Integrated framework for optimizing power and thermal management parameters of hydrogen-electric propulsion aircraft

Abstract

The invention belongs to the technical field of aviation electric propulsion, and provides a power and thermal management parameter optimization integrated framework suitable for a high-power hydrogen electric propulsion aircraft, which mainly comprises an overall design and parameter optimization module, a power distribution and control module and a comprehensive thermal management analysis module, the overall design and parameter optimization module realizes optimal balance of thrust, energy efficiency and stability of the aircraft through aerodynamic design, mission profile analysis, propulsion system configuration and weight estimation; the power distribution and control module dynamically distributes power output of power sources such as a lithium battery, a hydrogen fuel cell and a hydrogen turbine engine based on a model predictive control method and by means of cooperative work of a top energy management controller and component control units, and the optimal power utilization rate of different flight stages is ensured. The comprehensive heat management analysis module integrates a low-temperature cooling loop, a non-low-temperature heat management system and a temperature monitoring and heat recovery unit, accurately controls and adjusts the temperature and heat consumption of key components, and ensures that the key components always run in a safe temperature range; through parameter transmission and feedback iterative optimization between the modules, the energy efficiency and stability of the aircraft under the high-load condition are remarkably improved, and the development requirements of future high-power hydrogen-electric propulsion aircrafts for high efficiency, low carbon emission and multi-working-condition adaptability are met.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace electric propulsion, and more specifically, relates to an integrated framework for optimizing power and thermal management parameters of a hydrogen-electric propulsion aircraft. Background Art

[0002] With the increasing demand of the global aviation industry for reducing carbon emissions and improving energy efficiency, aerospace electric propulsion technology has gradually become a key direction for future aviation development. Compared with traditional fuel propulsion systems, electric propulsion technology significantly reduces fuel consumption and pollutant emissions by introducing clean energy such as hydrogen energy and electric energy, while greatly improving energy utilization efficiency. Currently, aerospace propulsion technology is developing towards high power, high power density and low carbon to meet the power requirements of larger and heavier aircraft, while improving propulsion efficiency and flight performance. Therefore, the hydrogen-based aerospace electric propulsion system emerges as an ideal solution, driving the aviation industry towards a more environmentally friendly and efficient future.

[0003] The hydrogen-electric propulsion system mainly includes two propulsion methods: hydrogen fuel cells and hydrogen turbine engines. Hydrogen fuel cells directly generate electric energy through the electrochemical reaction of hydrogen and oxygen, providing continuous and clean power for the electric propulsion system, which is suitable for medium and small power propulsion requirements; while hydrogen turbine engines drive turbines through hydrogen combustion to generate strong thrust, meeting the propulsion tasks of aircraft with high power requirements. With the increasing demand for higher power density and energy efficiency, the application of superconducting technology has become particularly important. Due to its extremely low resistance, superconducting materials can significantly reduce energy losses in high-power hydrogen-electric propulsion systems, improving the overall efficiency. The application of superconducting motors and cables not only reduces heat losses during power transmission, but also reduces the system weight, thereby further improving the performance and endurance of the aircraft.

[0004] The performance, energy efficiency and stability of high-power hydrogen-electric propulsion aircraft depend on the collaborative optimization of multiple key technologies. Parameter optimization is the key to ensuring that the system meets the performance requirements. By precisely optimizing key parameters such as the propulsion system, aerodynamic design and weight distribution, the best balance between thrust and energy efficiency can be achieved. The power distribution module dynamically adjusts the output of multiple power sources and energy sources during different flight phases, improving the dynamic performance and energy utilization efficiency of the aircraft, and ensuring the stability and reliability of the aircraft at each stage. However, high-power systems pose severe thermal management challenges under high-load operation. The system needs to precisely control the temperatures of hydrogen fuel cells, hydrogen turbine engines and superconducting components through efficient heat dissipation and heat recovery mechanisms, and flexibly adjust the cooling system according to different flight phases to ensure the safety of the system while operating efficiently. Therefore, there is an urgent need to significantly improve the overall performance of high-power hydrogen-electric propulsion systems through the collaborative design of parameter optimization, power distribution and comprehensive thermal management to meet the requirements of aircraft for high power density, energy efficiency and operation stability.

