Testing method for airplane de-icing and anti-icing system

Abstract

The invention relates to a test method for an airplane de-icing and anti-icing system. The method comprises the following steps: selecting a test model from a test model library; determining a corresponding calculation mode from a calculation mode library according to the selected test model; setting initial parameters of the test model, and inputting the initial parameters into a calculation mode; testing based on the calculation model, and determining a test result; and determining an output format according to the test result, and outputting the test result of the target format. Compared with the prior art, the method has the advantages of improving the test efficiency and the like.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft de - icing and anti - icing, and particularly to a test method for an aircraft de - icing and anti - icing system. Background Art

[0002] In the existing aviation field, aircraft icing has always been an important factor affecting aircraft safety. Existing de - icing and anti - icing design methods rely more on wind tunnel experiments and actual flight test conditions, which are relatively costly in terms of both money and time. Therefore, in order to solve this problem, developing an efficient and accurate test software is of great significance for optimizing the design of aircraft de - icing and anti - icing systems.

[0003] In the prior art, due to the complexity of the required data, the operation difficulty of the aircraft de - icing and anti - icing test system is high, the time required for test design is long, and the efficiency of test analysis is also low. Summary of the Invention

[0004] The purpose of the present invention is to provide a test method for an aircraft de - icing and anti - icing system to reduce the operation difficulty of the aircraft de - icing and anti - icing test system and reduce the time required for test design.

[0005] The purpose of the present invention can be achieved by the following technical solutions:

[0006] A test method for an aircraft de - icing and anti - icing system, the method comprising the following steps:

[0007] Select a test model from a test model library;

[0008] Obtain the flight state of the aircraft, and determine the corresponding calculation mode from a calculation mode library according to the flight state;

[0009] The determination of the corresponding calculation mode is specifically as follows:

[0010] When the flight state is in an equilibrium state, select a steady - state calculation mode, and combine a transient calculation mode to obtain the fluid density and the fluid density change equation; based on the fluid density and the fluid density change equation, select a multiphase flow extension equation, an aerodynamic field solution equation, a calculation equation for droplet trajectories, and an icing process simulation equation;

[0011] Set the initial parameters of the test model, and input the initial parameters into the calculation mode;

[0012] Perform a test based on the calculation model to determine the test result;

[0013] Determine the output format according to the test result, and output the test result in the target format.

[0014] Furthermore, the specific steps of performing a test based on the calculation model to determine the test result are:

[0015] The multiphase flow expansion equation analyzes the phase change of air with liquid water and ice based on the fluid density and the fluid density change equation. The air dynamic field solution equation analyzes the airflow distribution around the aircraft based on the fluid density and the fluid density change equation. Based on the airflow distribution, the calculation equation of the droplet trajectory is used to obtain the predicted movement path of the cold water droplets in the airflow. Based on the movement path, the droplets that will hit the wing surface are determined. For the droplets that will hit the wing surface, the icing process simulation equation is used to simulate the test results of icing.

[0016] Further, the specific steps for determining the droplets that will hit the wing surface based on the movement path are as follows:

[0017] Based on the airflow distribution, the droplet velocity is determined, the droplet motion equation is constructed to predict the movement path of the cold water droplets in the airflow, the proportion of droplets captured by the wing surface is determined based on the capture coefficient, and the droplets that will hit the wing surface are obtained by combining the proportion captured by the wing surface with the movement path.

[0018] Further, the proportion of droplets captured by the wing surface is the ratio between the mass of the droplets hitting the surface and the mass of the oncoming water droplets per unit area.

[0019] Further, the movement path is predicted based on the droplet motion equation in the calculation equation of the droplet trajectory.

[0020] Further, the droplet motion equation is:

[0021]

[0022] where m p represents the droplet mass, v p represents the droplet velocity, F D is the drag force, F G is the gravitational force, F B is the buoyancy force.

[0023] Further, the drag force is:

[0024]

[0025] where C D is the drag coefficient, A p is the droplet projected area, ρ represents the fluid density, and u represents the velocity vector.

[0026] Further, the test results of the simulated icing satisfy the mass exchange relationship between ice, water, and steam and the energy exchange relationship between ice, water, and air.

[0027] Further, the mass exchange relationship between ice, water, and steam is:

[0028] q 冷却 +q 凝结 +q 热传递 =q 相变 +q 融化

[0029] where q 冷却 is the cooling of the air to the droplet, q 凝结 is the heat released by the condensation of the droplet on the surface, q 热传递 is the heat conduction between the surface and the environment, q 相变 is the latent heat released by the water edge being ice, q 融化 is the heat consumed by the anti-icing system heating.

[0030] Furthermore, the energy exchange relationship among ice, water, and air is:

[0031]

[0032] where S m represents the source term generated by the phase change.

[0033] Compared with the prior art, the present invention has the following beneficial effects:

[0034] The present invention selects a test model from a test model library according to test requirements, where the test model library includes multiple preset test models; determines a corresponding calculation mode from a calculation mode library according to the selected test model, including a state calculation mode, a transient calculation mode, a multiphase flow expansion formula, an aerodynamic field solution formula, a droplet trajectory calculation formula, and an icing process simulation formula, and can call the calculation mode to test the initial parameters. The trajectory is simulated through the calculation equation of the droplet trajectory, and the frozen water droplets are determined based on the trajectory simulation and the proportion of the droplets colliding with the wing, thereby reducing the number of water droplets that need to be simulated, reducing the operation difficulty of the aircraft anti-icing and de-icing test system, and reducing the time required for test design. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 is a schematic diagram of the composition of a test system for an aircraft anti-icing and de-icing system;

[0036] Figure 2 is a schematic diagram of the composition of a test model library;

[0037] Figure 3 is a flowchart of a test method for designing an aircraft test system;

[0038] Figure 4 is a flowchart of a test method for a test system for an aircraft anti-icing and de-icing system.

