Aircraft cabin thermal environment control method, device, electronic equipment and medium

Abstract

The present application relates to the technical field of aircraft cabin thermal environment control, and specifically to a method, device, electronic device, and medium for aircraft cabin thermal environment control. The method comprises: upon detecting that the aircraft cabin environment control system has been activated, determining the temperature distribution parameters of the first predetermined number of discrete nodes of the aircraft cabin during the target time period, wherein the temperature distribution parameters of each discrete node are obtained by differentially solving the preset heat transfer equation using the Euler method based on a preset differential equation and its initial value, and then fitting iteratively; and controlling the temperature of the aircraft cabin based on the temperature distribution parameters of the first predetermined number of discrete nodes so that the temperature of the aircraft cabin conforms to the preset standard temperature distribution. This solves the problem of large errors and low accuracy in existing cabin temperature numerical solution technologies, thereby achieving the purpose of improving the accuracy of cabin thermal environment control.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft cabin thermal environment control, and in particular to an aircraft cabin thermal environment control method, device, electronic equipment, and medium. Background Art

[0002] With the rapid development of modern aerospace, aircraft cabin thermal environment control has become an essential component of aircraft onboard systems. The design of aircraft cabin thermal environment control must consider the reliability and tolerance of cabin operating equipment, the human body's requirements for survival and comfort, and the impact of heat transfer between the cabin structure and its associated thermal fluid structures. Existing aircraft cabin thermal environment control primarily utilizes differential equations based on Taylor's formula for calculation. However, this approach suffers from large error accumulation and low computational accuracy due to non-repeatable calculations. Summary of the Invention

[0003] In view of this, one of the technical problems solved by the embodiments of the present application is to provide a method, device, electronic equipment and medium for controlling the thermal environment of an aircraft cabin to solve the problem of error accumulation caused by the increase of the distance from the initial point after the error occurs in the effective fitting area.

[0004] In a first aspect of an embodiment of the present application, a method for controlling the thermal environment of an aircraft cabin is disclosed, the method comprising:

[0005] When it is detected that the aircraft cabin environmental control system is activated, temperature distribution parameters of a predetermined number of discrete nodes in the aircraft cabin during a target time period are determined, wherein the temperature distribution parameters of each discrete node are obtained by performing a differential solution of a preset heat transfer equation using the Euler method and an iterative fitting process based on a preset differential equation and its initial values;

[0006] The temperature of the aircraft cabin is controlled according to the temperature distribution parameters of the first predetermined number of discrete nodes, so that the temperature of the aircraft cabin conforms to a preset standard temperature distribution.

[0007] Further,

[0008] When the aircraft is in transient working state with internal heat source, the heat transfer tensor equation is:

[0009] Where ρ represents the density of the cabin structure or air, c ρ represents the specific heat capacity of the cabin structure or the air, t is the inspection time of the cabin operating environment, λ is the thermal conductivity of the cabin structure or the air, x i is the cabin space coordinate, T is the temperature corresponding to the local time point, The internal heat source characteristics in the cabin that represent the heat dissipation of people or electronic equipment;

[0010] When the aircraft is in a steady-state state with no internal heat source, the heat transfer equation is:

[0011] Furthermore, the heat transfer equation is determined by:

[0012] Based on the heat transfer equations corresponding to the various aircraft, a heat transfer equation corresponding to a predetermined aircraft model is determined.

[0013] Furthermore, when it is detected that the aircraft cabin environment control system is activated, determining the temperature distribution parameters of the first predetermined number of discrete nodes of the aircraft cabin during the target time period includes:

[0014] Determine the spatial domain equation structure and the time domain equation structure of the heat transfer direction;

[0015] Discretely solve the spatial domain equation structure and the time domain equation structure respectively, and the results of the cross-space domain equation structure and the time domain equation structure are used as the initial solution values of each other:

[0016] Based on the spatial domain equation structure and the cockpit, the initial results are given, and the spatial domain equation structure is discretized and solved using the Euler method. The solution of the Euler method is iteratively processed using a preset proxy equation. The spatial domain equation structure is iteratively solved using the proxy equation until convergence, and the temperature parameters of a predetermined number of spatial domain discrete points at the current time point are obtained;

[0017] a) using the time domain equation structure and the spatial domain equation result as its initial value, discretely solving the time domain equation structure for the temperature parameters of a predetermined number of spatial domain discrete points for a number of subsequent time steps, and obtaining the temperature distribution of the predetermined number of spatial domain discrete points at each time discrete point;

[0018] b) discretizing and solving the spatial domain equation structure using the Euler method based on the spatial domain equation structure and the time domain equation results as initial results, iteratively processing the solution of the Euler method using a proxy equation, iteratively solving the spatial domain equation structure using the proxy equation until convergence, and obtaining temperature parameters of a predetermined number of spatial domain discrete points at the current time point;

[0019] Repeat steps a) and b) until the temperature within the specified range is obtained.

[0020] The spatial domain equation structure includes:

[0021]

[0022] The time domain equation structure includes:

[0023]

[0024]

[0025] In the above formula, i, j and k represent any dimension of the three-dimensional space, x i0 It represents the starting point of any dimension in three-dimensional space, and T is the temperature corresponding to the local time point.

