Method for optimizing layout of components in aircraft cabin under multi-heat-source constraint

Abstract

The invention belongs to the technical field of aircraft thermal management, and particularly relates to an aircraft cabin component layout optimization method under multi-heat-source constraint, which comprises the following steps: step 1, inputting component allowable temperature, a heat source temperature time-varying curve, a cabin arrangement space and an initial component position; 2, establishing a simulation model by using a three-dimensional transient heat conduction-radiation coupling finite element analysis method; 3, finite element thermal radiation simulation calculation is carried out, and the maximum surface temperature of the component is obtained; 4, when it is detected that the temperature of the component exceeds an allowable value, position optimization is carried out by adopting a gradient-guided iterative algorithm, and a partial derivative of a temperature field of a characterization point of the component model to a space coordinate is calculated by utilizing a disturbance method; and adjusting the position along the temperature reduction direction at a fixed step length and ensuring that the new coordinate is always in the corresponding area. Wherein the step 3 to the step 4 are circulated until the temperatures of all the components reach the standard, and the optimized position is output.

Description

Technical Field

[0001] This invention belongs to the field of aircraft thermal management technology, specifically relating to a method for optimizing the layout of components inside an aircraft cabin under multiple heat source constraints. It is a design method for iteratively optimizing the arrangement of components through thermal radiation simulation under the condition that there are multiple fixed heat sources in the narrow space inside the cabin. Background Technology

[0002] Aircraft cabin thermal management faces severe challenges due to the confined space (typically less than 1 cubic meter) requiring the placement of electronic components within rigid constraints such as structural elements and cable channels. Multiple fixed high-temperature heat sources (e.g., nozzles, thermal batteries) are typically present within the cabin, with temperatures reaching up to 450°C and exhibiting dynamic variations. Due to the cumulative effect of multiple reflections of thermal radiation within the confined space, local temperatures can exceed theoretical predictions for single heat sources by more than 40%. Existing technologies rely on empirical layout methods, which depend on engineers' subjective judgment and cannot quantify the impact of radiative heat transfer, leading to a high risk of overheating. Simplified heat conduction models ignore the dominant role of radiative heat transfer (accounting for over 60% of total heat transfer within the cabin), resulting in significant prediction errors. Global optimization algorithms suffer from a severe lack of engineering practicality due to the explosion of solution space dimensions (optimizing the positions of 4 components requires searching a million-level solution space). Therefore, how to optimize component layout and determine placement positions that meet component temperature limitations is a technical problem that needs to be solved in this field. Summary of the Invention

[0003] (a) Technical problems to be solved

[0004] The technical problem this invention aims to solve is: how to provide a component layout optimization method suitable for multi-heat source radiation environments within the confined space of an aircraft cabin. By establishing a dynamic thermal radiation propagation model and combining it with spatial constraints, iterative optimization of component placement is achieved. The core objectives include: accurately predicting the three-dimensional distribution of multi-heat source radiation fields within the sealed cabin; dynamically guiding component position adjustments through finite element numerical simulation; and ensuring that the temperature of all components remains strictly below allowable limits throughout operation, while simultaneously meeting the hard constraints of the cabin space.

[0005] (II) Technical Solution

[0006] To address the aforementioned technical problems, this invention provides a method for optimizing the layout of components within an aircraft cabin under multiple heat source constraints. The technical problem addressed by this method is how to optimize the component layout and determine a layout that meets the temperature limitations of the components. The technical solution adopted is shown in the appendix. Figure 1 As shown, the objective is achieved by constructing a ternary collaborative optimization model of "simulation-iteration-constraint". The method includes the following steps:

[0007] Step 1: Input the allowable temperature of the components, the time-varying curve of the heat source temperature, the available space inside the cabin, and the initial position of the components;

[0008] Step 2: Establish a simulation model using the three-dimensional transient heat conduction-radiation coupled finite element analysis method;

[0009] Step 3: Conduct finite element thermal radiation simulation calculations to obtain the maximum surface temperature of the components;

[0010] Step 4: When the temperature of a component exceeds the allowable value, a gradient-guided iterative algorithm is used to optimize the position. The partial derivative of the temperature field of the component model representation point with respect to the spatial coordinates is calculated using the perturbation method. Then, the position is adjusted with a fixed step size along the direction of temperature decrease, and the new coordinates are always within the corresponding region.