[0039] In the figure, the aircraft de-icing system test 100, test requirements 200, test model library 300, parameter setting module 400, calculation mode library 600, calculation execution module 700, result output module 800, analysis module 900, aircraft anti / de-icing system test results 1000, wing anti / de-icing system test model 210, engine anti / de-icing system test model 220, air data probe anti / de-icing system test model 230, wing leading edge hot air anti-icing model 211, engine compressor bleed air thermal anti-icing model 212, wing leading edge and tail fin pneumatic belt de-icing model 213, wing electric pulse de-icing model 214, wing electric heating de-icing model 215, engine compressor bleed air heating anti-icing model 221, in-air fan ice removal model 222, pitot tube anti / de-icing model 231, pitot tube electric heating de-icing model 232, angle of attack detector anti-icing and de-icing model 233, total air temperature probe anti / de-icing model 234, cockpit windshield anti-icing and defogging model 235, and cockpit windshield electric heating de-icing model 236. Detailed implementation manners

[0040] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. This embodiment is implemented on the premise of the technical solution of the present invention, and gives detailed implementation manners and specific operation processes, but the protection scope of the present invention is not limited to the following embodiments.

[0041] The existing test systems for designing aircraft anti-icing and de-icing systems have problems such as high operation difficulty, long test design time, and low test analysis efficiency. The present invention discloses the concept of establishing a test model library, which includes multiple test models. The test model library can be established by professional numerical developers and verified, which can reduce the modeling difficulty of the aircraft and also reduce the technical requirements for aircraft designers; on this basis, the test model library, parameter setting module, result output module, and analysis module are set, and only the design-related parameters are open to designers, shielding a large number of calculation detail parameters used by the calculation execution module, which is beneficial for designers to quickly master and use.

[0042] An embodiment of the present invention provides a test system for an aircraft anti / de-icing system, including: a test model library for selecting a corresponding test model according to test requirements, where the test model library contains multiple pre-set test models; a calculation mode library for selecting a corresponding calculation mode according to the determined test model, where the calculation mode library contains multiple preset calculation modes; a parameter setting module for setting the initial parameters of the test model and inputting the set initial parameters into the determined calculation mode; a calculation execution module for performing tests according to the determined test model and the input initial parameters and outputting test results; and a result output module for determining the result output format according to the test results and outputting the test results in the target format.

[0043] Figure 1 Schematically shows a schematic diagram of the composition of a test system for designing aircraft anti-icing and de-icing according to an embodiment of the present invention.

[0044] The present invention provides a test system and a test method for an aircraft anti-icing and de-icing system, which are used to reduce the operation difficulty of the aircraft anti-icing and de-icing test system, reduce the time required for test design, and improve the efficiency of test analysis.

[0045] The test system for an aircraft anti-icing and de-icing system provided by the present invention includes a test model library 300, a parameter setting module 400, a calculation mode library 600, a calculation execution module 700, and a result output module 800.

[0046] The test model library 300 is used to select a test model 500 according to the test requirements 200 for designing an aircraft anti-icing and de-icing system, wherein the test model library 300 includes a plurality of preset test models 500.

[0047] According to an embodiment of the present invention, the test model library 300 contains all the models required to complete the test work, and all the test models 500 in the test model library 300 have completed the preparatory work such as preliminary modeling and mesh generation, and can be directly selected or called to perform test operations.

[0048] According to an embodiment of the present invention, the test model library 300 selects a specific test model 500 from the test model library 300 according to the test requirements 200. Specifically, after the test model library 300 can select and determine the test model 500 in its storage space, it imports the test model 500 into the test system for the aircraft anti-icing and de-icing system for subsequent test operations.

[0049] The calculation mode library 600 is used to determine the calculation mode corresponding to the test model 500.

[0050] According to an embodiment of the present invention, the calculation mode library 600 can call different versions of the calculation mode by determining the installation location of the calculation mode. For example, the called calculation mode can be AMESIM. According to actual requirements, the calculation mode library 600 will select a new version of AMESIM to ensure the applicability of the calculation mode.

[0051] The parameter setting module 400 is used to set the initial parameters of the test model 500 and input the initial parameters into the calculation mode determined in the calculation mode library 600. For example, for the wing leading edge hot air anti-icing model of the wing anti-icing and de-icing system, the initial parameters can be at least one of the aircraft stage, ambient pressure, aircraft flight speed, cloud range, cloud temperature, supercooled water droplet diameter, and liquid water content.

[0052] According to an embodiment of the present invention, during the test operation, the initial parameters may change, and the parameter setting module 400 can input the updated parameters into the determined calculation mode. Still taking the hot air anti-icing model of the leading edge of the wing of the wing anti-icing and de-icing system as an example, after the preset parameters are updated, the parameter setting module 400 can import the changed flight stage of the aircraft, ambient pressure, aircraft flight speed, cloud range, cloud temperature, supercooled water droplet diameter, and liquid water content into the calculation mode.

[0053] The calculation execution module 700 is configured to call the determined calculation mode in the calculation mode library to test the initial parameters imported by the parameter setting module 400 and determine the test result.

[0054] According to an embodiment of the present invention, the test system will display a corresponding operation interface to the user. The operation interface facing the user includes a plurality of operation buttons, and the above-mentioned plurality of operation buttons are connected to the calculation execution module 700. When the user operates on the operation interface, the calculation execution module 700 responds to the request from the user and calls the calculation mode determined by the calculation mode library 600 to perform a calculation operation. For example, the user's operation interface includes "calculate execution" and "calculate abort" buttons. The calculation execution module 700 responds to the request of the "calculate execution" button and calls the corresponding calculation mode to start the test; the calculation execution module 700 responds to the request of the "calculate abort" button and calls the corresponding calculation mode to abort the test.

[0055] The result output module 800 is configured to determine the output format according to the test result and output the test result 1000 of the aircraft anti-icing and de-icing system in the target format.

[0056] The present invention directly selects the test model from the test model library, avoiding the process of the operator modeling and debugging the test model based on professional knowledge, reducing the modeling difficulty of the aircraft, reducing the technical requirements for aircraft designers, and also reducing the modeling time of the aircraft model; by setting the test model library, parameter setting module, and result output module, only the design-related parameters are open to the operator, shielding a large number of calculation detail parameters used by the calculation engine, which is conducive to the operator quickly mastering and using the test system, reducing the time for the operator to familiarize with the operating system, and improving the test design efficiency; by automatically generating the test result in the target format through the result output module, the work efficiency of test result analysis can be improved. A test system for an aircraft anti-icing and de-icing system proposed by the present invention can reduce the difficulty of anti-icing and de-icing system testing, reduce the operation time, and enable aircraft designers to devote more energy to the design itself.

