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

Abstract

This invention relates to the field of energy system technology for near-space vehicles, and provides a reconfigurable power control and distribution system and method for near-space low-speed vehicles. The system includes: a solar cell array, a lithium battery, an electrical load, and a reconfigurable power control and distribution network. The network connects the solar cell bus, the lithium battery bus, and the load bus. The network includes N bidirectional power converters, N contactors, and a reconfiguration controller; the rear end of each bidirectional power converter is connected to the lithium battery bus, and the front end is connected to either the solar cell bus or the load bus via contactors. The reconfiguration controller controls the engagement state of the contactors based on sampling results from each bus, dynamically configuring the bidirectional power converters as power controllers or power distributors, and uniformly controlling the pulse width of the bidirectional power converters. This enables flexible configuration of the number of power controllers and power distributors in near-space low-speed vehicles, reducing the vehicle's weight.

Description

Technical Field

[0001] This invention relates to the field of energy system technology for near-space vehicles, and in particular to a reconfigurable power control and distribution system and method for low-speed near-space vehicles. Background Technology

[0002] Near-space low-speed aircraft, such as stratospheric airships and high-altitude balloons, are characterized by long-duration loiter times and large payload capacities, placing extremely high demands on the reliability and efficiency of their energy systems. A solar-powered regenerative energy system is one of the key technologies for achieving long-duration flight in near-space low-speed aircraft. This system includes a solar array, lithium-ion battery packs, a power controller, and a power distribution unit. The power controller performs maximum power point tracking (MPPT) on the solar array and converts the electrical energy output from the solar array to power the lithium-ion battery packs. The power distribution unit converts the output bus voltage of the lithium-ion battery to the voltage required by the load, thus powering the payload of the near-space low-speed aircraft.

[0003] Existing energy system solutions can realize the generation, storage, and power control of near-space low-speed aircraft's regenerative energy systems, and have been verified through experiments. However, in the design and testing of near-space low-speed aircraft regenerative energy systems, it was also found that existing technical solutions have significant redundancy in size and weight, and cannot further meet the requirements for weight reduction of near-space low-speed aircraft. Summary of the Invention

[0004] This invention provides a reconfigurable power control and distribution system and method for near-space low-speed aircraft, addressing the problem that existing technologies suffer from significant redundancy in size and weight, failing to further meet the weight reduction requirements of near-space low-speed aircraft. The invention enables flexible configuration of the number of power controllers and power distributors in near-space low-speed aircraft, thereby reducing their weight. The technical solution proposed by this invention is as follows:

[0005] In a first aspect, the present invention provides a reconfigurable power control and distribution system for near-space low-speed aircraft, comprising:

[0006] Solar cell array;

[0007] Lithium batteries;

[0008] Electrical load;

[0009] A reconfigurable power control and distribution network connects the solar cell bus, lithium battery bus, and 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 that supplies power to the electrical loads.

[0010] The reconfigurable power control and distribution network includes N bidirectional power converters, N contactors, and a reconfiguration controller.

[0011] 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 via the contactor.

[0012] The reconfiguration controller is used to sample the solar cell bus, load bus, and lithium battery bus to obtain sampling results. Based on the sampling results of the solar cell bus, load bus, and lithium battery bus, it controls the engagement state of the contactor, dynamically configures the bidirectional power converter as a power controller or distributor, and uniformly controls the pulse width of the bidirectional power converter to achieve maximum power point tracking control, lithium battery charging control, and load power supply control in the near-space low-speed aircraft's recirculating energy system.

[0013] Optionally, the contactor includes:

[0014] The first port connects to the solar cell bus;

[0015] The second port connects to the load busbar;

[0016] The third port connects to the bidirectional power converter;

[0017] The contactor controls the connection of the third port to the first port or the second port via a coil;

[0018] Specifically, 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.

[0019] Optionally, the control logic of the reconfiguration controller includes:

[0020] The contactor array control logic is used to dynamically adjust the number of power controllers and distributors based on the maximum power output of the solar cell array and the power consumption of the load bus.

[0021] The lithium battery charging control logic is used to control the bidirectional power converter configured as a power controller to perform maximum power point tracking and constant voltage or constant current charging of the lithium battery.

[0022] 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.

[0023] Optionally, the sampling results include the real-time time and location information of the aircraft and the power consumption of the payload bus; the contactor array control logic includes:

[0024] The first thread is used to calculate the maximum power output of the solar array based on the real-time time and location information of the aircraft, determine the required number of power controllers N1 based on the maximum power output of the solar array and the rated power of the bidirectional power converter, and configure the remaining bidirectional power converters as power distributors, with the number of power distributors being N-N1.

[0025] The second thread works synchronously or in quasi-parallel with the first thread.

[0026] 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 distribution units, the first thread is paused and the number of distribution units is increased until the power consumption of the load bus is lower than the second preset multiple of the total rated power of the distribution units, and then the first thread is resumed.

[0027] Optionally, the sampling results include lithium battery voltage and lithium battery charging current; the lithium battery charging control logic is as follows:

[0028] 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.

[0029] In the second working state, if the lithium battery voltage has not reached the constant voltage point and the lithium battery charging current has reached 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.

