Hydrogen storage system supporting structure design method and system suitable for aircraft

Abstract

The invention relates to the technical field of liquid hydrogen storage structure design, and discloses a hydrogen storage system supporting structure design method and system suitable for an aircraft, and the design method specifically comprises the steps: firstly, determining the type of the aircraft and the requirements of space, load, heat leakage and the like of a supporting structure according to an application scene and a design boundary; the working condition of the storage tank is analyzed, and parameter modeling is conducted on stress, heat conduction and the like of the supporting structure; checking the thermal performance and strength of the support structures with different configurations; in combination with the weight and the cost, an optimal structure is obtained through a multi-objective optimization algorithm; and finally, carrying out topology, parameter optimization and multi-physics field simulation on the optimal structure of the multi-objective optimization algorithm to obtain an optimal scheme. By optimizing the design method and process of the aircraft hydrogen storage system supporting structure, it is guaranteed that the supporting structure has enough structural strength and stability under various working conditions, the external heat exchange amount can be controlled to be the minimum, and external heat transfer is effectively reduced.

Description

Technical Field

[0001] This invention relates to the field of liquid hydrogen storage structure design technology, and more specifically to a design method and system for a support structure of a hydrogen storage system suitable for aircraft. Background Technology

[0002] Liquid hydrogen, as an important fuel, has wide applications in aerospace and other fields. Generally, the placement of liquid hydrogen storage tanks requires mechanical support. This mechanical structure must ensure the stability of the hydrogen storage system and, to withstand the various mechanical loads experienced by the liquid hydrogen tank during aircraft operation, the support structure needs sufficient structural strength to ensure the overall mechanical strength of the hydrogen storage system. On the other hand, since there is direct contact between the mechanical structure and the hydrogen storage tank, the contact points may have insulation deficiencies. Since liquid hydrogen storage requires a cryogenic environment of -253°C, the thermal insulation of the tank is a core challenge in tank design, requiring minimizing heat transfer to ensure stable storage of liquid hydrogen during long-duration flights. Therefore, the design of the support structure for the aircraft's hydrogen storage system must consider both strength verification and thermal insulation.

[0003] Currently, the support structure for hydrogen storage systems designed based on existing design methods cannot simultaneously meet the comprehensive requirements of high strength, low heat leakage, and lightweight for aircraft hydrogen storage systems. Summary of the Invention

[0004] To address the problems and shortcomings of existing technologies, this invention proposes a design method and system for the support structure of hydrogen storage systems suitable for aircraft. It optimizes the design process of the support structure for airborne liquid hydrogen storage tanks, ensuring that the structure has sufficient structural strength and stability under various operating conditions, while minimizing external heat exchange.

[0005] To achieve the above-mentioned objectives, the technical solution of the present invention is as follows: This invention discloses a design method for a support structure of a hydrogen storage system suitable for aircraft, the design method comprising the following steps: Step S1. Based on the application scenario and design boundaries, determine the aircraft type and set the space constraints, load requirements, heat leakage limits, and integrated monitoring requirements for the support structure; Step S2. Analyze the working conditions of the liquid hydrogen storage tank according to the task requirements, and perform parametric modeling of the stress, heat conduction and installation space and interface layout of the liquid hydrogen storage tank support structure, including the mechanism mathematical model and three-dimensional geometric model of the support structure, etc. Step S3. Based on the parameter modeling results of step S2, analyze and verify the thermal performance of the support structure under different support configurations and the strength under different working conditions and loads; Step S4. Under the condition that the support structure meets the requirements of strength and thermal insulation performance, the weight and manufacturing cost of the support structure are comprehensively considered, and the optimal support structure for the liquid hydrogen storage tank is obtained through numerical modeling and multi-objective optimization algorithm. Step S5. Perform topology and parameter optimization and multiphysics simulation on the selected liquid hydrogen storage tank support structure to obtain the optimal support structure scheme.

