A ground scale test method and device for an aviation dual-voltage system hybrid system

Abstract

The application relates to the technical field of aviation dual-voltage hybrid technology, in particular to a ground scale-down test method and device for an aviation dual-voltage hybrid system; the method comprises the following steps: determining the architecture of a real scale-down prototype system; determining the architecture of a simulation device system; controlling the real scale-down prototype system and the simulation device system to perform a ground scale-down test; and analyzing and verifying the aviation dual-voltage hybrid system according to test data of the ground scale-down test; thus, the problem that the system architecture and the control method of the dual-voltage hybrid system cannot be fully and effectively verified is solved.

Description

Technical Field

[0001] This application relates to the field of aviation dual-voltage hybrid technology, and more specifically, to a ground-scale test method and apparatus for an aviation dual-voltage hybrid system. Background Technology

[0002] Hybrid power systems combine the high energy density and long range of traditional fuel propulsion systems with the low emissions and high efficiency of pure electric propulsion systems, and have become a research hotspot and an important technological development direction in the field of aerospace propulsion. In the development of the 270V / 540V dual-voltage hybrid system, ground-based scaled-down testing is a crucial verification step in the research and development process.

[0003] However, most commonly used ground testing methods are geared towards single-voltage powertrain systems or conventional hybrid powertrain configurations. Their test architecture and verification logic are not adapted to the unique operating mechanism of dual-voltage systems. In actual testing, it is difficult to accurately simulate the unique characteristics of voltage coordination regulation, multi-source power distribution, and dynamic response to operating condition switching under the 270V / 540V dual-voltage system. They cannot fully cover the core operating scenarios of dual-voltage hybrid systems and cannot fully and effectively verify the system architecture and control methods of dual-voltage hybrid systems. Summary of the Invention

[0004] To address the challenge of adequately and effectively verifying the system architecture and control methods of dual-voltage hybrid systems, this application provides a ground-based scaled-down test method and apparatus for aviation dual-voltage hybrid systems.

[0005] In a first aspect, this application provides a ground-scaled test method for an aviation dual-voltage hybrid system, the ground-scaled test method comprising:

[0006] The architecture of a scaled-down prototype system is determined; wherein, the scaled-down prototype system includes a turboshaft engine, a bidirectional motor, and a gearbox; the gearbox includes a transmission gear set and a first extension shaft, a second extension shaft, and a third extension shaft respectively drivenly connected to the transmission gear set; the first extension shaft is drivenly connected to the turboshaft engine; the second extension shaft is drivenly connected to the bidirectional motor;

[0007] The architecture of the simulation equipment system is determined; wherein, the simulation equipment system includes a first power supply, a second power supply, a mechanical load unit, an electrical load unit, and a power distribution management unit; the first power supply is a power supply with a first voltage system; the second power supply is a bidirectional power supply with a second voltage system; the first voltage is greater than the second voltage; the input terminal of the mechanical load unit is connected to the third extended shaft for transmission; the power distribution management unit is electrically connected to the bidirectional motor, the first power supply, the second power supply, and the electrical load unit respectively;

[0008] Control the real scaled-down prototype system and the simulation equipment system to conduct ground-based scaled-down tests;

[0009] The aviation dual-voltage hybrid system was analyzed and verified based on the test data from the ground-scaled test.

[0010] Optionally, the mechanical load unit includes a load motor and a first electrical load; the load motor is drivenly connected to the third extended shaft; the load motor is electrically connected to the first electrical load, and the load motor provides electrical energy to the first electrical load.

[0011] Optionally, the step of controlling the scaled-down prototype system and the simulation equipment system to conduct a ground-based scaled-down test includes:

[0012] Based on the requirements of ground-scale tests under parallel power mode, the bidirectional motor is controlled to be in motor mode, the first power source is controlled to output electrical energy at a first voltage to the bidirectional motor, the second power source is controlled to output electrical energy at a second voltage to the electrical load unit, and the turboshaft engine and the bidirectional motor are controlled to provide shaft power to the mechanical load unit.

[0013] Optionally, the step of analyzing and verifying the aviation dual-voltage hybrid system based on the test data from the ground-based scale-down test includes:

[0014] The stability of the bidirectional motor's electric power is determined based on the voltage and current of the bidirectional motor in the ground-scale test of the parallel power mode.

