A distributed power supply system for hybrid-powered aircraft

Abstract

This invention discloses a distributed power supply system for a hybrid-powered aircraft, comprising a left power grid, a middle power grid, a right power grid, and a rear power grid, each of which is electrically connected to the other three power grids. The left power grid includes a left power battery pack, a left distributed power supply module, and a left motor. The middle power grid includes a left main power grid channel, a main power grid emergency channel, and a main power grid right channel. The right power grid includes a right distributed power supply module, which is electrically connected to the right power battery pack and the right motor. The rear power grid includes a rear distributed power supply module, which is electrically connected to the rear power battery pack and the rear motor. This invention, employing the aforementioned distributed power supply system for a hybrid-powered aircraft, can solve the stability and security problems of the power grid after a power source is lost. It offers flexible power distribution control, automatically switching control through power failure, and improves energy utilization.

Description

Technical Field

[0001] This invention relates to the field of power supply technology for hybrid aircraft, and in particular to a distributed power supply system for hybrid aircraft. Background Technology

[0002] The environmental problems caused by the air transport industry are receiving increasing attention. Both the United States and the European Union have set new requirements and specific development goals for the next generation of commercial aircraft in terms of fuel consumption, noise control, and pollution emissions. NASA, using the performance of existing aircraft as a benchmark, has conducted research on N+X generation aircraft, with N+3 generation aircraft (technology level for 2030-2035) requiring a 70% reduction in fuel consumption and an 80% reduction in nitrogen oxide emissions. The European Union has also proposed using 2000 technology levels as a benchmark, aiming to achieve a 75% reduction in carbon dioxide emissions, a 90% reduction in nitrogen oxide emissions, and a 65% reduction in noise emissions by 2050. GE has proposed hybrid turbine electric propulsion systems as a potential replacement for gas turbine engines, and NASA has begun exploring, through ground and flight tests, whether distributed hybrid electric propulsion systems will become the next revolutionary turning point in civil aviation.

[0003] Distributed electric propulsion aircraft are a new concept aircraft that emerged with the development of electric aircraft. Multiple propellers or fans distributed on the wings or fuselage, driven by electric motors, form the propulsion system that provides the main thrust. Distributed electric propulsion aircraft significantly improve the aerodynamic characteristics of the aircraft by utilizing the propulsion-aerodynamic coupling effect, reducing wing area and thus lowering the structural weight. The propellers have no high-pressure turbine blades, and the power distribution further reduces the overall sound pressure level of aerodynamic noise. The redundancy of multiple propellers provides more reliable thrust assurance, thus offering higher aerodynamic efficiency, carrying capacity, environmental friendliness, and robustness in flight control and thrust provision compared to traditional electric aircraft.

[0004] Distributed electric propulsion is widely used in hybrid aircraft due to its advantages of high aerodynamic efficiency, high structural strength, high propulsion efficiency, high safety margin, and high control margin. It realizes the spatial topology of the engine and generator through distributed layout, which provides an application basis for distributed power supply of aircraft. Summary of the Invention

[0005] The purpose of this invention is to provide a distributed power supply system for hybrid-powered aircraft that can solve the problems of power grid stability and security after a power source is lost. The system offers flexible power distribution control and can automatically switch control in case of power failure, thereby improving energy utilization.

[0006] To achieve the above objectives, the present invention provides a distributed power supply system for a hybrid-powered aircraft, comprising a left power grid, a middle power grid, a right power grid, and a rear power grid, wherein each power grid is electrically connected to the other three power grids.

[0007] The left power grid includes a left distributed power supply module, which is electrically connected to the left power battery pack and the left motor respectively.

[0008] The central power grid includes a main power grid left channel, a main power grid emergency channel, and a main power grid right channel. Both the main power grid left channel and the main power grid right channel are electrically connected to the main power grid emergency channel. A main power grid left channel generator is electrically connected to the main power grid left channel, and a main power grid right channel generator is electrically connected to the main power grid right channel.

[0009] The right-side power grid includes a right-side distributed power supply module, which is electrically connected to the right-side power battery pack and the right-side motor respectively.

[0010] The rear power grid includes a rear distributed power supply module, which is electrically connected to the rear power battery pack and the rear motor.

[0011] Preferably, the left channel of the main power grid and the emergency channel of the main power grid are electrically connected through a first AC contactor and a second DC contactor; the right channel of the main power grid and the emergency channel of the main power grid are electrically connected through a second AC contactor and a fifth DC contactor.

