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

Abstract

The invention relates to the technical field of aviation cockpit thermal environment control, in particular to an aviation cockpit thermal environment control method and device, electronic equipment and a medium. The method comprises the steps that when it is detected that an aircraft cockpit environment control system is started, temperature distribution parameters of a front preset number of discrete nodes of an aircraft cockpit in a target attention time period are determined, and the temperature distribution parameters of all the discrete nodes are obtained according to a preset differential equation and an initial value thereof; carrying out difference solution on a preset heat transfer equation by adopting an Euler method and then carrying out fitting iteration; and controlling the temperature of the aircraft cockpit according to the temperature distribution parameters of the predetermined number of discrete nodes so as to enable the temperature of the aircraft cockpit to accord with preset standard temperature distribution. The problem that an existing cabin temperature numerical value solving technology is large in error and accurate is solved, and therefore the purpose of improving the cabin thermal environment control precision is achieved.

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, thermal environment control of aircraft cabins has become an indispensable component of aircraft onboard systems. On the one hand, the design of thermal environment control of aircraft cabins needs to consider the reliability and tolerance of cabin operating equipment, the requirements of human survival and comfort, and on the other hand, the influence of heat exchange between the cabin structure and its associated thermal fluid structure. Existing aircraft cabin thermal environment control mainly uses differential equations based on Taylor's formula for calculation, but this method has the problem of large error accumulation and low calculation 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 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 a thermal environment in an aircraft cabin is disclosed, the method comprising:

[0005] When it is detected that the aircraft cabin environment control system is activated, the temperature distribution parameters of the first predetermined number of discrete nodes of the aircraft cabin in the target time period are determined, wherein the temperature distribution parameters of each discrete node are obtained by differentially solving the preset heat transfer equation using the Euler method and then fitting iteratively according to the preset differential equation and its initial value;

[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 meets the preset standard temperature distribution.

[0007] Further,

[0008] When the working state of the aircraft is transient 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 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, the heat transfer equation corresponding to the predetermined model of aircraft is determined.

[0013] Further, 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 in 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 value of each other:

[0016] According to the spatial domain equation structure and the cockpit, the initial result is given, the spatial domain equation structure is discretized and solved by using the Euler method, the solution of the Euler method is iteratively processed by using the preset proxy equation, and the spatial domain equation structure is iteratively solved by 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) according to the time domain equation structure and the spatial domain equation result as its initial value, the temperature parameters of a predetermined number of spatial domain discrete points for a number of subsequent time steps are discretely solved for the time domain equation structure to obtain the temperature distribution of the predetermined number of spatial domain discrete points at each time discrete point;

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

[0019] Repeat a) and b) until the temperature in 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.

[0026] Further, 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 meets a preset standard temperature, including:

[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 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, 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 according to the differential equation and the updated initial value and using the Euler method.

[0034] In a second aspect of the 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 is used to determine the temperature distribution parameters of the first predetermined number of discrete nodes of the aircraft cabin in the target time period when the aircraft cabin environment control system is detected to be activated, wherein the temperature distribution parameters of each discrete node are obtained by differentially solving the preset heat transfer equation using the Euler method and then fitting iteratively according to the preset differential equation and its initial value;

[0036] 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 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 heat transfer equation of the aircraft cabin according to the differential equation and the initial value 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 controlling the cabin temperature. This method of obtaining a result near the true value by the Euler method and using the fitting iteration method to approximate the true value can not only shorten the solution iteration time and reduce the node density requirement, but also solves the error accumulation caused by the increase of the distance from the initial point after the error occurs in the effective fitting area. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 A schematic diagram of a 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 an embodiment of the present application;

[0042] Figure 3 A model diagram of an aircraft cabin 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 solution and advantages of the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[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 may 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 the present application clearer, the implementation methods of the present 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 environment control system is activated, the temperature distribution parameters of the first predetermined number of discrete nodes of the aircraft cabin in the target focus time period are determined, wherein the temperature distribution parameters of each discrete node are obtained by differentially solving the preset heat transfer equation using the Euler method and then fitting iteratively according to the preset differential equation and its initial value.

[0049] Specifically, it can be determined that the aircraft cabin environment control system is 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 a sensor for the aircraft cabin temperature exceeds a threshold.

[0050] Specifically, the number of nodes and the number of time steps in the spatial discretization of the aircraft cockpit may be preset, so as to calculate 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 a command.