[0057] According to an embodiment of the present invention, such as Figure 1As shown, the test system further includes an analysis module 900. The analysis module 900 can preset a plurality of calculated values based on the initial parameters set by the parameter setting module 400, and determine a plurality of test results corresponding to the plurality of calculated values by using the calculation mode determined by the calculation mode library 600; compare and sort the plurality of test results, and output the sorted plurality of test results in a preset order. For example, taking the hot air anti-icing model of the leading edge of the wing of the wing anti-icing and anti-deicing system as an example, the initial parameter is the cloud temperature. The initial parameter, the calculation execution module 700 outputs the test result corresponding to the initial parameter. The analysis module 900 can run and compare the above-mentioned plurality of test results, and then output the sorted plurality of test results in a preset order.

[0058] According to an embodiment of the present invention, sorting according to a preset order can be determined according to the error degree between the test result and the technical standard. For example, sort the plurality of test results in ascending order of the error degree, and then output the plurality of test results.

[0059] According to an embodiment of the present invention, the analysis module 900 can directly output the sorted plurality of aircraft anti-icing and anti-deicing system design test results 1000; it can also output the aircraft anti-icing and anti-deicing system test results 1000 in a sorted target format through the result output module 800.

[0060] According to an embodiment of the present invention, the analysis module 900 can analyze at least one of the amount of aircraft icing, the size of the icing range, the shape of the ice layer, the radius of curvature of the aircraft icing part, and the icing intensity value.

[0061] According to an embodiment of the present invention, the analysis module 900 is further configured to compare the plurality of test results with a preset standard interval to determine the analysis results of the plurality of test results. The analysis results include meeting the standard requirements and not meeting the standard requirements.

[0062] According to an embodiment of the present invention, the preset standard interval can be set as a numerical interval of the standard requirements. Compare the plurality of test results with the numerical interval of the standard requirements. When the test result is within the standard numerical interval, determine that the analysis result of the test result meets the standard requirements; when the test result is outside the standard numerical interval, determine that the analysis result of the test result does not meet the standard requirements.

[0063] The test system for the aircraft anti-icing and anti-deicing system provided by the present invention automatically outputs the required test results through the analysis module, automatically calculates and compares the test results under different parameters, determines the analysis results of the test results, and can effectively reduce the analysis time of the designers and improve the work efficiency of the test result analysis.

[0064] Figure 2 Schematically shows a composition schematic diagram of a test model library according to an embodiment of the present invention.

[0065] According to an embodiment of the present invention, as Figure 2 shown, the test model library 200 includes a wing anti-icing and de-icing system test model 210, an engine anti-icing and de-icing system test model 220, and an air data probe anti-icing and de-icing system test model 230. The test model library 200 further includes a wing leading edge anti-icing model, including a wing leading edge electrothermal anti-icing model and a hot air anti-icing model for the internal duct system of the wing, for analyzing the anti-icing situation of the wing leading edge;

[0066] An engine inlet anti-icing and de-icing model, including an engine inlet lip anti-icing and de-icing model and an acoustic anti-icing model for the inner surface of the engine inlet, for analyzing the engine inlet anti-icing and de-icing model;

[0067] A propeller blade leading edge electrothermal de-icing model, for analyzing the de-icing situation of the propeller blade leading edge;

[0068] A windshield electrothermal wire anti-icing model, for analyzing the anti-icing situation of the windshield;

[0069] A sensor probe anti-icing and de-icing model, for analyzing the anti-icing and de-icing situation of the sensor probe.

[0070] As Figure 2 shown, the wing anti-icing and de-icing system test model 210 includes a wing leading edge hot air anti-icing model 211, an engine compressor bleed hot anti-icing model 212, a wing leading edge and tail fin pneumatic band de-icing model 213, a wing electric pulse de-icing model 214, and a wing electric heating de-icing model 215.

[0071] The wing leading edge hot air anti-icing model 211 is used to analyze the anti-icing situation of the wing leading edge. The engine compressor bleed hot anti-icing model 212 is used to analyze the anti-icing situation of the wing. The wing leading edge and tail fin pneumatic band de-icing model 213 is used to analyze the de-icing situation of the wing leading edge and tail fin. The wing electric pulse de-icing model 214 is used to analyze the de-icing situation of the wing part. The wing electric heating de-icing model 215 is used to analyze the de-icing situation of the wing part.

[0072] As Figure 2 shown, the engine anti-icing and de-icing system test model 220 includes an engine compressor bleed heating anti-icing model 221 and an air fan ice removal model 222.

[0073] The engine compressor bleed heating anti-icing model 221 is used to analyze the anti-icing situation of the aircraft engine. The air fan ice removal model 222 is used to analyze the in-air ice removal situation of the aircraft engine.

[0074] As Figure 2As shown, the test model 230 of the air data probe anti-icing system includes an airspeed tube anti-icing model 231, an airspeed tube electric heating anti-icing model 232, an angle-of-attack detector anti-icing model 233, an atmospheric total temperature probe anti-icing model 234, a cockpit windshield anti-icing and defogging model 235, and a cockpit windshield electric heating anti-icing model 236.

[0075] The airspeed tube anti-icing model 231 is used to analyze the anti-icing and de-icing conditions of the airspeed tube. The airspeed tube electric heating anti-icing model 232 is used to analyze the de-icing condition of the airspeed tube. The angle-of-attack detector anti-icing model 233 is used to analyze the anti-icing and de-icing conditions of the angle-of-attack detector. The atmospheric total temperature probe anti-icing model 234 is used to analyze the anti-icing and de-icing conditions of the atmospheric total temperature probe. The cockpit windshield anti-icing and defogging model 235 is used to analyze the anti-icing and defogging conditions of the cockpit windshield. The cockpit windshield electric heating anti-icing model 236 is used to analyze the de-icing condition of the cockpit windshield.