[0011] The process involves repeating steps 3 and 4 until all components reach the specified temperature, at which point the optimized position is output.

[0012] Step 1: Input in the form of Appendix Figure 2 The allowable temperature T of the m components shown i lim Time-varying temperature curves T for n heat sources, i = 1, 2, ..., m. j (t), j = 1, 2, ..., n, and spatial location Q j (x,y,z), j=1,2,...,n, where Ω(x,y,z) is the available space inside the cabin and the initial positions of the components. Where (x, y, z) are spatial coordinate variables.

[0013] Step 2 involves establishing a simulation model using a three-dimensional transient heat conduction-radiation coupled finite element analysis method. The governing equations of the finite element analysis method are expressed as follows:

[0014]

[0015] In formula (1), ρ is the material density, C p Let T be the specific heat capacity of the material, t be the temperature, t be the time, and k be the thermal conductivity. It represents the partial derivative with respect to the spatial coordinate variables (x, y, z). For the radiative heat flux density, the calculation uses a modified Stefan-Boltzmann law model:

[0016]

[0017] In formula (2), σ=5.669×10 -8 W / (m 2 ·K 4 ) is the Stefan constant, ε iLet F be the surface emissivity of the i-th component. i→j The viewpoint factor is calculated using the Monte Carlo ray tracing method; the boundary conditions of the simulation model are set as follows: a time-varying temperature boundary T is applied with a fixed heat source. j (t), j=1,2,...,n, the surface of the component is considered as a diffuse reflective surface.

[0018] Step 3 involves conducting finite element thermal radiation simulation calculations to obtain the maximum surface temperature T of the component. i max ,i=1,2,...,m.

[0019] In step 4, when the component temperature exceeds the allowable value, a gradient-guided iterative algorithm is used to optimize the position, and the partial derivative of the temperature field at the component model representation point with respect to spatial coordinates (x, y, z) is calculated using the perturbation method.

[0020]

[0021] Then adjust the position along the direction of decreasing temperature with a fixed step size (Δx, Δy, Δz) and ensure that the new coordinates are always within the Ω(x, y, z) region;

[0022] Repeat steps 3 and 4 until all components reach the specified temperature, then output the optimized position.

[0023] (III) Beneficial Effects

[0024] Compared with the prior art, the beneficial effects of the present invention are:

[0025] (1) In terms of temperature control, eliminate the risk of overheating and ensure that the temperature of all points is strictly below the allowable value;

[0026] (2) The computational efficiency is significantly improved, with convergence achieved in an average of 7 iterations, which is more than two orders of magnitude faster than the global optimization algorithm. The spatial adaptability is comprehensively enhanced, and the optimization results satisfy 100% of the mechanical interference constraints, avoiding the constraint conflict problems that often occur in traditional schemes;

[0027] (3) The system's scalability is significantly broadened, supporting complex scenarios with any number of heat sources (n≥2) and components (m≥2), expanding the applicable scenario range by 200%. Engineering verification shows that the radiative heat flux density of the optimized components decreases by more than 43%, effectively ensuring the long-term reliable operation of components inside the aircraft cabin. Attached Figure Description

[0028] Figure 1 This is a flowchart of the cabin component layout optimization method of the present invention.

[0029] Figure 2It is a time-varying curve of a fixed heat source temperature.

[0030] Figure 3 This is a diagram showing the initial positions of heat sources / cabin interior space / components (brown: components; others: fixed heat sources).

[0031] Figure 4 It is a curve showing the temperature iteration convergence of the components inside the cabin. Detailed Implementation

[0032] To make the objectives, contents, and advantages of the present invention clearer, the specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples.

[0033] To address the aforementioned technical problems, this invention provides a method for optimizing the layout of components within an aircraft cabin under multiple heat source constraints. The technical problem addressed by this method is how to optimize the component layout and determine a layout that meets the temperature limitations of the components. The technical solution adopted is shown in the appendix. Figure 1 As shown, the objective is achieved by constructing a ternary collaborative optimization model of "simulation-iteration-constraint". The method includes the following steps:

[0034] Step 1: Input the allowable temperature of the components, the time-varying curve of the heat source temperature, the available space inside the cabin, and the initial position of the components;

[0035] Step 2: Establish a simulation model using the three-dimensional transient heat conduction-radiation coupled finite element analysis method;

[0036] Step 3: Conduct finite element thermal radiation simulation calculations to obtain the maximum surface temperature of the components;

[0037] Step 4: When the temperature of a component exceeds the allowable value, a gradient-guided iterative algorithm is used to optimize the position. The partial derivative of the temperature field of the component model representation point with respect to the spatial coordinates is calculated using the perturbation method. Then, the position is adjusted with a fixed step size along the direction of temperature decrease, and the new coordinates are always within the corresponding region.

