Hybrid power system of aircraft

Abstract

The invention discloses a hybrid power system of an aircraft, which relates to the technical field of flight equipment and comprises a motor, a generator and a battery, and the motor is respectively connected with the generator and the battery. In the takeoff and landing modes of the aircraft, the generator and the battery can uniformly distribute the electric power to the motor respectively, so that the motor obtains the electric power with the same power from the generator and the battery respectively, thereby realizing the balanced distribution of the electric power in the takeoff and landing stages, and ensuring that the motor obtains enough power. In the cruising mode of the aircraft, the generator can uniformly distribute the electric power to the motor, and the generator can charge the battery by using the surplus electric power, so that the cruising ability of the aircraft can be improved, and the overall working efficiency and reliability of the aircraft can be improved.

Description

Technical Field

[0001] This application relates to the field of flight equipment technology, and in particular to a hybrid power system for an aircraft. Background Technology

[0002] With the development of aviation technology, electric aircraft are gradually becoming the trend of future aviation development. Traditional aircraft power systems mostly rely on fuel engines or pure electric power systems, but pure electric aircraft have certain limitations in terms of range, power requirements during takeoff and landing, and system redundancy. In particular, the limited range of pure electric aircraft, and the limited battery capacity and electric motor power supply, have become bottlenecks restricting their widespread application.

[0003] Existing all-electric aircraft still cannot meet the demands of long-duration flight and heavy-load conditions due to insufficient battery range and energy density. In particular, during takeoff and landing, electric motors need to provide a large amount of power instantaneously, while pure battery systems, due to battery capacity limitations, often struggle to meet these high power requirements, easily leading to insufficient flight time or inadequate system stability. Summary of the Invention

[0004] The purpose of this application is to provide a hybrid power system for aircraft, which aims to solve the technical problem of insufficient range of pure electric power systems in the prior art.

[0005] To achieve the above objectives, this application proposes a hybrid power system for an aircraft, the hybrid power system of which includes an electric motor, a generator, and a battery, wherein the electric motor is connected to the generator and the battery respectively; In the takeoff and landing modes of the aircraft, the generator and the battery can distribute power evenly to the motor, so that the motor can obtain the same amount of power from the generator and the battery respectively; In the aircraft's cruise mode, the generator can distribute power evenly to the motors, and the generator can use excess power to charge the battery.

[0006] In one embodiment, the number of motors is one, the number of batteries is at least two, and one motor is connected to at least two batteries so that at least two batteries power one motor.

[0007] In one embodiment, each motor includes at least two winding circuits, the number of batteries corresponds one-to-one with the number of winding circuits, and each battery is connected to each corresponding winding circuit.

[0008] In one embodiment, the number of batteries is one, and the number of motors is at least two. One battery is connected to at least two motors respectively, so that one battery provides power to at least two motors.

[0009] In one embodiment, the number of batteries is at least two, the number of motors is at least two, the number of batteries corresponds one-to-one with the number of motors, and at least two batteries and at least two motors are respectively connected to each other.

[0010] In one embodiment, the number of batteries is six, namely a first battery, a second battery, a third battery, a fourth battery, a fifth battery, and a sixth battery; the number of motors is six, namely a first motor, a second motor, a third motor, a fourth motor, a fifth motor, and a sixth motor; the first battery is connected to the first motor and the second motor; the second battery is connected to the second motor and the third motor; the third motor is connected to the third motor and the fourth motor; the fourth battery is connected to the fourth motor and the fifth motor; the fifth battery is connected to the fifth motor and the sixth motor; and the sixth battery is connected to the sixth motor and the first motor.

[0011] In one embodiment, the aircraft's hybrid power system further includes an inverter, through which the battery is connected to the motor.

[0012] In one embodiment, the hybrid power system of the aircraft further includes chargers, the number of which corresponds one-to-one with the batteries, and the chargers are connected to the generator and the batteries respectively.

[0013] In one embodiment, the hybrid power system of the aircraft further includes a busbar, through which the generator is connected to the motor.

[0014] In one embodiment, the charger is connected to the generator and the battery respectively via the busbar.