[0015] Optionally, the step of controlling the scaled-down prototype system and the simulation equipment system to conduct a ground-based scaled-down test includes:

[0016] Based on the ground-scale test requirements under the power supply mode, the bidirectional motor is controlled to generate power in the second voltage system, the voltage of the first power supply and the second power supply are both controlled to be 0, the bidirectional motor is controlled to output electrical energy to the electrical load unit, and the turboshaft engine is controlled to provide shaft power to the bidirectional motor and the mechanical load unit respectively.

[0017] Optionally, the step of analyzing and verifying the aviation dual-voltage hybrid system based on the test data from the ground-based scale-down test includes:

[0018] The power generation stability of the bidirectional motor is determined based on the voltage change of the electrical load unit in the ground-scale test of the power supply mode.

[0019] Optionally, the step of controlling the scaled-down prototype system and the simulation equipment system to conduct a ground-based scaled-down test includes:

[0020] Based on the ground-scale test requirements under the electric energy storage mode, the bidirectional motor is controlled to generate electricity in the second voltage mode, the voltage of the first power source is controlled to be 0, the voltage of the second power source is controlled to be the third voltage, the bidirectional motor is controlled to output electrical energy to the second power source and the electric load unit respectively, and the turboshaft engine is controlled to provide shaft power to the bidirectional motor and the mechanical load unit respectively; wherein, the third voltage is less than the second voltage.

[0021] Optionally, the step of analyzing and verifying the aviation dual-voltage hybrid system based on the test data from the ground-based scale-down test includes:

[0022] The stability of the bidirectional motor's power generation is determined based on the voltage change of the electrical load unit in the ground-scale test of the energy storage mode.

[0023] During the ground-scale test, when the bidirectional motor switches between multiple operating modes and enters the power generation state after the operating mode is switched, the power generation stability of the bidirectional motor is judged based on the dynamic voltage change of the electrical load unit.

[0024] Optionally, the step of analyzing and verifying the aviation dual-voltage hybrid system based on the test data from the ground-based scale-down test includes:

[0025] During the dynamic switching between multiple operating modes in the ground-scale test, the shaft power stability of the turboshaft engine is determined based on the speed fluctuation of the turboshaft engine.

[0026] Secondly, this application provides a ground-scaled test apparatus for an aviation dual-voltage hybrid system, applicable to the ground-scaled test method for an aviation dual-voltage hybrid system as described in any one of the first aspects, the ground-scaled test apparatus comprising:

[0027] The real prototype determination module is used to determine the architecture of the real scaled-down prototype system;

[0028] The simulation equipment determination module is used to determine the architecture of the simulation equipment system;

[0029] The test control module is used to control the real scaled-down prototype system and the simulation equipment system to conduct ground scaled-down tests.

[0030] The verification module is used to analyze and verify the aviation dual-voltage hybrid system based on the test data from the ground-scaled test.

[0031] To address the challenge of achieving sufficient and effective verification of the system architecture and control methods for dual-voltage hybrid systems, this application offers the following advantages:

[0032] This application employs a collaborative experimental architecture built upon a scaled-down prototype system and a simulation system. The scaled-down prototype system is equipped with a turboshaft engine, a bidirectional motor, and a gearbox, enabling mechanical power transmission with the simulation system via the gearbox's drive link. The simulation system includes a first power supply, a second power supply, a mechanical load unit, an electrical load unit, and a power distribution management unit. The functional separation of the first and second power supplies allows for the simulation of different battery operating modes and the working states of the energy storage unit under various conditions. Combined with the flexible parameter adjustment capabilities of the simulation system, this experimental architecture accurately reproduces the voltage coordination control, multi-source power distribution, and dynamic response characteristics under dual-voltage systems, achieving thorough verification of the architecture and control methods of the aerospace dual-voltage hybrid system. This allows for the completion of various functional tests using a scaled-down system with a consistent architecture before the development of a full-power aerospace dual-voltage hybrid system prototype, enabling early identification of problems in the control strategy, improving development efficiency, and avoiding repeated iterations during the development process. Meanwhile, this solution eliminates the need for batteries and DC / DC converters. It achieves the corresponding functions by using power supplies with different voltage systems in conjunction with a power distribution management unit. This reduces testing costs, avoids the safety risks associated with battery use under extreme conditions, and improves the safety of ground-based scale-down testing. Attached Figure Description

[0033] Figure 1 A flowchart of the ground-scale test method for the aviation dual-voltage hybrid system of Embodiment 1 is shown;

[0034] Figure 2 A schematic diagram of the structure of the scaled-down prototype system and the simulation equipment system of Embodiment 1 is shown.