[0026] Furthermore, controlling the temperature of the aircraft cabin based on the temperature distribution parameters of the first predetermined number of discrete nodes so that the temperature of the aircraft cabin meets a preset standard temperature includes:

[0027] determining a cabin temperature based on temperature distribution parameters of a first predetermined number of discrete nodes;

[0028] The temperature distribution parameters of the first predetermined number of discrete nodes are compared with the standard temperature distribution, and the air-conditioning temperature of the aircraft cabin is adjusted according to the comparison result.

[0029] Furthermore, before controlling the temperature of the aircraft cabin based on the temperature distribution parameters of the first predetermined number of discrete nodes so that the temperature of the aircraft cabin meets a preset standard temperature, the method includes at least one of the following:

[0030] Determine the standard temperature based on the pre-configured standard file;

[0031] Obtain temperature configuration parameters based on the preset interface and determine the standard temperature.

[0032] Furthermore, the method further comprises:

[0033] The initial value is updated with the fitted temperature of the last time step of the target time period, so as to solve the preset heat transfer equation by difference based on the differential equation and the updated initial value and using the Euler method.

[0034] In a second aspect of an embodiment of the present application, a device for controlling the thermal environment of an aircraft cabin is disclosed, the device comprising:

[0035] an aircraft cabin temperature determination module, configured to, upon detecting that the aircraft cabin environmental control system has been activated, determine the temperature distribution parameters of the first predetermined number of discrete nodes in the aircraft cabin during a target time period, wherein the temperature distribution parameters of each discrete node are obtained by iteratively fitting a preset heat transfer equation using a differential solution of a preset differential equation and its initial values using the Euler method;

[0036] The aircraft cabin temperature control module is used to control the temperature of the aircraft cabin based on the temperature distribution parameters of a predetermined number of discrete nodes so that the temperature of the aircraft cabin meets the preset standard temperature distribution.

[0037] In a third aspect of an embodiment of the present application, an electronic device is disclosed. The electronic device includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the steps of the above method are implemented.

[0038] In a fourth aspect of the embodiments of the present application, a computer-readable storage medium is disclosed, which stores a computer program. When the computer program is executed by a processor, the steps of the above method are implemented.

[0039] The present application has the following advantages: by solving the temperature distribution of a predetermined number of discrete points of the aircraft cabin heat transfer equation based on differential equations and initial values and using the Euler method, the cabin temperature can be obtained through fitting processing, and then compared with the standard temperature to achieve the purpose of cabin temperature control. This method of obtaining a result near the true value using the Euler method and simultaneously applying a fitting iterative method to approximate the true value not only shortens the solution iteration time and reduces the node density requirement, but also solves the problem of error accumulation caused by increasing distance from the initial point after errors occur within the effective fitting area. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 A schematic flow chart of a method for controlling the thermal environment of an aircraft cabin provided in one embodiment of the present application;

[0041] Figure 2 A schematic cross-sectional view of an aircraft cabin provided in accordance with one embodiment of the present application;

[0042] Figure 3 A diagram of an aircraft cockpit model provided for one embodiment of the present application;

[0043] Figure 4 A schematic structural diagram of an aircraft cabin thermal environment control device provided in one embodiment of the present application. DETAILED DESCRIPTION

[0044] In order to make the purpose, technical solutions and advantages of this application more clear, the following further describes this application in detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain this application and are not intended to limit this application.

[0045] It should be noted that although the functional modules are divided in the device schematic and the logical order is shown in the flowchart, in some cases, the steps shown or described can be performed in a different order than the module division in the device or the order in the flowchart.

[0046] In order to make the objectives, technical solutions and advantages of this application clearer, the implementation methods of this application will be further described in detail below with reference to the accompanying drawings.

[0047] According to one embodiment of the present application, a method for controlling the thermal environment of an aircraft cabin is provided. Figure 1 As shown, the method includes step S101 and step S102.

[0048] Step S101: When it is detected that the aircraft cabin environmental control system is activated, the temperature distribution parameters of the first predetermined number of discrete nodes in the aircraft cabin during the target time period are determined. The temperature distribution parameters of each discrete node are obtained by iteratively fitting the preset heat transfer equation using the Euler method and a differential solution based on a preset differential equation and its initial values.

[0049] Specifically, the aircraft cabin environment control system may be determined to be activated when a preset aircraft power supply system is turned on, a button for the aircraft cabin temperature control system is triggered, or a temperature detected by an aircraft cabin temperature sensor exceeds a threshold.

[0050] Specifically, the number of spatially discrete nodes and the number of time steps in the aircraft cockpit may be preset, thereby calculating the temperature distribution of each node in the aircraft cockpit.

[0051] Specifically, multiple fitting algorithms can be preset and one of them can be used as a default fitting algorithm for processing. When applied, the default fitting algorithm can also be adjusted according to commands.

[0052] Step S102: Controlling the temperature of the aircraft cabin according to the temperature distribution parameters of the first predetermined number of discrete nodes, so that the temperature of the aircraft cabin complies with a preset standard temperature distribution.