[0012] Preferably, the left channel of the main power grid and the left distributed power supply module are electrically connected via a left DC / AC converter and a first DC contactor, respectively.

[0013] Preferably, the right channel of the main power grid and the right distributed power supply module are electrically connected via a right DC / AC converter and a fourth DC contactor, respectively.

[0014] Preferably, the main power grid emergency channel and the rear distributed power supply module are electrically connected via a third DC contactor and a DC / DC converter, respectively.

[0015] Preferably, the rear distributed power supply module is electrically connected to the left distributed power supply module via a sixth DC contactor; the rear distributed power supply module is electrically connected to the right distributed power supply module via a seventh DC contactor; and the left distributed power supply module is electrically connected to the right distributed power supply module via both the sixth and seventh DC contactors.

[0016] Preferably, when at least one of the left-side distributed power supply module, the left channel of the main power grid, the emergency channel of the main power grid, the right channel of the main power grid, the right-side distributed power supply module, and the rear-side distributed power supply module experiences a power supply anomaly, the power supply system is reconfigured, and redundant power is provided by a power supply channel or power battery pack that can supply power normally.

[0017] Preferably, when the main power grid left channel loses power, the main power grid emergency channel, the left power battery pack, the right power battery pack and the rear power battery pack shall provide redundant power to the main power grid left channel in sequence.

[0018] When the main power grid emergency channel loses power, the main power grid right channel, main power grid left channel, right power battery pack, left power battery pack and rear power battery pack shall provide redundant power to the main power grid emergency channel in sequence.

[0019] When the main power grid right channel loses power, the main power grid emergency channel, right power battery pack, left power battery pack and rear power battery pack shall provide redundant power to the main power grid right channel in sequence.

[0020] Preferably, SOC state thresholds are pre-set for the left power battery pack, right power battery pack, and rear power battery pack respectively. When the power supply of the left distributed power supply module is abnormal, the SOC state of the left power battery pack is first checked. If the SOC state of the left power battery pack is not below the threshold, the right power battery pack supplies power to the left distributed power supply module. If the SOC state of the right power battery pack is not below the threshold, the rear power battery pack supplies power to the left distributed power supply module. If the SOC state of the rear power battery pack is not below the threshold, the left power battery pack, right power battery pack, and rear power battery pack continue to supply power independently, providing redundant power supply in sequence.

[0021] When the right-side distributed power supply module experiences a power supply malfunction, the SOC status of the right power battery pack is first checked. If the SOC status of the right power battery pack is below the threshold, the left power battery pack supplies power to the right-side distributed power supply module. If the SOC status of the left power battery pack is below the threshold, the rear power battery pack supplies power to the right-side distributed power supply module. If the SOC status of the rear power battery pack is below the threshold, the right power battery pack, left power battery pack, and rear power battery pack continue to supply power independently, providing redundant power supply in sequence.

[0022] When the power supply of the rear distributed power supply module is abnormal, the SOC status of the rear power battery pack is first detected. If the SOC status of the rear power battery pack is not below the threshold, the right power battery pack supplies power to the rear distributed power supply module. If the SOC status of the right power battery pack is not below the threshold, the left power battery pack supplies power to the rear distributed power supply module. If the SOC status of the left power battery pack is not below the threshold, the rear power battery pack, left power battery pack, and right power battery pack continue to supply power independently, providing redundant power supply in sequence.

[0023] Preferably, when the main power grid emergency channel, the main power grid right channel, and the main power grid left channel all lose power supply, and only one of the left power battery pack, the right power battery pack, and the rear power battery pack can supply power and the SOC state of that power battery pack is not below the threshold, the power supply interconnection is downgraded, and that power battery pack only supplies power to the local distributed power supply module and the main power grid emergency channel.

[0024] Therefore, the above-mentioned distributed power supply system for hybrid-powered aircraft can solve the problems of power grid stability and security after a power source is lost. The power distribution control is flexible and can automatically switch control through power failure, thereby improving energy utilization.

[0025] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the installation position of an embodiment of a distributed power supply system for a hybrid-electric aircraft relative to the aircraft according to the present invention;

[0027] Figure 2 This is a schematic diagram of the composition structure of an embodiment of a distributed power supply system for a hybrid-powered aircraft according to the present invention;

[0028] Figure 3 This is a power supply logic flowchart of an embodiment of a distributed power supply system for a hybrid-powered aircraft according to the present invention.

