078] 4. Update the duty cycle: Add the adjustment amount to the current duty cycle D to obtain the duty cycle D of the next cycle new : D new = D + ΔD The calculation process of the duty cycle in the constant current protection mode is as follows: 1. Sample the bus current of the lithium battery: Obtain the current bus current I in real time bus .

[0079] 2. Calculate the error: The difference ΔI from the preset constant current value I ref :

[0080] 3. PI controller calculation: Calculate the duty cycle adjustment amount ΔD through the PI controller:

[0081] K p 、K i should be selected to ensure that the current is stable below I ref .

[0082] 4. Update the duty cycle: Add the adjustment amount ΔD to the current duty cycle D to obtain the duty cycle D of the next cycle new : D new = D + ΔD The charging control logic of the present invention realizes the efficient, safe and flexible control of the lithium battery charging process through multi-mode switching, unified configuration and dynamic response. It significantly improves the energy utilization rate, extends the battery life, and reduces the system complexity. The MPPT mode tracks the maximum power point in real time to avoid energy waste. The constant current working mode charges quickly at high current to shorten the early stage time; the constant voltage working mode precisely controls in the later stage to avoid overcharging the battery. The constant voltage working mode strictly limits the upper voltage limit to prevent the precipitation of lithium ions or thermal runaway; the constant current working mode avoids overheating of the battery through current limitation. The multi-mode switching can quickly respond to changes in the battery state to prevent abnormal working conditions. The reconstruction controller uniformly configures the duty cycle parameters to reduce the interference between multiple controllers and improve the system robustness.

[0083] In an optional embodiment, the load power supply control logic controls a bidirectional power converter configured as a power distributor to achieve constant voltage control and constant current protection functions for the load bus. The sampling result includes the load bus current; referring to Figure 9 as shown, the load power supply control logic is as follows: First, sample and judge the load bus. If the load bus current exceeds the total rated current of the power distributor, the power distributor enters the constant current protection mode and calculates the duty cycle of the next cycle according to the output constant current method to obtain the duty ratio value duty5; If the load bus current does not exceed the total rated current of the power distributor, the power distributor enters the constant voltage operation mode and calculates the duty cycle of the next cycle according to the output constant voltage method to obtain the duty ratio value duty4. The power distributor adjusts the duty cycle of the bidirectional power converter to limit the output current to be constant within the rated value and prevent overload damage. The duty cycle of the next cycle is dynamically calculated based on the preset constant current value and the current bus current to ensure accurate current control.

[0084] The duty cycles of all power distributors are uniformly configured by the reconstruction controller. To ensure the stability and current sharing of the control process, the reconstruction controller configures the duty cycles of all power distributors as duty4 or duty5 at the same time, and all power distributors perform power conversion according to duty4 or duty5. The power distributor maintains the bus voltage constant by adjusting the duty cycle to ensure the stable operation of the backend equipment. The duty cycle of the next cycle is dynamically calculated based on the preset constant voltage value and the current bus voltage to achieve voltage closed-loop control.

[0085] The control period of this control logic is T2. After reaching T2, the reconstruction controller resamples the load bus and performs the next control.

[0086] Through the dynamic switching between constant - current protection and constant - voltage control, the present invention achieves precise management of the load bus current and voltage, ensuring equipment safety and system stability. The constant - current protection mode effectively prevents equipment damage caused by bus - current overload. By restricting the current in real - time, it avoids safety accidents such as fires and explosions caused by short - circuits, overloads, or abnormal operating conditions, significantly improving system reliability. The constant - voltage operating mode ensures stable output of the bus voltage, providing a reliable power environment for backend equipment (such as motors, controllers, communication modules, etc.). After reducing voltage fluctuations, the equipment failure rate decreases, the service life extends, and the maintenance cost reduces. The system can quickly switch the operating mode according to the real - time current sampling results to adapt to different load requirements. For example, when the load suddenly increases, the system can quickly enter the constant - current protection mode to avoid overload; after the load stabilizes, it switches back to the constant - voltage mode to optimize energy efficiency. The unified configuration of the reconfigurable controller simplifies the system design and reduces the complexity of multi - controller collaborative work. This architecture is easy to expand and can adapt to different power levels and numbers of distribution units to meet the requirements of different - scale systems. By dynamically adjusting the duty cycle, the system can achieve high - efficiency energy conversion in both constant - voltage and constant - current modes. It avoids energy waste in traditional fixed - control methods and improves overall energy efficiency.

[0087] The reconfigurable power control and distribution method for near - space low - speed aircraft provided by the present invention will be described below. The reconfigurable power control and distribution method for near - space low - speed aircraft described below can be mutually referred to corresponding to the reconfigurable power control and distribution system for near - space low - speed aircraft described above.