[0053] Specifically, the standard temperature distribution can be determined according to the heat transfer equation of the aircraft cabin.

[0054] In the embodiment of the present application, the temperature distribution of a predetermined number of discrete points in the aircraft cabin heat transfer equation is solved using the Euler method based on differential equations and initial values. The cabin temperature is then obtained through fitting, and then compared with a standard temperature to achieve the purpose of cabin temperature control. This method of obtaining a result near the true value using the Euler method and simultaneously applying a fitting iterative method to approximate the true value not only shortens the solution iteration time and reduces the node density requirement, but also solves the problem of error accumulation caused by errors occurring within the effective fitting area as the distance from the initial point increases.

[0055] In some embodiments, when the aircraft is in a transient operating state with an internal heat source, the heat transfer tensor equation is:

[0056] Where ρ represents the density of the cabin structure or air, c ρrepresents the specific heat capacity of the cabin structure or the air, t is the inspection time of the cabin operating environment, λ is the thermal conductivity of the cabin structure or the air, x i is the cabin space coordinate, T is the temperature corresponding to the local time point, is the internal heat source characteristic in the cabin that represents the heat dissipation of people or electronic equipment. When the aircraft is in a steady state with no internal heat source, the heat transfer equation is:

[0057] Operating states include steady state and transient state. Steady state describes an aircraft's prolonged cruising state, where its altitude and speed remain essentially constant. Transient state describes periods of rapid change in speed and altitude, such as during takeoff and landing. In practice, the aircraft's operating state can be determined by monitoring changes in altitude and speed. Different differential equations corresponding to different operating states can be pre-stored locally or converted in real time.

[0058] When applied, when the aircraft's working state is transient and some physical characteristics of the tensor equation with internal heat source (such as ambient temperature, pressure, aircraft kitchen heating, etc. corresponding to the flight altitude) are corrected and updated according to other relevant sensors.

[0059] In some embodiments, determining the heat transfer equation includes:

[0060] Based on the heat transfer equations corresponding to the various aircraft, a heat transfer equation corresponding to a predetermined aircraft model is determined.

[0061] The embodiment of the present application queries the corresponding heat transfer direction through the aircraft model, thereby expanding the application models of the method provided by the embodiment of the present application and improving the commercial value of the method provided by the present application.

[0062] In some embodiments, step S101 further includes:

[0063] Discretely solve the spatial domain equation structure and the time domain equation structure respectively, and the results of the cross-space domain equation structure and the time domain equation structure are used as the initial solution values of each other:

[0064] Based on the spatial domain equation structure and the cockpit, the initial results are given, and the spatial domain equation structure is discretized and solved using the Euler method. The solution of the Euler method is iteratively processed using a preset proxy equation. The spatial domain equation structure is iteratively solved using the proxy equation until convergence, and the temperature parameters of a predetermined number of spatial domain discrete points at the current time point are obtained;

[0065] a) using the time domain equation structure and the spatial domain equation result as its initial value, discretely solving the time domain equation structure for the temperature parameters of a predetermined number of spatial domain discrete points for a number of subsequent time steps, and obtaining the temperature distribution of the predetermined number of spatial domain discrete points at each time discrete point;

[0066] b) discretizing and solving the spatial domain equation structure using the Euler method based on the spatial domain equation structure and the time domain equation results as initial results, performing proxy equation iterative processing on the solution results of the Euler method, and iteratively solving the spatial domain equation structure using the proxy equation until convergence, thereby obtaining temperature parameters of a predetermined number of spatial domain discrete points at the current time point;

[0067] Repeat steps a) and b) until the temperature within the specified range is obtained.

[0068] Among them, the spatial domain equation structure includes:

[0069]

[0070] The time domain equation structure includes:

[0071]

[0072] In the above formula, i, j and k represent any dimension of the three-dimensional space, x i0 It represents the starting point of any dimension in three-dimensional space, and T is the temperature corresponding to the local time point.

[0073] In some embodiments, step S102 further includes:

[0074] The temperature distribution parameters of the first predetermined number of discrete nodes are compared with the standard temperature distribution, and the air-conditioning temperature of the aircraft cabin is adjusted according to the comparison result.

[0075] Specifically, if the temperature parameter at any spatial point is greater than the corresponding standard temperature over a short period of time, a command to lower the cabin air conditioning temperature is generated; otherwise, a command to increase the cabin air conditioning temperature is generated. In application, the generated command to increase or decrease the cabin air conditioning temperature is sent to the air conditioner, which then performs the corresponding temperature increase or decrease, achieving intelligent management of cabin temperature adjustment.

[0076] In the above embodiment, before step S102, the method further includes at least one of the following:

[0077] Determine the standard temperature based on the pre-configured standard file;

[0078] Obtain temperature configuration parameters based on the preset interface and determine the standard temperature.

[0079] This application provides two methods for obtaining standard temperatures: one based on standard documents (such as national standards), achieving cabin temperature control in accordance with national standards; the other for adjusting the temperature based on customer requirements, for example, controlling the cabin temperature based on the temperature required for fresh produce. These two temperature control methods enable flexible cabin temperature control based on different application scenarios.