[0076] According to an embodiment of the present invention, as Figure 1 and Figure 2 shown, the parameter setting module 400 is used to transfer scenario feature calculation parameters to the test model 500 in the test model library 200, where the scenario feature calculation parameters include at least one of the following multiple feature parameters:

[0077] The scenario feature calculation parameters transferred to the wing leading-edge hot air anti-icing model 211 include at least one of the following: the stage of the aircraft, the ambient pressure, the flight speed of the aircraft, the cloud range, the cloud temperature, the diameter of supercooled water droplets, and the liquid water content.

[0078] The scenario feature calculation parameters transferred to the engine compressor bleed air thermal anti-icing model 212 include at least one of the following: the stage of the aircraft, the ambient pressure, the flight speed of the aircraft, the cloud range, the cloud temperature, the diameter of supercooled water droplets, and the liquid water content.

[0079] The scenario feature calculation parameters transferred to the wing leading-edge and tail fin pneumatic band de-icing model 213 include at least one of the following: the stage of the aircraft, the flight speed of the aircraft, the amount of ice on the aircraft, the size of the icing range, the shape of the ice layer, the radius of curvature of the body icing part, and the icing intensity.

[0080] The scenario feature calculation parameters transferred to the wing electric pulse de-icing model 214 include at least one of the following: the stage of the aircraft, the flight speed of the aircraft, the amount of ice on the aircraft, the size of the icing range, the shape of the ice layer, the radius of curvature of the body icing part, and the icing intensity.

[0081] The scene feature calculation parameters transmitted by the wing electric heating de-icing model 215 include at least one of the following: the stage of the aircraft, the flight speed of the aircraft, the ice accumulation amount of the aircraft, the size of the icing range, the shape of the ice layer, the curvature radius of the icing part of the airframe, and the icing intensity.

[0082] The scene feature calculation parameters transmitted by the engine compressor bleed air heating anti-icing model 221 include at least one of the following: the stage of the aircraft, the ambient pressure, the flight speed of the aircraft, the cloud range, the cloud temperature, the diameter of supercooled water droplets, and the liquid water content.

[0083] The scene feature calculation parameters transmitted by the air fan ice removal model 222 include at least one of the following: the stage of the aircraft, the flight altitude of the aircraft, the flight speed of the aircraft, the ice accumulation amount of the aircraft, the size of the icing range, and the shape of the ice layer.

[0084] The scene feature calculation parameters transmitted by the pitot tube anti-icing and de-icing model 231 include at least one of the following: the stage of the aircraft, the ambient pressure, the flight speed of the aircraft, the cloud range, the cloud temperature, the diameter of supercooled water droplets, and the liquid water content.

[0085] The scene feature calculation parameters transmitted by the pitot tube electric heating de-icing model 232 include at least one of the following: the stage of the aircraft, the flight speed of the aircraft, the ice accumulation amount of the aircraft, the size of the icing range, the shape of the ice layer, the curvature radius of the icing part of the airframe, and the icing intensity.

[0086] The scene feature calculation parameters transmitted by the angle of attack detector anti-icing and de-icing model 233 include at least one of the following: the stage of the aircraft, the flight altitude of the aircraft, the ambient pressure, the flight speed of the aircraft, the cloud range, the cloud temperature, the diameter of supercooled water droplets, the liquid water content, the ice accumulation amount of the aircraft, the size of the icing range, the shape of the ice layer, the curvature radius of the icing part of the airframe, and the icing intensity.

[0087] The scene feature calculation parameters transmitted by the total air temperature probe anti-icing and de-icing model 234 include at least one of the following: the stage of the aircraft, the flight altitude of the aircraft, the ambient pressure, the flight speed of the aircraft, the cloud range, the cloud temperature, the diameter of supercooled water droplets, the liquid water content, the ice accumulation amount of the aircraft, the size of the icing range, the shape of the ice layer, the curvature radius of the icing part of the airframe, and the icing intensity.

[0088] The scene feature calculation parameters transmitted by the cockpit windshield anti-icing and defogging model 235 include at least one of the following: the stage of the aircraft, the ambient pressure, the flight speed of the aircraft, the cloud range, the cloud temperature, the diameter of supercooled water droplets, and the liquid water content.

[0089] The scene feature calculation parameters transmitted by the cockpit windshield electric heating and de-icing model 236 include at least one of the following: the stage of the aircraft, the flight altitude of the aircraft, the ambient pressure, the flight speed of the aircraft, the amount of ice accretion on the aircraft, the size of the icing range, the shape of the ice layer, the radius of curvature of the airframe icing, and the icing intensity. The scene feature calculation parameters also include the scene feature calculation parameters transmitted by the electrothermal anti-icing model of the leading edge of the wing, including at least one of the following: the heater power density distribution, the geometric dimensions of the heating area, and the heat conduction characteristics of the laminated structure;

[0090] The scene feature calculation parameters transmitted by the electrothermal anti-icing model of the leading edge of the wing include at least one of the following: the temperature and pressure of the hot air, the geometric parameters of the duct, and the flow distribution characteristics;

[0091] The scene feature calculation parameters transmitted by the anti-icing model of the engine inlet lip include at least one of the following: the layout of the heat exchanger, the anti-icing air flow rate, and the characteristics of the structural material;

[0092] The scene feature calculation parameters transmitted by the acoustic wave anti-icing model of the inner surface of the engine inlet include at least one of the following: the acoustic wave frequency, the sound pressure level, and the acoustic wave action area;

[0093] The scene feature calculation parameters transmitted by the electrothermal de-icing model of the leading edge of the propeller blade include at least one of the following: the layout of the heating elements, the power control strategy, and the influence of the rotation effect;

[0094] The scene feature calculation parameters transmitted by the windshield electric heating wire anti-icing model include at least one of the following: the distribution density of the electric heating wires, the heating power control, and the glass layer structure;

[0095] The scene feature calculation parameters transmitted by the sensor probe anti-icing and de-icing model include at least one of the following: the heating power, the probe shape, and the installation position.

[0096] According to an embodiment of the present invention, as Figure 1 shown, the parameter setting module 400 is further configured to transmit general feature calculation parameters to the test model 500 in the test model library 300. The general feature calculation parameters include at least one of the following: the calculation time, the maximum number of internal iterations, the skewness, the relaxation factor, and the solution history parameters.