[0006] Preferably, in step S3, the strength of the support structure under different working conditions and strength loads is analyzed and verified. Specifically, the maximum stress that the support structure needs to bear under different working conditions and the maximum design stress of the material used in the support structure are calculated, and the two are compared to determine whether the support structure meets the strength requirements.

[0007] Preferably, the different operating condition loads include impact loads during the aircraft's takeoff, acceleration, separation, trajectory change, and landing phases.

[0008] As a preferred embodiment, the calculation method for the maximum stress that the support structure needs to bear under different working conditions is as follows: Equation (1); In the formula: N g Impact load; W This refers to the full load weight of the liquid hydrogen storage tank. F t The maximum stress that the supporting structure needs to withstand.

[0009] Preferably, the maximum design stress of the material used in the supporting structure is calculated as follows: F s =[ σ ]× A Equation (2); In the formula, F s The maximum design stress of the material used to support the structure; σ The allowable shear stress of the material used to support the structure; A The equivalent cross-sectional area of ​​the supporting structure.

[0010] Preferably, the heat conduction of the support structure is parametrically modeled, specifically by identifying the main heat transfer paths between the liquid hydrogen storage tank and the aircraft body in the support structure, thereby establishing an equivalent thermal path model or a finite element thermal analysis model; the main heat transfer paths include heat conduction, radiation and contact heat leakage.

[0011] Preferably, the thermal performance of the support structure is analyzed and verified, specifically by calculating the heat leakage of the support structure under different support configurations and comparing it with the design upper limit value to determine whether the insulation performance requirements are met. The calculation method for the heat leakage of the support structure under different support configurations is as follows: Equation (3); In the formula, This refers to the heat loss from the liquid hydrogen storage tank through the supporting structure. To support the thermal conductivity of the structural material; B To support the cross-sectional area of ​​the structure in contact with the liquid hydrogen storage tank; The support length is for the supporting structure; ≈293 ; ≈20K.

[0012] Preferably, the multi-objective optimization algorithm adopts any one of the following: non-dominated sorting genetic algorithm, particle swarm optimization algorithm, and simulated annealing algorithm.

[0013] Based on the same inventive concept, another aspect of the present invention discloses a support structure design system suitable for a hydrogen storage system of an aircraft. This support structure design system is used to implement the aforementioned support structure design method for a hydrogen storage system of an aircraft, comprising: The requirement parameter determination module is used to determine the aircraft type and set the space constraints, load requirements, heat leakage limit and integrated monitoring requirements of the support structure based on the application scenario and design boundaries. The parametric modeling module is used to analyze the working conditions of liquid hydrogen storage tanks according to task requirements, and to perform parametric modeling of the stress, heat conduction, installation space and interface layout of the liquid hydrogen storage tank support structure. The performance analysis and verification module is used to analyze and verify the thermal performance of the support structure under different support configurations and the strength under different working conditions and loads, based on the parameter modeling results of the parameter modeling module. The multi-objective optimization module is used to obtain the optimal liquid hydrogen storage tank support structure by comprehensively considering the weight and manufacturing cost of the support structure, under the condition that the support structure meets the requirements of strength and thermal insulation performance, through numerical modeling and multi-objective optimization algorithm. The topology parameter optimization and simulation module is used to perform topology and parameter optimization and multiphysics simulation on the results of the multi-objective optimization module to obtain the optimal support structure scheme.

[0014] Furthermore, in another aspect, the present invention also discloses a support structure for a hydrogen storage system suitable for aircraft, wherein the support structure is designed using the aforementioned design method for a hydrogen storage system support structure suitable for aircraft.