[0030] If the first or second operating state is not met, the power controller enters the maximum power point tracking mode and calculates the duty cycle for the next cycle according to the maximum power point tracking control method.

[0031] The duty cycle of all power controllers is configured uniformly by the reconfiguration controller.

[0032] Optionally, the sampling result includes the load bus current; the load power supply control logic includes:

[0033] If the load bus current exceeds the sum of the rated currents of the distribution units, the distribution units will enter constant current protection mode and calculate the duty cycle of the next cycle according to the constant current output method.

[0034] If the load bus current does not exceed the total rated current of the distribution unit, the distribution unit enters the constant voltage working mode and calculates the duty cycle of the next cycle according to the constant voltage output method.

[0035] The duty cycle of all power distribution units is configured uniformly by the reconfiguration controller.

[0036] In a second aspect, the present invention provides a reconfigurable power control and power distribution method for near-space low-speed aircraft, using the reconfigurable power control and power distribution system for near-space low-speed aircraft as described in the first aspect, the method comprising:

[0037] The solar cell bus, load bus, and lithium battery bus are sampled by the reconfiguration controller to obtain the sampling results;

[0038] By reconfiguring the controller based on the sampling results of the solar cell bus, load bus, and lithium battery bus, the contactor's engagement state is controlled, and the bidirectional power converter is dynamically configured as a power controller or distributor. The pulse width of the bidirectional power converter is uniformly controlled to achieve maximum power point tracking control, lithium battery charging control, and load power supply control in the near-space low-speed aircraft's recirculating energy system.

[0039] Optionally, the sampling results include the real-time time and location information of the aircraft and the power consumption of the payload bus; contactor array control is achieved in the following manner:

[0040] The first thread calculates the maximum power output of the solar array based on the real-time time and location information of the aircraft. Based on the maximum power output of the solar array and the power of the bidirectional power converter, it determines the required number of power controllers N1. The remaining bidirectional power converters are configured as power distributors, and the number of power distributors is N-N1.

[0041] The second thread works synchronously or in quasi-parallel with the first thread.

[0042] 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 total rated power of the distribution units, the first thread is paused and the number of distribution units is increased until the power consumption of the load bus is lower than the second preset multiple of the total rated power of the distribution units, after which the first thread is resumed.

[0043] Optionally, the sampling results include lithium battery voltage and lithium battery charging current; lithium battery charging control is achieved in the following manner:

[0044] 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.

[0045] In the second working state, if the lithium battery voltage has not reached the constant voltage point and the lithium battery charging current has reached 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.

[0046] If the first or second operating state is not met, the power controller enters the maximum power point tracking mode and calculates the duty cycle for the next cycle according to the maximum power point tracking control method.

[0047] The duty cycle of all power controllers is configured uniformly by the reconfiguration controller.

[0048] Optionally, the sampling results include the load bus current; load power supply control is achieved in the following manner:

[0049] If the load bus current exceeds the sum of the rated currents of the distribution units, the distribution units will enter constant current protection mode and calculate the duty cycle of the next cycle according to the constant current output method.

[0050] If the load bus current does not exceed the total rated current of the distribution unit, the distribution unit enters the constant voltage working mode and calculates the duty cycle of the next cycle according to the constant voltage output method.

[0051] The duty cycle of all power distribution units is configured uniformly by the reconfiguration controller.

[0052] Based on the above technical solution, the beneficial effects of the present invention compared with the prior art are as follows:

[0053] This invention provides a reconfigurable power control and distribution system and method for near-space low-speed aircraft. The reconfigurable power control and distribution network consists of N bidirectional power converters, N contactors, and a reconfiguration controller. This modular design allows each component to have independent functions and can be flexibly configured according to actual needs. The back end of the bidirectional power converter is uniformly connected to the lithium battery bus, while the front end is connected to the solar cell bus or load bus via contactors. This architecture allows the reconfiguration controller to dynamically adjust the contactor engagement state according to different operating scenarios and energy states, flexibly configuring the bidirectional power converter as a power controller or a power distributor. The reconfigurable design of this invention enables the system to dynamically adjust the operating state of the equipment according to actual needs, avoiding unnecessary equipment redundancy. Through the intelligent control of the reconfiguration controller, the system can accurately adjust the number of bidirectional power converters and contactors in operation based on the real-time status of the solar cell bus, load bus, and lithium battery bus. The reconfiguration controller uniformly controls the pulse width of the bidirectional power converters, achieving a high degree of integration of multiple functions such as maximum power point tracking control, lithium battery charging control, and load power supply control in the near-space low-speed aircraft's cyclic energy system. This centralized control method not only improves the system's control accuracy and efficiency, but also reduces the need for a separate controller for each function, further reducing the weight of near-space low-speed aircraft.

[0054] Other features and advantages of the invention will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention are realized and obtained in accordance with the structures particularly pointed out in the description, claims and drawings.

[0055] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings. Attached Figure Description

[0056] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0057] Figure 1 This is a schematic diagram of the architecture of the existing mainstream near-space low-speed aircraft's recycle energy system.

[0058] Figure 2 This is a schematic diagram of the architecture of a recycle energy system using a three-port converter.

[0059] Figure 3 It is a graph showing the power generation of solar cells on a near-space low-speed aircraft over time.