[0097] According to an embodiment of the present invention, the result output module 800 is configured to: determine a result output format that matches the current test result according to the test result determined by the calculation execution module 700, where the test result includes at least one of a table, a numerical value, a picture, and a curve graph; insert the test result into a preset position of the result output format to generate a test report, and finally output the test report. Specifically, after the calculation execution module 700 completes the calculation, the result output module 800 automatically sorts out the calculated test results; after determining the result output format corresponding to the current test result, inserts the sorted test results into the target position of the result output format.

[0098] According to an embodiment of the present invention, the target format of the test report is the word format, and the result output module 800 can insert the test result into a preset position of the word template to automatically generate a test report. For example, taking the hot air anti-icing model of the wing leading edge as an example, the output report of the hot air anti-icing model of the wing leading edge has two parts: a test model and calculation results. Among them, the test model part is mainly a numerical model. The numerical model introduces the models selected for the hot air anti-icing model of the wing leading edge, such as a two-dimensional air flow field calculation model, a water droplet impingement characteristic calculation model, an icing model, etc. The calculation result part includes a velocity field, a temperature field, a pressure field, an MVD field, and an LWC field. Taking one of the field quantities as an independent variable, a curve graph of the change in the maximum lift coefficient and the percentage decrease in the lift-to-drag ratio and a curve graph of the aerodynamic characteristics of related variables are generated. The result output module 900 determines that the word report to be output is the report of the hot air anti-icing model of the wing leading edge according to the test result obtained by the calculation engine module 700. At this time, the result output module 900 inserts the corresponding table, numerical value, picture, and curve graph into the preset position of the template to generate a complete word version of the test result.

[0099] The present invention can effectively reduce the analysis time of designers and improve the work efficiency of test result analysis by using the result output module to automatically output the required test results and automatically generate reports, and can also improve the readability of test results through the test results in the target format.

[0100] An embodiment of the present invention also provides a test method applied to the above test system, including: selecting a test model from a test model library according to test requirements, where the test model library includes multiple preset test models; determining a corresponding calculation mode from a calculation mode library according to the selected test model; the parameter setting module sets the initial parameters of the test model and inputs the parameters into the calculation mode; the calculation execution module calls the calculation mode to test the initial parameters to determine the test result; the result output module determines the output format according to the test result and outputs the test result in the target format.

[0101] Figure 3The flowchart of the test method for a test system of an aircraft anti-icing and de-icing system according to an embodiment of the present invention is schematically shown.

[0102] As Figure 3 shown, the test method includes operations S301 to S305.

[0103] In operation S301, a test model is selected from a test model library according to test requirements, wherein the test model library includes a plurality of pre-designed test models.

[0104] According to an embodiment of the present invention, the test model library is established according to the design requirements of the aircraft anti-icing and de-icing system, and the test models included in the test model library are all models stored in the test system by professionals after simulation and debugging, and these test models can be directly applied. For example, for the wing leading edge hot air anti-icing model, professionals carry out simulations of the icing distribution and icing degree of the wing leading edge at different temperatures. After successful modeling and debugging, the wing leading edge hot air anti-icing model is stored in the test model library. In actual application, designers do not need to carry out modeling and debugging of the test model and can directly call the corresponding test model from the test model library for the test system.

[0105] According to an embodiment of the present invention, in the case where designers carry out simulations of the icing distribution and icing degree of the wing leading edge at different temperatures, the calculation execution module needs to select the wing leading edge hot air anti-icing model.

[0106] In operation S302, the calculation mode library determines the calculation model corresponding to the test model.

[0107] According to an embodiment of the present invention, the calculation mode library determines the calculation mode that can be applied to the selected test model.

[0108] In operation S303, the parameter setting module sets the initial parameters of the test model and inputs the initial parameters into the calculation execution module.

[0109] According to an embodiment of the present invention, in the case where the test model is determined and imported into the test system, on the parameter setting interface, the parameter setting module sets the initial parameters of the test model and transmits the parameters to the calculation execution module. Still taking the wing leading edge hot air anti-icing model as an example, parameters such as cloud layer temperature, supercooled water droplet diameter, and liquid water content are set through the parameter setting module on the parameter setting interface. After the setting is completed, the parameter setting module conveys the parameters into the calculation mode. In the case where the initial parameters change during the test, the parameter setting module can input the changed initial parameters into the calculation mode so that the test model updates the test results. For example, after the cloud layer temperature is changed, the value corresponding to the cloud layer temperature in the test model will also be updated.

[0110] In operation S304, the calculation execution module responds to a request from the user, performs tests based on the input initial parameters, and outputs the test results.

[0111] According to an embodiment of the present invention, the calculation execution module can respond to a request from the user through an operation interface. For example, in response to a user request from the "Calculation Execution" button on the operation interface, it submits a test model and conducts calculations; in response to a user request from the "Calculation Abort" button on the operation interface, it aborts the ongoing calculation process.

[0112] The formulas designed in the calculation execution module include:

[0113] The calculation mode library module performs relevant calculations based on the model selected from the model library. The calculation formulas involved include:

[0114] Calculation modes: steady-state calculation mode, transient calculation mode

[0115] Steady-state calculation mode:

[0116] (1) Continuity equation

[0117]

[0118] u is the velocity vector.

[0119] (2) Momentum equation

[0120]

[0121] ρ is the fluid density, p is the pressure, μ is the dynamic viscosity, and F is the body force (such as gravitational acceleration).

[0122] (3) Energy equation

[0123]

[0124] Where c p is the specific heat capacity, T is the temperature, k is the thermal conductivity, is the heat source term.

[0125] Transient calculation mode:

[0126] (1) Continuity equation

[0127]

[0128] Where represents the change of density with time.

[0129] (2) Momentum equation

[0130]

[0131] Represents the acceleration of the fluid.

[0132] (3) Energy equation

[0133]

[0134] Represents the change of temperature density with time.

[0135] Multiphase flow expansion formula:

[0136] (1) Euler - Euler model

[0137]

[0138] Among them, α i is the volume fraction of the phase, and F ij is the same acting force.