[0015] The beneficial effects of this invention are: 1. This invention initially clarifies the application scenario and design boundaries, and accurately sets structural, thermal and spatial parameters for different aircraft with different space constraints, load requirements, heat leakage limits, etc., avoiding design deviations caused by ambiguous input conditions, providing targeted basis for subsequent modeling and analysis, and improving the matching degree between the design scheme and actual needs. 2. This invention, through a combination of structural strength calculation and preliminary verification, and thermal performance analysis and insulation verification, verifies the mechanical strength of the supporting structure under conditions such as impact loads and static loads. It also checks whether the heat leakage of the supporting structure meets the upper limit requirements. This allows for early identification of insufficient strength or excessive heat leakage, preventing the design from being scrapped and restarted due to fundamental performance defects in subsequent optimization stages, thus shortening the design cycle and reducing iteration costs. 3. This invention introduces a multi-objective optimization model and algorithm. Under the premise of meeting the requirements of strength and thermal insulation, it quantitatively optimizes conflicting objectives such as structural weight and manufacturing cost, generates the optimal solution set, provides a scientific basis for decision-making for different performance focuses, and avoids the problem of objective imbalance in traditional empirical design.

[0016] 4. Based on multi-objective optimization, this invention combines topology and parameter optimization with multiphysics simulation processes. It optimizes the structural shape based on the principle of optimal material distribution, continuously fine-tunes key parameters such as support thickness and cross-sectional dimensions, and verifies the performance under the action of multiphysics through thermal-structural coupling simulation. This achieves a synergistic improvement in structural lightweighting and thermal insulation performance. At the same time, it can quantify indicators such as strength / mass ratio and heat flux density distribution, providing accurate data support for manufacturing process selection and further improving the engineering practicality of the design scheme. Attached Figure Description

[0017] The foregoing and hereinafter detailed description of the invention becomes clearer when read in conjunction with the following drawings, in which: Figure 1 This is a flowchart illustrating the design method for the support structure of a hydrogen storage system applicable to aircraft according to the present invention; Figure 2 This is a system architecture diagram of the support structure design for the hydrogen storage system of an aircraft, applicable to the present invention. Figure 3 This is a schematic diagram of a liquid hydrogen storage tank. Detailed Implementation

[0018] To enable those skilled in the art to better understand the technical solutions of this invention, specific embodiments will be used to further illustrate the technical solutions for achieving the objectives of this invention. It should be noted that the technical solutions claimed by this invention include, but are not limited to, the following embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without inventive effort should fall within the scope of protection of this invention. Because liquid hydrogen storage requires a cryogenic environment of -253°C, the thermal insulation of the storage tank is a core challenge in its design. Generally, liquid hydrogen storage tanks require mechanical support. This mechanical structure must ensure the stability of the hydrogen storage system. Furthermore, due to the direct contact between the mechanical structure and the storage tank, insulation deficiencies may exist at the contact points. Based on basic heat transfer analysis, the majority of the cooling loss from liquid hydrogen storage tanks occurs through leakage at the contact points. This invention addresses the design problem of the support structure for liquid hydrogen storage tanks on aircraft, proposing a design process that ensures the designed support structure possesses sufficient structural strength and stability under various operating conditions while minimizing external heat transfer.

[0019] This embodiment first discloses a design method for a support structure of a hydrogen storage system suitable for aircraft. Firstly, a structural schematic diagram of a liquid hydrogen storage tank is shown below. Figure 3 As shown, this liquid hydrogen storage tank includes nested inner and outer layers. The outer layer has legs on both sides to support the horizontal liquid hydrogen storage tank (i.e., the support structure of the liquid hydrogen storage tank). Both support structures on both sides include heat insulation components. During installation, the support structures on both sides of the tank are fixed to struts, thus securing the liquid hydrogen storage tank. Therefore, the support structure of the hydrogen storage system of this invention refers to the legs on both sides of the liquid hydrogen storage tank. The presence of support structures on both sides of the liquid hydrogen storage tank effectively ensures the stability of the overall structure. Furthermore, the use of fiberglass insulation components effectively reduces heat transfer efficiency, decreases heat leakage at the support structure locations, reduces energy loss, and is more energy-efficient and environmentally friendly.