[0060] Figure 4 This is a schematic diagram of the architecture of the reconfigurable power control and power distribution system for near-space low-speed aircraft provided by the present invention.

[0061] Figure 5 This is a schematic diagram of the architecture of the reconfigurable power control and distribution network provided by the present invention.

[0062] Figure 6 This is a schematic diagram of the port of the contactor provided by the present invention.

[0063] Figure 7 This is a schematic diagram of the contactor array control logic provided by the present invention.

[0064] Figure 8 This is a schematic diagram of the lithium battery charging control logic provided by the present invention.

[0065] Figure 9 This is a schematic diagram of the load power supply control logic provided by the present invention. Detailed Implementation

[0066] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0067] An existing energy cycle system scheme includes a solar cell array, a power controller, a lithium battery, a power distribution unit, and electrical loads. This scheme configures the power controller and power distribution unit separately, as shown in the reference... Figure 1 As shown, the power controller and the power distributor work independently, each performing its own function, and together support the power generation, charging and power consumption needs of the near-space low-speed aircraft.

[0068] There are also energy cycle system solutions that use three-port converters, see reference. Figure 2 As shown, the solar cell array, lithium battery, and electrical load are connected to the corresponding interfaces of the three-port converter. The three-port converter can achieve maximum power tracking of the solar cell, charge control of the lithium battery, and regulated output of the load port under certain conditions.

[0069] Existing technologies can realize the generation, storage, and power control of near-space low-speed aircraft's regenerative energy systems, and have been verified through experiments. However, the design and testing of near-space low-speed aircraft regenerative energy systems have also revealed that existing technologies have significant redundancy in size and weight. This redundancy is due to the inherent characteristics of the technologies. The energy systems designed with existing solutions are very large in size and weight, and cannot further meet the weight reduction requirements for near-space low-speed aircraft. The reasons are as follows:

[0070] When a low-speed near-space spacecraft is in flight, the sunlight illuminating its solar array exhibits a sinusoidal pattern. Correspondingly, referencing... Figure 3 As shown, the solar cell's power generation is highest at noon, lowest at sunrise and sunset, and zero at night. To ensure that all solar energy received by the solar cells throughout the day can be converted into electrical energy, the power controller's power capacity needs to encompass the maximum output power of the solar cell array. This results in redundancy in the power controller's power design. Only at noon does the power controller operate at full power; for most of the remaining time, the actual power output is less than the rated power. Therefore, designing a power controller specifically to meet the noon power requirement is a waste of the energy system's size and weight.

[0071] Similarly, similar issues exist at the power distribution end of energy systems. The operating status of the payload of near-space low-speed aircraft can be categorized into full power, medium power, and standby states based on power consumption. The power consumption state of the payload is not time-domain stable; generally, it only operates at full power during specific periods, and spends most of the time in medium power or standby mode.

[0072] In existing energy system designs, the rated power of the power distribution unit needs to be determined based on the peak power of the load. This creates redundancy in the power distribution unit. Designing a power distribution unit that matches the short-term peak power of the load is also a waste of the energy system's size and weight.

[0073] The present invention proposes a reconfigurable power control and distribution system and method for near-space low-speed aircraft, which employs a bidirectional power converter network to form the reconfigurable power control and distribution network. Each bidirectional power converter can be configured as a power controller or a power distributor according to the needs of the system, and can be flexibly switched as needed, thus solving the problem of wasted volume and weight in the energy system.

[0074] Reference Figure 4 As shown, the reconfigurable power control and distribution system for near-space low-speed aircraft provided by the present invention includes a solar cell array, a lithium battery, an electrical payload, and a reconfigurable power control and distribution network.

[0075] 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 bus.

[0076] Lithium batteries: As energy storage devices, they provide electrical energy when there is insufficient sunlight or during peak energy demand, and are connected to the system through the lithium battery bus.

[0077] Electrical loads: The various electrical equipment of the aircraft obtains electrical energy through the load bus.

[0078] In this invention, the busbar leading out from the solar cell array is called the solar cell busbar, the busbar leading out from the lithium battery is called the lithium battery busbar, and the busbar supplying power to the electrical loads 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.

[0079] Reconfigurable power control and distribution networks are the core components, refer 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 bus, and the front end is connected to the solar cell bus or load bus through contactors, realizing bidirectional transmission and conversion of electrical energy.

[0080] When the bidirectional power converter is connected to the solar cell bus under the control of a contactor, it functions as a power controller; conversely, when it is connected to the load bus under the control of a contactor, it functions as a power distributor. The bidirectional power converter enables bidirectional energy flow. When the contactor's input is connected to the solar cell bus, the bidirectional power converter controls the energy flow to the lithium battery to charge it; when the contactor's input is connected to the load bus, the bidirectional power converter controls the energy flow from the lithium battery to the load bus to discharge it and provide regulated power to the downstream load.

[0081] The contactor responds to the instructions of the reconfiguration controller (i.e.) Figure 5 The control signals 1-N in the system switch the connection status between the bidirectional power converter and the solar cell bus or load bus.