[0035] Reference numerals: 10. Scaled-down prototype system; 11. Turboshaft engine; 12. Bidirectional motor; 13. Gearbox; 131. Transmission gear set; 132. First extension shaft; 133. Second extension shaft; 134. Third extension shaft; 20. Simulation equipment system; 21. First power supply; 22. Second power supply; 23. Mechanical load unit; 231. Load motor; 232. First electrical load; 24. Electrical load unit; 25. Power distribution management unit; 251. First relay; 252. Third relay; 253. Control module; 26. First controller; 261. Second controller; 262. Detailed Implementation

[0036] The present disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those skilled in the art to better understand and thus implement the present disclosure, and are not intended to imply any limitation on the scope of the disclosure.

[0037] As used herein, the term "comprising" and its variations are to be interpreted as open-ended terms meaning "including but not limited to". The term "based on" is to be interpreted as "at least partially based on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment". The term "another embodiment" is to be interpreted as "at least one other embodiment". The terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "vertical", "horizontal", "lateral", "longitudinal", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments and are not intended to limit the indicated devices, elements, or components to having a specific orientation or being constructed and operated in a specific orientation. Furthermore, some of the above terms may be used to indicate other meanings besides orientations or positional relationships; for example, the term "upper" may in some cases indicate a dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application according to the specific circumstances. In addition, the terms "installed", "set up", "equipped with", "connected", and "linked" should be interpreted broadly. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or an internal connection between two devices, elements, or components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances. Furthermore, the terms "first," "second," etc., are mainly used to distinguish different devices, elements, or components (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance or quantity of the indicated devices, elements, or components. Unless otherwise stated, "a plurality of" means two or more.

[0038] During the ground-scale test of the aviation dual-voltage hybrid system, existing ground test methods are unable to accurately simulate the unique operating characteristics of the dual-voltage system, such as voltage coordinated regulation, multi-source power distribution, and dynamic response to operating condition switching. This makes it impossible to comprehensively and fully verify the system architecture and control methods of the aviation dual-voltage hybrid system, and it is difficult to complete the corresponding ground-scale test verification work before the full-power system prototype development stage.

[0039] Example 1:

[0040] In this embodiment, a ground-scale test method for an aviation dual-voltage hybrid system is provided, such as... Figure 1 As shown, the ground-scale test method includes steps S10 to S40. The ground-scale test method executes steps S10, S20, S30, and S40 sequentially.

[0041] Step S10: Determine the architecture of the scaled-down prototype system 10. Among other things, such as... Figure 2 As shown, the scaled-down prototype system 10 includes a turboshaft engine 11, a bidirectional motor 12, and a gearbox 13, which together form the core unit of the hybrid power system at a scaled-down scale, realizing the integrated coupling of fuel power and electric power. The gearbox 13 includes a transmission gear set 131 and a first extension shaft 132, a second extension shaft 133, and a third extension shaft 134, which are respectively connected to the transmission gear set 131, realizing the convergence and divergence of power from multiple paths and ensuring power matching and stable transmission between various power components. The first extension shaft 132 is connected to the turboshaft engine 11, enabling the input of power output from the turboshaft engine 11 to the gearbox 13. The second extension shaft 133 is connected to the bidirectional motor 12, realizing bidirectional power transmission between the bidirectional motor 12 and the gearbox 13, adapting to both electric drive and power recovery operating conditions.

[0042] Step S20 involves determining the architecture of the simulation equipment system 20 and building a test simulation environment adapted to the real scaled-down prototype system 10 to support the simulation verification of the dual-voltage system operating characteristics. Among these steps... Figure 2 As shown, the simulation equipment system 20 includes a first power supply 21, a second power supply 22, a mechanical load unit 23, an electrical load unit 24, and a power distribution management unit 25, which together constitute an electromechanical integrated test and verification system, covering all dimensions of test requirements for power output and power distribution. The first power supply 21 is a power supply with a first voltage system, and the second power supply 22 is a bidirectional power supply with a second voltage system. The first voltage is greater than the second voltage, thereby constructing a dual-voltage power supply system with a high-low voltage combination, replacing the battery and DC / DC converter components in the traditional test scheme. This reduces test costs while avoiding battery safety risks under extreme operating conditions and improving the safety of the test process. The input end of the mechanical load unit 23 is connected to the third extended shaft 134 for transmission, simulating the mechanical load under actual application scenarios. The power distribution management unit 25 is electrically connected to the bidirectional motor 12, the first power supply 21, the second power supply 22, and the electrical load unit 24, respectively, to realize power scheduling, voltage coordination control, and load power distribution under the dual-voltage system, supporting the simulation of voltage coordination, power distribution, and dynamic response characteristics.