[0020] In terms of structural form, based on the connection method between the support structure and the cryogenic storage tank, the support structure is divided into two main categories: continuous support and point support. Commonly used support forms in cryogenic containers include stainless steel tie rods, slings, slings, and clamp structures; steel pipe support structures; fiberglass structures; structures combining fiberglass with steel pipes and slings; spherical support structures; and multi-layer laminated structures, among others. The optimal structure needs to be selected based on factors such as the structural form of the container body and usage requirements. For horizontal containers, the inner and outer containers are connected by a compression rod at the top. This ensures that the cooling contraction occurs when the container is filled with liquid hydrogen while reducing the contact area between the inner and outer containers, thereby reducing heat leakage.

[0021] Figure 1 This is a flowchart illustrating the design method of the hydrogen storage system support structure for aircraft according to the present invention, with reference to... Figure 1 As shown, the specific design process for the support structure of the liquid hydrogen storage tank is as follows: Step S1. Based on the application scenario and design boundaries, determine the aircraft type and set the space constraints, load requirements, heat leakage limits, and integrated monitoring requirements for the support structure.

[0022] Before designing the support structure, it is necessary to first clarify the specific application scenario of the liquid hydrogen storage tank in order to set the corresponding structural, thermal, and spatial parameters as design input conditions. The hydrogen storage system addressed in this invention is mainly used in various aerospace vehicles, such as high-altitude long-endurance UAVs, launch vehicles, and manned spacecraft. Different platforms have different requirements for the support structure. For example, in high-altitude UAVs, due to the compact airframe and limited payload capacity, there are high requirements for the lightweight and compactness of the support structure, while ensuring good thermal insulation performance to reduce heat loss. In rockets or heavy-lift aircraft, the liquid hydrogen storage tank is subjected to severe acceleration impacts during takeoff or landing, making the strength and shock absorption capacity of the support structure even more critical. In addition, the support structure also needs to integrate sensor brackets to achieve real-time monitoring of the remaining liquid hydrogen level.

[0023] Step S2. Analyze the working conditions of the liquid hydrogen storage tank according to the task requirements, perform parametric modeling of the stress, heat conduction and installation space and interface layout of the liquid hydrogen storage tank support structure, and establish the mechanism mathematical model and three-dimensional geometric model of the support structure. In this invention, the following analysis was performed on liquid hydrogen storage tanks during parameter modeling: (1) Determine the total weight of the liquid hydrogen storage tank, including the inner layer, outer layer, insulation layer and the mass of liquid hydrogen stored inside; (2) Determine the impact loads borne by the liquid hydrogen storage tank under different operating conditions (flight and landing phases), including but not limited to the stages of takeoff, acceleration, separation, trajectory change, and landing of the aircraft. For example, an acceleration of more than 3.5g may occur during the vertical landing phase. For impact loads, the impact loads of the liquid hydrogen storage tank can be obtained by analyzing Newton's second law based on the flight profile of the aircraft.

[0024] (3) Liquid hydrogen storage tanks are usually installed horizontally, and the supporting structure should fit the tank body as closely as possible to reduce redundant space; (4) Liquid hydrogen storage tanks must be reserved with liquid hydrogen inlet pipe, gas outlet pipe, heat replenishment pipe and liquid level sensor interface. All kinds of pipelines must pass through or bypass the support structure to avoid interference. (5) The aircraft airframe structure restricts the installation location of the liquid hydrogen storage tank support structure, and it must avoid lines, pipelines and other structural components; (6) Conduct preliminary thermal analysis to control the heat leakage generated by the support structure within a certain range. The specific process is as follows: identify the main heat transfer paths (conduction, radiation, and contact heat leakage) between the liquid hydrogen storage tank and the aircraft body in the support structure, and establish an equivalent thermal path model or finite element thermal analysis model as the heat conduction model of the support structure. Based on the established heat conduction model, the total heat leakage of the support structure under different support configurations can be calculated.