[0080] The solution process of the method provided in this application is described below in conjunction with the following steps S10-S50.

[0081] S10: Based on the desired cabin environment requirements (e.g., GJB1193-91 requires a transport aircraft temperature of 27 degrees Celsius under steady-state conditions on the ground), the cabin's structural physics and related physical properties are obtained. When applied, the tensor equations for transient aircraft operating conditions with internal heat sources (e.g., ambient temperature and pressure at altitude, aircraft galley heating, etc.) are corrected and updated based on other relevant sensors.

[0082] S20: Establish the current working state and obtain initial or boundary conditions based on the relevant working state.

[0083] S30: Establish the heat transfer equation as follows: Where ρ represents the density of the cabin structure or air, c ρ represents the specific heat capacity of the cabin structure or the air, t is the inspection time of the cabin operating environment, λ is the thermal conductivity of the cabin structure or the air, x i is the cabin space coordinate, T is the temperature corresponding to the local time point, It is the internal heat source characteristic in the cabin that represents the heat dissipation of people or electronic equipment.

[0084] S40: Solving the heat transfer equation, specifically including: S401 to S405.

[0085] S401: First, a conventional difference method is used to solve the result of each cabin space point at the time.

[0086] S402: Selecting a region (or time period) that requires a more accurate solution, which is usually a region (or time period) with more fluctuations.

[0087] S403: For multi-dimensional space-time, first determine the time point to solve the change space and obtain the result, perform iterations in one-dimensional space, and take three-dimensional space as an example to transform the three directions in turn to establish the spatial domain difference equation. The equation is as follows:

[0088] The spatial domain equation structure includes:

[0089]

[0090] In the above formula, i, j and k represent any dimension of the three-dimensional space, x i0 Indicates the starting point of any dimension in three-dimensional space, T is the temperature corresponding to the local time point. The above spatial domain equation structure adopts The equation is solved by conventional differential equation methods such as Euler in space domain, and then the result obtained by Euler method is iteratively processed by proxy equation, and the spatial domain equation structure is iteratively solved by proxy equation until convergence.

[0091] S404: After the solution is completed, the next time step is iterated until the time of interest (ie, all time steps) is calculated.

[0092] S405: When it is necessary to continue optimizing the time domain, a time domain difference equation can be constructed. The equation is as follows:

[0093] The time domain equation structure includes:

[0094]

[0095] In the above formula, i, j and k represent any dimension of the three-dimensional space, x i0 Represents the starting point of any dimension in three-dimensional space, and T is the temperature corresponding to the local time point. Solve the Euler method in the time domain: A proxy equation is applied to the previously calculated result, and the time-domain equation structure is iteratively solved using the proxy equation until convergence. When applied, the proxy equation can be a polynomial fit, interpolation, neural network, or other algorithm. The Euler method solution is iteratively fitted to the proxy equation to approximate the true value, thereby reducing the requirement for discrete point density during temperature prediction for the target area. Since the calculated result approximates the true value through continuous iteration of the Euler method, the problem of low accuracy caused by accumulated errors during the calculation process is resolved.

[0096] S50: Compare the cabin temperature calculated in S40 with a preset standard temperature, and control the cabin temperature based on the comparison result. For example, if the cabin temperature is lower than the standard temperature, the cabin air conditioning is controlled to increase the temperature; if the cabin temperature is higher than the standard temperature, the cabin air conditioning is controlled to decrease the temperature.

[0097] Among them, the use of The process of solving the differential equation includes steps 1) to 5).

[0098] Step 1): Based on the initial value y0, use the Euler method to solve the first N values of the discrete points;

[0099] Step 2): Fit the equation for the first N values. In the embodiments of the present application, methods such as m-degree polynomials (m < N), Lagrange interpolation, Pade method, neural networks, etc. are used to fit the above N value results;

[0100] Step 3): Substitute the fitting result into the right side, calculate the definite integral and add y0.

[0101] Step 4): Repeatedly execute Step 2) and Step 3) for iteration until the iteration reaches the specified number of times or the result remains unchanged, and obtain the fitting result y*.

[0102] Step 5): Apply y* and the Euler method (the initial value of the Euler method is the fitting prediction result of y*) to the subsequent points, and compare the two. When the difference between y* and the result of the Euler method exceeds the specified range, use the last time of the target attention period to determine the next target attention period.

[0103] Step 6): Repeat Steps 2 - 5 to complete the specified domain.