[0043] Step S30: Control the real scaled-down prototype system 10 and the simulation equipment system 20 to conduct a ground scaled-down test.

[0044] Step S40 involves analyzing and verifying the aviation dual-voltage hybrid system based on the test data from the scaled-down ground test. This allows for comprehensive and accurate verification of the architectural feasibility and control performance of the dual-voltage parallel hybrid system under scaled-down conditions. It enables the completion of relevant functional tests using a scaled-down system with the same architecture before the development of a full-power hybrid system prototype, allowing for early identification of problems in the control strategy, improving development efficiency, avoiding repeated development processes, and providing a reliable basis for full-scale system integration.

[0045] In the scaled-down prototype system 10, the power ratio of the turboshaft engine 11 to the full-power engine is 1:X. In this application, the power ratio of the simulation equipment system 20 to the full-power motor is also 1:X.

[0046] The power of the electrical load unit 24 is scaled down to the power of the full-power electrical equipment by a ratio of 1:X.

[0047] In this application, the ground-scale test method for the aviation dual-voltage hybrid system can complete the test verification of the aviation dual-voltage hybrid system at a lower cost. Before the development of the full-power aviation dual-voltage hybrid system prototype, relevant functional tests can be completed based on the real scaled-down prototype system 10 with the same architecture and the simulation equipment system 20. Problems in the control strategy can be discovered in advance, improving development efficiency and avoiding repeated development processes.

[0048] Furthermore, the ground-based scaled-down test method for the aviation dual-voltage hybrid system eliminates the need for a battery and DC / DC converter component. Instead, the first power supply 21, the second power supply 22, and the power distribution management unit 25 work together to replace the function of the battery and DC / DC converter. This reduces test costs while improving the safety of the power simulation process, avoiding the safety risks associated with battery use under extreme conditions, and enhancing the safety of the ground-based scaled-down test process.

[0049] Furthermore, the mechanical load unit 23 includes a load motor 231 and a first electrical load 232, forming an electrically controlled mechanical load simulation architecture, providing flexible load simulation capabilities for the experiment. The load motor 231 is connected to the third extended shaft 134 for transmission, and can receive the mechanical power output from the gearbox 13 via the third extended shaft 134, converting the mechanical power into electrical power, thus realizing the conversion of mechanical energy into electrical energy. The load motor 231 is electrically connected to the first electrical load 232, and the load motor 231 provides electrical energy to the first electrical load 232. The converted electrical energy can be consumed by the first electrical load 232 to simulate the magnitude of mechanical load under different operating conditions, ensuring the accuracy and adjustability of load condition simulation in the ground-scale test.

[0050] Further, step S30 includes step S31.

[0051] Step S31: Based on the ground-scale test requirements of the parallel power mode, the bidirectional motor 12 is controlled to be in electric state, enabling it to operate in power output mode and providing power input for parallel power output. The first power supply 21 is controlled to output electrical energy at the first voltage to the bidirectional motor 12, providing electrical energy at the corresponding voltage level to the electric bidirectional motor 12, matching the power supply characteristics of the first voltage system. The second power supply 22 is controlled to output electrical energy at the second voltage to the electrical load unit 24, constructing a load power supply link of the second voltage system, simulating the actual operating conditions of the low-voltage side electrical load. The turboshaft engine 11 and the bidirectional motor 12 are controlled to provide shaft power to the mechanical load unit 23, realizing the parallel convergence and joint output of fuel power and electric power. Through the above control method, the complete operating state of the parallel power mode under the dual voltage system can be accurately realized, truly simulating the voltage coordination, power distribution and dynamic response characteristics under this condition, ensuring the comprehensiveness and accuracy of the system architecture and control method verification in the parallel hybrid mode.

[0052] Further, step S40 includes step S41.

[0053] Step S41: Based on the voltage and current of the bidirectional motor 12 in the ground-scale test of the parallel power mode, determine the stability of the bidirectional motor 12's electric power. By collecting and calculating the voltage and current data of the bidirectional motor 12 in the ground-scale test of the parallel power mode, the real-time operating power of the bidirectional motor 12 is obtained. This verifies whether its steady-state power is stable within ±1% of the target power, thus completing the determination of electric power stability. This directly reflects the smoothness of the electric power output under the parallel power condition, promptly identifies abnormal power fluctuations and control strategy deviations, provides data basis for the optimization and adjustment of the motor control logic under the dual-voltage system, and ensures the reliability and operational consistency of the power output in the parallel hybrid mode.