[0005] In view of the above problems, the present invention proposes an integrated framework for optimizing the power and thermal management parameters of a hydrogen-electric propulsion aircraft, aiming to solve the challenges of efficient design and integrated energy management of the power system of high-power aircraft. The integrated framework realizes the maximization of energy efficiency and the improvement of system stability under high-load conditions by optimizing the key parameter design, dynamic power distribution strategy and efficient thermal management system of the aircraft. The present invention effectively improves the energy utilization efficiency of the hydrogen-electric propulsion aircraft at each flight stage, ensures the safe operation of the power system, and meets the technical requirements of future aviation for high power density and low carbon emissions. Summary of the Invention

[0006] To solve the technical problems of multi-condition adaptive coupling design, multi-objective optimization, power distribution and control of multiple power sources, and efficient heat dissipation and real-time heat regulation of high-power hydrogen-electric propulsion aircraft, the present invention proposes an integrated framework for optimizing the power and thermal management parameters of a hydrogen-electric propulsion aircraft; the framework realizes the maximization of energy efficiency and the improvement of system stability under high-load conditions by optimizing key design parameters, implementing a dynamic power distribution strategy, and introducing an efficient thermal management system, ensuring the reasonable allocation of power and the efficient utilization of energy of the aircraft under different flight conditions, thereby improving the overall performance, operation reliability and energy efficiency.

[0007] To achieve the above object, the present invention proposes an integrated framework for optimizing the power and thermal management parameters of a high-power hydrogen-electric propulsion aircraft, which mainly includes an overall design and parameter optimization module, a power matching and control module, and a comprehensive thermal management module; the overall design and parameter optimization module is responsible for the integrated design of the propulsion system and aerodynamics, weight estimation and mission assessment to achieve the optimal balance of thrust, energy efficiency and flight stability; the power distribution and control module is responsible for dynamically adjusting the power output of each power source and energy source, and at the same time monitoring and controlling the operating state of the underlying components to ensure the efficient collaborative work of multiple power sources and the optimal utilization of energy; the comprehensive thermal management module is responsible for the heat management of the aircraft at different flight stages, real-time monitoring and adjusting the temperature and heat consumption of each key component to ensure the safe and stable operation of the aircraft under complex working conditions.

[0008] The overall design and parameter optimization module combines aerodynamic design to optimize the configuration of the hydrogen-electric propulsion system, determines the maximum and rated values of the power, energy and efficiency of each component according to the mission profile, analyzes the center-of-gravity distribution and structural stability under different flight profiles through weight estimation, and realizes the optimal balance of thrust demand, fuel consumption and endurance of the hydrogen-electric propulsion aircraft through parameter evaluation and feedback iteration.

[0009] The power distribution and control module dynamically adjusts the power output of each power source and energy source based on the real-time operating conditions of the aircraft, using a model predictive control energy management controller, and precisely monitors and adjusts the key parameters of multiple core components such as the lithium battery management system, hydrogen gas turbine / fuel cell control unit, and superconducting motor control unit, to achieve stable, efficient, and reliable operation of the aircraft's power system.

[0010] The integrated thermal management analysis module achieves efficient cooling and heat regulation through a cryogenic cooling loop and a thermal management system. The temperature monitoring unit continuously monitors the operating temperatures of multiple components such as superconducting motors, cryogenic power electronics, and hydrogen fuel cells, and dynamically adjusts the cooling strategy based on real-time data to ensure that the aircraft always remains within a safe temperature range under complex operating conditions.

[0011] Preferably, the overall design and parameter optimization module employs a multi-objective optimization algorithm to ensure an optimal balance among aerodynamic performance, propulsion system efficiency, weight balance, and mission requirements.

[0012] Preferably, the power distribution and control module integrates a model predictive control energy management strategy to efficiently coordinate the energy distribution among lithium batteries, fuel cells, and hydrogen turbine engines.

[0013] Preferably, the integrated thermal management analysis module integrates a cryogenic cooling loop and a thermal management system according to the cooling requirements of different components to achieve efficient cooling and heat regulation of each component.

[0014] Generally speaking, compared with the existing power system design and optimization methods, the power and thermal management parameter optimization integration framework of a hydrogen-electric propulsion system for high-power hybrid aircraft of the present invention has the following benefits:

[0015] 1. The power and thermal management parameter optimization integration framework of the hydrogen-electric propulsion aircraft of the present invention improves the propulsion efficiency and energy utilization rate, achieving synergistic efficiency enhancement of the system.

[0016] 2. The overall design and parameter optimization module of the present invention significantly improves the lift-to-drag ratio, endurance, and flight stability of the aircraft, greatly enhancing the mission adaptability.