[0082] The reconfiguration controller samples the solar cell bus, load bus, and lithium battery bus to obtain sampling results. Based on these results, it controls the contactor's engagement state, dynamically configures the bidirectional power converter as a power controller or distributor, and uniformly controls the pulse width of the bidirectional power converter (i.e.,...). Figure 5 The pulse width signal (1-N) is used to achieve maximum power point tracking control, lithium battery charging control, and payload power supply control in the near-space low-speed aircraft recycle energy system.

[0083] The bidirectional converter uses MOSFET, GaN, or SiC power devices and supports Buck / Boost bidirectional operating modes. The rated power is designed according to the system reference. The contactor uses magnetic latching relays or solid-state switches, which have fast response and long life characteristics. The reconfigurable controller is equipped with a processor and a high-precision sampling system to achieve real-time control.

[0084] The working process of the system of this invention is as follows:

[0085] 1. Sampling and Status Monitoring: The reconfiguration 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.

[0086] 2. Contactor array control: Based on the sampling results, the reconfiguration controller determines whether the bidirectional power converter should be connected to the solar cell bus or the load bus. By controlling the contactor's engagement state, the dynamic configuration of the contactor array is achieved.

[0087] 3. Bidirectional Power Converter Operating Mode Configuration: When the bidirectional power converter is connected to the solar cell bus, it can act as a power controller, converting the electrical energy output from the solar cell array to charge the lithium battery or power the load. When the bidirectional power converter is connected to the load bus, it can act as a power distributor, allocating the electrical energy stored in the lithium battery or the electrical energy directly output from the solar cell array to the load according to its power demand.

[0088] 4. Maximum Power Point Tracking Control: The reconfiguration controller performs unified control of 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.

[0089] 5. Lithium battery charging control: Based on the charging status of the lithium battery and the output power of the solar array, the reconfiguration controller adjusts the operating parameters of the bidirectional power converter to achieve intelligent charging of the lithium battery, ensuring that the lithium battery operates at its normal operating point and extending its service life.

[0090] 6. Load power supply control: Based on the load's power demand and the system's energy status, the reconfiguration controller rationally allocates power to ensure a stable power supply to the load.

[0091] Existing technologies in power control and distribution systems for near-space low-speed aircraft suffer from significant redundancy in size and weight due to limitations in traditional design architectures, making it difficult to meet increasingly stringent weight reduction requirements. The reconfigurable power control and distribution system proposed in this invention, through a unique architectural design, allows for flexible changes in the number of power controllers and distributors, effectively reducing aircraft weight. Specifically, the core reconfigurable power control and distribution network consists of N bidirectional power converters, N contactors, and a reconfiguration controller. This modular design allows each component to have independent functionality and can be flexibly configured according to actual needs. The back end of the bidirectional power converters is uniformly connected to the lithium battery bus, while the front end is connected to the solar cell bus or load bus via contactors. This architecture allows the reconfiguration controller to dynamically adjust the contactor engagement state according to different operating scenarios and energy states, flexibly configuring the bidirectional power converters as power controllers or distributors. For example, when the output power of the solar cell array is sufficient, some bidirectional power converters can be configured as power controllers to store excess electrical energy in lithium batteries; when the load power demand is large, the bidirectional power converters can be configured as power distributors to provide additional electrical energy support for the load.

[0092] Traditional power control and distribution systems typically employ fixed power controllers and distributors, requiring a complete set of equipment regardless of actual operating conditions, leading to equipment redundancy in many cases. The reconfigurable design of this invention allows the system to dynamically adjust the operating status of the equipment according to actual needs, avoiding unnecessary equipment redundancy.

[0093] By reconfiguring the intelligent control of the controller, the system can precisely adjust the number of bidirectional power converters used as power controllers and distributors based on the real-time status of the solar cell bus, load bus, and lithium battery bus.

[0094] The reconfigurable controller provides unified control over the pulse width of the bidirectional power converter, achieving a high degree of integration of multiple functions in the circulating energy system, including maximum power point tracking control, lithium battery charging control, and load power supply control. This centralized control approach not only improves the system's control accuracy and efficiency but also reduces the need for separate controllers for each function, further reducing the system's weight.

[0095] The reconfigurable controller can adjust the system's operating parameters in real time based on factors such as the aircraft's flight status, energy reserves, and payload power requirements. For example, when the aircraft enters a shaded area, the controller can adjust the lithium battery's charging and discharging strategy in advance to ensure stable operation of the aircraft during periods without sunlight exposure, while avoiding overcharging and over-discharging of the lithium battery, extending its lifespan, and reducing the additional weight burden caused by battery replacement.

[0096] This reconfigurable power control and distribution system is suitable for near-space low-speed aircraft, such as stratospheric airships and high-altitude balloons. These aircraft are characterized by long-duration loiter times and large payload capacities, placing high demands on the reliability and efficiency of their energy systems. This system can effectively solve the energy supply challenges of near-space aircraft, improve their endurance and mission execution capabilities, and has broad application prospects in fields such as communications, meteorological monitoring, and environmental monitoring.

[0097] The control core of the reconfigurable power control and power distribution architecture proposed in this invention is Figure 5 The reconfiguration controller in the system consists of three parts: contactor array control logic, lithium battery charging control logic, and load power supply control logic.

[0098] The contactor array control logic is used to configure the number of power controllers and distributors, improving 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 regulation of the load bus and the current sharing among the power modules.