[0029] Figure Labels

[0030] 1. Left power grid; 101. Left power battery pack; 102. Left distributed power supply module; 103. Left motor; 2. Central power grid; 21. Left channel of main power grid; 211. Generator of left channel of main power grid; 212. Left DC / AC converter; 213. First DC contactor; 214. Second DC contactor; 215. First AC contactor; 22. Emergency channel of main power grid; 221. Third DC contactor; 222. DC / DC converter; 23. Right channel of main power grid; 2 31. Main power grid right channel generator; 232. Right DC / AC converter; 233. Fourth DC contactor; 234. Fifth DC contactor; 235. Second AC contactor; 3. Right power grid; 301. Right power battery pack; 302. Right distributed power supply module; 303. Right motor; 4. Rear power grid; 401. Rear power battery pack; 402. Rear distributed power supply module; 403. Rear motor; 404. Sixth DC contactor; 405. Seventh DC contactor. Detailed Implementation

[0031] The technical solution of the present invention will be further described below with reference to the accompanying drawings and embodiments.

[0032] Unless otherwise defined, the technical or scientific terms used in this invention shall have the ordinary meaning understood by one of ordinary skill in the art to which this invention pertains. The terms "first," "second," and similar terms used in this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Terms such as "comprising" or "including" mean that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, without excluding other elements or objects. Terms such as "connected" or "linked" are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. Terms such as "upper," "lower," "left," and "right" are used only to indicate relative positional relationships; when the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0033] Example 1

[0034] like Figure 1 As shown, the present invention provides a distributed power supply system for a hybrid power aircraft, including a left power grid 1, a middle power grid 2, a right power grid 3 and a rear power grid 4, and each power grid is electrically connected to the other three power grids.

[0035] The left power grid 1 includes a left distributed power supply module 102, which is electrically connected to the left power battery pack 101 and the left motor 103.

[0036] The central power grid 2 includes a main power grid left channel 21, a main power grid emergency channel 22, and a main power grid right channel 23. Both the main power grid left channel 21 and the main power grid right channel 23 are electrically connected to the main power grid emergency channel 22. The main power grid left channel 21 is energized with a main power grid left channel generator 211, and the main power grid right channel 23 is energized with a main power grid right channel generator 231.

[0037] The right power grid 3 includes a right distributed power supply module 302, which is electrically connected to the right power battery pack 301 and the right motor 303 respectively.

[0038] The rear power grid 4 includes a rear distributed power supply module 402, which is electrically connected to the rear power battery pack 401 and the rear motor 403.

[0039] The main power grid left channel 21 and the main power grid emergency channel 22 are electrically connected through the first AC contactor 215 and the second DC contactor 214; the main power grid right channel 23 and the main power grid emergency channel 22 are electrically connected through the second AC contactor 235 and the fifth DC contactor 234.

[0040] The main power grid left channel 21 and the left distributed power supply module 102 are electrically connected through the left DC / AC converter 212 and the first DC contactor 213, respectively.

[0041] The right channel 23 of the main power grid and the right distributed power supply module 302 are electrically connected through the right DC / AC converter 232 and the fourth DC contactor 233, respectively.

[0042] The main power grid emergency channel 22 and the rear distributed power supply module 402 are electrically connected through the third DC contactor 221 and the DC / DC converter 222, respectively.

[0043] The rear distributed power supply module 402 is electrically connected to the left distributed power supply module 102 via the sixth DC contactor 404; the rear distributed power supply module 402 is electrically connected to the right distributed power supply module 302 via the seventh DC contactor 405; the left distributed power supply module 102 is electrically connected to the right distributed power supply module 302 via the sixth DC contactor 404 and the seventh DC contactor 405 respectively.

[0044] When at least one of the following power supply modules experiences a power supply anomaly: left-side distributed power supply module 102, main grid left channel 21, main grid emergency channel 22, main grid right channel 23, right-side distributed power supply module 302, or rear-side distributed power supply module 402, the power supply system is reconfigured. Redundant power supply is provided by a power supply channel or power battery pack that can supply power normally. The power supply method is as follows: Figure 3 As shown, the details are as follows:

[0045] When the main grid left channel 21 loses power, the main grid emergency channel 22, left power battery pack 101, right power battery pack 301 and rear power battery pack 401 successively provide redundant power to the main grid left channel 21.

