A method and system for simulating ice scenes

Abstract

The present invention discloses an ice scene simulation method and system, the method is applied to an ice scene simulation system including a control device and an aircraft simulator, the aircraft simulator including a control module, the method including: determining the simulation type through the control device, the simulation type including an icing model and an anti-icing model; determining the icing rate and icing location through the control device, simulating the icing model based on the icing location and the icing rate; determining the deicing rate and the deicing location according to the trigger operation received by the control module, simulating the anti-icing model based on the deicing location and the deicing rate. The above technical scheme simulates the icing model according to the icing location and the icing rate, realizes the simulation of the icing amount determined according to the icing rate at the icing location, simulates the anti-icing simulation according to the deicing location and the deicing rate, realizes the simulation of deicing according to the deicing rate at the icing location, realizes the simulation of ice scene through the icing model and the anti-icing model, and provides a simulated ice scene for aircraft research and flight training.

Description

Technical Field

[0001] The embodiments of the present invention relate to the field of aircraft technology, and in particular to an ice scene simulation method and system. Background Art

[0002] Flight simulators are widely used in aircraft design, development, and aircraft performance research. Flight simulators in simulated environments can be used to train pilots and crew members. Pilots can conduct flight training in a variety of environments in aircraft simulators. During actual flight, the flight environment is complex and changeable, including changes in air density, turbulence, wind shear, cloudiness, precipitation, and icing.

[0003] In the existing technology, flight simulators can provide relatively independent flight states. Environmental designers can simulate complex environmental scenarios according to design requirements. After on-site staff set up the simulation environment, R&D personnel can study aircraft performance in the simulation environment. Of course, pilots can also train in aircraft simulators.

[0004] However, existing technologies are unable to simulate ice scenes. Summary of the invention

[0005] The present invention provides an ice scene simulation method and system to achieve the simulation of ice scenes of a flight simulator and provide simulated ice scenes for aircraft research and flight training.

[0006] In a first aspect, an embodiment of the present invention provides an ice scene simulation method, which is applied to an ice scene simulation system, wherein the ice scene simulation system includes: a control device and an aircraft simulator, wherein the aircraft simulator includes a control module, and the method includes:

[0007] Determining a simulation type by the control device, the simulation type including an icing model and an anti-icing model;

[0008] Determine the icing rate and the icing location by the control device, and simulate the icing model based on the icing location and the icing rate;

[0009] A deicing rate and a deicing location are determined according to the trigger operation received by the control module, and the anti-icing model is simulated based on the deicing location and the deicing rate.

[0010] The technical solution of an embodiment of the present invention provides an ice scene simulation method, which is applied to an ice scene simulation system, wherein the ice scene simulation system includes: a control device and an aircraft simulator, wherein the aircraft simulator includes a control module, and the method includes: determining a simulation type through the control device, wherein the simulation type includes an icing model and an anti-icing model; determining an icing rate and an icing location through the control device, and simulating the icing model based on the icing location and the icing rate; determining a deicing rate and a deicing location according to a trigger operation received by the control module, and simulating the anti-icing model based on the deicing location and the deicing rate. In the above technical scheme, the on-site staff can trigger the control device to determine whether the simulation type is an icing model or an anti-icing model; when the simulation type is an icing model, the on-site staff can continue to trigger the control device to determine the icing rate and the icing location, and simulate the icing model according to the icing location and the icing rate, so as to simulate the icing amount determined according to the icing rate at the icing location; when the simulation type is an anti-icing model, the pilot or researcher on the aircraft simulator can trigger the control module, and then the aircraft simulator can determine the de-icing rate and the de-icing location according to the trigger operation sent by the control module, and simulate the anti-icing simulation according to the de-icing location and the de-icing rate, so as to simulate de-icing according to the de-icing rate at the icing location, and realize the simulation of icing scenes and anti-icing scenes through the icing model and the anti-icing model, so as to provide a simulated icing scene for flight training, and provide a data basis for studying the operation of aircraft in icing scenes and anti-icing scenes.

[0011] Furthermore, the icing model includes a general icing model and a deep icing model. The general icing model includes a wing icing model, a fuselage icing model, an engine icing model and a sensor icing model. The icing parts of the wing icing model are the wings, the icing parts of the fuselage icing model are the fuselage, the icing parts of the engine icing model are the engines, the icing parts of the sensor icing model are the sensors, and the icing parts of the deep icing model are the wings, the fuselage, the engines and the sensors.