[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 meets 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] The embodiment of the present application solves the temperature distribution of a predetermined number of discrete points of the heat transfer equation of the aircraft cabin by using the Euler method based on differential equations and initial values, so that the cabin temperature can be obtained through fitting processing, and then compared with the standard temperature to achieve the purpose of controlling the cabin temperature. This method of obtaining a result near the true value by the Euler method and using a fitting iteration method to approximate the true value can not only shorten the solution iteration time and reduce the node density requirement, but also solves the error accumulation caused by the increase of the distance from the initial point after the error occurs in the effective fitting area.

[0055] In some embodiments, when the working state of the aircraft is transient 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 without an internal heat source, the heat transfer equation is:

[0057] The working state includes steady state and transient state. Among them, the steady state is used to characterize the long-term cruising state of the aircraft, that is, the stage where the flight altitude and speed remain basically unchanged; the transient state characterizes the stage where the aircraft's flight speed and altitude change rate is large during takeoff and landing. When applied, the working state of the aircraft can be determined by detecting the changes in the altitude and speed of the aircraft. When applied, different differential equations corresponding to different working states can be pre-stored locally or converted in real time.

[0058] When applied, some physical characteristics of the tensor equation with transient internal heat sources in the aircraft's working state (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, the heat transfer equation corresponding to the predetermined model of aircraft 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 plays a role in 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 value of each other:

[0064] According to the spatial domain equation structure and the cockpit, the initial result is given, the spatial domain equation structure is discretized and solved by using the Euler method, the solution of the Euler method is iteratively processed by using the preset proxy equation, and the spatial domain equation structure is iteratively solved by 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) according to the time domain equation structure and the spatial domain equation result as its initial value, the temperature parameters of a predetermined number of spatial domain discrete points for a number of subsequent time steps are discretely solved for the time domain equation structure to obtain the temperature distribution of the predetermined number of spatial domain discrete points at each time discrete point;

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

[0067] Repeat a) and b) until the temperature in 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.

[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 of any spatial point at each short time is greater than the corresponding standard temperature, an instruction to reduce the air conditioning temperature of the aircraft cabin is generated; otherwise, an instruction to increase the air conditioning temperature of the aircraft cabin is generated. When applied, the generated instruction to increase or decrease the air conditioning temperature of the aircraft cabin is sent to the air conditioner, and the air conditioner performs the corresponding heating or cooling processing, thereby realizing intelligent management of aircraft 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 temperature. One is to control the cabin temperature according to the national standard based on the standard document (such as the national standard document). The other is to adjust the temperature according to the customer's requirements. For example, the cabin temperature is controlled according to the temperature required by fresh products. Through the setting of these two temperature control methods, the purpose of flexibly controlling the cabin temperature according to different application scenarios is achieved.

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

[0081] S10: Obtain the structural physics and related physical parameters of the cabin according to the required cabin environment requirements (for example, GJB1193-91 requires that the transport aircraft requirement is 27 degrees Celsius under steady-state conditions on the ground). When applied, some physical characteristics of the tensor equation with transient internal heat sources in the aircraft's working state (such as ambient temperature, pressure, aircraft kitchen heating, etc. corresponding to the flight altitude) are corrected and updated according to other related 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 establish a time point to solve the change space and obtain the result, perform iterations in one-dimensional space respectively, and take three-dimensional space as an example to transform 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 represents the starting point of any dimension in three-dimensional space, T is the temperature corresponding to the local time point, and the above spatial domain equation structure is adopted The type of equation is solved by conventional difference equation methods such as Euler in space domain, and then the result obtained by Euler method is iteratively processed by proxy equation, and the structure of the spatial domain equation 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 may be constructed, and 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 the three-dimensional space, and T is the temperature at the local time. The type equation is used to solve the calculation in the time domain: the previously obtained result is processed by the proxy equation, and the proxy equation is used to iteratively solve the time domain equation structure until convergence. When applied, the proxy equation can be a polynomial fitting, interpolation, neural network and other algorithms. The solution result of the Euler method is fitted and iterated through the proxy equation to obtain the approximate true value, thereby reducing the requirements for the density of discrete points in the temperature prediction process of the target area. Since the calculation result is close to the true value through continuous iteration of the Euler method, the problem of low accuracy of the calculation result caused by the accumulation of errors in the calculation process is solved.