[0025] After clarifying the aforementioned usage requirements and boundary conditions, parametric modeling was further performed on the stress, heat conduction, installation space, and interface layout of the support structure (establishing a mechanistic mathematical model of the support structure (such as heat conduction and force equations) and a three-dimensional geometric model), which served as the input basis for subsequent structural strength analysis and heat conduction calculations. This modeling step laid the foundation for the optimization of the support structure, ensuring that the design process was targeted and systematic, and avoiding a disconnect between thermal design and structural design.

[0026] Step S3. Based on the heat conduction model established in Step S2, analyze and verify the thermal performance of the support structure under different support configurations, and analyze and verify the strength of the support structure under different working conditions and loads according to the force equation established in Step S2.

[0027] The specific process for analyzing and verifying the thermal performance of the supporting structure is as follows: The total heat leakage of the support structure under different support configurations is calculated using the following formula and compared with the design upper limit value to determine whether the insulation performance requirements are met. If the total heat leakage of the support structure meets the requirements, it is considered that the insulation performance meets the requirements and is verified. If the requirements are not met, the shape parameters of the support structure or the support structure material needs to be modified. Equation (3); In the formula, To prevent heat loss in the supporting structure; To support the thermal conductivity of the structural material; B To support the cross-sectional area of ​​the structure in contact with the liquid hydrogen storage tank; The support length is for the supporting structure; ≈293 ; ≈20K.

[0028] The specific process for analyzing and verifying the strength of the supporting structure is as follows: When calculating the strength of the support structure, it is necessary to consider the tank capacity and overall load requirements. In the airborne liquid hydrogen system, the support structure bears the static load of the loaded medium and the self-weight of the inner and outer layers, and also needs to withstand the effects of vertical upward impact loads under flight conditions and onboard landing.

[0029] For the supporting structures on the left and right sides of the liquid hydrogen storage tank, the maximum stress that needs to be borne under different working loads can be calculated using formula (1): Equation (1); In the formula: N g Impact load; W This refers to the full load weight of the liquid hydrogen storage tank. F t The maximum stress that the supporting structure needs to bear; Furthermore, the maximum design stress of the material used in the supporting structure is calculated using formula (2): F s =[ σ ]× A Equation (2); In the formula, F s The maximum design stress of the material used to support the structure; σ The allowable shear stress of the material used to support the structure (that is, the maximum shear stress that the material can accept). A The equivalent cross-sectional area of ​​the supporting structure; By obtaining the shape parameters of the supporting structure, the equivalent cross-sectional area can be calculated. Substituting this equivalent cross-sectional area, the maximum shear stress the material can withstand can be calculated. Then, by comparing the maximum stress the supporting structure needs to bear under different load conditions with the maximum design stress the material can withstand, it can be determined whether the current supporting configuration meets the strength requirements. If it does not meet the requirements, the equivalent cross-sectional area needs to be changed or the material used in the supporting structure needs to be replaced.

[0030] In the embodiments described in this invention, the support structure adopts a continuous support form of all fiberglass pipes. Compared with traditional metal supports, fiberglass material can effectively reduce the weight of the support structure, while increasing the strength of the overall structure and reducing heat leakage.

[0031] Step S4. Under the condition of meeting the strength and thermal insulation performance requirements, taking into account the weight and manufacturing cost of the support structure, the optimal liquid hydrogen storage tank support structure is obtained through numerical modeling and multi-objective optimization algorithm.

[0032] To design the support structure of liquid hydrogen storage tanks more scientifically, this invention further introduces a multi-objective optimization modeling approach. Under the premise of meeting basic requirements such as strength and thermal insulation performance, it comprehensively considers engineering factors such as structural quality and manufacturing cost, and achieves automatic iteration and optimization selection under different support configuration schemes through multi-objective optimization algorithms.