[0099] Specifically, the contactor array control logic dynamically adjusts the number of power controllers and distributors based on the maximum power output of the solar array and the power consumption of the load bus. The lithium battery charging control logic controls the bidirectional power converter configured as a power controller to perform maximum power point tracking and constant voltage or constant current charging of the lithium battery. The load power supply control logic controls the bidirectional power converter configured as a distributor to perform constant voltage control and constant current protection of the load bus.

[0100] Regarding contactor array control, such as Figure 6 As shown, each contactor has three ports: the first port is the solar cell bus port, connected to the solar cell bus (photovoltaic array output), used to receive the DC input of the solar power generation system. The second port is the load bus port, connected to the load bus (load end), used to supply power to the aircraft payload (such as communication equipment, sensors, etc.). The third port is the converter port, connected to a bidirectional power converter (bidirectional DC / DC converter), serving as the hub for energy transmission.

[0101] The internal switch of the contactor is a double-pole double-throw structure, connected by a coil (each contactor corresponds to one coil, i.e.) Figure 5 The circuit (containers 1-N) controls whether the third port connects to the first or second port. When the third port is connected to the first port, the bidirectional power converter is configured as a power controller to perform power conversion between the solar cell bus and the lithium battery bus, realizing 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 power distributor to perform power conversion between the lithium battery bus and the load bus, realizing energy distribution from the lithium battery bus (energy storage) to the load bus (load).

[0102] The coil control logic is electromagnetically driven. The coil switches contacts via electromagnetic force to achieve a mechanical connection between the third port and the first or second port.

[0103] Traditional solutions require independent configuration of power controllers and power distributors. This invention achieves functional reuse through contactor switching. The bidirectional power converter can be dynamically configured as either a power controller or a power distributor, reducing hardware redundancy and system complexity. The operating mode automatically switches according to the spacecraft's mission phase (e.g., sunlight or shadow) and load requirements: during sunlight, the solar cell bus charges the lithium battery through the power controller or directly supplies power to the load. During shadow, the lithium battery supplies power to the load through the power distributor, ensuring continuous operation. The bidirectional power converter operates in its high-efficiency range in both modes, improving overall system efficiency. The short switching time of the double-pole double-throw contactor ensures continuous power supply and avoids the risk of load power outages. Through functional reuse and hardware simplification, the total weight of the contactors and power converter is reduced, lowering spacecraft launch costs. The double-pole double-throw contactor achieves functional reuse of the power controller and power distributor through mechanical switching, solving the problems of hardware redundancy, large weight, and poor flexibility in traditional solutions, significantly improving the energy management efficiency and reliability of near-space low-speed spacecraft. This invention adapts to the energy management requirements of day-night cycles, extending the spacecraft's endurance. Power can be flexibly allocated through the power distribution mode, supporting the connection of multiple types of loads.

[0104] The reconfigurable controller is responsible for controlling the entire reconfigurable power control and distribution network. It mainly has two functions: First, based on the sampling results of the solar cell bus, load bus, and lithium battery bus, it controls the engagement state of the contactor array and configures the number of power controllers and distributors. Second, based on the operating point of the solar cell array, the operating point of the lithium battery, and the operating state of the load, it uniformly controls the pulse width of the bidirectional power converter array to ensure the normal operation of functions such as maximum power point tracking, lithium battery charging control, and load power supply in the circulating energy system.

[0105] In an optional embodiment, the sampling results include the real-time time and location information of the aircraft and the power consumption of the payload bus. The real-time time and location information is used to calculate the maximum power output of the solar array. The power consumption of the payload bus is used to dynamically adjust the number of power distribution units.

[0106] Reference Figure 7 As shown, the contactor array control logic is divided into two threads, referred to as the first thread and the second thread.

[0107] The first thread is used to calculate the maximum power output P1 of the solar array based on the real-time time and location information of the aircraft, and to calculate the maximum power output P1 of the solar array based on the rated power P of the bidirectional power converter. DC Determine the required number of power controllers N1, where N1 = P1 / P DC Configure the remaining bidirectional power converters as power distribution units, with the number of power distribution units N2 being N-N1. Configure according to N1 and N2. Figure 5The control signals 1-N are used to configure the power controller and the number of power distributors through the relay status.

[0108] The second thread works synchronously or in quasi-parallel with the first thread.

[0109] 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 α of the total rated power of the distribution units, i.e., P L >α×N2×P DC At this point, the load bus is considered to have higher priority than the solar cell bus. First, the first thread is paused and the number of power distributors is increased (N2 = N2 + 1) until the power consumed by the load bus is lower than the second preset multiplier β (P) of the total rated power of the power distributors. L <β×N2×P DC After that, the first thread resumes running.

[0110] The calculation method for the maximum power output of a solar cell array can be found in the descriptions in existing technologies, and will not be repeated here.