[0017] 3. The power distribution and control module of the present invention significantly improves the energy management efficiency, achieving efficient coordination of each power source and optimal distribution of energy.

[0018] 4. The integrated thermal management analysis module of the present invention achieves efficient cooling and heat regulation of key components, effectively extending the service life of the components and reducing the operation and maintenance costs of the aircraft. Description of the Drawings

[0019] To more clearly illustrate the embodiments of the present invention, the accompanying drawings in the embodiments are briefly introduced below. They are used together with the embodiments of the present invention to explain the present invention and do not constitute a limitation to the present invention.

[0020] Figure 1 It is a schematic diagram of an integrated framework for parameter optimization, power distribution, and thermal management applicable to a high-power hydrogen-electric propulsion aircraft provided by the embodiment;

[0021] Figure 2 It is a schematic diagram of the overall design and parameter optimization module of a hydrogen-electric propulsion aircraft provided by the embodiment;

[0022] Figure 3 It is a schematic diagram of the power distribution and control module of a hydrogen-electric propulsion aircraft provided by the embodiment;

[0023] Figure 4 It is a schematic diagram of the comprehensive thermal management analysis module of a hydrogen-electric propulsion aircraft provided by the embodiment. Specific Embodiments

[0024] In order to make the objectives, technical solutions, and advantages of the present invention clearer and more understandable, the present invention will be 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 invention and are not used to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0025] Figure 1 It is a schematic diagram of an integrated framework for power distribution and thermal management parameter optimization of a hydrogen-electric propulsion aircraft provided by the embodiment, including an overall design and parameter optimization module, a power distribution and control module, and a comprehensive thermal management analysis module. The modules are closely integrated and coordinated through parameter transfer, real-time monitoring, and feedback adjustment, enabling the hydrogen-electric propulsion system to maintain high energy efficiency and operating stability under high load and complex working conditions.

[0026] The overall design and parameter optimization module provides key design parameters for the configuration of the propulsion system, integrating aerodynamics, mission profiles, and environmental parameters, as well as weight estimation and parameter evaluation, to ensure the overall performance balance of the aircraft.

[0027] The overall design and parameter optimization module provides key design parameters as inputs and transfers them to the power distribution and control module and the comprehensive thermal management module.

[0028] During the parameter optimization process, it also receives feedback information from the power distribution and control module for real-time adjustment of the design parameters to meet the power demand under actual working conditions.

[0029] The power distribution and control module dynamically allocates power to each power source under different working conditions to meet the real-time power demand of the aircraft. It uniformly regulates multiple core components such as the hydrogen fuel cell, turbine engine, and battery management system through the energy management controller to ensure the efficient collaborative operation of the power system.

[0030] The power distribution and control module feeds back real-time data on the operating status, power output, and energy consumption to the integrated thermal management analysis module, so that the latter can adjust the cooling strategy according to the power load and operating status to ensure the temperature balance of the system.

[0031] The integrated thermal management module ensures that the temperatures of all key components are maintained within a safe range during different flight phases through real-time temperature monitoring, cryogenic cooling circuits, and non-cryogenic thermal management systems. The efficient heat dissipation and heat recovery mechanisms further improve the overall energy efficiency of the system.

[0032] The integrated thermal management module feeds back the temperature data and cooling requirements of key components to the parameter optimization module to ensure that the heat load and cooling system requirements are optimally considered in the design phase.

[0033] The integrated thermal management module real-time feeds back the temperature status of each component to the power control module. When the temperature exceeds the safe range, it guides the power control module to dynamically adjust the power output to maintain the system temperature balance.

[0033] Figure 2 Shows a schematic diagram of the overall design and parameter optimization module of the hydrogen-electric propulsion aircraft in the embodiment, mainly including four sub-modules: aerodynamic design, mission profile and environmental parameters, hydrogen-electric propulsion system design, and weight estimation and parameter evaluation. Each module realizes collaborative optimization through parameter transfer and feedback mechanisms to meet the requirements of the aircraft in terms of performance, energy efficiency, and stability.

[0034] The aerodynamic design module receives profile parameters and mission payload information from the mission profile and environmental parameters module, including key flight parameters such as flight altitude, speed, and airflow conditions.

[0035] The aerodynamic design module optimizes and generates aerodynamic parameters such as lift-to-drag ratio, wing aspect ratio, and aerodynamic efficiency according to the mission profile and payload requirements, and transfers them to the hydrogen-electric propulsion system design module and the weight estimation and parameter evaluation module.