[0104] The following describes the present application in combination with the AG600 aircraft. Assume that the cabin heat exchange of the AG600 aircraft is in a stable state before startup. Under the condition of extremely hot weather and ground parking, the outside cabin environmental temperature is 312.4K, the outer surface temperature of the skin is 338K, and the outside cabin air velocity is 0.8m / s; the regulated air temperature in the cabin is constant at 298K, and the convective heat transfer surface heat transfer coefficient in the cabin is 14.26W / (m2·K); the initial temperature of the bottom cabin is 305K, and the convective heat transfer surface heat transfer coefficient in the cabin is 11.34W / (m2·K). As Figure 2 The floor of the model is 2438mm wide, and its detailed structure diagram is as Figure 3 , ignoring the influence of the floor beam according to the geometric structure, it becomes a two-dimensional layered structure, namely the cabin air layer, felt layer, floor layer, air interlayer, insulation layer, bottom cabin ceiling layer, and their material properties are as follows:

[0105] name Size m Thermal conductivity W / mK <![CDATA[Specific heat capacity J / (m 3 ·K)]]> floor beams 0.002×0.045 42.8 3.6613×106 Skin 0.0018 120.8 <![CDATA[2.512×10 6 ]]> Insulation layer (under floor) 0.025 0.038 <![CDATA[2.88×10 4 ]]> Bottom cabin ceiling 0.002 15.4 <![CDATA[3.726×10 6 ]]> Floor felt 0.006 0.043 <![CDATA[2.56×10 4 ]]> floor 0.003 42.8 <![CDATA[3.6613×10 6 ]]>

[0106] First step: According to the cabin standard requirements related to civil aircraft, obtain the cabin cross-sectional structure of the AG600 ( Figure 2 ), simplify and assume it as a two-dimensional structure, and list the physical property parameters in the above table. For the Figure 2 floor, form a Figure 3 model according to its characteristics.

[0107] Step 2: Obtained the ground state: "In the extremely hot weather ground shutdown state, the cabin ambient temperature is 312.4K, the skin outer surface temperature is 338K, and the cabin air velocity is 0.8m / s; the cabin conditioned air temperature is constant at 298K, and the cabin convection heat transfer surface heat transfer coefficient is 14.26W / (m2·K); the bottom cabin initial temperature is 305K, and the cabin convection heat transfer surface heat transfer coefficient is 11.34W / (m2·K)"

[0108] Step 3: According to the method from step 1 to step 2, Figure 2 The cockpit, luggage rack, bottom cabin, and cockpit models are also built with related models;

[0109] Step 4: For the cockpit, luggage rack, bottom cabin, cockpit model and floor model, the boundary conditions of each connected part are established.

[0110] Step 5: Since the aircraft is in a steady-state state with no internal heat source, the heat transfer equation is:

[0111]

[0112] Therefore, for Figure 2 and Figure 3 Two-dimensional steady-state case of the structure:

[0113]

[0114] Step 6: Solve the cockpit, luggage rack, bottom cabin, cockpit and floor models separately to obtain the following equations, which are then solved:

[0115] x represents the starting point of any dimension in two-dimensional space, x0 represents the starting point of any dimension in three-dimensional space, and T is the temperature corresponding to the local time point.

[0116] Step 7: Update the results of the interconnected parts based on the solution results of each part of the cockpit, luggage rack, bottom cabin, cockpit and floor model.

[0117] Step 8: Repeat steps 5 and 6 to reach a convergent judgment result and obtain the cabin temperature result.

[0118] Step 9: Based on the results of step 7, compare the standard GJB1193-91, which requires a transport aircraft temperature of 27 degrees Celsius under steady-state conditions on the ground. If the temperature deviates accordingly, adjust the air conditioning to increase or decrease the temperature. Repeat steps 5 to 9 until the relevant standard requirements are met.

[0119] The following describes the results of Table 1 obtained by solving the temperature of the closed cabin using the following differential equation. The differential equation is as follows: Where y is 100 degrees Celsius, x is day, and the temperature change during the day is expected. The following table lists the temperatures at the corresponding time points with a step size of 0.1 from 0 to 1, where the first line is the true value result of the analytical solution. Step 1: Use the Euler method to solve the above differential equation with a step size of 0.1 day, and obtain 11 points between 0 and 1, as shown in the second row of Table 1; Step 2: Use the cubic equation to fit the results of the second row, substitute it into the above differential equation, and use y(0) as the initial value of the definite integral to obtain the results of the third row; Step 3: Use the cubic equation to fit the results of the third row, substitute it into the above differential equation, and use y(0) as the initial value of the definite integral to obtain the results of the fourth row; Step 4: Repeat steps 3 and 4, and repeat until the 31st line, to obtain a total of 30 rows of prediction results including the Euler results, the first row is the true value result of the measurement comparison; Step 5: Take the last point of the last fitting in the fifth step, the last point of the thirty-first row (i.e. the last row) of Table 1, y(1) = 0.551715499 as the initial result, and predict the subsequent interval results; Step 6: Use the last fitting formula in the fifth step to predict the subsequent specified interval results, and compare its calculated results with the results of the subsequent fitting using the Euler method. When its fitting results have a large deviation from the Euler method, such as 10%, return to step 3; Step 7: Repeat the above six and seven steps until the required result interval is completely solved.

[0120] Table 1

[0121]

[0122]

[0123] The table above shows that the first fitting iteration after the Euler equation yields several times higher accuracy. After the second fitting iteration, the first two digits of all points agree, allowing for higher precision than the Euler method. Furthermore, within the effective fitting region, there is no accumulation of error as points move further from the initial zero point. The Euler method is used to determine the region close to the true value, while the fitting iteration method is used to approximate the true value. The two methods are alternately coupled to achieve a close approximation to the true value without significant error accumulation.

