A control system and control method for an aviation hybrid energy system

Abstract

The present application relates to a control system and control method for an aviation hybrid energy system, the system comprising: a turboshaft engine module for consuming fuel and outputting mechanical energy; a generator module connected to the engine module to obtain the mechanical energy output by the turboshaft engine module and convert it into electrical energy; a generator output control module connected to the generator module to detect the electrical energy output of the generator and rectify the output current of the generator module; a backup battery module connected to the engine output control module to recover and / or compensate for the electrical energy output by the generator module. A system output monitoring module connected to the generator output control module and the backup battery module to monitor the current total output power of the system. Through this technical solution, the flight performance of the aircraft can be improved and the probability of secondary failures can be reduced.

Description

Technical Field

[0001] The present application relates to the field of aircraft energy management technology, and in particular to a control system, control method, computer equipment, storage medium and embedded system program product for an aviation hybrid energy system. Background Art

[0002] With the development of civil aviation technology, aviation hybrid power technology has emerged, which uses turboshaft engines and power motors as hybrid power in civil aircraft to increase the overall flight performance of the aircraft.

[0003] The existing Chinese invention patent with publication number CN114728699A discloses an electrical architecture for a hybrid thermal / electric propulsion aircraft, the aircraft includes two turboshaft engines, each turboshaft engine is provided with an electronic control system, and the architecture includes for each turboshaft engine: a high-voltage DC propulsion power distribution network; a non-propulsion power distribution network, the non-propulsion power distribution network is coupled to the load of the aircraft or the turboshaft engine; a plurality of first motors, the first motors are mechanically coupled to the high-pressure shaft of the turboshaft engine, each of the first motors is configured to: operate in motor mode to provide mechanical propulsion power, and operate in generator mode to receive mechanical power and provide electricity; a plurality of second motors, the second motors are mechanically coupled to the low-pressure shaft of the turboshaft engine, and the second motors are configured to: operate in motor mode The invention relates to a power distribution network for the electric vehicle, wherein the electric vehicle is a plurality of electric vehicles, and wherein the electric vehicle is a plurality of electric vehicles ...

[0004] However, the above technical solution still has the following technical problems: the control system needs to control two output characteristics to achieve the same working requirements, which increases the discreteness of the system. When a node fails, the load of another unit will be greatly increased, and even cause a secondary failure. Summary of the invention

[0005] Based on this, it is necessary to provide a control system, control method, computer equipment, computer-readable storage medium and embedded system program product for an aviation hybrid energy system that can reduce the occurrence rate of secondary failures in response to the above-mentioned technical problems.

[0006] In a first aspect, the present application also provides a control system for an aviation hybrid energy system, the system comprising:

[0007] A turboshaft engine module for consuming fuel and outputting mechanical energy;

[0008] A generator module is connected to the engine module to obtain the mechanical energy output by the turboshaft engine module and convert it into electrical energy;

[0009] A generator output control module is connected to the generator module to detect the power output of the generator and rectify the output current of the generator module;

[0010] A backup battery module is connected to the engine output control module to recover and / or compensate the electric energy output by the generator module;

[0011] The system output monitoring module is connected to the generator output control module and the backup battery module to monitor the current total output power of the system.

[0012] In one embodiment, the generator module further includes a rotation speed detection module for detecting the generator rotation speed and controlling the output power of the backup battery module according to the generator rotation speed.

[0013] In a second aspect, the present application provides a control method for an aviation hybrid energy system, the method comprising:

[0014] Get the current output power of the generator;

[0015] Get the current total power consumption of the system;

[0016] Compare and determine the relationship between the current total power consumption of the system and the current output power of the generator;

[0017] If the current total power consumption of the system is greater than the current output power of the generator;

[0018] Then the backup battery system is controlled to perform power compensation;

[0019] If the current total power consumption of the system is less than the current output power of the generator;

[0020] The backup battery system is controlled to recover power.

[0021] In one of the embodiments, the method further includes: acquiring generator speed data;

[0022] Determine whether the generator speed data is lower than the preset warning speed threshold;

[0023] If so, the system is switched to be powered by the backup battery module.

