An aircraft multi-source heterogeneous power supply system and a regulation method thereof

Abstract

The application discloses an aircraft multi-source heterogeneous power supply system and a regulation and control method thereof, which comprises a battery pack, a first gas turbine generator, a first generator controller, a first gas switch valve, a second gas turbine generator, a second generator controller and a second gas switch valve. According to the comparison result of the real-time power of the power load, the rated power of the first generator controller and the rated power of the second generator controller, the on-off of the first gas switch valve and the second gas switch valve and the power supply state of the battery pack connected to the power supply bus are controlled. The application is applied to the field of aircraft electrical design, adopts a system architecture of combined power supply of gas turbine power generation and battery pack, effectively improves the system energy density, reduces the system volume and weight, and effectively realizes automatic and reliable switching between ground power supply, redundant gas turbine power generation and the battery pack, thereby guaranteeing the system power supply reliability and realizing efficient utilization of primary energy.

Description

Technical Field

[0001] This invention relates to the field of aircraft electrical design technology, specifically to a multi-source heterogeneous power supply system for aircraft and its control method. Background Technology

[0002] For aircraft capable of round-trip air transport, a typical flight mission consists of five phases: takeoff, air-breathing acceleration climb, rocket-assisted acceleration climb, reentry energy management, and approach / landing. The power modes and flight environments of such aircraft vary greatly across different mission phases, resulting in orders-of-magnitude differences in the types of electrical loads, power consumption, and load characteristics. For example, the takeoff and air-breathing acceleration climb phases require the simultaneous operation of high-voltage, high-power electromechanical loads such as air servo motors, power intake and exhaust actuators, circulation pumps, and landing gear, as well as pipeline solenoid valves and low-voltage, low-power electronic loads, with peak power requirements reaching hundreds of kilowatts. The rocket-assisted acceleration climb and reentry energy management phases only require the operation of low-power valves and electronic loads, and low-power servo mechanisms, significantly reducing power consumption. The approach / landing phase, however, again presents a concentrated power supply requirement for high-power electromechanical loads. Meanwhile, during the takeoff and acceleration climb phases when peak power demand is highest, the engine of this type of aircraft cannot provide shaft power output and can only provide gas flow for power generation. After the acceleration climb phase ends, the gas flow supply capacity disappears completely, and subsequent flight phases cannot rely on the gas flow to continuously generate electricity.

[0003] In existing power supply technologies in similar fields, traditional launch vehicles only have a single flight mission during the ascent phase, resulting in a simple flight profile, small and uniform electrical load power across the entire rocket. They generally use chemical battery packs to directly power the entire rocket load. This approach cannot meet the wide-ranging power demands of spacecraft operating between Earth and space. When facing peak power demands of hundreds of kilowatts, pure chemical battery power supply leads to a sharp increase in system size and weight, failing to meet the stringent weight constraints of the spacecraft. Conventional aircraft generally employ a three-tiered power supply architecture: a main power source from an engine turbine shaft-driven generator, a backup power source from an air turbine, and an emergency power source from chemical batteries. This architecture relies on the continuous shaft power provided by the engine for continuous power generation, which is completely unsuitable for the unique dynamic characteristics of spacecraft operating between Earth and space without shaft power output and only able to provide gas flow for short periods. Furthermore, it cannot resolve the contradiction between system redundancy and energy efficiency caused by the extremely high peak-to-average power ratio. Summary of the Invention

[0004] To address the shortcomings of the existing technology, this invention provides a multi-source heterogeneous power supply system for aircraft and its control method, which can achieve efficient and highly reliable power supply for the entire flight profile and the entire load of the aircraft under the strict weight constraints of a spacecraft traveling between Earth and space.