[0033] In the design of supporting structures, the following conflicting objectives are the main challenges: (1) Maximize structural strength: The supporting structure must withstand the maximum load of the tank under flight conditions, especially the vertical impact load; (2) Minimize heat conduction: The supporting structure should minimize heat leakage and reduce the rate at which heat from the external environment enters the storage tank; (3) Minimize mass: The lower the overall structural mass, the higher the payload efficiency of the aircraft; Control manufacturing costs: The selection of materials and the processing of the structure should minimize the overall manufacturing cost.

[0034] Therefore, the optimization objective of a typical multi-objective optimization model is established as follows: Equation (4); In the formula, f 1 represents relative heat loss; f 2 represents relative weight; f 3 represents manufacturing costs; This refers to the heat loss from the liquid hydrogen storage tank through the supporting structure. To support the self-weight of the structure; To support the total cost of structural manufacturing and installation, To limit the heat loss due to structural leakage; To support the upper limit of the structure's self-weight; To support the budget for structural manufacturing and installation costs.

[0035] In the above multi-objective optimization algorithm, the strength constraint of the supporting structure is that the maximum shear stress does not exceed the yield shear stress: Equation (5); In the formula, The maximum shear stress on the supporting structure; Yield shear stress of the material used to support the structure.

[0036] Upper limit constraint on thermal conduction: Equation (6); in, This refers to the heat loss from the liquid hydrogen storage tank through the supporting structure. To limit the heat loss due to structural leakage.

[0037] Once the support structure design scheme is determined, the first step is to check whether it meets the relevant constraints (strength check and thermal performance check), and then calculate the costs of these schemes. f 1 and f 2 and f 3. Finally, the optimal solution is selected from the different support structure design schemes using a multi-objective optimization algorithm (the minimum sum of the three is the optimization objective of the whole scheme).

[0038] In this invention, the multi-objective optimization algorithm can be any one of the following: non-dominated sorting genetic algorithm, particle swarm optimization algorithm, or simulated annealing algorithm. NSGA-II (non-dominated sorting genetic algorithm) is recommended as the multi-objective optimization algorithm.

[0039] Step S5. Perform topology and parameter optimization and multiphysics simulation on the selected liquid hydrogen storage tank support structure to obtain the optimal support structure scheme. In the embodiments described in this invention, the actual physical structure can be optimized based on the preferred support structure obtained by the multi-objective optimization algorithm in step S4. Specifically, based on the existing support structure, topology optimization is used to improve the shape of the support structure, such as reducing weight and improving thermal insulation performance. Combined with multiphysics simulation, "thermal-structural coupling simulation" is performed to output the optimal support structure parameters (such as support position, cross-section, material layer thickness, etc.).

[0040] Topology optimization: Based on the principle of "optimal material distribution", under given space and boundary loads, it automatically generates material distribution schemes, determines the areas to be retained and removed from the structure, and achieves the goal of minimum mass or minimum compliance. Parameter optimization: Continuous tuning of key parameters of the support structure (such as support thickness, cross-sectional shape, opening location, composite layer thickness, etc.); Coupled simulation: Combining thermal-structural multiphysics finite element simulation tools, strength, heat conduction and deformation are analyzed in a coordinated manner for each design scheme; Design variable sample generation: Use Latin hypercube sampling, DOE design or Bayesian optimization to generate parameter combinations, improve convergence speed and sample diversity; The final output not only includes the determination of whether the structural strength and thermal performance are qualified, but also quantifies the performance indicators of each design scheme in dimensions such as "strength / mass ratio", "heat flux density distribution" and "material utilization rate", which can further guide structural modification and manufacturing process selection.