[0124] Another embodiment of the present application provides an aircraft cabin thermal environment control device, such as Figure 4 As shown, the device 40 includes: an aircraft cabin temperature distribution determination module 401 and an aircraft cabin temperature control module 402 .

[0125] Aircraft cabin temperature determination module 401 is configured to, upon detecting that the aircraft cabin environment control system has been activated, determine the temperature distribution parameters of the first predetermined number of discrete nodes in the aircraft cabin during a target time period. The temperature distribution parameters of each discrete node are obtained by iteratively fitting a preset heat transfer equation using a differential solution of a preset differential equation and its initial values using the Euler method.

[0126] The aircraft cabin temperature control module 402 is configured to control the temperature of the aircraft cabin according to the temperature distribution parameters of the first predetermined number of discrete nodes, so that the temperature of the aircraft cabin complies with a preset standard temperature distribution.

[0127] In the embodiment of the present application, the temperature distribution of a predetermined number of discrete points in the aircraft cabin heat transfer equation is solved using the Euler method based on differential equations and initial values. The cabin temperature is then obtained through fitting, and then compared with a standard temperature to achieve the purpose of cabin temperature control. This method of obtaining a result near the true value using the Euler method and simultaneously applying a fitting iterative method to approximate the true value not only shortens the solution iteration time and reduces the node density requirement, but also solves the problem of error accumulation caused by increasing distance from the initial point after errors occur within the effective fitting area.

[0128] Furthermore, when the aircraft is in a transient operating state with an internal heat source, the heat transfer tensor equation is:

[0129] Where ρ represents the density of the cabin structure or air, c ρ represents the specific heat capacity of the cabin structure or the air, t is the inspection time of the cabin operating environment, λ is the thermal conductivity of the cabin structure or the air, x i is the cabin space coordinate, T is the temperature corresponding to the local time point, is the internal heat source characteristic in the cabin that represents the heat dissipation of people or electronic equipment. When the aircraft is in a steady state with no internal heat source, the heat transfer equation is:

[0130] Furthermore, the aircraft cabin temperature determination module further includes:

[0131] The heat transfer equation determination submodule is used to determine the heat transfer equation corresponding to the predetermined model of aircraft based on the heat transfer equations corresponding to multiple aircraft.

[0132] Furthermore, the aircraft cabin temperature determination module includes:

[0133] Discretely solve the spatial domain equation structure and the time domain equation structure respectively, and the results of the cross-space domain equation structure and the time domain equation structure are used as the initial solution values of each other:

[0134] Based on the spatial domain equation structure and the cockpit, the initial results are given, and the spatial domain equation structure is discretized and solved using the Euler method. The solution of the Euler method is iteratively processed using a preset proxy equation. The spatial domain equation structure is iteratively solved using the proxy equation until convergence, and the temperature parameters of a predetermined number of spatial domain discrete points at the current time point are obtained;

[0135] a) using the time domain equation structure and the spatial domain equation result as its initial value, discretely solving the time domain equation structure for the temperature parameters of a predetermined number of spatial domain discrete points for a number of subsequent time steps, and obtaining the temperature distribution of the predetermined number of spatial domain discrete points at each time discrete point;

[0136] b) discretizing and solving the spatial domain equation structure using the Euler method based on the spatial domain equation structure and the time domain equation results as initial results, performing proxy equation iterative processing on the solution results of the Euler method, and iteratively solving the spatial domain equation structure using the proxy equation until convergence, thereby obtaining temperature parameters of a predetermined number of spatial domain discrete points at the current time point;

[0137] Repeat steps a) and b) until the temperature within the specified range is obtained.

[0138] The spatial domain equation structure includes:

[0139]

[0140] The time domain equation structure includes:

[0141]

[0142] In the above formula, i, j and k represent any dimension of the three-dimensional space, x i0 It represents the starting point of any dimension in three-dimensional space, and T is the temperature corresponding to the local time point.

[0143] Furthermore, the aircraft cabin temperature control module includes:

[0144] The temperature parameter comparison processing module is used to compare the temperature distribution parameters of the first predetermined number of discrete nodes with the standard temperature distribution, and adjust the air conditioning temperature of the aircraft cabin according to the comparison result.

[0145] Furthermore, the aircraft cabin temperature control module further includes:

[0146] A first determining submodule is configured to determine a standard temperature based on a preconfigured standard file;

[0147] The second determination submodule is used to obtain temperature configuration parameters based on a preset interface and determine the standard temperature.

[0148] Furthermore, the aircraft cabin temperature determination module further includes:

[0149] The update calculation submodule is used to update the initial value with the fitting temperature of the last time step of the target time period, so as to perform a differential solution to the preset heat transfer equation based on the differential equation and the updated initial value and using the Euler method.

[0150] The device of this embodiment can execute the method provided in the embodiment of this application. The implementation principle is similar and will not be repeated here.