[0005] To achieve the above objective, the present invention provides an aircraft multi-source heterogeneous power supply system, comprising a power supply bus, an electrical load, a ground power supply, a ground control device and a power distributor, wherein the ground power supply is electrically connected to the power supply bus, and the power distributor is electrically connected to the power supply bus, the electrical load and the ground control device respectively; The power supply system further comprises a storage battery pack, a first gas turbine generator, a first generator controller, a first gas on-off valve, a second gas turbine generator, a second generator controller and a second gas on-off valve; The storage battery pack, the first generator controller and the second generator controller are electrically connected to the power supply bus respectively, the first gas turbine generator and the second gas turbine generator are electrically connected to the first generator controller and the second generator controller respectively, and the first gas on-off valve and the second gas on-off valve are respectively arranged on gas pipelines of the first gas turbine generator and the second gas turbine generator; The first generator controller and the second generator controller are respectively in communication connection with the first gas on-off valve and the second gas on-off valve, and are configured to control on-off of the first gas on-off valve and the second gas on-off valve and a power supply state of the storage battery pack connected to the power supply bus according to a comparison result of real-time power of the electrical load, rated power of the first generator controller and rated power of the second generator controller.

[0006] In one embodiment, when P L > P1+P2, the first generator controller and the second generator controller respectively control the first gas on-off valve and the second gas on-off valve to open, and the storage battery pack, the first gas turbine generator and the second gas turbine generator jointly supply power to the power supply bus; wherein, P L is real-time power of the electrical load, P1 is rated power of the first generator controller, and P2 is rated power of the second generator controller.

[0007] In one embodiment, when P L < P1+P2, the second generator controller controls the second gas on-off valve to close, and a single generator power supply mode is entered; In the single generator power supply mode: when P L > P1, the storage battery pack and the first gas turbine generator jointly supply power to the power supply bus; when P L < P1, the first generator controller controls the first gas on-off valve to close, and the storage battery pack independently supplies power to the power supply bus; Among them, P L P1 is the real-time power of the electrical load, P2 is the rated power of the first generator controller, and P2 is the rated power of the second generator controller.

[0008] In one embodiment, when the battery pack supplies power to the power bus alone, the real-time power of the electrical load is continuously collected and the average power P within a first set time window is calculated. L1 : When P L1 When P1 is less than or equal to 1, the battery pack supplies power to the power supply bus independently. When P L1 When P1 is reached, the first generator controller controls the first gas switch valve to open.

[0009] In one embodiment, after the first generator controller controls the first gas switch valve to open, the real-time power of the electrical load is continuously collected and the average power P within a second set time window is calculated. L2 When P L2 When P1+P2, the second generator controller controls the second gas switch valve to open.

[0010] In one embodiment, the window lengths of both the first set time window and the second set time window are 5s to 10s.

[0011] To achieve the above objectives, the present invention also provides a control method for the above-mentioned multi-source heterogeneous power supply system of an aircraft, comprising the following steps: Step 1: Connect the ground power supply to the power supply bus and send a power-on command to the power distributor through the ground control equipment to complete the ground power-on of each electrical load; Step 2: Send start commands to the first generator controller and the second generator controller through the ground control equipment, and simultaneously control the opening of the first gas switch valve and the second gas switch valve. The first gas turbine generator and the second gas turbine generator start and generate electricity. At the same time, the power supply path of the ground power supply is automatically shut off, completing the power transfer from the generator to the ground. Step 3: Collect the real-time power P of the electrical load. L Comparison P L Based on the numerical relationship between the rated power P1 of the first generator controller and the rated power P2 of the second generator controller, the corresponding control strategy is executed: If P L >P1+P2 controls the battery pack to connect to the power supply bus, and jointly supplies power with the first gas turbine generator and the second gas turbine generator; If P L =P1+P2, maintaining the current state of dual-generator power supply; if P L <P1+P2, controlling to turn off the second gas on-off valve and entering the single-generator power supply mode; Step 4, in the single-generator power supply mode, comparing P L with the rated power P1 of the first generator controller to implement a corresponding control strategy: if P L > P1, controlling the battery pack to connect to the power supply bus for combined power supply with the first gas turbine generator; if P L = P1, maintaining the current state of single-generator power supply; if P L < P1, controlling to turn off the first gas on-off valve and entering the independent power supply mode of the battery pack; Step 5, in the independent power supply mode of the battery pack, continuously collecting the real-time power of the electrical load and calculating the average power P within a first set time window L1 and the average power P within a second set time window L2 , comparing P L1 and P L2 with the rated power P1 of the first generator controller and the rated power P2 of the second generator controller to implement a corresponding control strategy: when P L1 ≤ P1, maintaining the independent power supply mode of the battery pack; when P L1 > P1, controlling the first gas on-off valve to open, and returning to step 4 when P L2 ≤ P1+P2, and returning to step 3 after controlling the second gas on-off valve to open when P L2 > P1+P2.