[0054] Furthermore, step S30 includes step S32. Either step S31 or step S32 can be performed.

[0055] Step S32: Based on the ground-scale test requirements under the power supply mode, the bidirectional motor 12 is controlled to generate power in the second voltage system, switching it to power generation operation and outputting electrical energy at the corresponding voltage level to meet the power output requirements under the power supply mode. The voltages of the first power supply 21 and the second power supply 22 are both controlled to 0, and the bidirectional motor 12 is controlled to output electrical energy to the electrical load unit 24, forming an energy transmission link that drives the motor to generate power and directly supplies electrical energy to the load, realizing the power distribution and load power supply process under the power supply mode. The turboshaft engine 11 is controlled to provide shaft power to the bidirectional motor 12 and the mechanical load unit 23 respectively, covering the dual power requirements of power generation drive and mechanical load drive. Through the above control logic, the operating state of the power supply mode under the dual voltage system can be fully realized, accurately simulating the power splitting, electrical output, and load response characteristics under this condition. This fully verifies the system's power supply capacity and power distribution rationality in the pure engine-driven power generation scenario, ensuring the comprehensiveness of the system architecture and control method verification under the power supply mode, and providing experimental data support for the power supply mode design and control strategy optimization of full-size hybrid systems.

[0056] Furthermore, step S40 includes step S42, and either step S41 or step S42 can be performed.

[0057] Step S42: Based on the voltage changes of the electrical load unit 24 during the ground-based scale-down test in power supply mode, the power generation stability of the bidirectional motor 12 is determined. By collecting voltage change data of the electrical load unit 24 during the ground-based scale-down test in power supply mode, it is verified whether the input voltage of the electrical load unit 24 is within the range of 250V to 280V under steady state. This indirectly reflects the power fluctuation state of the bidirectional motor 12's power output, thereby completing the determination of the power generation stability of the bidirectional motor 12. This can accurately identify abnormal power output and control strategy deviations under power generation conditions, verify the adaptability and effectiveness of the power generation control logic in power supply mode, and provide reliable experimental data for the architecture optimization and control strategy adjustment of the dual-voltage hybrid system in power generation mode, ensuring the continuity of load power supply and the stability of system operation under power supply mode.

[0058] Furthermore, step S30 includes step S33, and one of steps S31, S32 and S33 can be performed.

[0059] Step S33: Based on the ground-based scaled-down test requirements of the energy storage mode, the bidirectional motor 12 is controlled to operate in the second voltage system's power generation state, switching the bidirectional motor 12 to power generation mode and outputting electrical energy at the corresponding voltage level, providing a power source for the energy storage mode. The voltage of the first power supply 21 is controlled to 0, cutting off the external power input of the first voltage system, eliminating interference from the high-voltage side power supply to the energy storage mode test conditions, and ensuring the independence of the test scenario. The voltage of the second power supply 22 is controlled to a third voltage, which is lower than the second voltage, putting the second power supply 22 in a charging state that can receive electrical energy, constructing an energy recovery path for the bidirectional power supply, replacing the traditional energy storage battery to complete the charging condition simulation, reducing test costs while avoiding safety risks during battery charging. For example, the third voltage is 268V and the second voltage is 270V. For example, the third voltage is 265V and the second voltage is 267V. For example, the third voltage is 260V and the second voltage is 266V. The bidirectional motor 12 is controlled to output electrical energy to the second power source 22 and the electrical load unit 24. The turboshaft engine 11 is controlled to provide shaft power to the bidirectional motor 12 and the mechanical load unit 23, covering the dual power requirements of power generation drive and mechanical load drive, thus replicating the power distribution state of a real hybrid system. Through the above control logic, the complete operation process of the energy storage mode under the dual-voltage system is realized, accurately simulating the power splitting, energy recovery and distribution, and dynamic response characteristics under this condition. This fully verifies the rationality of the system architecture and the adaptability of the control method in the energy storage scenario, providing reliable experimental data support for the energy storage operating condition design and control strategy tuning of full-size hybrid systems.

[0060] Furthermore, step S40 includes step S43, which includes steps S431 and S432. Steps S41, S42 and S43 can be selected to be executed.