[0012] Further, simulating the icing model based on the icing location and the icing rate includes:

[0013] Determining that the icing location is a wing, a fuselage, an engine, or a sensor, and simulating a general icing amount on the wing, the fuselage, the engine, or the sensor based on the icing rate to simulate the wing icing model, the fuselage icing model, the engine icing model, or the sensor icing model;

[0014] The icing parts are determined to be wings, fuselage, engines and sensors. When the icing amount is greater than a preset icing amount, the deep icing amount is simulated based on the icing rate to simulate the deep icing model.

[0015] Furthermore, the anti-icing model includes a general anti-icing model, and the general anti-icing model includes a wing anti-icing model, an engine anti-icing model and a sensor anti-icing model. The deicing part of the wing anti-icing model is the wing, the deicing part of the engine anti-icing model is the engine air intake, and the deicing part of the sensor anti-icing model is the sensor.

[0016] Further, determining a deicing rate and a deicing position according to the trigger operation received by the control module, and simulating the anti-icing model based on the deicing position and the deicing rate, including:

[0017] The trigger operation includes turning on a wing de-icing button, determining that the de-icing part is a wing, determining the de-icing rate according to the trigger operation, and controlling the opening of a wing de-icing valve to simulate the wing anti-icing model based on the de-icing rate;

[0018] The trigger operation includes turning on the engine de-icing button, determining that the de-icing location is the engine air intake, determining the de-icing rate according to the trigger operation, and controlling the engine nacelle de-icing valve to simulate the engine anti-icing model based on the de-icing rate;

[0019] The trigger operation includes turning on a sensor de-icing button, determining the de-icing part as a sensor, determining the de-icing rate according to the trigger operation, and controlling the turning on of a heating wire to simulate the sensor anti-icing model based on the de-icing rate.

[0020] Further, controlling to open the wing de-icing valve to simulate the wing anti-icing model based on the de-icing rate includes:

[0021] The wing de-icing valve is controlled to be opened within a preset time period, and the wing anti-icing model when the aircraft is on the ground is simulated based on the de-icing rate.

[0022] Furthermore, the anti-icing model includes an ice-shedding model, and the deicing part of the ice-shedding model is the engine blades.

[0023] Further, determining a deicing rate and a deicing position according to the trigger operation received by the control module, and simulating the anti-icing model based on the deicing position and the deicing rate, including:

[0024] The trigger operation includes adjusting the engine speed, determining that the deicing part is the engine blade, and controlling the engine blade to rotate according to the engine speed included in the trigger operation to simulate the ice-shedding model based on the deicing rate.

[0025] Further, controlling the engine blades to rotate according to the engine speed included in the triggering operation includes:

[0026] The engine blades are controlled to alternately rotate at an accelerated speed and a decelerated speed according to the engine speed included in the trigger operation.

[0027] In a second aspect, an embodiment of the present invention further provides an ice scene simulation system, comprising: a control device and an aircraft simulator, the aircraft simulator comprising a control module, the control device being used to: determine a simulation type of an ice scene, the simulation type comprising an icing model and an anti-icing model; determine an icing rate and an icing location, and simulate the icing model based on the icing location and the icing rate; the control module being used to: determine a de-icing rate and a de-icing location according to a received trigger operation, and simulate the anti-icing model based on the de-icing location and the de-icing rate.

[0028] The description of the second aspect in this application can refer to the detailed description of the first aspect; and the beneficial effects of the description of the second aspect can refer to the analysis of the beneficial effects of the first aspect, which will not be repeated here.

[0029] In this application, the name of the ice scene simulation system does not limit the device or functional module itself. In actual implementation, these devices or functional modules may appear with other names. As long as the functions of each device or functional module are similar to those of this application, they fall within the scope of the claims of this application and their equivalent technologies.

[0030] These and other aspects of the present application will become more apparent from the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0032] Figure 1 A schematic diagram of an ice scene simulation system provided by an embodiment of the present invention;

[0033] Figure 2 A flowchart of an ice scene simulation method provided in Embodiment 1 of the present invention;

[0034] Figure 3 This is a flow chart of an ice scene simulation method provided in Embodiment 2 of the present invention. DETAILED DESCRIPTION

[0035] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0036] The term "and / or" in this article is merely a description of the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can mean: A exists alone, A and B exist at the same time, and B exists alone.