[0012] Compared with the prior art, the present invention has the following beneficial technical effects: 1. The power supply system in the present invention adopts a system architecture of combined power supply by gas turbine power generation and battery pack, which effectively improves the energy density of the system and reduces the volume and weight of the system; 2. The regulation method of the present invention can effectively realize automatic and reliable switching among ground power supply, redundant gas turbine power generation and the battery pack, which not only ensures the power supply reliability of the system but also realizes efficient utilization of primary energy. Description of Drawings

[0013] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0014] Figure 1 This is a schematic diagram of the structure of the multi-source heterogeneous power supply system for an aircraft in an embodiment of the present invention; Figure 2 This is a flowchart of the control method in an embodiment of the present invention.

[0015] Reference numerals: 1. Power supply busbar; 2. Electrical load; 3. Ground power supply; 4. Ground control equipment; 5. Power distributor; 6. Battery pack; 7. First gas turbine generator; 8. First generator controller; 9. First gas switch valve; 10. Second gas turbine generator; 11. Second generator controller; 12. Second gas switch valve.

[0016] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0017] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0018] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0019] Furthermore, in this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0020] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two elements or the interaction between two elements, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0021] Furthermore, the technical solutions of the various embodiments of the present invention can be combined with each other, but only if they are feasible for those skilled in the art. If the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

[0022] like Figure 1 The diagram illustrates a multi-source heterogeneous power supply system for an aircraft disclosed in this embodiment. It mainly includes a power supply bus 1, an electrical load 2, a ground power source 3, ground control equipment 4, a power distributor 5, a battery pack 6, a first gas turbine generator 7, a first generator controller 8, a first gas switching valve 9, a second gas turbine generator 10, a second generator controller 11, and a second gas switching valve 12. The ground power source 3, battery pack 6, first generator controller 8, and second generator controller 11 are electrically connected to the power supply bus 1. The power distributor 5 is electrically connected to the power supply bus 1, the electrical load 2, and the ground control equipment 4. The ground control equipment 4 is electrically connected to the first generator controller 8 and the second generator controller 11. By employing a system architecture that combines gas turbine power generation and battery pack 6 for power supply, the system's energy density is effectively improved, while its size and weight are reduced.

[0023] The first gas turbine generator 7 is electrically connected to the first generator controller 8, and the second gas turbine generator 10 is electrically connected to the second generator controller 11. A first gas switching valve 9 is located on the gas pipeline of the first gas turbine generator 7 and is used to control whether the first gas turbine generator 7 generates electricity; a second gas switching valve 12 is located on the gas pipeline of the second gas turbine generator 10 and is used to control whether the second gas turbine generator 10 generates electricity. Preferably, both the first gas switching valve 9 and the second gas switching valve 12 are located on the gas outlet pipeline to improve their service life. The first generator controller 8 is communicatively connected to the first gas switching valve 9 to control its on / off state; the second generator controller 11 is communicatively connected to the second gas switching valve 12 to control its on / off state.

[0024] In this embodiment, the power supply system has a built-in control strategy module in communication connection with the first generator controller 8, the second generator controller 11 and the storage battery pack 6, which is configured to control the on-off of the first gas on-off valve 9 and the second gas on-off valve 12 and the power supply state of the storage battery pack 6 connected to the power supply bus 1 according to the comparison result of the real-time power of the electric load 2, the rated power of the first generator controller 8 and the rated power of the second generator controller 11.