[0061] Step S431: Determine the power generation stability of the bidirectional motor 12 based on the voltage change of the electrical load unit 24 in the ground-scale test of the energy storage mode.

[0062] In step S432, during the switching between multiple operating modes in the ground-based scaled-down test, when the bidirectional motor 12 is in power generation mode after the operating mode switch, the stability of the power generation of the bidirectional motor 12 is determined based on the dynamic voltage change of the electrical load unit 24. By collecting the voltage change data of the electrical load unit 24 during the ground-based scaled-down test in the energy storage mode, it is verified whether the input voltage of the electrical load unit 24 is within the range of 250V to 280V under steady state. This can indirectly map the power fluctuation state of the bidirectional motor 12's power generation output, thereby completing the determination of the stability of the bidirectional motor 12's power generation under this steady-state condition. This method can accurately identify abnormal power output and control strategy deviations under energy storage conditions, and verify the adaptability and effectiveness of the corresponding power generation control logic.

[0063] To address the dynamic transition process of switching between multiple operating modes and the power surge scenario of the electrical load unit 24, when the bidirectional motor 12 switches to generator mode, dynamic voltage change data of the electrical load unit 24 is collected to verify whether the dynamic input voltage is within the range of 200V to 330V and whether the voltage recovery time is less than 40ms, thereby determining the stability of the generator power. By analyzing the system's dynamic response characteristics during the operating condition switching process, the voltage coordination and power regulation capabilities during the mode switching phase are verified, achieving full coverage of steady-state operation and dynamic transition scenarios, and further improving the comprehensiveness and accuracy of the verification of the dual-voltage hybrid system architecture and control method.

[0064] Furthermore, step S40 includes step S44, and one of steps S41, S42, S43 and S44 can be performed.

[0065] Step S44: During the dynamic switching between multiple operating modes in the ground-scaled test, the shaft power stability of the turboshaft engine 11 is judged based on the speed fluctuation of the turboshaft engine 11. By collecting real-time speed data of the turboshaft engine 11 during the dynamic switching of multiple operating modes, the fluctuation amplitude and change law of the speed are analyzed to verify whether the speed fluctuation of the turboshaft engine 11 during the dynamic switching process does not exceed ±1%. This accurately determines the stability of the shaft power output of the turboshaft engine 11 during the operating condition transition phase, intuitively reflects the power coordination control effect during the mode switching process, timely identifies power impact and control deviation, verifies the adaptability of the power system under the multi-mode switching logic, provides reliable experimental basis for optimizing the operating condition switching control strategy of the dual-voltage hybrid system, and ensures the smooth operation and reliability of the system during the full operating condition transition process.

[0066] The power distribution management unit 25 includes a first relay 251, a second relay 252 and a third relay 253.

[0067] The scaled-down prototype system 10 also includes a control module 26, which comprises a first controller 261 and a second controller 262. The bidirectional motor 12 is connected to the power distribution management unit 25 via the first controller 261. The load motor 231 is connected to the first electrical load 232 via the second controller 262.

[0068] For example:

[0069] In parallel power mode, the first relay 251 and the third relay 253 are closed, the second relay 252 is open, the first power supply 21 outputs electrical energy in power mode, and the dual-voltage motor is in 540V motor mode; the second power supply 22 outputs electrical energy in power mode, the electrical load unit 24 consumes electrical energy to simulate the operation of electrical equipment, the load motor 231 is in generator mode, and the mechanical load unit 23 consumes electrical energy to simulate the operation of mechanical rotor.

[0070] In the power supply mode, the second relay 252 is closed, the first relay 251 and the third relay 253 are open, the first power supply 21 is not working, the second power supply 22 is not working, the dual-voltage system motor is in 270V generating state, the electrical load unit 24 consumes electrical energy to simulate the operation of electrical equipment, the load motor 231 is in generating state, and the mechanical load unit 23 consumes electrical energy to simulate the operation of mechanical rotor.

[0071] In the energy storage mode, the second relay 252 and the third relay 253 are closed, the first relay 251 is open, the first power supply 21 is not working, the second power supply 22 is in load mode to simulate battery charging, the dual-voltage system motor is in 270V power generation state, the electric load unit 24 consumes energy to simulate the operation of electrical equipment, the load motor 231 is in power generation state, and the mechanical load unit 23 consumes energy to simulate the operation of mechanical rotor.

[0072] In the corresponding full-power hybrid system for verification, the mechanical rotor power is set as a parameter. The power consumption of airborne equipment is a parameter. The rated power of the full-power dual-voltage motor is .