[0046] When the main grid emergency channel 22 loses power, the main grid right channel 23, main grid left channel 21, right power battery pack 301, left power battery pack 101 and rear power battery pack 401 will sequentially provide redundant power to the main grid emergency channel 22.

[0047] When the main grid right channel 23 loses power, the main grid emergency channel 22, right power battery pack 301, left power battery pack 101 and rear power battery pack 401 will sequentially provide redundant power to the main grid right channel 23.

[0048] SOC (State of Charge) thresholds are pre-set for the left power battery pack 101, right power battery pack 301, and rear power battery pack 401. When the power supply of the left distributed power supply module 102 is abnormal, the SOC status of the left power battery pack 101 is checked first. If the SOC status of the left power battery pack 101 is not below the threshold, the right power battery pack 301 supplies power to the left distributed power supply module 102. If the SOC status of the right power battery pack 301 is not below the threshold, the rear power battery pack 401 supplies power to the left distributed power supply module 102. If the SOC status of the rear power battery pack 401 is not below the threshold, the left power battery pack 101, right power battery pack 301, and rear power battery pack 401 continue to supply power independently, providing redundant power supply in sequence.

[0049] When the right-side distributed power supply module 302 experiences a power supply malfunction, the SOC status of the right power battery pack 301 is first checked. If the SOC status of the right power battery pack 301 is below the threshold, the left power battery pack 101 supplies power to the right-side distributed power supply module 302. If the SOC status of the left power battery pack 101 is below the threshold, the rear power battery pack 401 supplies power to the right-side distributed power supply module 302. If the SOC status of the rear power battery pack 401 is below the threshold, the right power battery pack 301, the left power battery pack 101, and the rear power battery pack 401 continue to supply power independently, providing redundant power in sequence.

[0050] When the power supply of the rear distributed power supply module 402 is abnormal, the SOC status of the rear power battery pack 401 is checked first. If the SOC status of the rear power battery pack 401 is not below the threshold, the right power battery pack 301 supplies power to the rear distributed power supply module 402. If the SOC status of the right power battery pack 301 is not below the threshold, the left power battery pack 101 supplies power to the rear distributed power supply module 402. If the SOC status of the left power battery pack 101 is not below the threshold, the rear power battery pack 401, the left power battery pack 101 and the right power battery pack 301 continue to supply power independently, and the power supply is redundant in sequence.

[0051] When the main power grid emergency channel 22, the main power grid right channel 23, and the main power grid left channel 21 all lose power, and only one of the left power battery pack 101, the right power battery pack 301, and the rear power battery pack 401 can provide power and the SOC state of that power battery pack is not below the threshold, the power supply interconnection is downgraded. That power battery pack only supplies power to the local distributed power supply module and the main power grid emergency channel 22 to ensure the safety of the aircraft's power supply.

[0052] Therefore, the above-mentioned distributed power supply system for hybrid-powered aircraft can solve the problems of power grid stability and security after a power source is lost. The power distribution control is flexible and can automatically switch control through power failure, thereby improving energy utilization.

[0053] 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 preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the technical solutions of the present invention, and these modifications or equivalent substitutions cannot cause the modified technical solutions to deviate from the spirit and scope of the technical solutions of the present invention.

Claims

1. A distributed power supply system for a hybrid-powered aircraft, characterized in that: It includes a left power grid, a middle power grid, a right power grid, and a rear power grid, and each power grid is electrically connected to the other three power grids; The left power grid includes a left distributed power supply module, which is electrically connected to the left power battery pack and the left motor respectively. The central power grid includes a main power grid left channel, a main power grid emergency channel, and a main power grid right channel. Both the main power grid left channel and the main power grid right channel are electrically connected to the main power grid emergency channel. A main power grid left channel generator is electrically connected to the main power grid left channel, and a main power grid right channel generator is electrically connected to the main power grid right channel. The right-side power grid includes a right-side distributed power supply module, which is electrically connected to the right-side power battery pack and the right-side motor respectively. The rear power grid includes a rear distributed power supply module, which is electrically connected to the rear power battery pack and the rear motor.