[0025] In this embodiment, let the real-time power of the electric load 2 be P L , the rated power of the first generator controller 8 is P1, the rated power of the second generator controller 11 is P2, the power supply voltage of the power supply bus 1 is U0, the power supply voltage of the ground power supply 3 is U1, the rated output voltage of the first generator controller 8 and the second generator controller 11 is U2, the output voltage of the storage battery pack 6 is U3, and the initial voltage of the storage battery pack 6 is U 30 , wherein U2>U1>U 30 .

[0026] In this embodiment, the process of controlling the on-off of the first gas on-off valve 9 and the second gas on-off valve 12 and the power supply state of the storage battery pack 6 connected to the power supply bus 1 according to the comparison result of the real-time power of the electric load 2, the rated power of the first generator controller 8 and the rated power of the second generator controller 11 specifically comprises: When P L <P1+P2, the second generator controller 11 controls the second gas on-off valve 12 to disconnect, and enters the single generator power supply mode. In the single generator power supply mode: When P L >P1, the storage battery pack 6 and the first gas turbine generator 7 jointly supply power to the power supply bus 1; When P L <P1, the first generator controller 8 controls the first gas on-off valve 9 to disconnect, and the storage battery pack 6 supplies power to the power supply bus 1 alone.

[0027] In the mode that the storage battery pack 6 supplies power to the power supply bus 1 alone, the real-time power of the electric load 2 is continuously collected and the average power P within a first set time window is calculated L1 : when P L1 ≤P1, the storage battery pack 6 is kept to supply power to the power supply bus 1 alone; when P L1 >P1, the first generator controller 8 controls the first gas on-off valve 9 to open. After the first generator controller 8 controls the first gas on-off valve 9 to open, the real-time power of the electric load 2 is continuously collected and the average power P within a second set time window is calculated L2 , when P L2>P1+P2, the second generator controller 11 controls the second gas switch valve 12 to open. Wherein, the window lengths of both the first set time window and the second set time window are 5s~10s, preferably 5s.

[0028] Based on the above control strategy, this embodiment further discloses a control method for the above-mentioned multi-source heterogeneous power supply system of an aircraft, with reference to Figure 2 , the control method mainly comprises the following steps: Step 1: connecting the ground power supply 3 to the power supply bus 1, wherein the power supply voltage U0 of the power supply bus 1 is equal to the output voltage U1 of the ground power supply 3, then sending a power-on instruction to the power distributor 5 through the ground control device 4, and completing the ground power-on of each electric load 2; Step 2: sending start instructions to the first generator controller 8 and the second generator controller 11 through the ground control device 4, synchronously controlling and opening the first gas switch valve 9 and the second gas switch valve 12, the first gas turbine generator 7 and the second gas turbine generator 10 start to generate power, the rated output voltage U2 of the first generator controller 8 and the second generator controller 11 is higher than the output voltage U1 of the ground power supply 3, the power supply path of the ground power supply 3 is automatically turned off, the aircraft-to-ground power conversion is completed, and at the same time the ground control device 4 disconnects the electrical connection with the first generator controller 8 and the second generator controller 11; Step 3: collecting the real-time power P of the electric load 2 L , comparing P L with the numerical relationship among the rated power P1 of the first generator controller 8 and the rated power P2 of the second generator controller 11, and executing a corresponding control strategy: if P L >P1+P2, controlling the storage battery pack 6 to access the power supply bus 1 to supply power jointly with the first gas turbine generator 7 and the second gas turbine generator 10; if P L =P1+P2, maintaining the current state of dual-generator power supply; if P L <P1+P2, controlling to turn off the second gas switch valve 12 and entering the single-generator power supply mode; Step 4: in the single-generator power supply mode, comparing P L with the numerical relationship between the rated power P1 of the first generator controller 8, and executing a corresponding control strategy: if P L >P1, controlling the storage battery pack 6 to access the power supply bus 1 to supply power jointly with the first gas turbine generator 7; if P L =P1, maintaining the current state of single-generator power supply; if P L<P1,control to turn off the first gas on-off valve 9, and enter the independent power supply mode of the battery pack 6; Step 5, in the independent power supply mode of the battery pack 6, continuously collect the real-time power of the electrical load 2 and calculate the average power P within the first set time window L1 and the average power P within the second set time window L2 , compare the numerical relationship among P L1 , P L2 , the rated power P1 of the first generator controller 8, and the rated power P2 of the second generator controller 11, and execute the corresponding control strategy: When P L1 ≤ P1, maintain the independent power supply mode of the battery pack 6; When P L1 > P1, control the first gas on-off valve 9 to open, and when P L2 ≤ P1+P2, return to step 4, and when P L2 > P1+P2, control the second gas on-off valve 12 to open and then return to step 3.