[0041] Based on the same inventive concept, embodiments of the present invention also disclose a support structure design system suitable for hydrogen storage systems in aircraft, such as... Figure 2 As shown, the architecture of the hydrogen storage system support structure design system is as follows: The requirement parameter determination module is used to determine the aircraft type and set the space constraints, load requirements, heat leakage limit and integrated monitoring requirements of the support structure based on the application scenario and design boundaries. The parametric modeling module is used to analyze the working conditions of liquid hydrogen storage tanks according to task requirements, and to perform parametric modeling of the stress, heat conduction, installation space and interface layout of the liquid hydrogen storage tank support structure. The performance analysis and verification module is used to analyze and verify the thermal performance of the support structure under different support configurations and the strength under different working conditions and loads, based on the parameter modeling results of the modeling module. The multi-objective optimization module is used to obtain the optimal liquid hydrogen storage tank support structure by comprehensively considering the weight and manufacturing cost of the support structure, under the condition that the support structure meets the requirements of strength and thermal insulation performance, through numerical modeling and multi-objective optimization algorithm. The topology parameter optimization and simulation module is used to perform topology and parameter optimization and multiphysics simulation on the results of the multi-objective optimization module to obtain the optimal support structure scheme.

[0042] Furthermore, this embodiment also provides a computer device, which includes a processor, an input device, an output device, and a memory, all interconnected. The memory stores a computer program, which includes program instructions, and the processor is configured to invoke the program instructions to execute the steps described in the above embodiment.

[0043] Furthermore, another aspect of this embodiment provides a computer-readable storage medium, characterized in that: the computer-readable storage medium stores a computer program, the computer program including program instructions, which, when executed by a processor, cause the processor to perform the steps in the above embodiments.

[0044] In this embodiment, the processor can be a central processing unit (CPU). The processor can also be other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, or combinations of the above types of chips.

[0045] Memory, as a non-transitory computer-readable storage medium, can be used to store non-transitory software programs, non-transitory computer-executable programs, and units, such as the program units corresponding to the above-described method embodiments of the present invention. The processor executes various functional applications and data processing of the processor by running the non-transitory software programs, instructions, and modules stored in the memory, thereby implementing the methods described in the above-described method embodiments.

[0046] The memory may include a program storage area and a data storage area. The program storage area may store the operating system and applications required for at least one function; the data storage area may store data created by the processor, etc. Furthermore, the memory may include high-speed random access memory and non-transitory memory, such as at least one disk storage device, flash memory device, or other non-transitory solid-state storage device. In some embodiments, the memory may optionally include memory remotely located relative to the processor, which can be connected to the processor via a network. Examples of such networks include, but are not limited to, the Internet, corporate intranets, local area networks, mobile communication networks, and combinations thereof.

[0047] The one or more units are stored in the memory and, when executed by the processor, perform the methods described in the above embodiments.

[0048] Those skilled in the art will understand that embodiments of the present invention can be provided as methods, systems, or computer program products. Therefore, the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects.

[0049] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A design method for a support structure of a hydrogen storage system suitable for aircraft, characterized in that, Includes the following steps: Step S1. Based on the application scenario and design boundaries, determine the aircraft type and set the space constraints, load requirements, heat leakage limits, and integrated monitoring requirements for the support structure; Step S2. Analyze the working conditions of the liquid hydrogen storage tank according to the task requirements, and perform parametric modeling of the stress, heat conduction, installation space and interface layout of the liquid hydrogen storage tank support structure. Step S3. Based on the parameter modeling results of step S2, analyze and verify the thermal performance of the support structure under different support configurations and the strength under different working conditions and loads; Step S4. Under the condition that the support structure meets the requirements of strength and thermal insulation performance, the weight and manufacturing cost of the support structure are comprehensively considered, and the optimal support structure for the liquid hydrogen storage tank is obtained through numerical modeling and multi-objective optimization algorithm. Step S5. Perform topology and parameter optimization and multiphysics simulation on the selected liquid hydrogen storage tank support structure to obtain the optimal support structure scheme.