[0024] In one embodiment, the specific method of controlling the backup battery system to perform power compensation includes:

[0025] Obtain the compensated output power according to the current output power of the generator, the current total power consumption of the system and the preset power compensation algorithm;

[0026] The backup battery module is controlled to compensate the output power for electrical energy output.

[0027] In a third aspect, the present application further provides a computer device, the computer device comprising a memory and a processor, the memory storing an embedded system program, and the processor implementing the following steps when executing the embedded system program:

[0028] Get the current output power of the generator;

[0029] Get the current total power consumption of the system;

[0030] Compare and determine the relationship between the current total power consumption of the system and the current output power of the generator;

[0031] If the current total power consumption of the system is greater than the current output power of the generator;

[0032] Then the backup battery system is controlled to perform power compensation;

[0033] If the current total power consumption of the system is less than the current output power of the generator;

[0034] The backup battery system is controlled to recover power.

[0035] In a fourth aspect, the present application further provides a computer-readable storage medium, on which an embedded system program is stored, and when the embedded system program is executed by a processor, the following steps are implemented:

[0036] Get the current output power of the generator;

[0037] Get the current total power consumption of the system;

[0038] Compare and determine the relationship between the current total power consumption of the system and the current output power of the generator;

[0039] If the current total power consumption of the system is greater than the current output power of the generator;

[0040] Then the backup battery system is controlled to perform power compensation;

[0041] If the current total power consumption of the system is less than the current output power of the generator;

[0042] The backup battery system is controlled to recover power.

[0043] In a fifth aspect, the present application further provides an embedded system program product, the embedded system program product comprising an embedded system program, and the embedded system program implements the following steps when executed by a processor:

[0044] Get the current output power of the generator;

[0045] Get the current total power consumption of the system;

[0046] Compare and determine the relationship between the current total power consumption of the system and the current output power of the generator;

[0047] If the current total power consumption of the system is greater than the current output power of the generator;

[0048] Then the backup battery system is controlled to perform power compensation;

[0049] If the current total power consumption of the system is less than the current output power of the generator;

[0050] The backup battery system is controlled to recover power.

[0051] The above-mentioned control system, control method, computer equipment, storage medium and embedded system program product for an aviation hybrid energy system realizes that the turboshaft engine converts the engine output into electrical energy through the generator and the control system, and is used in conjunction with the battery pack to adapt to the stepped and fluctuating output characteristics of the turboshaft engine, thereby ensuring smooth total system output and high dynamic output performance. The electrical energy generated by the generator is supplemented or recovered according to the actual output power of the aircraft, changing the traditional mode of controlling the turboshaft engine and the generator at the same time to provide power for the aircraft, reducing the discreteness of the system while also reducing the probability of secondary failures. BRIEF DESCRIPTION OF THE DRAWINGS

[0052] Figure 1 A system structure topology diagram of a control system for an aviation hybrid energy system;

[0053] Figure 2 A flow chart of a control method for an aviation hybrid energy system;

[0054] Figure 3 is the output characteristic curve diagram of the turboshaft engine;

[0055] Figure 4 FIG. 4 is a diagram showing the internal structure of a computer device in one embodiment. DETAILED DESCRIPTION

[0056] In order to make the purpose, technical solution and advantages of the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0057] In one embodiment, Figure 1 As shown, a control system for an aviation hybrid energy system is provided, including: a turboshaft engine module, a generator module, a generator output control module, a backup battery module and a system output monitoring module.

[0058] The turboshaft engine module is used to consume fuel and output mechanical energy. Due to the mechanical structure and characteristics of the turboshaft engine, its throttle curve and output power curve are completely nonlinear and curve relationships, but are fluctuation graphs with step characteristics. The specific graphs are as follows: Figure 2 shown.

[0059] The generator module is connected to the engine module to obtain the mechanical energy output by the turboshaft engine module and convert it into electrical energy. In this embodiment, the generator module uses a high power density generator with a power density of 6KW / kg and a comprehensive conversion efficiency of 93.6%.