[0015] The above-mentioned technical solution of this application has at least the following beneficial technical effects: The technical solution of this application connects the motor to both the generator and the battery. During takeoff and landing, the generator and battery can evenly distribute power to the motor, ensuring that the motor receives equal power from both sources. This balanced power distribution during takeoff and landing guarantees sufficient power for the motor. During cruise, the generator can also evenly distribute power to the motor and use excess power to charge the battery, improving the aircraft's range and ultimately enhancing its overall efficiency and reliability. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of an embodiment of the hybrid power system of an aircraft provided in this application. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this application clearer, the application will be further described in detail below with reference to specific embodiments and accompanying drawings. It should be understood that these descriptions are merely exemplary and not intended to limit the scope of this application. Furthermore, descriptions of well-known structures and technologies are omitted in the following description to avoid unnecessarily obscuring the concepts of this application.

[0018] The embodiments described in this application are only some, not all, of the embodiments described herein. All other embodiments obtained by those skilled in the art based on the embodiments described herein without inventive effort are within the scope of protection of this application.

[0019] With the development of aviation technology, electric aircraft are gradually becoming the trend of future aviation development. Traditional aircraft power systems mostly rely on fuel engines or pure electric power systems, but pure electric aircraft have certain limitations in terms of range, power requirements during takeoff and landing, and system redundancy. In particular, the limited range of pure electric aircraft, and the limited battery capacity and electric motor power supply, have become bottlenecks restricting their widespread application.

[0020] Existing all-electric aircraft still cannot meet the demands of long-duration flight and heavy-load conditions due to insufficient battery range and energy density. In particular, during takeoff and landing, electric motors need to provide a large amount of power instantaneously, while pure battery systems, due to battery capacity limitations, often struggle to meet these high power requirements, easily leading to insufficient flight time or inadequate system stability.

[0021] To address the aforementioned technical problems, this application proposes a hybrid power system for aircraft. Please refer to [link / reference]. Figure 1In one embodiment of this application, the hybrid power system of the aircraft includes a motor, a generator, and a battery, with the motor connected to both the generator and the battery. Specifically, the motor can be a permanent magnet synchronous motor, a brushless DC motor, or an AC asynchronous motor; the generator can be a turboshaft generator or a constant-speed drive generator; and the battery can be a lithium-ion battery, a solid-state battery, or a nickel-metal hydride battery, without limitation. In one specific embodiment, an 800V lithium-ion battery is used. During takeoff and landing modes, the generator and battery can distribute power evenly to the motor, allowing the motor to obtain the same power from both the generator and the battery. During cruise mode, the generator can distribute power evenly to the motor, and can use excess power to charge the battery.

[0022] The technical solution of this application connects the motor to both the generator and the battery. During takeoff and landing, the generator and battery can evenly distribute power to the motor, ensuring that the motor receives equal power from both sources. This balanced power distribution during takeoff and landing guarantees sufficient power for the motor. During cruise, the generator can also evenly distribute power to the motor and use excess power to charge the battery, improving the aircraft's range and ultimately enhancing its overall efficiency and reliability.

[0023] In one embodiment, there is one motor and at least two batteries. One motor is connected to at least two batteries, so that at least two batteries power one motor. This embodiment, by connecting one motor to at least two batteries, provides a more stable and continuous power supply, which is beneficial for the efficient operation of the motor under different operating conditions. Simultaneous power supply from multiple batteries can effectively distribute the load, avoiding motor performance degradation or shutdown due to single battery failure or insufficient power. Furthermore, by optimizing battery energy output, it helps improve motor efficiency, ensuring the aircraft can operate smoothly under various load conditions.

[0024] In one embodiment, each motor includes at least two winding circuits, and the number of batteries corresponds one-to-one with the number of winding circuits, with each battery connected to its corresponding winding circuit. This embodiment, by ensuring a one-to-one correspondence between the number of winding circuits and batteries in each motor, achieves more precise power distribution, ensuring that each winding circuit receives a stable and sufficient power supply, which is beneficial for improving the motor's operating efficiency and stability. By directly connecting each battery to its corresponding winding circuit, power loss and uneven distribution are avoided, extending battery life and reducing motor performance fluctuations caused by uneven battery power supply.

[0025] In one embodiment, there is one battery and at least two motors. One battery is connected to at least two motors respectively, so that one battery provides power to at least two motors. This embodiment, by providing power to multiple motors with a single battery, effectively simplifies system design, reduces the number of batteries, lowers system costs, and ensures that the power needs of multiple motors are met during operation. Simultaneously powering multiple motors with a single battery improves the overall space utilization of the system, reduces the size and weight of the equipment, and facilitates a more compact and efficient design while ensuring a stable power supply.