[0036] The aerodynamic design module performs iterative optimization based on the center of gravity position and weight distribution information fed back by the weight estimation module to ensure the balance and stability of the aerodynamic design under actual flight conditions.

[0037] The mission profile and environmental parameters module receives information such as payload requirements and environmental conditions in the aircraft design requirements or specific mission requirements.

[0038] The mission profile and environmental parameter module provides the profile parameters (including flight altitude, speed, distance and mission payload) to the aerodynamic design module and the hydrogen-electric propulsion system design module to ensure that the design of each module meets the requirements of the mission profile.

[0039] The mission profile module updates the profile parameters in a timely manner according to the payload mass and mission adjustment information fed back by the weight estimation and parameter evaluation module, and optimizes the adaptability of the aircraft under different mission conditions.

[0040] The hydrogen-electric propulsion system design module optimizes the thrust output efficiency based on the lift-to-drag ratio and aerodynamic parameters provided by the aerodynamic design module.

[0041] The hydrogen-electric propulsion system design module determines the power requirements for different stages such as take-off, climb, cruise, descent and landing based on the flight profile parameters provided by the mission profile and environmental parameter module.

[0042] The hydrogen-electric propulsion system design module generates and outputs parameters such as power distribution, thrust requirements, and environmental requirements of each power source, and transmits them to the power distribution and control module and the weight estimation and parameter evaluation module.

[0043] The hydrogen-electric propulsion system design module provides an adjusted energy structure, including the power and energy ratio of hydrogen fuel cells or hydrogen gas turbines and energy storage batteries, to adapt to load changes in different flight phases.

[0044] The hydrogen-electric propulsion system design module makes design adjustments based on the component weight and fuel consumption rate information fed back by the weight estimation and parameter evaluation module to ensure that the power system meets the overall weight and energy efficiency requirements.

[0045] The weight estimation and parameter evaluation module uses the lift-to-drag ratio and aerodynamic parameters provided by the aerodynamic design module to estimate the center of gravity position and weight distribution of the aircraft.

[0046] The weight estimation and parameter evaluation module combines the component weight, fuel consumption, emissions, heat rate and efficiency data provided by the hydrogen-electric propulsion system design module to perform a comprehensive weight and energy efficiency analysis.

[0047] The weight estimation and parameter evaluation module feeds back the center of gravity position, weight distribution and stability information to the overall design module to ensure the stability of the aircraft under different load and mission conditions.

[0048] The weight estimation and parameter evaluation module feeds back the weight distribution and load characteristics to the aerodynamic design module so that the aerodynamic design can be adjusted according to different load conditions.

[0049] The weight estimation and parameter evaluation module performs iterative optimization based on the parameters transmitted by each module to ensure that the aircraft design achieves the best balance of stability, maneuverability, and energy efficiency under different mission profiles.

[0040] Figure 3 FIG. is a schematic diagram of the power distribution and control module of a hydrogen-electric propulsion aircraft provided by the embodiment. Through the coordinated operation of the energy management controller and multiple sub-control units, the power output of each power source is dynamically allocated to ensure the best performance and energy efficiency of the aircraft under different flight phases and operating conditions.

[0041] Based on the required power data provided by the overall design module, the energy management controller receives the power requirements under specific tasks and operating conditions, and performs power distribution calculations on the basis of considering constraints such as power / energy balance, speed / torque, etc.

[0042] Based on the model predictive control method, the energy management controller pre-calculates the optimal power distribution of each power source through the establishment of a system model and the prediction of future operating conditions, and sends the optimization results to the lithium battery management system and the hydrogen fuel cell / turbine engine control unit to improve the response speed and accuracy of power control.

[0043] According to the power, fuel flow rate, and real-time operating efficiency fed back by the control units of each component at the bottom layer, the model predictive control energy management controller dynamically adjusts the power distribution to achieve the optimal energy efficiency and performance of the system.

[0044] Table 1 shows the key parameters involved in the model predictive controller

[0045] According to the power command transmitted by the energy management controller, the lithium battery management system controls the discharge rate and power output of the battery using parameters such as real-time voltage, current, and temperature.

[0046] The lithium battery management system real-time feeds back voltage, current, and temperature data to the energy management controller, and provides the required power support to the high-power hydrogen-electric propulsion system.

[0047] According to the feedback of the energy management controller, the lithium battery management system adjusts the discharge rate of the battery, optimizes the battery usage efficiency, and prevents overheating or over-discharge to ensure the stability of the battery system.