[0037] The terms "first" and "second" and the like in the specification and drawings of this application are used to distinguish different objects, or to distinguish different processing of the same object, rather than to describe a specific order of objects.

[0038] In addition, the terms "including" and "having" and any variations thereof mentioned in the description of the present application are intended to cover non-exclusive inclusions. For example, a process, method, system, product or device that includes a series of steps or units is not limited to the listed steps or units, but may optionally include other steps or units that are not listed, or may optionally include other steps or units that are inherent to these processes, methods, products or devices.

[0039] It should be mentioned before discussing exemplary embodiments in more detail that some exemplary embodiments are described as processes or methods depicted as flow charts. Although the flow charts describe various operations (or steps) as sequential processes, many operations therein can be implemented in parallel, concurrently or simultaneously. In addition, the order of various operations can be rearranged. The process can be terminated when its operation is completed, but can also have additional steps not included in the accompanying drawings. The process can correspond to methods, functions, procedures, subroutines, subprograms, etc. In addition, the embodiments in the present invention and the features in the embodiments can be combined with each other without conflict.

[0040] It should be noted that, in the embodiments of the present application, words such as "exemplary" or "for example" are used to indicate examples, illustrations or descriptions. Any embodiment or design described as "exemplary" or "for example" in the embodiments of the present application should not be interpreted as being more preferred or more advantageous than other embodiments or designs. Specifically, the use of words such as "exemplary" or "for example" is intended to present related concepts in a specific way.

[0041] In the description of the present application, unless otherwise specified, “plurality” means two or more.

[0042] Figure 1 A schematic diagram of an ice scene simulation system provided by an embodiment of the present invention is shown in FIG. Figure 1 As shown, the ice scene simulation system may include a control device 110 and an aircraft simulator 120 that are communicatively connected to each other. The control device 110 may be set on an operating table so that on-site staff can operate the control device 110. The aircraft simulator 120 may include a control module 1210, an aerodynamic module 1220, an engine module 1230, a vision module 1240, a motion module 1250, a sound module 1260, a display module 1270, and the like.

[0043] The ice scene simulation method proposed by the present invention will be described in detail below with reference to diagrams and embodiments.

[0044] Embodiment 1

[0045] Figure 2 This is a flow chart of an ice scene simulation method provided in the first embodiment of the present invention. This embodiment is applicable to the situation where an ice scene needs to be simulated on an aircraft simulator. The method is applied to Figure 1 The ice scene simulation system shown in FIG. Figure 2 As shown, the method specifically comprises the following steps:

[0046] Step 210: Determine the simulation type by the control device.

[0047] The control device is arranged on the operating table and includes an interactive module. On-site staff can trigger the interactive module to input type information, and then the control device can determine the simulation type of the current ice scene based on the type information received by the interactive module. The simulation types include icing model and anti-icing model.

[0048] Specifically, when the type information received by the interaction module is icing information, it can be determined that the simulation type is an icing model. Therefore, it is necessary to simulate the icing scene based on the ice scene simulation system; when the type information received by the interaction module is anti-icing information, it can be determined that the simulation type is an anti-icing model. Therefore, it is necessary to simulate the anti-icing scene based on the ice scene simulation system.

[0049] In the embodiment of the present invention, after receiving the type information input by the on-site staff, the simulation type of the ice scene can be determined, so as to simulate the ice scene according to the current demand.

[0050] Step 220: Determine the freezing rate and freezing location through the control device, and simulate the freezing model based on the freezing location and the freezing rate.

[0051] Icing locations can include the wings, fuselage, engines and sensors, and icing rates can include light, moderate, severe and extreme.

[0052] Specifically, the interactive module can also receive the icing rate and icing location input by the on-site staff, and simulate the icing location of the aircraft in the ice scene according to the icing location, and simulate the icing amount of the icing location of the aircraft in the ice scene according to the icing rate, so as to realize the simulation of the icing model.

[0053] Among them, the icing model may include a general icing model and a deep icing model. The general icing model may include a wing icing model, a fuselage icing model, an engine icing model and a sensor icing model. The icing part of the wing icing model is the wing, the icing part of the fuselage icing model is the fuselage, the icing part of the engine icing model is the engine, the icing part of the sensor icing model is the sensor, and the icing part of the deep icing model may be the wing, fuselage, engine and sensor.