2. The design method for a support structure of a hydrogen storage system suitable for aircraft according to claim 1, characterized in that, In step S3, the strength of the support structure under different working conditions and strength loads is analyzed and verified. Specifically, the maximum stress that the support structure needs to bear under different working conditions and the maximum design stress of the materials used in the support structure are calculated, and the two are compared to determine whether the support structure meets the strength requirements.

3. The design method for a support structure of a hydrogen storage system suitable for aircraft according to claim 1, characterized in that, The different operating conditions include impact loads during the aircraft's takeoff, acceleration, separation, trajectory change, and landing phases.

4. The design method for a support structure of a hydrogen storage system suitable for aircraft according to claim 2, characterized in that, The calculation method for the maximum stress that the supporting structure needs to bear under different working conditions is as follows: Equation (1); In the formula: N g Impact load; W This refers to the full load weight of the liquid hydrogen storage tank. F t The maximum stress that the supporting structure needs to withstand.

5. The design method for a support structure of a hydrogen storage system suitable for aircraft according to claim 2, characterized in that, The maximum design stress of the material used in the supporting structure is calculated as follows: F s =[ σ ]× A Equation (2); In the formula, F s The maximum design stress of the materials used to support the structure; [ σ The allowable shear stress of the material used to support the structure; A The equivalent cross-sectional area of ​​the supporting structure.

6. The design method for a support structure of a hydrogen storage system suitable for aircraft according to claim 1, characterized in that, Parametric modeling of heat conduction in the support structure is performed, specifically by identifying the main heat transfer paths between the liquid hydrogen storage tank and the aircraft body in the support structure, thereby establishing an equivalent thermal path model or a finite element thermal analysis model.

7. The design method for a support structure of a hydrogen storage system suitable for aircraft according to claim 6, characterized in that, The main heat transfer paths include conduction, radiation, and contact heat leakage.

8. The design method for a support structure of a hydrogen storage system suitable for aircraft according to claim 1, characterized in that, The thermal performance of the support structure was analyzed and verified, specifically: the heat leakage of the support structure under different support configurations was calculated and compared with the design upper limit value to determine whether the insulation performance requirements were met; the calculation methods for the heat leakage of the support structure under different support configurations are as follows: Equation (3); In the formula, This refers to the heat loss from the liquid hydrogen storage tank through the supporting structure. To support the thermal conductivity of the structural material; B To support the cross-sectional area of ​​the structure in contact with the liquid hydrogen storage tank; The support length is for the supporting structure; ≈293 ; ≈20K.

9. The design method for a support structure of a hydrogen storage system suitable for aircraft according to claim 1, characterized in that, The multi-objective optimization algorithm can be any one of the following: non-dominated sorting genetic algorithm, particle swarm optimization algorithm, or simulated annealing algorithm.

10. A design system for a support structure of a hydrogen storage system suitable for aircraft, characterized in that, The support structure design system is used to implement the support structure design method for a hydrogen storage system suitable for aircraft as described in any one of claims 1-9, including: The requirement parameter determination module determines the aircraft type and sets the space constraints, load requirements, heat leakage limits, and integrated monitoring requirements of the support structure based on the application scenario and design boundaries. The parameter modeling module analyzes the working conditions of the liquid hydrogen storage tank according to the task requirements, and performs parameter modeling on the stress, heat conduction, installation space and interface layout of the liquid hydrogen storage tank support structure. The performance analysis and verification module analyzes and verifies the thermal performance of the support structure under different support configurations and the strength under different working conditions and loads, based on the results of parametric modeling. The multi-objective optimization module, under the condition that the support structure meets the requirements of strength and thermal insulation performance, comprehensively considers the weight and manufacturing cost of the support structure, and obtains the optimal support structure for the liquid hydrogen storage tank through numerical modeling and multi-objective optimization algorithm. The topology parameter optimization and simulation module performs topology and parameter optimization and multiphysics simulation on the selected liquid hydrogen storage tank support structure to obtain the optimal support structure scheme.

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