[0048] When the hydrogen-electric propulsion system uses a hydrogen fuel cell as the main power source, the fuel cell control unit receives the power distribution command of the energy management controller and controls the output power of the fuel cell as needed to meet the power demand of the aircraft.

[0049] The fuel cell control unit feeds back parameters such as real-time power output, current, voltage, and fuel consumption to the energy management controller and provides the main power support required for the hydrogen-electric propulsion system.

[0050] Based on the feedback data of current, voltage, and fuel utilization rate, the fuel cell control unit dynamically adjusts its working state, optimizes the hydrogen consumption efficiency, and ensures a stable power output.

[0051] When the hydrogen-electric propulsion system uses a hydrogen turbine engine as the main power source, the turbine engine control unit receives the power command from the energy management controller and adjusts the fuel flow rate and output power according to the flight conditions to meet the thrust requirements.

[0052] The turbine engine control unit feeds back data such as power output, fuel flow rate, rotational speed, and torque to the energy management controller and provides the mechanical power required for the hydrogen-electric propulsion system.

[0053] Based on the real-time feedback data of rotational speed, torque, and efficiency, the turbine engine control unit dynamically adjusts its operating state to optimize the hydrogen utilization rate and output stability.

[0054] When the hydrogen fuel cell is the main power source, the superconducting motor operates in the motor mode.

[0055] When the hydrogen turbine engine is the main power source, the superconducting motor operates in the power generation and electric modes respectively to achieve efficient power conversion and auxiliary drive.

[0056] The superconducting generator control unit receives the working command from the energy management controller, controls the rotational speed and power output of the generator, and feeds back the real-time voltage, current, rotational speed, and efficiency data to the energy management controller.

[0057] The superconducting generator control unit combines the data fed back by the power distribution and thermal management module to dynamically adjust the power output, ensuring that the generator operates within an efficient and safe temperature range to meet the overall power demand and optimize the fuel utilization rate.

[0058] The superconducting motor receives the command from the energy management controller, controls the power output, rotational speed, and torque of the motor, and feeds back the real-time voltage, current, rotational speed, torque, and efficiency data to the energy management controller.

[0059] The superconducting motor dynamically adjusts the power output according to the data fed back by the power distribution and thermal management module to ensure its operation within an efficient state and a safe temperature range.

[0060] The hydrogen-electric propulsion system feeds back the actual aerodynamic parameters, power output, and temperature parameters to each sub-control unit in the power distribution and control module, enabling the energy management controller to adjust the power distribution according to the actual working conditions and achieve the optimal power output and efficiency of the system.

[0061] Figure 4 Shows a schematic diagram of the overall design and parameter optimization module of a hydrogen-electric propulsion aircraft in an embodiment. Heat management of the hydrogen-electric propulsion system is achieved through a cryogenic cooling loop, a non-cryogenic thermal management system, and a temperature monitoring and heat recovery unit, ensuring that the system remains within a safe temperature range under different operating conditions.

[0062] The temperature monitoring unit receives real-time temperature and temperature threshold data of key components such as liquid hydrogen storage tanks, superconducting motors, superconducting cables, cryogenic power electronics, hydrogen fuel cells, hydrogen turbine engines, and lithium batteries.

[0063] The temperature monitoring unit transmits the temperature data to the cryogenic cooling loop and the non-cryogenic thermal management system for regulating the cooling strategy.

[0064] When a temperature anomaly occurs, the temperature monitoring unit feeds back an alarm signal to the energy management control module and each component control unit to dynamically adjust the power output and prevent component overheating and damage.

[0065] The cryogenic cooling loop is dedicated to cooling cryogenic components such as liquid hydrogen storage tanks, superconducting motors, superconducting cables, and cryogenic power electronics. By adjusting the flow rate of the cooling medium through direct cooling or heat exchange cooling, it ensures the stable operation of cryogenic components at a safe temperature.

[0066] Table 2 shows the temperature parameters involved in the cryogenic cooling loop Component Name Symbol Operating Temperature Range Unit Liquid Hydrogen Storage Tank <![CDATA[T tank > 20-25 K Superconducting Motor <![CDATA[T scm / scg > 20-65 K Superconducting Cable <![CDATA[T cable > 30-65 K Cryogenic Power Electronics <![CDATA[T cpe > 30-160 K

[0067] The cryogenic cooling loop based on liquid hydrogen cooling technology utilizes the low boiling point characteristic of liquid hydrogen to achieve efficient heat exchange with cryogenic components and adapts to the dynamic cooling requirements of cryogenic components by adjusting the flow rate of the cooling medium.