[0054] When it is determined that the icing part is the wing, the icing rate can be used to simulate the amount of icing on the wing in the ice scene to realize the simulation of the wing icing model; when it is determined that the icing part is the fuselage, the icing rate can be used to simulate the amount of icing on the fuselage in the ice scene to realize the simulation of the fuselage icing model; when it is determined that the icing part is the engine, the icing rate can be used to simulate the amount of icing on the engine in the ice scene to realize the simulation of the engine icing model; when it is determined that the icing part is the sensor, the icing rate can be used to simulate the amount of icing on the sensor in the ice scene to realize the simulation of the sensor icing model; when it is determined that the icing parts are the wing, fuselage, engine and sensor, the icing rate can be used to simulate the amount of icing on the wing, fuselage, engine and sensor in the ice scene to realize the simulation of the deep icing model.

[0055] In an embodiment of the present invention, after determining the simulation type of the ice scene, the icing model can be determined according to the icing parts input by the on-site staff, the amount of ice in the icing parts in the icing model can be determined according to the icing rate input by the on-site staff, and the icing model corresponding to the icing parts can be simulated based on the icing amount.

[0056] Step 230: Determine a deicing rate and a deicing location according to the trigger operation received by the control module, and simulate the anti-icing model based on the deicing location and the deicing rate.

[0057] Among them, the deicing parts include wings, engine air inlets, sensors and engine blades. The anti-icing model includes a general anti-icing model and an ice-swinging model. The general anti-icing model includes a wing anti-icing model, an engine anti-icing model and a sensor anti-icing model. The deicing part of the wing anti-icing model is the wing, the deicing part of the engine anti-icing model is the engine air inlet, the deicing part of the sensor anti-icing model is the sensor, and the deicing part of the ice-swinging model is the engine blade.

[0058] The control module is respectively communicated with the wing de-ice button, the engine de-ice button, the sensor de-ice button and the engine throttle lever, and the trigger operation can be triggered by the staff in the aircraft simulator through the wing de-ice button, the engine de-ice button, the sensor de-ice button or the engine throttle lever.

[0059] Specifically, if the trigger operation is triggered by the staff in the aircraft simulator through the wing deicing button, it can be determined that the deicing part is the wing. Since the correspondence between the deicing part and the deicing rate is pre-stored in the aircraft simulator, after determining that the deicing part is the wing, the deicing rate corresponding to the wing can be determined, and the deicing rate corresponding to the wing is greater than the icing rate of the wing icing model, so that as the deicing time increases, the amount of ice on the wing gradually decreases, thereby realizing the simulation of the wing anti-icing model that deices the wing according to the deicing rate. If the trigger operation is triggered by the staff in the aircraft simulator through the engine deicing button, it can be determined that the deicing part is the engine intake. Similarly, after determining that the deicing part is the engine intake, it can be determined that the deicing rate corresponding to the engine intake is greater than the icing rate of the engine icing model, so that as the deicing time increases, the amount of ice on the engine intake gradually decreases, thereby realizing the simulation of the engine anti-icing model that deices the engine intake according to the deicing rate. If the triggering operation is triggered by the staff in the aircraft simulator through the sensor de-icing button, it can be determined that the de-icing part is the sensor. Similarly, after determining that the de-icing part is the sensor, it can be determined that the de-icing rate corresponding to the sensor is greater than the icing rate of the sensor icing model, so that as the de-icing time increases, the amount of ice on the sensor gradually decreases, thereby realizing the simulation of the engine anti-icing model that de-ices the sensor according to the de-icing rate.

[0060] If the trigger operation is that the staff in the aircraft simulator adjusts the engine speed through the engine throttle lever, it can be determined that the deicing part is the engine blade. After determining that the deicing part is the engine blade, the engine speed can be determined according to the deicing rate, so that the engine blade rotates based on the engine speed determined according to the deicing rate. First, the speed of the engine blade can be reduced from the low-pressure rotor speed N1 to the minimum allowable low-pressure rotor speed IDLE, and maintained for a preset time period. At this time, part of the ice on the engine blade will be thrown off due to centrifugal force, and then the speed of the engine blade can be increased to (70% to 90%) N1, so that the ice on the engine blade is affected by the moment of inertia and then part of it is thrown off, realizing the simulation of the ice throwing model for deicing the engine blade according to the deicing rate.