[0088] The present invention also provides a reconfigurable power control and distribution method for near - space low - speed aircraft, using the reconfigurable power control and distribution system for near - space low - speed aircraft as described above. The method includes: S110. Sampling the solar - cell bus, load bus, and lithium - battery bus through the reconfigurable controller to obtain sampling results; S120. According to the sampling results of the solar - cell bus, load bus, and lithium - battery bus, the reconfigurable controller controls the suction state of the double - pole double - throw contactor, dynamically configures the bidirectional power converter as a power controller or a distribution unit, and uniformly controls the pulse width of the bidirectional power converter to achieve maximum - power tracking control, lithium - battery charging control, and load - power - supply control in the near - space low - speed aircraft cyclic energy system.

[0089] In an optional embodiment, the sampling results include the real - time time and position information of the aircraft and the power consumption of the load bus. The contactor array control is achieved through the following methods: The first thread calculates the maximum power generation of the solar cell array based on the real-time time and position information of the aircraft, determines the required number N1 of power controllers according to the maximum power generation of the solar cell array and the rated power of the bidirectional power converter, and configures the remaining bidirectional power converters as distributors, and the number of distributors is N - N1; The second thread works synchronously and quasi-parallel with the first thread; The second thread monitors the power consumption of the load bus in real time. When the consumed power of the load bus exceeds the first preset multiple of the total rated power of the distributors, the first thread is paused and the number of distributors is increased until the consumed power of the load bus is lower than the second preset multiple of the total rated power of the distributors, and then the first thread is resumed.

[0090] In an optional embodiment, the sampling results include the lithium battery voltage and the lithium battery charging current; the lithium battery charging control is realized by the following method: In the first working state, if the lithium battery voltage reaches the constant voltage point, the power controller enters the constant voltage working mode and calculates the duty ratio of the next cycle according to the constant voltage control method; In the second working state, if the lithium battery voltage does not reach the constant voltage point and the lithium battery charging current reaches the constant current point, the power controller enters the constant current working mode and calculates the duty ratio of the next cycle according to the constant current control method; If the above first working state or second working state is not satisfied, the power controller enters the maximum power tracking mode and calculates the duty ratio of the next cycle according to the maximum power tracking control method; The duty ratios of all power controllers are uniformly configured by the reconstruction controller.

[0091] In an optional embodiment, the sampling results include the load bus current; the load power supply control is realized by the following method: If the load bus current exceeds the total rated current of the distributors, the distributors enter the constant current protection mode and calculate the duty ratio of the next cycle according to the output constant current method; If the load bus current does not exceed the total rated current of the distributors, the distributors enter the constant voltage working mode and calculate the duty ratio of the next cycle according to the output constant voltage method; The duty ratios of all distributors are uniformly configured by the reconstruction controller.

[0092] Through the description of the above embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on such an understanding, the essence of the above technical solution, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to enable a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0093] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A reconfigurable power control and distribution system for a near-space low-speed aircraft, characterized in that, Comprising: Solar cell array; Lithium battery; Electrical load; Reconfigurable power control and distribution network, connecting the solar cell bus, the lithium battery bus and the load bus; wherein, the solar cell bus is the bus led out from the solar cell array, the lithium battery bus is the bus led out from the lithium battery, and the load bus is the bus for supplying power to the electrical load; The reconfigurable power control and distribution network includes N bidirectional power converters, N contactors and a reconfiguration controller; The rear end of the bidirectional power converter is connected to the lithium battery bus, and the front end is connected to the solar cell bus or the load bus through the contactor; The reconfiguration controller is used to sample the solar cell bus, the load bus and the lithium battery bus to obtain sampling results, and according to the sampling results of the solar cell bus, the load bus and the lithium battery bus, control the suction state of the contactor, dynamically configure the bidirectional power converter as a power controller or a distributor, and uniformly control the pulse width of the bidirectional power converter to achieve maximum power tracking control, lithium battery charging control and load power supply control in the cyclic energy system of the near-space low-speed aircraft.

2. The reconfigurable power control and distribution system for near-space low-speed aircraft according to claim 1, wherein The contactor includes: A first port, connected to the solar cell bus; A second port, connected to the load bus; A third port, connected to the bidirectional power converter; The contactor controls the third port to be connected to the first port or the second port through a wire coil; Wherein, when the third port is connected to the first port, the bidirectional power converter is configured as a power controller for performing power conversion between the solar cell bus and the lithium battery bus; when the third port is connected to the second port, the bidirectional power converter is configured as a distributor for performing power conversion between the lithium battery bus and the load bus.

3. The reconfigurable power control and distribution system for near-space low-speed aircraft according to claim 1, characterized in that, The control logic of the reconfiguration controller includes: Contactor array control logic, used to dynamically adjust the number of power controllers and distributors according to the maximum power generation of the solar cell array and the power consumption of the load bus; Lithium battery charging control logic, used to control the bidirectional power converter configured as a power controller to perform maximum power tracking and constant voltage or constant current charging of the lithium battery; Load power supply control logic, used to control the bidirectional power converter configured as a distributor to perform constant voltage control and constant current protection of the load bus.