[0139] (2) Euler - Lagrange model

[0140] Gas phase: Describes the gas flow field with the continuity equation and momentum equation

[0141] Liquid phase (discrete phase): Tracks the motion of each water droplet using the Lagrangian method:

[0142]

[0143] Among them, F D is the drag force, F G is the gravitational force, and F B is the buoyancy force.

[0144] (3) Ice phase change model

[0145] Used to describe the phase change between ice and water:

[0146]

[0147] Among them, L is the latent heat, is the phase change factor (volume fraction of ice).

[0148] 1. Solution of aerodynamic field

[0149] (1) N - S equation

[0150] The basic equation describing fluid motion:

[0151]

[0152] Among them, ρ is the fluid density, u is the velocity vector, p is the pressure, μ is the dynamic viscosity, and F is the external force (such as gravity). When performing steady - state calculations, the time - derivative term is removed Turbulence calculation:

[0153] Approximate methods for dealing with turbulent effects generally include the following models:

[0154] k-ε model:

[0155]

[0156] Among them, k represents the turbulent kinetic energy, ε represents the turbulent dissipation rate, and P k represents the turbulent generation term.

[0157] SST k-ω model:

[0158] An improved turbulent model introducing near-wall region treatment:

[0159]

[0160] Among them, ω represents the turbulent vorticity frequency, and v t represents the turbulent viscosity coefficient.

[0161] Compressibility effect:

[0162] Considering the compression characteristics of the air flow, the energy equation is combined with the state equation:

[0163] Energy equation

[0164]

[0165] Among them, e is the internal energy, h = e + p / ρ represents the enthalpy, and T is the temperature 0.

[0166] State equation (ideal gas assumption):

[0167] p = ρRT

[0168] Among them, R is the gas constant.

[0169] 2. Calculation of droplet trajectories

[0170] Lagrangian method

[0171] The equation describing the droplet motion is based on Newton's second law:

[0172]

[0173] Among them, m p represents the droplet mass, v p represents the droplet velocity, F D is the drag force, F G is the gravitational force, F B is the buoyancy force.

[0174] Drag force formula:

[0175]

[0176] C D is the drag coefficient, and A p is the projected area of the droplet.

[0177] Calculation of the capture coefficient:

[0178] The capture coefficient β represents the proportion of droplets captured by the wing surface:

[0179]

[0180] It is necessary to determine which droplets will impact the wing surface through trajectory simulation.

[0181] 3. Icing process simulation

[0182] Energy balance equation

[0183] Icing involves energy exchange among ice, water, and air, and the energy balance equation is:

[0184] q 冷却 + q 凝结 + q 热传递 = q 相变 + q 融化

[0185] Among them, q 冷却 is the cooling of the droplet by the air, q 凝结 is the heat released by the condensation of the droplet on the surface, q 热传递 is the heat conduction between the surface and the environment, q 相变 is the latent heat released when water turns into ice, q 融化 is the heat consumed by the anti-icing system for heating.

[0186] Mass conservation equation:

[0187] Describes the mass exchange relationship among ice, water, and vapor:

[0188]

[0189] S m refers to the source term generated by the phase change (mass change between ice and water).

[0190] Calculation of the phase change process:

[0191] The phase change heat conduction equation is adopted:

[0192]

[0193] Among them, L is the latent heat of solidification of water, is the volume fraction of ice.

[0194] In operation S305, the result output module determines the result output format according to the test result and outputs the test result in the target format.

[0195] According to an embodiment of the present invention, the target format output by the result output module is the word format. In the case of determining the result output format according to the test result, the corresponding test result is stored in the target position in the word report, and the test result in the word format is output. For example, the test result obtained by modifying the hot air anti-icing model of the leading edge of the wing includes tables, numerical values, pictures, and curve graphs. The corresponding word format report template is determined according to the format of the output test result, and the tables, numerical values, pictures, and curve graphs are input and stored in the corresponding positions of the report template, and the test result is output.

[0196] Figure 4 The flowchart of the test method of the test system for the aircraft anti-icing and de-icing system according to another embodiment of the present invention is schematically shown.

[0197] As Figure 4 shown, the test method includes operations S301 to S305, and further includes operations S401 to S403, wherein, the operations S301 to S305 are the same as or similar to Figure 3 the operations, which will not be elaborated here.

[0198] In operation S401, after the result output module outputs the test result in the target format, the analysis module presets a plurality of calculated values based on the initial parameters.

[0199] According to an embodiment of the present invention, the analysis module automatically sets a plurality of calculated values close to the initial parameters according to the initial parameters.

[0200] In operation S402, based on the plurality of calculated values, a plurality of test results corresponding to the plurality of calculated values are determined.

[0201] According to an embodiment of the present invention, the analysis module calculates in parallel according to the set plurality of calculated values to obtain a plurality of test results.

[0202] In operation S403, the plurality of test results are compared and sorted, and the sorted plurality of test results are output in a preset order.

[0203] According to an embodiment of the present invention, in the case of developing the hot air anti-icing model of the leading edge of the wing, it is possible to check whether there is icing on the leading edge of the wing through the sorted plurality of test results output. If so, check the icing distribution and icing degree. It is also possible to check whether there is icing on the leading edge of the wing by the analysis module calling the test result in the target format output by the result output module. If so, check the icing distribution and icing degree.

[0204] The present invention stores the models built in the early stage in a test model library, selects a test model from the test model library according to the test requirements, and completes the parameter setting, calculation execution, etc. of the test through a calculation mode selection library, a calculation execution module, and a parameter setting module. Finally, the test results are analyzed through a result output module and an analysis module, saving the test time, enabling non-professionals to complete the complex aircraft de-icing and anti-icing system design test work through simple model calculations, and improving work efficiency.

[0205] According to another aspect disclosed by the present invention, there is provided a test system for designing aircraft de-icing and anti-icing, including: a test model library for selecting a corresponding test model according to the test requirements, wherein the test model library contains a plurality of pre-set test models; a calculation mode library for selecting a corresponding calculation mode according to the determined test model, wherein the calculation mode library contains a plurality of preset calculation modes; a parameter setting module for setting the initial parameters of the test model and inputting the set initial parameters into the determined calculation mode; a calculation execution module for performing a test according to the determined test model and the input initial parameters and outputting a test result; and a result output module for determining the format of the result output according to the test result and outputting the test result in the target format.