[0061] In an embodiment of the present invention, after determining the simulation type of the ice scene, the deicing location and deicing rate can also be determined based on the triggering operation triggered by the staff in the aircraft simulator through the wing deicing button, the engine deicing button, the sensor deicing button or the engine throttle lever, and then the deicing location is deiced based on the deicing rate, thereby realizing the simulation of the anti-icing model corresponding to the deicing location.

[0062] An ice scene simulation method provided in a first embodiment of the present invention is applied to an ice scene simulation system, wherein the ice scene simulation system includes: a control device and an aircraft simulator, wherein the aircraft simulator includes a control module, and the method includes: determining a simulation type through the control device, wherein the simulation type includes an icing model and an anti-icing model; determining an icing rate and an icing location through the control device, and simulating the icing model based on the icing location and the icing rate; determining a deicing rate and a deicing location according to a trigger operation received by the control module, and simulating the anti-icing model based on the deicing location and the deicing rate. According to the above technical scheme, the on-site staff can trigger the control device to determine whether the simulation type is an icing model or an anti-icing model; when the simulation type is an icing model, the on-site staff can continue to trigger the control device to determine the icing rate and the icing location, and simulate the icing model according to the icing location and the icing rate, so as to simulate the icing amount determined according to the icing rate at the icing location; when the simulation type is an anti-icing model, the pilot or researcher on the aircraft simulator can trigger the control module, and then the aircraft simulator can determine the de-icing rate and the de-icing location according to the trigger operation sent by the control module, and simulate the anti-icing simulation according to the de-icing location and the de-icing rate, so as to simulate de-icing according to the de-icing rate at the icing location, and realize the simulation of icing scenes and anti-icing scenes through the icing model and the anti-icing model, so as to provide a simulated icing scene for flight training, and provide a data basis for studying the operation of aircraft in icing scenes and anti-icing scenes.

[0063] Embodiment 2

[0064] Figure 3 This is a flow chart of an ice scene simulation method provided in the second embodiment of the present invention. This embodiment is specific based on the above embodiment. Figure 3 As shown, in this embodiment, the method may further include:

[0065] Step 310: Determine the simulation type by the control device.

[0066] The simulation types include icing models and anti-icing models. The icing models include general icing models and deep icing models. The general icing models include wing icing models, fuselage icing models, engine icing models and sensor icing models. The icing parts of the wing icing model are the wings, the icing parts of the fuselage icing model are the fuselage, the icing parts of the engine icing model are the engines, the icing parts of the sensor icing model are the sensors, and the icing parts of the deep icing model are the wings, fuselage, engines and sensors.

[0067] The anti-icing model includes a general anti-icing model and an ice-swinging model. The general anti-icing model includes a wing anti-icing model, an engine anti-icing model and a sensor anti-icing model. The deicing part of the wing anti-icing model is the wing, the deicing part of the engine anti-icing model is the engine air inlet, the deicing part of the sensor anti-icing model is the sensor, and the deicing part of the ice-swinging model is the engine blade.

[0068] Step 320: Determine the freezing rate and freezing location through the control device.

[0069] As described in the first embodiment, after receiving the type information, icing rate and icing location input by the on-site staff, the simulation type of the ice scene can be determined to simulate the ice scene according to the current demand.

[0070] Step 330: Determine that the icing location is a wing, a fuselage, an engine, or a sensor, and simulate a general icing amount on the wing, the fuselage, the engine, or the sensor based on the icing rate to simulate the wing icing model, the fuselage icing model, the engine icing model, or the sensor icing model.

[0071] 1) When simulating the wing icing model, under the premise of allowing icing, the amount of ice on the wing / tail can continue to increase according to the icing rate. Based on the amount of ice, the continuous icing model and the theoretical icing model can be simulated. After the aircraft is frozen, the amount of ice can affect the aircraft's drag coefficient and lift coefficient, and thus affect the aircraft's flight performance. In addition to the increase in overall drag, it may also include a decrease in lift, a decrease in stall angle of attack, a change in pitch moment, a decrease in control efficiency, and a change in control force. When ice accumulates on the wings and tail, the aerodynamic characteristics and flight characteristics of the aircraft can become significantly unstable. Due to ice accumulation, the shape of the streamlined parts changes, the airfoil is distorted (deformed), and the friction resistance and pressure difference resistance are increased. Ice accumulation deforms the wing shape, destroys the smooth flow of air around the wing surface, significantly reduces lift, accelerates stall, increases stall speed, and reduces the critical angle of attack; at the same time, it will increase the weight of the aircraft, increase drag, and increase fuel consumption.