[0068] The cooling loop based on hydrogen-helium heat exchange uses a mixed medium of hydrogen and helium and conducts efficient heat exchange through a microchannel or plate-fin hydrogen-helium heat exchanger to achieve a more stable cooling effect and meet the cooling requirements under different cryogenic operating conditions.

[0069] The flow rate and temperature change data of the cooling loop are fed back to the temperature monitoring unit and the energy management controller in real time. When the cooling demand increases, the system can dynamically adjust the cooling power.

[0070] The non-cryogenic thermal management system mainly targets non-cryogenic components such as hydrogen fuel cells, hydrogen turbine engines, and lithium batteries. Based on the principles of heat conduction and forced convection, it regulates heat through air-cooled heat dissipation or a fluid heat exchange system.

[0071] The non-low-temperature thermal management system feeds back data on the real-time temperature of components, the flow rate of the cooling medium, and the heat exchange efficiency to the temperature monitoring unit and the energy management control module. When the cooling load increases, the system can automatically enhance its cooling capacity.

[0072] Based on the feedback from the temperature monitoring unit, the high-efficiency heat dissipation and heat recovery unit collects excess heat from high-temperature components.

[0073] The high-efficiency heat dissipation and heat recovery unit reuses part of the heat through thermal energy conversion technologies (such as thermoelectric power generation or reheating cycle) for heating the environmental control system or other energy-consuming needs, improving the energy utilization efficiency.

[0074] The high-efficiency heat dissipation and heat recovery unit feeds back the recovery efficiency and heat flow data to the temperature monitoring unit and the cooling system in real time, so that the system can perform dynamic optimization and adjustment according to the actual working conditions.

[0075] Through multi-level feedback and dynamic regulation, the comprehensive thermal management module ensures the temperature stability and safety of each component of the aircraft under complex working conditions, while achieving efficient heat energy utilization and recovery.

[0076] The above embodiments are only used to clearly illustrate the technology and features of the present invention, so that those of ordinary skill in the art can easily understand and implement it, and are not used to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made without departing from the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. The present invention is an integrated framework for optimizing power and thermal management parameters for high-power hydrogen-electric propulsion aircraft, characterized in that: It includes an overall design and parameter optimization module, a power allocation and control module, and an integrated thermal management module; the overall design and parameter optimization module achieves the optimal balance between the vehicle's thrust, energy efficiency, and flight stability through aerodynamic design, mission profile analysis, propulsion system configuration, and weight estimation; the power allocation and control module is based on the model predictive control method, using the top-level energy management controller to work in coordination with the control units of each underlying component to dynamically allocate the power output of power sources such as lithium batteries, hydrogen fuel cells, and hydrogen turbine engines to ensure optimal power utilization at different flight stages; the integrated thermal management module includes a low-temperature cooling loop, a non-low-temperature thermal management system, a temperature monitoring unit, and a heat recovery unit, which are used to monitor and adjust the temperature of key components of the aircraft in real time to ensure that they operate efficiently within a safe temperature range; collaborative optimization is achieved between the modules through parameter transfer and feedback mechanisms, and power output and temperature management are dynamically adjusted at different flight stages to meet the energy efficiency, stability, and low-carbon emission requirements of the aircraft under high load conditions.

2. The power and thermal management parameter optimization integrated framework of a hydrogen-electric propulsion aircraft according to claim 1, characterized in that: The overall design and parameter optimization module is based on a multi-objective optimization algorithm, which achieves the optimal balance between aircraft performance and energy efficiency by coordinating and optimizing aerodynamic parameters, propulsion system configuration and weight distribution.

3. The power and thermal management parameter optimization integrated framework of a hydrogen-electric propulsion aircraft according to claim 1, characterized in that: The energy management controller in the power distribution and control module uses a model predictive control method, combined with real-time flight conditions and power requirements, to optimize the power output of each power source to improve energy utilization efficiency.

4. The power and thermal management parameter optimization integrated framework of a hydrogen-electric propulsion aircraft according to claim 1, characterized in that: The cryogenic cooling circuit in the integrated thermal management module is used to cool cryogenic components such as liquid hydrogen storage tanks, superconducting motors and cryogenic power electronics. The cooling medium flow is adjusted by hydrogen / helium direct cooling or hydrogen-helium heat exchange cooling to achieve safe temperature control of the cryogenic components.

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