[0060] The generator output control module is connected to the generator module to detect the power output of the generator and rectify the output current of the generator module. Since the engine speed is not fixed, the output voltage of the generator will change with the engine speed. By setting the generator output control module, the output voltage can be rectified and filtered to output stable direct current, thereby improving the stability of the aircraft system and enhancing the control performance of the aircraft system.

[0061] The backup battery module is connected to the engine output control module to recover and / or compensate for the electric energy output by the generator module. In addition, the backup battery module is also used to provide backup energy for the aircraft. When the turboshaft engine runs out of fuel or fails to drive the generator module to generate electricity, the backup battery module provides electricity to the aircraft, thereby driving the aircraft to maintain flight status. After the turboshaft engine module and the generator module fail to work normally, the aircraft can continue to fly for a period of time with the power support of the backup battery module to achieve a safe landing.

[0062] The system output monitoring module is connected to the generator output control module and the backup battery module to monitor the current total output power of the system.

[0063] Each module in the above-mentioned control system for an aviation hybrid energy system can be implemented in whole or in part by software, hardware, or a combination thereof. Each of the above-mentioned modules can be embedded in or independent of a processor in a computer device in the form of hardware, or can be stored in a memory in a computer device in the form of software, so that the processor can call and execute operations corresponding to each of the above modules.

[0064] When the control system of the aviation hybrid energy system is working, the turboshaft engine module is ignited and started, consuming fuel to output mechanical energy to drive the generator module to generate alternating current. The electric energy generated by the engine is converted from unstable alternating current to stable direct current through the rectification and filtering functions of the engine output control module, and is transmitted to various functional modules of the aircraft through the circuit to achieve take-off and start the flight mission. In the process of performing the flight mission, due to the nonlinear and step-type output characteristics of the turboshaft engine module, the power output of the generator module is not stable. At this time, the extra power output of the generator can be recovered through the backup battery module, that is, when the output power of the generator module is higher than the actual power of the aircraft, the backup battery module is charged to realize the recovery of the extra electric energy produced by the generator module. When the output power of the generator module is lower than the actual power of the aircraft, the backup battery module is controlled to discharge to supplement the aircraft power consumption that is insufficient to be met by the output power of the generator module. The power recovery or power compensation function of the backup battery module cooperates with the generator module to make the total energy output more stable, so that the aircraft can obtain a sufficiently stable energy supply, extend the endurance time of the aircraft, and comprehensively improve the flight performance of the aircraft. Furthermore, by controlling the backup battery module to supplement or recover the output power of the generator module, the discreteness of the aircraft system can be reduced, and the probability of secondary failure can also be reduced.

[0065] Based on the same inventive concept, an embodiment of the present application also provides a control method for an aviation hybrid energy system for controlling the control system for the above-mentioned aviation hybrid energy system. The implementation method for solving the problem provided by the method is similar to the implementation scheme recorded in the above-mentioned method. Therefore, the specific limitations in the embodiment of the control method for an aviation hybrid energy system provided below can be found in the above limitations on the control system for an aviation hybrid energy system, which will not be repeated here.

[0066] In one embodiment, Figure 2 As shown, a control method for an aviation hybrid energy system is provided, comprising the following steps:

[0067] S100: Obtain the current output power of the generator.

[0068] Among them, the output power of the generator can be calculated by the current, voltage and other parameters at the input end of the generator output control module, so as to calculate the output power of the generator module, and the current power of the generator can also be calculated by the rotational speed of the output shaft of the turboshaft engine module and / or the input shaft of the generator module.

[0069] S200: Obtain the current total power consumption of the system.

[0070] Among them, the current total power consumption of the system is the total energy consumption power of each energy consumption module of the system. In this embodiment, the current total power consumption of the system is a theoretical value obtained by calculating based on the calibrated power of each energy consumption component of the aircraft, which is a system preset value.

[0071] S300: Compare and determine the magnitude relationship between the current total power consumption of the system and the current output power of the generator.

[0072] Through step S300, it can be determined whether the current output power of the engine can meet the current energy consumption demand of the aircraft.

[0073] S310: If the current total power consumption of the system is greater than the current output power of the generator, the backup battery system is controlled to perform power compensation. The specific method is as follows:

[0074] S311: Obtaining compensated output power according to the current output power of the generator, the current total power consumption of the system and a preset power compensation algorithm.