[0111] This invention dynamically optimizes the number of power controllers and power distribution units by combining the maximum power output of the solar array with the real-time power consumption of the load bus. A first thread configures the number of power controllers in real-time based on the solar array's power output, ensuring maximum energy utilization. A second thread dynamically adjusts the number of power distribution units based on load demand, preventing system crashes due to overload. Dynamic configuration of the bidirectional power converter reduces the number of independent power controllers and power distribution units, lowering system weight. The dual-thread architecture ensures that the system can still recover stable operation through dynamic adjustments under overload conditions. The reconfigured controller unifies and coordinates all devices, achieving global optimization of MPPT, lithium battery charging, and load power supply.

[0112] In an optional embodiment, regarding lithium battery charging control, the lithium battery charging control logic controls a bidirectional power converter configured as a power controller to achieve maximum power point tracking and constant voltage or constant current charging control functions for the lithium battery. The sampling results mentioned above include lithium battery voltage and lithium battery charging current; refer to... Figure 8 As shown, the lithium battery charging control logic is as follows:

[0113] First, the lithium battery voltage is sampled and assessed. If the lithium battery voltage reaches the constant voltage point (referred to as the first operating state), the power controller enters the constant voltage operating mode and calculates the duty cycle for the next cycle according to the constant voltage control method, obtaining the duty cycle value duty3. The duty cycle is adjusted through closed-loop feedback to maintain a constant output voltage and prevent overcharging. This ensures safe charging of the battery during the full charge phase, avoiding electrolyte decomposition or thermal runaway caused by excessive voltage.

[0114] If the lithium battery voltage has not reached the constant voltage point and the lithium battery charging current has reached the constant current point (referred to as the second operating state), the power controller enters the constant current operating mode and calculates the duty cycle for the next cycle according to the constant current control method, obtaining the duty cycle value duty2. The current can be kept constant through PWM modulation to quickly replenish the battery. This achieves efficient fast charging when the battery capacity is low, shortening the charging time.

[0115] If the first or second working state is not met, i.e., the constant voltage and constant current conditions are not met, the power controller enters the maximum power point tracking mode (MPPT mode) and calculates the duty cycle of the next cycle according to the maximum power point tracking control method to obtain the duty cycle value duty1.

[0116] The duty cycle of all power controllers is uniformly configured by the reconfiguration controller to ensure multi-channel collaborative operation. To ensure the stability and current sharing of the control process, the reconfiguration controller simultaneously configures the duty cycle of all power controllers to duty1, duty2, or duty3, and all power controllers perform power conversion according to duty1, duty2, or duty3.

[0117] The control cycle of this control logic is T1. After T1 is reached, the reconfiguration controller resamples the lithium battery bus and starts the next control cycle.

[0118] The duty cycle calculation process under constant pressure operating mode is as follows:

[0119] 1. Sample lithium battery bus voltage: Obtain the current bus voltage V in real time. bus .

[0120] 2. Calculation error: The error is related to the preset constant pressure value V. ref The difference ΔV:

[0121]

[0122] 3. PI controller calculation: The duty cycle adjustment ΔD is calculated using a proportional-integral (PI) controller.

[0123]

[0124] In the formula, K p K is a proportionality coefficient that controls the response speed. i The integral coefficient is used to eliminate steady-state error.

[0125] 4. Update duty cycle: Add the adjustment amount to the current duty cycle D to obtain the duty cycle D for the next cycle. new :

[0126] D new =D+ΔD

[0127] The duty cycle calculation process under constant current protection mode is as follows:

[0128] 1. Sample lithium battery bus current: Obtain the current bus current I in real time. bus .

[0129] 2. Calculation error: Compared with the preset constant current value I ref The difference ΔI:

[0130]

[0131] 3. PI controller calculation: The duty cycle adjustment ΔD is calculated using the PI controller.

[0132]

[0133] K p , K i The selection needs to ensure that the current is stable at I ref the following.

[0134] 4. Update duty cycle: Add the current duty cycle D to the adjustment amount ΔD to obtain the duty cycle D for the next cycle. new :

[0135] D new = D +ΔD

[0136] This invention's charging control logic achieves efficient, safe, and flexible control of the lithium battery charging process through multi-mode switching, unified configuration, and dynamic response. It significantly improves energy utilization, extends battery life, and reduces system complexity. The MPPT mode tracks the maximum power point in real time, avoiding energy waste. The constant current mode enables rapid charging under high current, shortening the initial charging time; the constant voltage mode provides precise control in the later stages, preventing overcharging. The constant voltage mode strictly limits the voltage upper limit to prevent lithium-ion deposition or thermal runaway; the constant current mode prevents battery overheating through current limiting. Multi-mode switching allows for rapid response to changes in battery state, preventing abnormal operating conditions. The reconfigured controller unifies the duty cycle parameters, reducing interference between multiple controllers and improving system robustness.

[0137] In an optional embodiment, the load power supply control logic controls a bidirectional power converter configured as a distributor to achieve constant voltage control and constant current protection for the load bus. The sampling results include the load bus current; refer to... Figure 9 As shown, the load power supply control logic is as follows:

[0138] First, the load bus is sampled and judged. If the load bus current exceeds the sum of the rated current of the distribution unit, the distribution unit enters the constant current protection mode and calculates the duty cycle of the next cycle according to the constant current output method, and obtains the duty cycle value duty5.