[0072] 2) When simulating the fuselage icing model, under the premise of allowing icing, the amount of ice on the fuselage can continue to increase according to the icing rate, affecting the total weight and center of gravity of the aircraft. After the aircraft is iced, the total weight of the aircraft increases, which increases the total weight of the aircraft input into the aerodynamic calculation, affects the center of gravity of the aircraft, and the engine needs to provide additional power to cope with the increased ice weight, increasing fuel consumption.

[0073] 3) When simulating the engine icing model, the icing parts can include the inlet duct and blades. The icing of the inlet duct will lead to the deterioration of the aerodynamic characteristics of the inner surface, making the inlet velocity field unevenly distributed and causing local separation of the airflow, causing engine surge, thereby reducing the engine thrust. In severe cases, the engine will be shut down. The icing of the blades will increase the weight of the blades and cause the compressor blades to vibrate. The increased vibration will cause ice chips to detach and enter the compressor, causing mechanical damage to the compressor. In severe cases, the engine will suddenly shut down (due to foreign body intrusion). Therefore, under the premise of allowing icing, the amount of ice on the inlet duct continues to increase according to the icing rate, and the high-pressure air outlet pressure (PS3) changes, affecting the engine performance, inducing engine surge or even stalling. The amount of ice on the blades continues to increase according to the icing rate, and the vibration value of the fuselage continues to increase. As the vibration continues, the ice on the blades suddenly separates, inducing abnormal engine shutdown (foreign body intrusion).

[0074] 4) When simulating the sensor icing model, the amount of ice on the sensor can continue to increase according to the icing rate, provided that icing is allowed. Since the sensor has an automatic heating function, the simulated sensor is partially blocked, which causes an unreliable airspeed indication failure and affects the normal flight of the aircraft. Sensor icing will affect the normal operation of the pitot tube, static pressure tube, angle of attack sensor and total temperature probe, and then affect the accuracy of instrument information and instrument flight.

[0075] It should be noted that the aerodynamic module included in the aircraft simulator can simulate the changes in aircraft flight force caused by the ice scene, provide engine status information and performance changes based on the engine module, provide visual simulation of wind, rain and ice caused by the ice scene based on the vision module, provide aircraft vibration simulation caused by the ice scene based on the motion module, provide aircraft sound simulation caused by the ice scene based on the sound module, and provide warning information caused by the ice scene based on the display module.

[0076] Step 340: Determine that the icing parts are the wings, fuselage, engine and sensor, and when the icing amount is greater than a preset icing amount, simulate the deep icing amount based on the icing rate to simulate the deep icing model.

[0077] Specifically, when simulating the deep icing model, the vision module experiences rain and snow weather changes, and the amount of ice on the wings, fuselage, engine and sensors can continue to increase according to the icing rate. After the amount of ice on the wings, fuselage, engine and sensors reaches 75%, the simulated deep icing model is realized.

[0078] When simulating the deep icing model, the engine indicates abnormalities and thrust changes as follows: a) The low-pressure rotor speed (N1) and high-pressure rotor speed (N2) fluctuate periodically according to the engine surge, that is, when the values ​​of N1 and N2 are large, the fluctuation is large; when the values ​​of N1 and N2 are small, the fluctuation is small, and the engine exhaust temperature (EGT) increases significantly. b) The engine thrust fluctuates according to the engine surge state, N1, N2, and EGT, causing thrust loss in the corresponding engine. c) When the wing de-ice button, engine de-ice button, sensor de-ice button, or engine throttle lever is triggered, the amount of ice in the corresponding iced area gradually decreases, and the speed of ice reduction is related to the set icing rate. If the amount of ice decreases to less than 70%, the simulated deep icing model will be exited; if the engine anti-icing failure causes the amount of ice to be greater than 70%, the simulated deep icing model will remain.

[0079] When simulating the deep icing model, the engine surge, abnormal noise and vibration are as follows: a) Within 1 minute of observing the change in rain and snow weather, the staff in the aircraft simulator will find that the increase in ice will cause ice to be sucked into the engine, making the airflow in the engine unsmooth and resulting in incomplete combustion and backfire. The engine intake flow rate will decrease, and when it reaches a certain level, a vibration under abnormal working conditions will occur, namely surge. This state is very harmful to the engine. b) The engine will have a periodic "boom" compressor stall sound according to the surge state. c) If the aircraft simulator component includes a motion system, the engine thrust will decrease and be accompanied by vibration. The vibration is mainly engine vibration, and the N1 and N2 vibration values ​​exceed the warning value.