[0026] In one embodiment, there are at least two batteries and at least two motors, with a one-to-one correspondence between the number of batteries and motors. Each of the at least two batteries is interconnected with each of the at least two motors. This embodiment, by connecting multiple batteries to multiple motors in a one-to-one correspondence, enables independent power supply to each motor from a single battery, ensuring even power distribution and efficient utilization. Furthermore, this approach helps improve the performance stability of the motors, avoiding unbalanced motor loads or unstable operation caused by uneven battery charge levels, thereby effectively improving the operating efficiency and reliability of the equipment. Independent power supply also ensures even distribution of battery wear, extending battery life and reducing the risk of malfunctions.

[0027] In one implementation, please refer to Figure 1 The system uses six batteries, designated as Battery 1, Battery 2, Battery 3, Battery 4, Battery 5, and Battery 6, and six motors, designated as Motor 1, Motor 2, Motor 3, Motor 4, Motor 5, and Motor 6. Battery 1 is connected to Motor 1 and Motor 2; Battery 2 is connected to Motor 2 and Motor 3; Motor 3 is connected to Motor 3 and Motor 4; Battery 4 is connected to Motor 4 and Motor 5; Battery 5 is connected to Motor 5 and Motor 6; and Battery 6 is connected to Motor 6 and Motor 1. This implementation precisely configures the six batteries and six motors, using a one-to-one connection method to ensure efficient and balanced power supply. Each battery powers only a fixed number of motors, avoiding power waste or insufficiency caused by too many or too few batteries. This solution effectively improves energy management efficiency, ensures system stability and efficiency, and enhances system reliability by strictly matching the number of batteries to motors, reducing redundancy or uneven battery charge levels.

[0028] In one embodiment, the aircraft's hybrid power system also includes an inverter, through which the battery is connected to the motor. This embodiment achieves efficient conversion and distribution of electrical energy by introducing an inverter to connect the battery and motor. The inverter's function is to convert the direct current supplied by the battery into alternating current suitable for the motor, thereby enabling the motor to operate more efficiently. In this way, optimal power transfer between the battery and motor can be achieved, improving the performance and stability of the hybrid power system.

[0029] In one embodiment, the aircraft's hybrid power system further includes chargers, with the number of chargers corresponding one-to-one with the batteries. Each charger is connected to both the generator and the battery. This embodiment provides an efficient battery charging and energy management solution by introducing a one-to-one correspondence between chargers and batteries and connecting the chargers to both the generator and the battery. In the aircraft's hybrid power system, the chargers can dynamically adjust the charging power based on the battery's state, ensuring that the battery maintains an optimal charge level during flight. This configuration not only effectively manages the battery charging and discharging process but also ensures the battery's health, preventing damage caused by charging too quickly or too slowly, thereby extending the battery's lifespan.

[0030] In one embodiment, the aircraft's hybrid power system also includes a busbar, through which the generator is connected to the motor. This embodiment achieves efficient power transfer between the generator and the motor by introducing a busbar into the aircraft's hybrid power system. As a centralized power connection component, the busbar can concentrate and evenly distribute the electrical energy output from multiple generators to the motors that require it, thereby improving the system's power management efficiency and operational stability. The busbar can efficiently deliver power from the generator to the motor and intelligently distribute it among multiple power input points.

[0031] In one embodiment, the charger is connected to both the generator and the battery via a busbar. This embodiment, by introducing a busbar into the aircraft's hybrid power system, enables the charger to connect to both the generator and the battery simultaneously, thereby achieving efficient power distribution and charging management. The busbar, acting as a centralized power transmission channel, can simultaneously deliver power generated by the generator to both the charger and the battery. This configuration not only improves the system's power utilization but also optimizes the battery charging process, allowing the charger to more effectively allocate electrical energy from the generator while charging the battery.

[0032] In motor failure scenarios, if a single winding of a motor fails, the problem can be addressed by adjusting the power distribution. Specifically, the system can appropriately reduce the power output of the symmetrical motors and correspondingly increase the power of the remaining windings on the failed motor to ensure stable system operation. Simultaneously, to avoid uneven battery load, the battery power supply can be adjusted to maintain a balanced discharge rate among the batteries, thereby preventing over-discharge of any single battery, extending battery life, and maintaining system reliability.