[0139] If the load bus current does not exceed the total rated current of the distribution unit, the distribution unit enters constant voltage operating mode and calculates the duty cycle for the next cycle according to the constant voltage output method, obtaining the duty cycle value duty4. The distribution unit limits the output current to within the rated value by adjusting the duty cycle of the bidirectional power converter, preventing overload damage. The duty cycle for the next cycle is dynamically calculated based on the preset constant current value and the current bus current to ensure precise current control.

[0140] The duty cycle of all power distribution units is uniformly configured by the reconfiguration controller. To ensure stability and current sharing during the control process, the reconfiguration controller simultaneously configures the duty cycle of all power distribution units to either duty 4 or duty 5, and all power distribution units perform power conversion according to duty 4 or duty 5. The power distribution units maintain a constant bus voltage by adjusting their duty cycles, ensuring stable operation of downstream equipment. The duty cycle for the next cycle is dynamically calculated based on the preset constant voltage value and the current bus voltage, achieving closed-loop voltage control.

[0141] The control cycle of this control logic is T2. After T2 is reached, the reconfiguration controller resamples the load bus and starts the next control cycle.

[0142] This invention achieves precise management of load bus current and voltage through dynamic switching between constant current protection and constant voltage control, ensuring equipment safety and system stability. The constant current protection mode effectively prevents equipment damage caused by bus current overload. By limiting 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 bus voltage output, providing a reliable power environment for downstream equipment (such as motors, controllers, and communication modules). Reduced voltage fluctuations lower equipment failure rates, extend service life, and reduce maintenance costs. The system can quickly switch operating modes based on real-time current sampling results to adapt to different load requirements. For example, when the load suddenly increases, the system can quickly enter constant current protection mode to avoid overload; after the load stabilizes, it switches back to constant voltage mode to optimize energy efficiency. The unified configuration of the reconfigured controller simplifies system design and reduces the complexity of multi-controller collaborative operation. This architecture is easily expandable and can adapt to different power levels and numbers of power distribution units, meeting the needs of systems of different sizes. By dynamically adjusting the duty cycle, the system can achieve efficient energy conversion in both constant pressure and constant current modes. This avoids the energy waste associated with traditional fixed control methods and improves overall energy efficiency.

[0143] The reconfigurable power control and distribution method for near-space low-speed aircraft provided by the present invention is described below. The reconfigurable power control and distribution method for near-space low-speed aircraft described below can be referred to in correspondence with the reconfigurable power control and distribution system for near-space low-speed aircraft described above.

[0144] The present invention also provides a reconfigurable power control and power distribution method for near-space low-speed aircraft, using the reconfigurable power control and power distribution system for near-space low-speed aircraft as described above, the method comprising:

[0145] S110. The solar cell bus, load bus and lithium battery bus are sampled by the reconfiguration controller to obtain the sampling results;

[0146] S120. By reconfiguring the controller based on the sampling results of the solar cell bus, load bus and lithium battery bus, the engagement state of the double-pole double-throw contactor is controlled, the bidirectional power converter is dynamically configured as a power controller or distributor, and the pulse width of the bidirectional power converter is uniformly controlled to achieve maximum power point tracking control, lithium battery charging control and load power supply control in the near-space low-speed aircraft recirculating energy system.

[0147] In an optional embodiment, the sampling results include the real-time time and location information of the aircraft and the power consumption of the payload bus; contactor array control is achieved in the following manner:

[0148] The first thread calculates the maximum power output of the solar array based on the real-time time and location information of the aircraft. Based on the maximum power output of the solar array and the rated power of the bidirectional power converter, it determines the required number of power controllers N1. The remaining bidirectional power converters are configured as power distributors, and the number of power distributors is N-N1.

[0149] The second thread works synchronously or in quasi-parallel with the first thread.

[0150] 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 total rated power of the distribution units, the first thread is paused and the number of distribution units is increased until the power consumption of the load bus is lower than the second preset multiple of the total rated power of the distribution units, after which the first thread is resumed.

[0151] In an optional embodiment, the sampling results include lithium battery voltage and lithium battery charging current; lithium battery charging control is achieved in the following manner:

[0152] 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.

[0153] In the second working state, if the lithium battery voltage has not reached the constant voltage point and the lithium battery charging current has reached 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.

[0154] If the first or second operating state is not met, the power controller enters the maximum power point tracking mode and calculates the duty cycle for the next cycle according to the maximum power point tracking control method.

[0155] The duty cycle of all power controllers is configured uniformly by the reconfiguration controller.

[0156] In an optional embodiment, the sampling results include the load bus current; load power supply control is achieved in the following manner:

[0157] If the load bus current exceeds the sum of the rated currents of the distribution units, the distribution units will enter constant current protection mode and calculate the duty cycle of the next cycle according to the constant current output method.

[0158] If the load bus current does not exceed the total rated current of the distribution unit, the distribution unit enters the constant voltage working mode and calculates the duty cycle of the next cycle according to the constant voltage output method.

[0159] The duty cycle of all power distribution units is configured uniformly by the reconfiguration controller.

[0160] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence 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 cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.