[0029] The regulation method in this embodiment constructs a closed-loop power matching regulation logic, which can adaptively complete the switching of working modes among combined power supply of dual gas turbine generators, single gas turbine generator power supply, independent power supply of battery pack 6, and multi-source combined energy supplementary power supply according to the real-time power of the electrical load 2, so as to effectively adapt to the full mission segment power characteristics and energy supply conditions of the space vehicle for round trip between heaven and earth. Meanwhile, through the design of the judgment threshold for the average power, the frequent switching problem caused by instantaneous fluctuation of load power is avoided, the action frequency of gas on-off valves and generators is greatly reduced, the service life of core components is prolonged, and the reliability of long-term operation of the system is further improved. In addition, the graded switching design of dual gas turbine generators realizes the redundant fault tolerance capability of mutual backup; when a single generator fails, the other generator can quickly undertake the basic power demand and cooperate with the battery pack 6 to supplement the power gap, ensuring uninterrupted power supply for the load of the whole vehicle, and greatly improving the power supply safety under extreme working conditions.

[0030] The above description is only the preferred embodiment of the present invention, and therefore does not limit the protection scope of the present invention. Any equivalent structural transformation made by using the description and accompanying drawings of the present invention under the inventive concept of the present invention, or direct or indirect application to other related technical fields, shall be included in the protection scope of the present invention.

Claims

1. A multi-source heterogeneous power supply system for an aircraft, comprising a power supply bus, an electrical load, a ground power supply, ground control equipment, and a power distribution unit, wherein the ground power supply is electrically connected to the power supply bus, and the power distribution unit is electrically connected to the power supply bus, the electrical load, and the ground control equipment, respectively; Its features are, It also includes a battery pack, a first gas turbine generator, a first generator controller, a first gas switching valve, a second gas turbine generator, a second generator controller, and a second gas switching valve; The battery pack, the first generator controller, and the second generator controller are electrically connected to the power supply bus, the first gas turbine generator and the second gas turbine generator are electrically connected to the first generator controller and the second generator controller, respectively, and the first gas switch valve and the second gas switch valve are respectively installed on the gas pipelines of the first gas turbine generator and the second gas turbine generator. The first generator controller and the second generator controller are respectively communicatively connected to the first gas switch valve and the second gas switch valve, and are used to control the opening and closing of the first gas switch valve and the second gas switch valve, as well as the power supply status of the battery pack connected to the power supply bus, based on the comparison result of the real-time power of the electrical load, the rated power of the first generator controller, and the rated power of the second generator controller. Let the supply voltage of the power supply bus be U0, the supply voltage of the ground power supply be U1, the rated output voltage of the first generator controller and the second generator controller be U2, and the initial voltage of the battery pack be U. 30 Where U2>U1>U 30 After the first gas turbine generator and the second gas turbine generator start and generate electricity, the rated output voltage U2 of the first generator controller and the second generator controller is higher than the output voltage U1 of the ground power supply, and the power supply path of the ground power supply is automatically shut off, completing the power transfer from the generator to the ground. In the mode where the battery pack supplies power to the power bus alone, the real-time power of the electrical load is continuously collected and the average power P within a first set time window is calculated. L1 When P L1 When P ≤ P1, the battery pack supplies power to the power supply bus independently; when P L1 When P1 is reached, the first generator controller controls the first gas switch valve to open. After the first generator controller controls the first gas switch valve to open, it continuously collects the real-time power of the electrical load and calculates the average power P within the second set time window. L2 When P L2 When P1+P2, the second generator controller controls the second gas switch valve to open; Wherein, P1 is the rated power of the first generator controller, P2 is the rated power of the second generator controller, and the window length of both the first and second set time windows is 5s to 10s.