[0096] S50: Compare the cabin temperature obtained in S40 with a preset standard temperature, and control the aircraft cabin temperature according to the comparison result. For example, if the cabin temperature is lower than the standard temperature, control the aircraft cabin air conditioner to increase the temperature; if the cabin temperature is higher than the standard temperature, control the aircraft cabin air conditioner to decrease the temperature.

[0097] Among them, using 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-th 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, that is, use the last time of the target attention time period for the next target attention time period.

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

[0104] The following is an illustration of the present application in conjunction 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 ground shutdown in extremely hot weather, 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 constantly 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, the felt layer, the floor layer, the air interlayer, the insulation layer, and the bottom cabin ceiling layer. Its 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 Skinning 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 cross-sectional structure of the cabin of the AG600 ( Figure 2 ), simplify and assume it as a two-dimensional structure, and list the physical property parameters in the above table. Among them, for Figure 2 the floor, form Figure 3 the model according to the characteristics.

[0107] Step 2: Obtained the ground state: "In the extremely hot weather ground shutdown state, the ambient temperature outside the cabin is 312.4K, the outer surface temperature of the skin is 338K, and the air velocity outside the cabin is 0.8m / s; the cabin conditioning air temperature is constant at 298K, and the heat transfer coefficient of the convective heat transfer surface in the cabin is 14.26W / (m2·K); the initial temperature of the bottom cabin is 305K, and the heat transfer coefficient of the convective heat transfer surface in the cabin 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 interact with each other.

[0110] Step 5: Since the working state of the aircraft is a steady state without an 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 respectively 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 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 result of step 7, compare the standard GJB1193-91 that requires the transport aircraft to be 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 is an explanation of 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 in a 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, and 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 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 to obtain the results of the fourth row; Step 4: Repeat steps 3 and 4, and repeat until the thirty-first row, to obtain a total of thirty 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 specified 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] From the table above, we can see that the first fitting iteration result after the Euler equation can improve the accuracy several times. After the second fitting iteration, the first two digits of all points are consistent. The accuracy of the result can meet the requirements of more sparse points compared with the Euler method. At the same time, there is no error accumulation in the effective fitting area as the point is farther away from the initial 0 point precision point. The Euler method is used to determine the area close to the true value, and the fitting iteration method is used to approximate the true value. The two are used alternately and coupled in intervals to achieve the approximation of the true value without serious 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] The aircraft cabin temperature determination module 401 is used to determine the temperature distribution parameters of the first predetermined number of discrete nodes of the aircraft cabin in the target time period when it is detected that the aircraft cabin environment control system is activated, wherein the temperature distribution parameters of each discrete node are obtained by differentially solving the preset heat transfer equation using the Euler method and then fitting iteratively according to the preset differential equation and its initial value;

[0126] The aircraft cabin temperature control module 402 is used 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 meets the preset standard temperature distribution.

[0127] The embodiment of the present application solves the temperature distribution of a predetermined number of discrete points of the heat transfer equation of the aircraft cabin by using the Euler method based on differential equations and initial values, so that the cabin temperature can be obtained through fitting processing, and then compared with the standard temperature to achieve the purpose of controlling the cabin temperature. This method of obtaining a result near the true value by the Euler method and using a fitting iteration method to approximate the true value can not only shorten the solution iteration time and reduce the node density requirement, but also solves the error accumulation caused by the increase of the distance from the initial point after the error occurs in the effective fitting area.

[0128] Furthermore, when the working state of the aircraft is transient with 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 without an 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 the various 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 value of each other:

[0134] According to the spatial domain equation structure and the cockpit, the initial result is given, the spatial domain equation structure is discretized and solved by the Euler method, the solution of the Euler method is iteratively processed by the preset proxy equation, and the spatial domain equation structure is iteratively solved by 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) according to the time domain equation structure and the spatial domain equation result as its initial value, the temperature parameters of a predetermined number of spatial domain discrete points for a number of subsequent time steps are discretely solved for the time domain equation structure to obtain the temperature distribution of the predetermined number of spatial domain discrete points at each time discrete point;

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

[0137] Repeat 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.

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

[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 comprises:

[0146] A first determination submodule is used 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 a 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 differential solution on the preset heat transfer equation according to the differential equation and the updated initial value and adopt the Euler method.

[0150] The device of this embodiment can execute the method provided in the embodiment of the present application, and its 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 used to execute the computer-readable instructions, wherein the computer-readable instructions are executed when executed to implement the above method.