[0038] The process involves repeating steps 3 and 4 until all components reach the specified temperature, at which point the optimized position is output.

[0039] Step 1: Input in the form of Appendix Figure 2 The allowable temperature T of the m components shown i lim Time-varying temperature curves T for n heat sources, i = 1, 2, ..., m. j (t), j = 1, 2, ..., n, and spatial location Q j (x,y,z), j=1,2,...,n, where Ω(x,y,z) is the available space inside the cabin and the initial positions of the components. Where (x, y, z) are spatial coordinate variables.

[0040] Step 2 involves establishing a simulation model using a three-dimensional transient heat conduction-radiation coupled finite element analysis method. The governing equations of the finite element analysis method are expressed as follows:

[0041]

[0042] In formula (1), ρ is the material density, C p Let T be the specific heat capacity of the material, t be the temperature, t be the time, and k be the thermal conductivity. It represents the partial derivative with respect to the spatial coordinate variables (x, y, z). For the radiative heat flux density, the calculation uses a modified Stefan-Boltzmann law model:

[0043]

[0044] In formula (2), σ=5.669×10 -8 W / (m 2 ·K 4 ) is the Stefan constant, ε i Let F be the surface emissivity of the i-th component. i→j The viewpoint factor is calculated using the Monte Carlo ray tracing method; the boundary conditions of the simulation model are set as follows: a time-varying temperature boundary T is applied with a fixed heat source. j (t), j=1,2,...,n, the surface of the component is considered as a diffuse reflective surface.

[0045] Step 3 involves conducting finite element thermal radiation simulation calculations to obtain the maximum surface temperature T of the component. i max ,i=1,2,...,m.

[0046] In step 4, when the component temperature exceeds the allowable value, a gradient-guided iterative algorithm is used to optimize the position, and the partial derivative of the temperature field at the component model representation point with respect to spatial coordinates (x, y, z) is calculated using the perturbation method.

[0047]

[0048] Then adjust the position along the direction of decreasing temperature with a fixed step size (Δx, Δy, Δz) and ensure that the new coordinates are always within the Ω(x, y, z) region;

[0049] Repeat steps 3 and 4 until all components reach the specified temperature, then output the optimized position.

[0050] Example 1

[0051] The layout of typical aircraft cabin components is optimized based on the method of this invention, and the invention is described in detail with reference to the optimization results. Obviously, the described embodiments are only a part of the embodiments of this invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0052] Based on the in-cabin component layout optimization process proposed in this invention, iterative optimization of the in-cabin component layout is carried out:

[0053] (1) Input key parameters: ① Allowable temperature T of 3 components i lim =[65,95,80],i=1,2,3, attached Figure 2 The time-varying temperature curves T of the five fixed heat sources shown are as follows. j (t), j=1,2,3,4,5, spatial location of heat source Q j (x,y,z), j=1,2,3,4,5, the available space Ω(x,y,z) inside the cabin and the initial positions of the components. With attachment Figure 3 The UG model shown is given;

[0054] (2) Establish a three-dimensional transient heat conduction-radiation coupled finite element model, and set the boundary conditions as follows: the heat source applies a time-varying temperature boundary T. j (t), j=1,2,3,4,5, the surface of the component is regarded as an adiabatic diffuse reflective surface.

[0055] (3) Conduct finite element thermal radiation simulation to obtain the maximum surface temperature T of different components. i max i = 1, 2, 3.

[0056] (4) Comparison with T i max <T i lim If i = 1, 2, 3, is satisfied, then the partial derivative of the temperature field with respect to spatial coordinates at the characterization point of the component model is calculated using the perturbation method. After the gradient direction is formed, the position is adjusted along the direction of decreasing temperature with a fixed step size (Δx, Δy, Δz) = 0.007, and the new coordinates are always within the Ω(x, y, z) region.

[0057] (5) After executing steps (3) and (4) and iterating 5 times, the temperatures of all three components met the standards. The convergence curves of the highest temperatures of the components during the optimization process are shown in the attached figure. Figure 4 As shown.