[0206] According to an embodiment disclosed by the present invention, the test system further includes an analysis module. After the calculation execution module outputs the test result, the analysis module presets a plurality of calculation values based on the initial parameters set by the parameter setting; determines corresponding multiple test results based on the plurality of calculation values; compares and sorts the multiple test results, and outputs the sorted multiple test results in a preset order; wherein the analysis module is used to analyze at least one of the aircraft icing amount, icing range size, ice layer shape, curvature radius of the aircraft icing part, and icing intensity.

[0207] According to an embodiment disclosed by the present invention, wherein the analysis module is further used to compare the multiple test results with a preset standard to determine the analysis results of the multiple test results, and these analysis results include those that meet the preset standard and those that do not meet the preset standard.

[0208] According to an embodiment disclosed by the present invention, the test model includes at least one of the following multiple test models: a wing de-icing and anti-icing system wing leading edge hot air anti-icing model for analyzing the anti-icing situation of the wing leading edge; a wing de-icing and anti-icing system engine compressor bleed air thermal anti-icing model for analyzing the anti-icing situation of the wing; a wing de-icing and anti-icing system wing leading edge and tail aerodynamic belt de-icing model for analyzing the de-icing situation of the wing leading edge and the tail; a wing de-icing and anti-icing system wing electric pulse de-icing model for analyzing the de-icing situation of the wing part;

[0209] The wing anti-icing system's wing electric heating anti-icing model is used to analyze the anti-icing situation of the wing section; the engine anti-icing system's engine compressor bleed air heating anti-icing model is used to analyze the anti-icing situation of the aircraft engine; the engine anti-icing system's in-air fan ice shedding model is used to analyze the in-air ice shedding situation of the aircraft engine; the air data probe anti-icing system's pitot tube anti-icing model is used to analyze the anti-icing and ice shedding situations of the pitot tube; the air data probe anti-icing system's pitot tube electric heating anti-icing model is used to analyze the ice shedding situation of the pitot tube; the air data probe anti-icing system's angle of attack detector anti-icing and de-icing model is used to analyze the anti-icing and ice shedding situations of the angle of attack detector; the air data probe anti-icing system's total air temperature probe anti-icing and de-icing model is used to analyze the anti-icing and ice shedding situations of the total air temperature probe; the air data probe anti-icing system's cockpit windshield anti-icing and defogging model is used to analyze the anti-icing and defogging situations of the cockpit windshield; the air data probe anti-icing system's cockpit windshield electric heating anti-icing model is used to analyze the ice shedding situation of the cockpit windshield.

[0210] According to the embodiments disclosed in the present invention, a parameter setting module is used to transfer the scene feature calculation parameters to the test models in the test model library, where the scene feature calculation parameters include at least one of the following multiple feature parameters: The scene feature calculation parameters transferred to the hot air anti-icing model of the wing leading edge of the wing anti-icing and de-icing system include at least one of the following: the stage of the aircraft, ambient pressure, aircraft flight speed, cloud range, cloud temperature, supercooled water droplet diameter, liquid water content; The scene feature parameters transferred to the engine compressor bleed air thermal anti-icing model of the wing anti-icing and de-icing system include at least one of the following: the stage of the aircraft, ambient pressure, aircraft flight speed, cloud range, cloud temperature, supercooled water droplet diameter, liquid water content; The scene feature parameters transferred to the pneumatic belt de-icing model of the wing leading edge and tail wing of the wing anti-icing and de-icing system include at least one of the following: the stage of the aircraft, aircraft flight speed, aircraft icing amount, icing range size, ice layer shape, curvature radius of the aircraft icing part, icing intensity; The scene feature parameters transferred to the wing electric pulse de-icing model of the wing anti-icing and de-icing system include at least one of the following: the stage of the aircraft, aircraft flight speed, aircraft icing amount, icing range size, ice layer shape, curvature radius of the aircraft icing part, icing intensity; The scene parameters transferred to the wing electric heating de-icing model of the wing anti-icing and de-icing system include at least one of the following: the stage of the aircraft, aircraft flight speed, aircraft icing amount, icing range size, ice layer shape, curvature radius of the aircraft icing part, icing intensity; The scene parameters transferred to the engine compressor bleed air heating anti-icing model of the engine anti-icing and de-icing system include at least one of the following: the stage of the aircraft, ambient pressure, aircraft flight speed, cloud range, cloud temperature, supercooled water droplet diameter, liquid water content; The scene parameters transferred to the engine air fan ice removal model of the engine anti-icing and de-icing system include at least one of the following: the stage of the aircraft, aircraft flight altitude, aircraft flight speed, aircraft icing amount, icing range size, ice layer shape; The scene parameters transferred to the pitot tube anti-icing model of the air data probe anti-icing and de-icing system include at least one of the following: the stage of the aircraft, ambient pressure, aircraft flight speed, cloud range, cloud temperature, supercooled water droplet diameter, liquid water content; The scene parameters transferred to the pitot tube electric heating de-icing model of the air data probe anti-icing and de-icing system include at least one of the following: the stage of the aircraft, aircraft flight speed, aircraft icing amount, icing range size, ice layer shape, curvature radius of the aircraft icing part, icing intensity; The scene parameters transferred to the angle of attack detector anti-icing model of the air data probe anti-icing and de-icing system include at least one of the following: the stage of the aircraft, aircraft flight altitude, ambient pressure, aircraft flight speed, cloud range, cloud temperature, supercooled water droplet diameter, liquid water content, aircraft icing amount, icing range size, ice layer shape, curvature radius of the aircraft icing part, icing intensity;Scenario parameters transmitted by the anti-icing model of the total air temperature probe in the air data probe anti-icing system include at least one of the following: aircraft phase, aircraft flight altitude, ambient pressure, aircraft flight speed, cloud range, cloud temperature, supercooled water droplet diameter, liquid water content, aircraft icing amount, icing range size, ice layer shape, curvature radius of the aircraft icing part, icing intensity; Scenario parameters transmitted by the anti-icing and defogging model of the cockpit windshield in the air data probe anti-icing system include at least one of the following: aircraft phase, ambient pressure, aircraft flight speed, cloud range, cloud temperature, supercooled water droplet diameter, liquid water content; Scenario parameters transmitted by the windshield electric heating anti-icing model in the air data probe anti-icing system include at least one of the following: aircraft phase, aircraft flight altitude, ambient pressure, aircraft flight speed, aircraft icing amount, icing range size, ice layer shape, curvature radius of the aircraft body icing, icing intensity.