4. The reconfigurable power control and distribution system for near-space low-speed aircraft according to claim 3, characterized in that, The sampling results include the real-time time and position information of the aircraft and the power consumption of the load bus; The contactor array control logic includes: A first thread, used to calculate the maximum power generation of the solar cell array according to the real-time time and position information of the aircraft, determine the required number of power controllers N1 according to the maximum power generation of the solar cell array and the rated power of the bidirectional power converter, and configure the remaining bidirectional power converters as distributors, and the number of distributors is N - N1; A second thread, and the second thread works synchronously and quasi-parallel with the first thread; The second thread is used to monitor the power consumption of the load bus in real time. When the power consumption of the load bus exceeds the first preset multiple of the total rated power of the distributors, pause the first thread and increase the number of distributors until the power consumption of the load bus is lower than the second preset multiple of the total rated power of the distributors and then resume the first thread.

5. The reconfigurable power control and distribution system for near-space low-speed aircraft according to claim 3, characterized in that, The sampling results include the lithium battery voltage and the lithium battery charging current; the lithium battery charging control logic is as follows: In the first working state, if the lithium battery voltage reaches the constant voltage point, the power supply controller enters the constant voltage working mode and calculates the duty cycle of the next cycle according to the constant voltage control method; In the second working state, if the lithium battery voltage does not reach the constant voltage point and the lithium battery charging current reaches the constant current point, the power supply controller enters the constant current working mode and calculates the duty cycle of the next cycle according to the constant current control method; If the above first working state or second working state is not satisfied, the power supply controller enters the maximum power tracking mode and calculates the duty cycle of the next cycle according to the maximum power tracking control method; The duty cycles of all power supply controllers are uniformly configured by the reconstruction controller.

6. The reconfigurable power control and distribution system for near-space low-speed aircraft according to claim 3, wherein The sampling results include the load bus current; The load power supply control logic includes: If the load bus current exceeds the sum of the rated currents of the distribution boxes, the distribution boxes enter the constant current protection mode and calculate the duty cycle of the next cycle according to the output constant current method; If the load bus current does not exceed the sum of the rated currents of the distribution boxes, the distribution boxes enter the constant voltage working mode and calculate the duty cycle of the next cycle according to the output constant voltage method; The duty cycles of all distribution boxes are uniformly configured by the reconstruction controller.

7. A reconfigurable power control and distribution method for near-space low-speed aircraft, characterized in that Using the reconfigurable power supply control and distribution system for near-space low-speed aircraft as described in any one of claims 1-6, the method includes: Sampling the solar cell bus, the load bus and the lithium battery bus through the reconstruction controller to obtain sampling results; Based on the sampling results of the solar cell bus, the load bus and the lithium battery bus, the reconstruction controller controls the suction state of the contactor, dynamically configures the bidirectional power converter as a power supply controller or a distribution box, and uniformly controls the pulse width of the bidirectional power converter to achieve maximum power tracking control, lithium battery charging control and load power supply control in the near-space low-speed aircraft cyclic energy system.

8. The reconfigurable power control and distribution method for near-space low-speed aircraft according to claim 7, characterized in that, The sampling results include the real-time time and position information of the aircraft and the power consumption of the load bus; the contactor array control is realized in the following manner: The first thread calculates the maximum power generation of the solar cell array according to the real-time time and position information of the aircraft, determines the required number of power supply controllers N1 according to the maximum power generation of the solar cell array and the rated power of the bidirectional power converter, and configures the remaining bidirectional power converters as distribution boxes, and the number of distribution boxes is N - N1; The second thread works synchronously and quasi-parallel with the first thread; The second thread monitors the power consumption of the load bus in real time. When the power consumption of the load bus exceeds the first preset multiple of the sum of the rated powers of the distribution boxes, the first thread is suspended and the number of distribution boxes is increased until the power consumption of the load bus is lower than the second preset multiple of the sum of the rated powers of the distribution boxes, and then the first thread is resumed.

9. The reconfigurable power supply control and power distribution method for near-space low-speed aircraft according to claim 7, characterized in that The sampling results include the lithium battery voltage and the lithium battery charging current; the lithium battery charging control is realized in the following manner: In the first working state, if the lithium battery voltage reaches the constant voltage point, the power supply controller enters the constant voltage working mode and calculates the duty cycle of the next cycle according to the constant voltage control method; Second working state: If the voltage of the lithium battery does not reach the constant voltage point and the charging current of the lithium battery reaches the constant current point, the power supply controller enters the constant current working mode and calculates the duty cycle of the next cycle according to the constant current control method; If the above first working state or second working state is not satisfied, the power supply controller enters the maximum power tracking mode and calculates the duty cycle of the next cycle according to the maximum power tracking control method; The duty cycles of all power supply controllers are uniformly configured by the reconstruction controller.

10. The reconfigurable power control and distribution method for near-space low-speed aircraft according to claim 7, characterized in that The sampling result includes the load bus current; the load power supply control is implemented in the following manner: If the load bus current exceeds the sum of the rated currents of the distributors, the distributor enters the constant current protection mode and calculates the duty cycle of the next cycle according to the output constant current method; If the load bus current does not exceed the sum of the rated currents of the distributors, the distributor enters the constant voltage working mode and calculates the duty cycle of the next cycle according to the output constant voltage method; The duty cycles of all distributors are uniformly configured by the reconstruction controller.

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