2. The distributed power supply system for a hybrid-powered aircraft according to claim 1, characterized in that: The left channel of the main power grid is electrically connected to the emergency channel of the main power grid via a first AC contactor and a second DC contactor; the right channel of the main power grid is electrically connected to the emergency channel of the main power grid via a second AC contactor and a fifth DC contactor.

3. The distributed power supply system for a hybrid-powered aircraft according to claim 1, characterized in that: The main power grid left channel and the left distributed power supply module are electrically connected via the left DC / AC converter and the first DC contactor, respectively.

4. A distributed power supply system for a hybrid-powered aircraft according to claim 1, characterized in that: The right channel of the main power grid and the right distributed power supply module are electrically connected via the right DC / AC converter and the fourth DC contactor, respectively.

5. A distributed power supply system for a hybrid-powered aircraft according to claim 1, characterized in that: The main power grid emergency channel and the rear distributed power supply module are electrically connected via a third DC contactor and a DC / DC converter, respectively.

6. A distributed power supply system for a hybrid-powered aircraft according to claim 1, characterized in that: The rear distributed power supply module is electrically connected to the left distributed power supply module via a sixth DC contactor; the rear distributed power supply module is electrically connected to the right distributed power supply module via a seventh DC contactor; the left distributed power supply module is electrically connected to the right distributed power supply module via both the sixth and seventh DC contactors.

7. A distributed power supply system for a hybrid-powered aircraft according to claim 1, characterized in that: When at least one of the following—the left-side distributed power supply module, the left channel of the main power grid, the emergency channel of the main power grid, the right channel of the main power grid, the right-side distributed power supply module, and the rear-side distributed power supply module—experiences a power supply anomaly, the power supply system is reconfigured, and redundant power is provided by a power supply channel or power battery pack that can supply power normally.

8. A distributed power supply system for a hybrid-powered aircraft according to claim 7, characterized in that: When the main power grid left channel loses power, the main power grid emergency channel, the left power battery pack, the right power battery pack and the rear power battery pack provide redundant power to the main power grid left channel in sequence. When the main power grid emergency channel loses power, the main power grid right channel, main power grid left channel, right power battery pack, left power battery pack and rear power battery pack shall provide redundant power to the main power grid emergency channel in sequence. When the main power grid right channel loses power, the main power grid emergency channel, right power battery pack, left power battery pack and rear power battery pack shall provide redundant power to the main power grid right channel in sequence.

9. A distributed power supply system for a hybrid-powered aircraft according to claim 7, characterized in that: SOC (State of Charge) thresholds are pre-set for the left, right, and rear power battery packs. When the power supply of the left distributed power supply module is abnormal, the SOC status of the left power battery pack is first checked. If the SOC status of the left power battery pack is not below the threshold, the right power battery pack supplies power to the left distributed power supply module. If the SOC status of the right power battery pack is not below the threshold, the rear power battery pack supplies power to the left distributed power supply module. If the SOC status of the rear power battery pack is not below the threshold, the left, right, and rear power battery packs continue to supply power independently, providing redundant power supply in sequence. When the right-side distributed power supply module experiences a power supply malfunction, the SOC status of the right power battery pack is first checked. If the SOC status of the right power battery pack is below the threshold, the left power battery pack supplies power to the right-side distributed power supply module. If the SOC status of the left power battery pack is below the threshold, the rear power battery pack supplies power to the right-side distributed power supply module. If the SOC status of the rear power battery pack is below the threshold, the right power battery pack, left power battery pack, and rear power battery pack continue to supply power independently, providing redundant power supply in sequence. When the power supply of the rear distributed power supply module is abnormal, the SOC status of the rear power battery pack is first detected. If the SOC status of the rear power battery pack is not below the threshold, the right power battery pack supplies power to the rear distributed power supply module. If the SOC status of the right power battery pack is not below the threshold, the left power battery pack supplies power to the rear distributed power supply module. If the SOC status of the left power battery pack is not below the threshold, the rear power battery pack, left power battery pack, and right power battery pack continue to supply power independently, providing redundant power supply in sequence.

10. A distributed power supply system for a hybrid-electric aircraft according to claim 9, characterized in that: When the main power grid emergency channel, the main power grid right channel, and the main power grid left channel all lose power supply, and only one of the left power battery pack, the right power battery pack, and the rear power battery pack can supply power and the SOC state of that power battery pack is not below the threshold, the power supply interconnection is downgraded, and that power battery pack only supplies power to the local distributed power supply module and the main power grid emergency channel.

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