[0211] According to an embodiment disclosed by the present invention, wherein the parameter setting module is further configured to transmit general feature calculation parameters to the test models in the test model library, and the general feature calculation parameters include at least one of the following: calculation time, maximum number of internal iterations, skewness, relaxation factor, solution history parameters.

[0212] According to an embodiment disclosed by the present invention, wherein the result output module is configured to: determine a result output format that matches the current test result according to the test result, and the test result includes at least one of a table, a numerical value, a picture, and a curve graph; insert the test result into a preset position of the result output format, generate a test report, and output the test report.

[0213] According to a second aspect disclosed by the present invention, a test method applied to the above test system is provided, including: selecting a test model from the test model library according to a test requirement, wherein the test model library includes a plurality of preset test models; determining a corresponding calculation mode from the calculation mode library according to the selected test model; the parameter setting module sets initial parameters of the test model and inputs the parameters into the calculation mode; the calculation execution module calls the calculation mode to test the initial parameters and determines a test result; the result output module determines an output format according to the test result and outputs the test result in the target format.

[0214] According to the embodiments disclosed by the invention, the test method further includes: after the calculation execution module outputs the test results, the analysis module presets a plurality of calculation values based on the initial parameters set according to the parameters; determines corresponding multiple test results based on the plurality of calculation values; compares and sorts the multiple test results, and outputs the sorted multiple test results in a preset order; wherein, the analysis module is used to analyze at least one of the aircraft icing amount, the icing range size, the ice layer shape, the curvature radius of the aircraft icing part, and the icing intensity.

[0215] The preferred specific embodiments of the present invention have been described in detail above. It should be understood that those of ordinary skill in the art can make many modifications and variations based on the concept of the present invention without creative efforts. Therefore, all technical solutions that can be obtained by those skilled in the art in the technical field based on the concept of the present invention through logical analysis, reasoning or limited experiments on the basis of the prior art should fall within the protection scope determined by the claims.

Claims

1. A test method for an aircraft de-icing and anti-icing system, characterized in that: The method comprises the following steps: Select a test model from the test model library; Obtain the flight status of the aircraft, and determine the corresponding calculation mode from the calculation mode library according to the flight status; The determination of the corresponding calculation mode is specifically: When the flight state is in equilibrium, the steady-state calculation mode is selected, and the fluid density and the fluid density change equation are obtained in combination with the transient calculation mode; based on the fluid density and the fluid density change equation, the multiphase flow expansion equation, the aerodynamic field solution equation, the droplet trajectory calculation equation and the icing process simulation equation are selected; Setting initial parameters of the test model and inputting the initial parameters into a calculation model; Conduct tests based on the calculation model and determine the test results; Determine the output format based on the test results, and output the test results in the target format.

2. A test method for an aircraft de-icing and anti-icing system according to claim 1, characterized in that: The specific steps of performing the test based on the calculation model and determining the test result are as follows: The multiphase flow expansion equation analyzes the phase change effect between air, liquid water and ice based on the fluid density and fluid density change equation. The aerodynamic field solution equation analyzes the airflow distribution around the aircraft based on the fluid density and fluid density change equation. The droplet trajectory calculation equation is used based on the airflow distribution to obtain the predicted movement path of the cold water droplets in the airflow. The droplets that will hit the wing surface are determined based on the movement path. The icing process simulation equation is used for the droplets that will hit the wing surface to simulate the icing test results.

3. A test method for an aircraft de-icing and anti-icing system according to claim 2, characterized in that: The specific steps of determining the droplets that will impact the wing surface based on the motion path are: The droplet velocity is determined based on the airflow distribution, the droplet motion equation is constructed, and the movement path of the cold water droplets in the airflow is predicted. The proportion of droplets captured by the wing surface is determined based on the capture coefficient. The proportion captured by the wing surface is combined with the movement path to obtain the droplets that will hit the wing surface.

4. A test method for an aircraft de-icing and anti-icing system according to claim 3, characterized in that: The proportion of droplets captured by the wing surface is the ratio between the mass of droplets impinging on the surface and the mass of incoming droplets per unit area.

5. A test method for an aircraft de-icing and anti-icing system according to claim 2, characterized in that: The motion path is predicted based on the droplet motion equation in the calculation equation of the droplet trajectory.

6. A test method for an aircraft de-icing and anti-icing system according to claim 5, characterized in that: The droplet motion equation is: Among them, m p represents the droplet mass, v p represents the droplet velocity, F D is the drag force, F G is gravity, F B It's buoyancy.

7. A test method for an aircraft de-icing and anti-icing system according to claim 6, characterized in that: The drag force is: Among them, C D is the drag coefficient, A p is the droplet projection area, ρ is the fluid density, and u is the velocity vector.

8. A test method for an aircraft de-icing and anti-icing system according to claim 2, characterized in that: The test results of the simulated freezing satisfy the mass exchange relationship between ice, water and steam and the energy exchange relationship between ice, water and air.

9. A test method for an aircraft de-icing and anti-icing system according to claim 8, characterized in that: The mass exchange relationship between ice, water and steam is: qcooling + qcondensation + qheat transfer = qphase change + qmelting Among them, qcooling is the cooling of the droplets by the air, qcondensation is the heat released when the droplets condense on the surface, qheat transfer is the heat conduction between the surface and the environment, qphase change is the latent heat released by the water edge to ice, and qmelting is the heat consumed by heating the anti-icing system.

10. A test method for an aircraft de-icing and anti-icing system according to claim 9, characterized in that: The energy exchange relationship between ice, water and air is: Among them, S m represents the source term generated by the phase change.

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