[0161] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to 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, include: Solar cell array; Lithium batteries; Electrical load; A reconfigurable power control and distribution network connects the solar cell bus, lithium battery bus, and 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 that supplies power to the electrical loads. 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 via the contactor. The reconfiguration controller is used to sample the solar cell bus, load bus, and lithium battery bus to obtain sampling results. Based on the sampling results of the solar cell bus, load bus, and lithium battery bus, it controls the engagement state of the contactor, dynamically configures the bidirectional power converter as a power controller or distributor, and uniformly controls the pulse width of the bidirectional power converter to achieve maximum power point tracking control, lithium battery charging control, and load power supply control in the near-space low-speed aircraft recirculating energy system. The contactor includes: The first port connects to the solar cell bus; The second port connects to the load busbar; The third port connects to the bidirectional power converter; The contactor controls the connection of the third port to the first port or the second port via a coil; Specifically, 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.

2. 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: The contactor array control logic is used to dynamically adjust the number of power controllers and distributors based on the maximum power output 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 point 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.

3. The reconfigurable power control and distribution system for near-space low-speed aircraft according to claim 2, characterized in that, The sampling results include the real-time time and location information of the aircraft and the power consumption of the payload bus. The contactor array control logic includes: The first thread is used to calculate the maximum power output of the solar array based on the real-time time and location information of the aircraft, determine the required number of power controllers N1 based on the maximum power output of the solar array and the rated power of the bidirectional power converter, and configure the remaining bidirectional power converters as power distributors, with the number of power distributors being N-N1. The second thread works synchronously or in 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 distribution units, the first thread is paused and the number of distribution units is increased until the power consumption of the load bus is lower than the second preset multiple of the total rated power of the distribution units, and then the first thread is resumed.

4. The reconfigurable power control and distribution system for near-space low-speed aircraft according to claim 2, characterized in that, The sampling results include lithium battery voltage and 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 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 has not reached the constant voltage point and the lithium battery charging current has reached 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 first or second operating state is not met, the power controller enters the maximum power point tracking mode and calculates the duty cycle for the next cycle according to the maximum power point tracking control method. The duty cycle of all power controllers is configured uniformly by the reconfiguration controller.

5. The reconfigurable power control and distribution system for near-space low-speed aircraft according to claim 2, characterized in that, 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 units, the distribution units will enter constant current protection mode and calculate the duty cycle of the next cycle according to the constant current output method. If the load bus current does not exceed the total rated current of the distribution unit, the distribution unit enters the constant voltage working mode and calculates the duty cycle of the next cycle according to the constant voltage output method. The duty cycle of all power distribution units is configured uniformly by the reconfiguration controller.

6. A reconfigurable power supply control and power distribution method for a near-space low-speed aircraft, characterized in that, The method of using the reconfigurable power control and distribution system for near-space low-speed aircraft as described in any one of claims 1-5 includes: The solar cell bus, load bus, and lithium battery bus are sampled by the reconfiguration controller to obtain the sampling results; By reconfiguring the controller based on the sampling results of the solar cell bus, load bus and lithium battery bus, the contactor's engagement state is controlled, the bidirectional power converter is dynamically configured as a power controller or distributor, and the pulse width of the bidirectional power converter is uniformly controlled to achieve maximum power point tracking control, lithium battery charging control and load power supply control in the near-space low-speed aircraft's recirculating energy system. The contactor includes: The first port connects to the solar cell bus; The second port connects to the load busbar; The third port connects to the bidirectional power converter; The contactor controls the connection of the third port to the first port or the second port via a coil; Specifically, 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.

7. The reconfigurable power supply control and distribution method for near-space low-speed aircraft according to claim 6, characterized in that, The sampling results include the aircraft's real-time time and location information, and the payload bus power consumption; contactor array control is achieved through the following method: The first thread calculates the maximum power output of the solar array based on the real-time time and location information of the aircraft. Based on the maximum power output of the solar array and the rated power of the bidirectional power converter, it determines the required number of power controllers N1. The remaining bidirectional power converters are configured as power distributors, and the number of power distributors is N-N1. The second thread works synchronously or in 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 total rated power of the distribution units, the first thread is paused and the number of distribution units is increased until the power consumption of the load bus is lower than the second preset multiple of the total rated power of the distribution units, after which the first thread is resumed.

8. The reconfigurable power supply control and distribution method for near-space low-speed aircraft according to claim 6, characterized in that, The sampling results include lithium battery voltage and lithium battery charging current; lithium battery charging control is achieved through 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 cycle of the next cycle according to the constant voltage control method. In the second working state, if the lithium battery voltage has not reached the constant voltage point and the lithium battery charging current has reached 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 first or second operating state is not met, the power controller enters the maximum power point tracking mode and calculates the duty cycle for the next cycle according to the maximum power point tracking control method. The duty cycle of all power controllers is configured uniformly by the reconfiguration controller.

9. The reconfigurable power supply control and distribution method for near-space low-speed aircraft according to claim 6, characterized in that, The sampling results include the load bus current; load power supply control is achieved through the following method: If the load bus current exceeds the sum of the rated currents of the distribution units, the distribution units will enter constant current protection mode and calculate the duty cycle of the next cycle according to the constant current output method. If the load bus current does not exceed the total rated current of the distribution unit, the distribution unit enters the constant voltage working mode and calculates the duty cycle of the next cycle according to the constant voltage output method. The duty cycle of all power distribution units is configured uniformly by the reconfiguration controller.

Images