2. The multi-source heterogeneous power supply system for aircraft according to claim 1, characterized in that, When P L When P1+P2, the first generator controller and the second generator controller respectively control the first gas switch valve and the second gas switch valve to open, and the battery pack, the first gas turbine generator and the second gas turbine generator jointly supply power to the power supply bus. Among them, P L This represents the real-time power of the electrical load.

3. The multi-source heterogeneous power supply system for aircraft according to claim 1 or 2, characterized in that, When P L < P1+P2, the second generator controller controls the second gas switch valve to disconnect and enter the single generator power supply mode; In the single generator power supply mode: When P L >At time P1, the battery pack and the first gas turbine generator jointly supply power to the power supply bus; When P L is less than P1, said first generator controller controls said first gas switch valve to open in a closed position, and said storage battery pack supplies power to said power supply bus independently; Among them, P L P1 is the real-time power of the electrical load, P2 is the rated power of the first generator controller, and P2 is the rated power of the second generator controller.

4. A method for controlling a multi-source heterogeneous power supply system for an aircraft as described in any one of claims 1 to 3, characterized in that, Includes the following steps: Step 1: Connect the ground power supply to the power supply bus and send a power-on command to the power distributor through the ground control equipment to complete the ground power-on of each electrical load; Step 2: Send start commands to the first generator controller and the second generator controller through the ground control equipment, and simultaneously control the opening of the first gas switch valve and the second gas switch valve. The first gas turbine generator and the second gas turbine generator start and generate electricity. At the same time, the power supply path of the ground power supply is automatically shut off, completing the power transfer from the generator to the ground. Step 3: Collect the real-time power P of the electrical load. L Comparison P L Based on the numerical relationship between the rated power P1 of the first generator controller and the rated power P2 of the second generator controller, the corresponding control strategy is executed: If P L >P1+P2 controls the battery pack to connect to the power supply bus, and jointly supplies power with the first gas turbine generator and the second gas turbine generator; If P L =P1+P2, maintaining the current state of dual-generator power supply; If P L <P1+P2, control to turn off the second gas switch valve and enter the single generator power supply mode; Step 4, in single generator power supply mode, compare P L The numerical relationship between the rated power P1 of the first generator controller and the actual power is used to execute the corresponding control strategy: If P L >P1 controls the battery pack to connect to the power supply bus and supply power together with the first gas turbine generator; If P L =P1, maintain the current state of single generator power supply; If P L <P1, control to turn off the first gas switch valve, and enter the independent power supply mode of the storage battery group; Step 5: In the battery pack-only power supply mode, continuously collect the real-time power of the electrical load and calculate the average power P within the first set time window. L1 and the average power P within the second set time window L2 Comparison P L1 P L2 Based on the numerical relationship between the rated power P1 of the first generator controller and the rated power P2 of the second generator controller, the corresponding control strategy is executed: When P L1 When P1 is ≤, maintain the battery pack's independent power supply mode; When P L1 >At P1, the first gas switch valve is opened, and at P L2 If P ≤ P1 + P2, return to step 4. L2 After controlling the second gas switch valve to open when P1+P2, return to step 3.

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