[0033] In battery failure scenarios, if a battery fails and cannot provide power, measures need to be taken to maintain the system's power supply. Specifically, the power of the symmetrical motors is appropriately reduced (typically by 10% to 20%) to decrease the demand on the batteries. Simultaneously, the remaining battery packs on the motor corresponding to the failed battery or inverter will provide additional power to compensate for the lost power. In this situation, the differentiated power distribution mechanism in the ring architecture plays a crucial role in ensuring balanced battery discharge. Please refer to [link to relevant documentation]. Figure 1 In a ring architecture, if one battery fails completely, it will cause the two motors connected to it to each lose power to a set of windings. In this situation, the system adjusts by having each adjacent motor draw more power from its corresponding battery for its remaining windings. Simultaneously, the differentiated power regulation mechanism in the ring architecture ensures more rational power distribution, guaranteeing a balanced battery discharge rate and preventing any single battery from over-discharging and affecting system stability. Furthermore, to maintain a suitable battery discharge rate, the system can further adjust the power of the symmetrical motors, appropriately reducing their output to avoid unnecessary excessive battery load and ensure the stable operation of the entire system.

[0034] The above-mentioned fault response methods ensure that the entire hybrid power system can still maintain efficient and stable operation in the event of motor or battery failure, minimizing the impact of the failure on the power system, extending equipment life, and improving the system's fault tolerance and safety.

[0035] This application aims to protect a hybrid power system for an aircraft. The technical solution of this application connects the motor to both a generator and a battery. During takeoff and landing, the generator and battery can evenly distribute power to the motor, ensuring that the motor receives equal power from both sources. This balanced power distribution during takeoff and landing guarantees sufficient power for the motor. In cruise mode, the generator can evenly distribute power to the motor and use excess power to charge the battery, improving the aircraft's range and ultimately enhancing its overall efficiency and reliability.

[0036] It should be understood that the specific embodiments described above are merely illustrative or explanatory of the principles of this application and do not constitute a limitation thereof. Therefore, any modifications, equivalent substitutions, improvements, etc., made without departing from the spirit and scope of this application should be included within the protection scope of this application. Furthermore, the appended claims are intended to cover all variations and modifications falling within the scope and boundaries of the appended claims, or equivalent forms of such scope and boundaries.

Claims

1. A hybrid power system for an aircraft, characterized in that, The hybrid power system comprises a motor, a generator and a battery, the motor is connected with the generator and the battery respectively; In the take-off and landing mode of the aircraft, the generator and the battery can uniformly distribute power to the motor respectively, so that the motor obtains the same power from the generator and the battery respectively; In the cruising mode of the aircraft, the generator can uniformly distribute power to the motor, and the generator can use the excess power to charge the battery.

2. The hybrid powertrain system of claim 1, wherein, The number of the motor is one, and the number of the battery is at least two, one motor is connected with at least two batteries, so that at least two batteries supply power to one motor.

3. The hybrid powertrain system of claim 2, wherein, Each motor comprises at least two winding circuits, the number of the battery corresponds to the number of the winding circuit, and each battery is connected with each corresponding winding circuit.

4. The hybrid powertrain system of claim 1, wherein, The number of the battery is one, and the number of the motor is at least two, one battery is connected with at least two motors respectively, so that one battery provides power for at least two motors.

5. The hybrid powertrain system of claim 1, wherein, The number of the battery is at least two, and the number of the motor is at least two, the number of the battery corresponds to the number of the motor, and at least two batteries and at least two motors are connected with each other respectively.

6. The hybrid powertrain system of claim 5, wherein, The number of the battery is six, and the number of the motor is six, the six batteries are respectively a first battery, a second battery, a third battery, a fourth battery, a fifth battery and a sixth battery, the six motors are respectively a first motor, a second motor, a third motor, a fourth motor, a fifth motor and a sixth motor, the first battery is connected with the first motor and the second motor respectively, the second battery is connected with the second motor and the third motor respectively, the third motor is connected with the third motor and the fourth motor respectively, the fourth battery is connected with the fourth motor and the fifth motor respectively, the fifth battery is connected with the fifth motor and the sixth motor respectively, and the sixth battery is connected with the sixth motor and the first motor respectively.

7. The hybrid powertrain system of claim 1, wherein, The hybrid power system of the aircraft further comprises an inverter, and the battery is connected with the motor through the inverter.

8. The hybrid powertrain system of claim 1, wherein, The hybrid power system of the aircraft further comprises a charging machine, the number of the charging machine corresponds to the number of the battery, and the charging machine is connected with the generator and the battery respectively.

9. The hybrid powertrain system of claim 1, wherein, The hybrid power system of the aircraft further comprises a bus bar, and the generator is connected with the motor through the bus bar.

10. The hybrid powertrain system of claim 9, wherein, The charging machine is connected with the generator and the battery through the bus bar respectively.

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