[0058] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for optimizing the layout of components inside an aircraft cabin under multiple heat source constraints, characterized in that, The method includes the following steps: Step 1: Input the allowable temperature of the components, the time-varying curve of the heat source temperature, the available space inside the cabin, and the initial position of the components; Step 2: Establish a simulation model using the three-dimensional transient heat conduction-radiation coupled finite element analysis method; Step 3: Conduct finite element thermal radiation simulation calculations to obtain the maximum surface temperature of the components; Step 4: When the temperature of a component exceeds the allowable value, a gradient-guided iterative algorithm is used to optimize the position. The partial derivative of the temperature field of the component model representation point with respect to the spatial coordinates is calculated using the perturbation method. Then, the position is adjusted with a fixed step size along the direction of temperature decrease, and the new coordinates are always within the corresponding region.

2. The method for optimizing the layout of aircraft cabin components under multiple heat source constraints as described in claim 1, characterized in that, Repeat steps 3-4 until all components reach the specified temperature, then output the optimized position.

3. The method for optimizing the layout of aircraft cabin components under multiple heat source constraints as described in claim 2, characterized in that, Step 1: Input the allowable temperature T of m components. i lim Time-varying temperature curves T for n heat sources, i = 1, 2, ..., m. j (t), j = 1, 2, ..., n, and spatial location Q j (x,y,z), j=1,2,...,n, where Ω(x,y,z) is the available space inside the cabin and the initial positions of the components. Where (x, y, z) are spatial coordinate variables.

4. The method for optimizing the layout of aircraft cabin components under multiple heat source constraints as described in claim 3, characterized in that, Step 2: Establish a simulation model using the three-dimensional transient heat conduction-radiation coupled finite element analysis method. The governing equations of the finite element analysis method are expressed as follows: In formula (1), ρ is the material density, C p Let T be the specific heat capacity of the material, t be the temperature, t be the time, and k be the thermal conductivity. It represents the partial derivative with respect to the spatial coordinate variables (x, y, z). For the radiative heat flux density, the calculation uses a modified Stefan-Boltzmann law model: In formula (2), σ=5.669×10 -8 W / (m 2 ·K 4 ) is the Stefan constant, ε i Let F be the surface emissivity of the i-th component. i→j The viewpoint factor is calculated using the Monte Carlo ray tracing method; the boundary conditions of the simulation model are set as follows: a time-varying temperature boundary T is applied with a fixed heat source. j (t), j=1,2,...,n, the surface of the component is regarded as a diffuse reflective surface.

5. The method for optimizing the layout of aircraft cabin components under multiple heat source constraints as described in claim 4, characterized in that, Step 3: Conduct finite element thermal radiation simulation calculations to obtain the maximum surface temperature T of the components. i max ,i=1,2,...,m.

6. The method for optimizing the layout of aircraft cabin components under multiple heat source constraints as described in claim 5, characterized in that, Step 4: When the component temperature exceeds the allowable value, a gradient-guided iterative algorithm is used to optimize the position, and the partial derivative of the temperature field at the component model representation point with respect to spatial coordinates (x, y, z) is calculated using the perturbation method. Then adjust the position along the direction of decreasing temperature with a fixed step size (Δx, Δy, Δz) and ensure that the new coordinates are always within the Ω(x, y, z) region; Repeat steps 3 and 4 until all components reach the specified temperature, then output the optimized position.

7. The method for optimizing the layout of aircraft cabin components under multiple heat source constraints as described in claim 6, characterized in that, The method described belongs to the field of aircraft thermal management technology.

8. The method for optimizing the layout of aircraft cabin components under multiple heat source constraints as described in claim 6, characterized in that, The method establishes a dynamic thermal radiation propagation model and combines it with spatial constraints to achieve iterative optimization of the component placement.

9. The method for optimizing the layout of aircraft cabin components under multiple heat source constraints as described in claim 6, characterized in that, The method accurately predicts the three-dimensional distribution of multi-heat source radiation fields in a sealed chamber; dynamically guides the adjustment of component positions through finite element numerical simulation; ensures that the temperature of all components is strictly below the allowable limit throughout the entire operation process, while meeting the hard constraint requirements of the chamber space.

10. The method for optimizing the layout of aircraft cabin components under multiple heat source constraints as described in claim 6, characterized in that, In terms of temperature control, the method eliminates the risk of overheating and ensures that the temperature at all points is strictly below the allowable value.

Images