[0152] Specifically, the 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 various exemplary logic blocks, modules and circuits described in conjunction with the disclosure of this application. The 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, etc.

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

[0154] The memory can 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 disk storage (including compressed optical disk, laser disk, optical disk, digital versatile disk, Blu-ray disk, etc.), magnetic disk storage medium or other magnetic storage device, or any other medium that can be used to carry or store the desired program code in the form of instructions or data structures and can be accessed by a computer, but is not limited to this.

[0155] Optionally, the memory is used to store the code of the computer program for executing 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 in the above embodiment.

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

[0157] The device embodiments described above are only illustrative, and the units described as separate components may or may not be physically separated, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0158] It will be appreciated by those skilled in the art that all or some of the steps and systems in the disclosed method above may be implemented as software, firmware, hardware and appropriate combinations thereof. Some physical components or all physical components may be implemented as software executed by a processor, such as a central processing unit, a digital signal processor or a microprocessor, or may be implemented as hardware, or may be implemented as an integrated circuit, such as an application specific integrated circuit. Such software may be distributed on a computer-readable medium, which may include a computer storage medium (or a non-transitory medium) and a communication medium (or a temporary medium). As known to those skilled in the art, the term computer storage medium includes volatile and non-volatile, removable and non-removable media implemented in any method or technology for storing information (such as computer-readable instructions, data structures, program modules or other data). Computer storage media include, but are not limited to, RAM, ROM, EEPROM, flash memory or other memory technologies, 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 may be used to store desired information and may be accessed by a computer. Furthermore, it is well known to those skilled in the art that 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-mentioned implementation mode. Technical personnel familiar with the field can also make various equivalent deformations or substitutions without violating the spirit of the present application. These equivalent deformations 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 environment control system is activated, the temperature distribution parameters of the first predetermined number of discrete nodes of the aircraft cabin in the target time period are determined, wherein the temperature distribution parameters of each discrete node are obtained by differentially solving the preset heat transfer equation using the Euler method and then fitting iteratively according to the preset differential equation and its initial value; 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 meets a preset standard temperature distribution.

2. The method according to claim 1, characterized in that When the working state of the aircraft is transient with internal heat source, the heat transfer tensor equation is: 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; When the working state of the aircraft is a steady state without an internal heat source, the heat transfer equation is:

3. The method according to claim 1, characterized in that: The heat transfer equation is determined by: Based on the heat transfer equations corresponding to the various aircraft, the heat transfer equation corresponding to the predetermined model of aircraft is determined.

4. The method according to claim 1, characterized in that When the aircraft cabin environment control system is detected to be activated, determining the temperature distribution parameters of the first predetermined number of discrete nodes of the aircraft cabin in the target time period includes: Determine the transformation form of the equation in the transient state with 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 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: According to the spatial domain equation structure and the cockpit, an initial result is given, the spatial domain equation structure is discretized and solved by using the Euler method, the solution result of the Euler method is iteratively processed by using a preset proxy equation, the spatial domain equation structure is iteratively solved by 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; a) solving the time domain equation structure based on the time domain equation structure and the spatial domain equation result as its initial value, discretely solving the time domain equation structure by using 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; b) using the spatial domain equation structure and the time domain equation result as the initial result, discretizing and solving the spatial domain equation structure using the Euler method, performing proxy equation iteration processing on the solution result of the Euler method, iteratively solving the spatial domain equation structure using the proxy equation until convergence, and obtaining the temperature parameters of a predetermined number of spatial domain discrete points at the current time point; Repeat 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, 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.

5. The method according to claim 1, characterized in that 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 according to 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.

6. The method according to claim 1, characterized in that Before 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, the method includes at least one of the following: Determining the standard temperature based on a preconfigured standard file; The temperature configuration parameters are acquired based on a preset interface to determine the standard temperature.

7. 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 according to the differential equation and the updated initial value and using the Euler method.

8. An aircraft cabin thermal environment control device, characterized in that: include: An aircraft cabin temperature determination module is used to determine the temperature distribution parameters of the first predetermined number of discrete nodes of the aircraft cabin in the target time period when the aircraft cabin environment control system is detected to be activated, wherein the temperature distribution parameters of each discrete node are obtained by differentially solving the preset heat transfer equation using the Euler method and then fitting iteratively according to the preset differential equation and its initial value; 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.

9. 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 used to execute the computer-readable instructions, wherein the computer-readable instructions execute the method according to any one of claims 1 to 7 when executed.

10. 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 7.

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