[0075] The power compensation algorithm is a preset correspondence between the current total power consumption of the system, the current output power of the generator and the output power of the backup battery module. In this embodiment, the generator output power is calculated by calculating the output power of the generator through the output shaft speed of the turboshaft engine module. The power compensation algorithm satisfies W 补偿 =W 耗 -W 涡 =W 耗 -W 电 / n, in this relationship, W 补偿 is the current total power consumption of the system, that is, the current instantaneous energy consumption of the aircraft system, W 涡 is the output power of the turboshaft engine module, W 电 is the output power of the generator module, and n is the energy conversion efficiency between the turboshaft engine module and the generator module, that is, the mechanical efficiency of the generator module.

[0076] Optionally, when the output power of the turboshaft engine module can be directly measured or calculated through parameters such as engine speed and generator speed, the output power of the turboshaft engine module can also be obtained by only using W 补偿 =W 耗 -W 涡 This relationship directly yields the compensation power.

[0077] That is, the compensated output power is obtained through the following steps:

[0078] S321: Obtain the current output power of the turboshaft engine module.

[0079] S322: Obtain the compensated output power according to the current output power of the turboshaft engine module, the current total power consumption of the system and a preset power compensation algorithm.

[0080] S312: Control the backup battery module to compensate for the output power and output electrical energy.

[0081] Switch the backup battery module to discharge mode and control the output power of the backup battery module to adapt to the stepped and fluctuating output characteristics of the turboshaft engine, thereby ensuring smooth total system output and high dynamic output performance.

[0082] S320: If the current total power consumption of the system is less than the current output power of the generator, the backup battery system is controlled to recover power.

[0083] Among them, the backup battery module is switched to charging mode to recover and store the extra electric energy generated by the generator module for subsequent use when power output compensation or the backup battery module is required to supply power alone, thereby improving the flight safety of the aircraft and enabling more efficient use of aircraft fuel.

[0084] S400: Acquire generator speed data.

[0085] S500: Determine whether the generator speed data is lower than a preset warning speed threshold.

[0086] S501: If yes, the system is switched to be powered by the backup battery module.

[0087] Through the above steps S400 to S501, the engine speed can be detected. If the engine speed is too low, the system will determine that the aircraft turboshaft engine module is operating abnormally. At this time, the aircraft's power supply mode is converted to power supply by the backup battery alone, thereby ensuring the continuous and stable output of the aircraft's power, thereby improving the aircraft's flight performance.

[0088] In one embodiment, a computer device is provided, including a memory and a processor, wherein an embedded system program is stored in the memory, and when the processor executes the embedded system program, the following steps are implemented:

[0089] S100: Obtain the current output power of the generator.

[0090] S200: Obtain the current total power consumption of the system.

[0091] S300: Compare and determine the magnitude relationship between the current total power consumption of the system and the current output power of the generator.

[0092] S310: If the current total power consumption of the system is greater than the current output power of the generator, the backup battery system is controlled to perform power compensation;

[0093] The specific method is as follows:

[0094] S311: Obtaining compensated output power according to the current output power of the generator, the current total power consumption of the system, and a preset power compensation algorithm;

[0095] S312: Control the backup battery module to compensate for the output power and output electrical energy.

[0096] S320: If the current total power consumption of the system is less than the current output power of the generator, the backup battery system is controlled to recover power.

[0097] S400: obtaining generator speed data;

[0098] S500: determining whether the generator speed data is lower than a preset warning speed threshold;

[0099] S501: If yes, the system is switched to be powered by the backup battery module.

[0100] In one embodiment, an embedded system program product is provided, including an embedded system program, which implements the following steps when executed by a processor:

[0101] S100: Obtain the current output power of the generator.

[0102] S200: Obtain the current total power consumption of the system.

[0103] S300: Compare and determine the magnitude relationship between the current total power consumption of the system and the current output power of the generator.