[0151] Another embodiment of the present application provides an electronic device, comprising a processor and a memory, wherein the memory stores computer-readable instructions, and the processor is configured to execute the computer-readable instructions, wherein the computer-readable instructions are executed when executed to implement the above method.

[0152] Specifically, a processor may be a CPU, a general-purpose processor, a DSP, an ASIC, an FPGA, or other programmable logic device, a transistor logic device, a hardware component, or any combination thereof. It may implement or execute the various exemplary logic blocks, modules, and circuits described in conjunction with the disclosure of this application. A processor may also be a combination that implements computing functions, such as a combination of one or more microprocessors, a combination of a DSP and a microprocessor, and the like.

[0153] Specifically, the processor is connected to the memory via a bus. The bus may include a path for transmitting information. The bus may be a PCI bus or an EISA bus. The bus may be divided into an address bus, a data bus, a control bus, etc.

[0154] The memory may be a ROM or other type of static storage device that can store static information and instructions, a RAM or other type of dynamic storage device that can store information and instructions, or an EEPROM, CD-ROM or other optical disk storage, optical disc storage (including compact disc, laser disc, optical disc, digital versatile disc, Blu-ray disc, etc.), magnetic disk storage medium or other magnetic storage device, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and can be accessed by a computer, but is not limited to these.

[0155] Optionally, the memory is used to store the code of the computer program that executes the solution of the present application, and the execution is controlled by the processor. The processor is used to execute the application program code stored in the memory to implement the actions of the device provided by the above embodiment.

[0156] Another embodiment of the present application provides a computer-readable storage medium storing computer-executable instructions, which are used to implement the above method when executed.

[0157] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate, i.e., they may be located in one place or distributed across multiple network units. Some or all of the modules may be selected based on actual needs to achieve the objectives of this embodiment.

[0158] Those skilled in the art will appreciate that all or some of the steps and systems in the method disclosed above can be implemented as software, firmware, hardware, and appropriate combinations thereof. Some physical components or all physical components can be implemented as software executed by a processor, such as a central processing unit, a digital signal processor, or a microprocessor, or implemented as hardware, or implemented as an integrated circuit, such as an application-specific integrated circuit. Such software can be distributed on a computer-readable medium, and the computer-readable medium can include computer storage media (or non-transitory media) and communication media (or temporary media). As known to those skilled in the art, the term computer storage media is included in any method or technology for storing information (such as computer-readable instructions, data structures, program modules, or other data) and is volatile and non-volatile, removable, and non-removable. Computer storage media includes, but is not limited to, RAM, ROM, EEPROM, flash memory, or other memory technology, CD-ROM, digital versatile disks (DVD), or other optical disk storage, magnetic cassettes, magnetic tapes, disk storage, or other magnetic storage devices, or any other medium that can be used to store desired information and can be accessed by a computer. Furthermore, as is well known to those skilled in the art, communication media typically embodies computer-readable instructions, data structures, program modules, or other data in a modulated data signal such as a carrier wave or other transport mechanism, and may include any information delivery media.

[0159] The above is a specific description of the preferred implementation of the present application, but the present application is not limited to the above implementation mode. Technical personnel familiar with the field can also make various equivalent modifications or substitutions without violating the spirit of the present application. These equivalent modifications or substitutions are all included in the scope defined by the claims of the present application.

Claims

1. A method for controlling the thermal environment of an aircraft cabin, characterized in that: include: When it is detected that the aircraft cabin environmental control system is activated, temperature distribution parameters of a predetermined number of discrete nodes in the aircraft cabin during a target time period are determined, wherein the temperature distribution parameters of each discrete node are obtained by performing a differential solution of a preset heat transfer equation using the Euler method and an iterative fitting process based on a preset differential equation and its initial values; The step of determining temperature distribution parameters of a first predetermined number of discrete nodes in the aircraft cabin during a target time period when the aircraft cabin environment control system is detected to be activated comprises: Determining a transformation form of an equation in a transient state with an internal heat source, wherein the transformation form of the equation includes a space domain equation structure and a time domain equation structure; Discretely solve the spatial domain equation structure and the time domain equation structure respectively, and use the results of the cross-space domain equation structure and the time domain equation structure as the initial solution value of each other: An initial result is given based on the spatial domain equation structure and the cockpit, the spatial domain equation structure is discretized and solved using the Euler method, the solution of the Euler method is iteratively processed using a preset proxy equation, the spatial domain equation structure is iteratively solved using the proxy equation until convergence, and temperature parameters of a predetermined number of spatial domain discrete points at the current time point are obtained; a) using the time domain equation structure and the spatial domain equation result as initial values, discretely solving the time domain equation structure by using the temperature parameters of a predetermined number of spatial domain discrete points for subsequent time steps to obtain the temperature distribution of the predetermined number of spatial domain discrete points at each time discrete point; b) discretizing and solving the spatial domain equation structure using the Euler method based on the spatial domain equation structure and the time domain equation result as initial results, performing proxy equation iterative processing on the solution result of the Euler method, iteratively solving the spatial domain equation structure using the proxy equation until convergence, and obtaining temperature parameters of a predetermined number of spatial domain discrete points at the current time point; Repeat steps a) and b) until the temperature within the specified range is obtained. The spatial domain equation structure includes: = ； ； ； ； ； The time domain equation structure includes: ； ； ； ； ； In the above formula, i, j and k represent any dimension of the three-dimensional space. Indicates the starting point of any dimension in three-dimensional space, T is the temperature corresponding to the local time point; The temperature of the aircraft cabin is controlled according to the temperature distribution parameters of the first predetermined number of discrete nodes, so that the temperature of the aircraft cabin conforms to a preset standard temperature distribution.