[0073] In parallel power mode, the first power supply 21 is set to a voltage of 540V, and the dual-voltage motor has a power output of [missing value]. The turboshaft engine 11 has a working power of The power of the load motor 231 is equal to the power of the mechanical load unit 23. The second power supply 22 is set to a voltage of 270V, and the power of the electrical load unit 24 is... The parameters have the following relationship:

[0074] ;

[0075] ;

[0076] ;

[0077] ;

[0078] In power supply mode, the first power supply 21 is set to 0 voltage, and the dual-voltage system motor generates power of [missing value]. The turboshaft engine 11 has a working power of The power of the load motor 231 is equal to the power of the mechanical load unit 23. The second power supply 22 is set to a voltage of 0, and the power of the electrical load unit 24 is... The parameters have the following relationship:

[0079] ;

[0080] ;

[0081] ;

[0082] In energy storage mode, the first power supply 21 is set to voltage 0, and the dual-voltage system motor generates power of [missing value]. The turboshaft engine 11 has a working power of The power of the load motor 231 is equal to the power of the mechanical load unit 23. The second power supply 22 is set to a voltage of 180V (simulating the voltage of a battery at low SOC), and its power is set to... The power of the 24 electrical load units is... The parameters have the following relationship:

[0083] ;

[0084] ;

[0085] ;

[0086] ;

[0087] By completing ground-based scaled-down tests of the hybrid system according to various modes, and by collecting information such as current and voltage of each component, the turboshaft engine 11 and the bidirectional motor 12 can be analyzed and verified.

[0088] Example 2:

[0089] In this embodiment, a ground-scale test device for an aviation dual-voltage hybrid system is provided, which is applied to a ground-scale test method for an aviation dual-voltage hybrid system. The ground-scale test device includes: a real prototype determination module, a simulation equipment determination module, a test control module, and a verification module.

[0090] The real prototype determination module is used to determine the architecture of the real scaled-down prototype system 10, which can clarify the composition and transmission connection relationship of the core power unit of the test, and provide a clear architectural benchmark for the construction of the test bench.

[0091] The simulation equipment determination module is used to determine the architecture of the simulation equipment system 20. It can complete the configuration planning of the dual-voltage power supply unit, load unit and power distribution management unit 25, and build a test simulation environment adapted to the operating characteristics of the dual-voltage system.

[0092] The test control module is used to control the real scaled-down prototype system 10 and the simulation equipment system 20 to conduct ground scaled-down tests. It can realize system operation regulation and working condition switching control under multiple working modes, and ensure that the ground scaled-down test is executed stably and orderly according to the preset logic.

[0093] The verification module is used to analyze and verify the aviation dual-voltage hybrid system based on the test data from the ground-scale test. It can complete the system performance analysis and operation status determination based on the collected test parameters, and realize the comprehensive verification of the dual-voltage hybrid system architecture and control method.

[0094] Through the modular device architecture described above, the entire process of ground-based scale-down testing can be controlled and its performance verified in an orderly manner. The feasibility of the architecture and the control performance can be verified before the development of a full-power system prototype, control strategy problems can be identified in advance, development efficiency can be improved, and the safety risks brought by battery components in traditional test schemes can be avoided, test costs can be reduced, and reliable device support can be provided for the integrated development of full-size dual-voltage hybrid systems.

[0095] Those skilled in the art will understand that the above embodiments are specific examples of implementing this disclosure, and in practical applications, various changes can be made in form and detail without departing from the scope of this disclosure.

Claims

1. A ground-scale test method for an aviation dual-voltage hybrid system, characterized in that, The ground-scale test method includes: The architecture of a scaled-down prototype system is determined; wherein, the scaled-down prototype system includes a turboshaft engine, a bidirectional motor, and a gearbox; the gearbox includes a transmission gear set and a first extension shaft, a second extension shaft, and a third extension shaft respectively drivenly connected to the transmission gear set; the first extension shaft is drivenly connected to the turboshaft engine; the second extension shaft is drivenly connected to the bidirectional motor; The architecture of the simulation equipment system is determined; wherein, the simulation equipment system includes a first power supply, a second power supply, a mechanical load unit, an electrical load unit, and a power distribution management unit; the first power supply is a power supply with a first voltage system; the second power supply is a bidirectional power supply with a second voltage system; the first voltage is greater than the second voltage; the input terminal of the mechanical load unit is connected to the third extended shaft for transmission; the power distribution management unit is electrically connected to the bidirectional motor, the first power supply, the second power supply, and the electrical load unit respectively; Control the real scaled-down prototype system and the simulation equipment system to conduct ground-based scaled-down tests; The aviation dual-voltage hybrid system was analyzed and verified based on the test data from the ground-scaled test. The mechanical load unit includes a load motor and a first electrical load; the load motor is drivenly connected to the third extended shaft; the load motor is electrically connected to the first electrical load, and the load motor provides electrical energy to the first electrical load.