[0104] S310: If the current total power consumption of the system is greater than the current output power of the generator, control the backup battery system to perform power compensation;

[0105] The specific method is as follows:

[0106] S311: Obtaining compensated output power according to the current output power of the generator, the current total power consumption of the system, and a preset power compensation algorithm;

[0107] S312: Control the backup battery module to compensate for the output power and output electrical energy.

[0108] S320: If the current total power consumption of the system is less than the current output power of the generator, the backup battery system is controlled to recover power.

[0109] S400: obtaining generator speed data;

[0110] S500: determining whether the generator speed data is lower than a preset warning speed threshold;

[0111] S501: If yes, the system is switched to be powered by the backup battery module.

[0112] A person of ordinary skill in the art can understand that all or part of the processes in the above-mentioned embodiment method can be completed by instructing the relevant hardware through an embedded system program, and the embedded system program can be stored in a non-volatile computer-readable storage medium. When the embedded system program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to the memory, database or other medium used in the embodiments provided in the present application can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetoresistive random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory can include random access memory (RAM) or external cache memory, etc. As an illustration and not limitation, RAM can be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM). The database involved in each embodiment provided in this application may include at least one of a relational database and a non-relational database. Non-relational databases may include distributed databases based on blockchains, etc., but are not limited to this. The processor involved in each embodiment provided in this application may be a general-purpose processor, a central processing unit, a graphics processor, a digital signal processor, a programmable logic device, a data processing logic device based on quantum computing, etc., but are not limited to this.

[0113] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0114] The above-described embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present application. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the attached claims.

Claims

1. A control system for an aviation hybrid energy system, characterized in that: include: A turboshaft engine module for consuming fuel and outputting mechanical energy; A generator module is connected to the engine module to obtain the mechanical energy output by the turboshaft engine module and convert it into electrical energy. The generator module also includes a speed detection module to detect the generator speed and control the output power of the backup battery module according to the generator speed; A generator output control module is connected to the generator module to detect the power output of the generator and rectify the output current of the generator module; A backup battery module, connected to the generator output control module, for recovering and / or compensating the electric energy output by the generator module; The system output monitoring module is connected to the generator output control module and the backup battery module to monitor the current total output power of the system; The control method adopted by the control system for the aviation hybrid energy system includes: Get the current output power of the generator; Get the current total power consumption of the system; Compare and determine the relationship between the current total power consumption of the system and the current output power of the generator; If the current total power consumption of the system is greater than the current output power of the generator; Then the backup battery system is controlled to perform power compensation; If the current total power consumption of the system is less than the current output power of the generator; Then the backup battery system is controlled to recover power; The specific steps of comparing and determining the magnitude relationship between the current total power consumption of the system and the current output power of the generator also include: Get generator speed data; Determine whether the generator speed data is lower than the preset warning speed threshold; If so, the system is switched to be powered by the backup battery module.

2. A control system for an aviation hybrid energy system according to claim 1, characterized in that: The specific method of controlling the backup battery system to perform power compensation includes: Get the current output power of the turboshaft engine module. Obtaining the compensated output power according to the current output power of the turboshaft engine module, the current total power consumption of the system, and a preset power compensation algorithm; The backup battery module is controlled to compensate the output power for electrical energy output.

3. The control system for an aviation hybrid energy system according to claim 1, characterized in that: The specific method of controlling the backup battery system to perform power compensation includes: Obtain the compensated output power according to the current output power of the generator, the current total power consumption of the system and the preset power compensation algorithm; The backup battery module is controlled to compensate the output power for electrical energy output.

4. A computer device, comprising a memory and a processor, wherein the memory stores an embedded system program, characterized in that: When the processor executes the embedded system program, the processor implements the steps of a control method adopted by a control system for an aviation hybrid energy system according to any one of claims 1 to 3.

5. A computer-readable storage medium having an embedded system program stored thereon, characterized in that: When the embedded system program is executed by the processor, the steps of the control method adopted by the control system for an aviation hybrid energy system according to any one of claims 1 to 3 are implemented.

6. An embedded system program product, comprising an embedded system program, characterized in that: When the embedded system program is executed by a processor, the steps of a control method adopted by a control system for an aviation hybrid energy system according to any one of claims 1 to 3 are implemented.

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