2. The method according to claim 1, characterized in that When the aircraft is in a transient operating state with an internal heat source, the heat transfer equation is: ,in, Indicates the density of the cabin structure or air substance, Indicates the specific heat capacity of the cabin structure or air material, t is the inspection time of the cabin operating environment, is the thermal conductivity of the cabin structure or air material, is the cabin space coordinate, T is the temperature corresponding to the local time point, The internal heat source characteristics in the cabin that represent the heat dissipation of people or electronic equipment; When the aircraft is in a steady state with no internal heat source, the heat transfer equation is: =0。 3. The method according to claim 1, characterized in that Methods for determining the heat transfer equation include: Based on the heat transfer equations corresponding to the various aircraft, a heat transfer equation corresponding to a predetermined aircraft model is determined.

4. The method according to claim 1, wherein The controlling the temperature of the aircraft cabin according to the temperature distribution parameters of the first predetermined number of discrete nodes so that the temperature of the aircraft cabin meets a preset standard temperature includes: The temperature distribution parameters of the first predetermined number of discrete nodes are compared with the standard temperature distribution, and the air-conditioning temperature of the aircraft cabin is adjusted according to the comparison result.

5. The method according to claim 1, wherein Before controlling the temperature of the aircraft cabin based on the temperature distribution parameters of the first predetermined number of discrete nodes so that the temperature of the aircraft cabin meets a preset standard temperature, the method includes at least one of the following: Determining the standard temperature based on a preconfigured standard file; The temperature configuration parameters are obtained based on a preset interface to determine the standard temperature.

6. The method according to claim 1, characterized in that The method further comprises: The initial value is updated with the fitting temperature of the last time step of the target time period, so as to perform a differential solution on the preset heat transfer equation based on the differential equation and the updated initial value and using the Euler method.

7. An aircraft cabin thermal environment control device, characterized in that: include: an aircraft cabin temperature determination module, configured to, upon detecting that the aircraft cabin environmental control system has been activated, determine the temperature distribution parameters of the first predetermined number of discrete nodes in the aircraft cabin during a target time period, wherein the temperature distribution parameters of each discrete node are obtained by iteratively fitting a preset heat transfer equation using a differential solution of a preset differential equation and its initial values using the Euler method; The aircraft cabin temperature determination module includes: Determining a transformation form of an equation in a transient state with an internal heat source, wherein the transformation form of the equation includes a space domain equation structure and a time domain equation structure; Discretely solve the spatial domain equation structure and the time domain equation structure respectively, and use the results of the cross-space domain equation structure and the time domain equation structure as the initial solution value of each other: An initial result is given based on the spatial domain equation structure and the cockpit, the spatial domain equation structure is discretized and solved using the Euler method, the solution of the Euler method is iteratively processed using a preset proxy equation, the spatial domain equation structure is iteratively solved using the proxy equation until convergence, and temperature parameters of a predetermined number of spatial domain discrete points at the current time point are obtained; a) using the time domain equation structure and the spatial domain equation result as initial values, discretely solving the time domain equation structure by using the temperature parameters of a predetermined number of spatial domain discrete points for subsequent time steps to obtain the temperature distribution of the predetermined number of spatial domain discrete points at each time discrete point; b) discretizing and solving the spatial domain equation structure using the Euler method based on the spatial domain equation structure and the time domain equation result as initial results, performing proxy equation iterative processing on the solution result of the Euler method, iteratively solving the spatial domain equation structure using the proxy equation until convergence, and obtaining temperature parameters of a predetermined number of spatial domain discrete points at the current time point; Repeat steps a) and b) until the temperature within the specified range is obtained. The spatial domain equation structure includes: = ； ； ； ； ； The time domain equation structure includes: ； ； ； ； ； In the above formula, i, j and k represent any dimension of the three-dimensional space. Indicates the starting point of any dimension in three-dimensional space, T is the temperature corresponding to the local time point; The aircraft cabin temperature control module is used to control the temperature of the aircraft cabin according to the temperature distribution parameters of a predetermined number of discrete nodes, so that the temperature of the aircraft cabin meets a preset standard temperature distribution.

8. An electronic device, characterized in that: The method comprises a processor and a memory, wherein the memory stores computer-readable instructions, and the processor is configured to execute the computer-readable instructions, wherein the computer-readable instructions execute the method according to any one of claims 1 to 6 when executed.

9. A computer-readable storage medium storing computer-executable instructions, wherein the computer-executable instructions are used to execute the method according to any one of claims 1 to 6.

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