2. The ground-scale test method for an aviation dual-voltage hybrid system according to claim 1, characterized in that, The control of the real scaled-down prototype system and the simulation equipment system to conduct ground-based scaled-down tests includes: Based on the requirements of ground-scale tests under parallel power mode, the bidirectional motor is controlled to be in motor mode, the first power source is controlled to output electrical energy at a first voltage to the bidirectional motor, the second power source is controlled to output electrical energy at a second voltage to the electrical load unit, and the turboshaft engine and the bidirectional motor are controlled to provide shaft power to the mechanical load unit.

3. The ground-scale test method for an aviation dual-voltage hybrid system according to claim 2, characterized in that, The analysis and verification of the aviation dual-voltage hybrid system based on the test data from the ground-based scaled-down test includes: The stability of the bidirectional motor's electric power is determined based on the voltage and current of the bidirectional motor in the ground-scale test of the parallel power mode.

4. The ground-scale test method for an aviation dual-voltage hybrid system according to claim 1, characterized in that, The control of the real scaled-down prototype system and the simulation equipment system to conduct ground-based scaled-down tests includes: Based on the ground-scale test requirements under the power supply mode, the bidirectional motor is controlled to generate power in the second voltage system, the voltage of the first power supply and the second power supply are both controlled to be 0, the bidirectional motor is controlled to output electrical energy to the electrical load unit, and the turboshaft engine is controlled to provide shaft power to the bidirectional motor and the mechanical load unit respectively.

5. The ground-scale test method for an aviation dual-voltage hybrid system according to claim 4, characterized in that, The analysis and verification of the aviation dual-voltage hybrid system based on the test data from the ground-based scaled-down test includes: The power generation stability of the bidirectional motor is determined based on the voltage change of the electrical load unit in the ground-scale test of the power supply mode.

6. The ground-scale test method for an aviation dual-voltage hybrid system according to claim 1, characterized in that, The control of the real scaled-down prototype system and the simulation equipment system to conduct ground-based scaled-down tests includes: Based on the ground-scale test requirements under the electric energy storage mode, the bidirectional motor is controlled to generate electricity in the second voltage mode, the voltage of the first power source is controlled to be 0, the voltage of the second power source is controlled to be the third voltage, the bidirectional motor is controlled to output electrical energy to the second power source and the electric load unit respectively, and the turboshaft engine is controlled to provide shaft power to the bidirectional motor and the mechanical load unit respectively; wherein, the third voltage is less than the second voltage.

7. The ground-scale test method for an aviation dual-voltage hybrid system according to claim 6, characterized in that, The analysis and verification of the aviation dual-voltage hybrid system based on the test data from the ground-based scaled-down test includes: The stability of the bidirectional motor's power generation is determined based on the voltage change of the electrical load unit in the ground-scale test of the energy storage mode. During the ground-scale test, when the bidirectional motor switches between multiple operating modes and enters the power generation state after the operating mode is switched, the power generation stability of the bidirectional motor is judged based on the dynamic voltage change of the electrical load unit.

8. The ground-scale test method for an aviation dual-voltage hybrid system according to claim 1, characterized in that, The analysis and verification of the aviation dual-voltage hybrid system based on the test data from the ground-based scaled-down test includes: During the dynamic switching between multiple operating modes in the ground-scale test, the shaft power stability of the turboshaft engine is determined based on the speed fluctuation of the turboshaft engine.

9. A ground-scaled test apparatus for an aviation dual-voltage hybrid system, applied to the ground-scaled test method for an aviation dual-voltage hybrid system according to any one of claims 1-8, characterized in that, The ground-scaled test apparatus includes: The real prototype determination module is used to determine the architecture of the real scaled-down prototype system; The simulation equipment determination module is used to determine the architecture of the simulation equipment system; The test control module is used to control the real scaled-down prototype system and the simulation equipment system to conduct ground scaled-down tests. The verification module is used to analyze and verify the aviation dual-voltage hybrid system based on the test data from the ground-scaled test.

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