[0080] When pilots are training in the deep icing model, the emergency operations are as follows: a) Perform emergency operations according to the Quick Checklist (QRH), Engine Limits or Surge or Stall section. For example, if the EGT decreases and the engine is operating normally, then end the scenario; if the EGT does not decrease, the engine is faulty, then go to the next step. b) Perform emergency operations according to the Quick Checklist (QRH), Engine High Vibration Value. For example, if the vibration value decreases and the engine is operating normally, then end the scenario; if the vibration value does not decrease, the engine is faulty, then go to the next step. c) If one or more of the following conditions occur: abnormal engine indications, engine indications are rapidly approaching or exceeding limits, abnormal engine noise is heard, which may be accompanied by airframe vibration, no response or abnormal response to movement of the thrust levers, flame is reported at the engine inlet or exhaust, then attempt to restore normal engine operation, if this is not possible, shut down the engine. d) If the engine stalls due to ice after about 3 minutes of engine surge, restart the engine, and the engine may accelerate to idle very slowly, especially at high altitudes. If N2 rises steadily and EGT remains within limits, the start is proceeding normally. If the engines do not start normally, the pilot will perform emergency operations according to the Quick Checklist (QRH) section "Loss of Thrust in Two or More Engines".

[0081] In the embodiment of the present invention, the simulation of the anti-icing model corresponding to the deicing part is realized.

[0082] Step 350: Determine a deicing rate and a deicing location according to the trigger operation received by the control module, and simulate the anti-icing model based on the deicing location and the deicing rate.

[0083] In one implementation, step 350 may specifically include:

[0084] The trigger operation includes determining that the deicing part is the wing when the wing deicing button is turned on, determining the deicing rate according to the trigger operation, and controlling the opening of the wing deicing valve to simulate the wing anti-icing model based on the deicing rate; the trigger operation includes determining that the deicing part is the engine air inlet when the engine deicing button is turned on, determining the deicing rate according to the trigger operation, and controlling the engine nacelle deicing valve to simulate the engine anti-icing model based on the deicing rate; the trigger operation includes determining that the deicing part is the sensor when the sensor deicing button is turned on, determining the deicing rate according to the trigger operation, and controlling the opening of the heating wire to simulate the sensor anti-icing model based on the deicing rate; the trigger operation includes determining that the deicing part is the engine blade when the engine speed is adjusted, and controlling the engine blade to rotate according to the engine speed included in the trigger operation to simulate the ice-shedding model based on the deicing rate.

[0085] In one embodiment, controlling the opening of a wing de-icing valve to simulate the wing anti-icing model based on the de-icing rate includes:

[0086] The wing de-icing valve is controlled to be opened within a preset time period, and the wing anti-icing model when the aircraft is on the ground is simulated based on the de-icing rate.

[0087] In one embodiment, controlling the engine blades to rotate according to the engine speed included in the triggering operation includes:

[0088] The engine blades are controlled to alternately rotate at an accelerated speed and a decelerated speed according to the engine speed included in the trigger operation.

[0089] 1) When simulating the wing anti-icing model, if the aircraft is on the ground, de-icing can be performed within the preset time period allowed by the aircraft under the premise of power supply and hot air. Therefore, the wing de-icing valve can be controlled to open within the preset time period to generate a de-icing rate greater than the ice formation rate, and dynamically simulate the wing anti-icing model. As the de-icing time increases, the amount of ice gradually decreases. When the de-icing time allowed by the aircraft is reached, the wing de-icing valve is controlled to be closed, so that the de-icing rate gradually decreases until it reaches 0. If the aircraft is in the air, de-icing is not limited by time. Under the premise of power supply and hot air, the wing de-icing valve is controlled to open to generate a de-icing rate greater than the ice formation rate to simulate the wing anti-icing model.

[0090] 2) When simulating the engine anti-icing model, under the premise of power supply and normal operation of the engine, the engine pod anti-icing valve is opened by simulating the engine de-icing button to generate a de-icing rate far greater than the icing rate, and the engine anti-icing model is dynamically simulated. After the engine pod anti-icing valve is opened, the amount of ice in the engine inlet duct is reduced, the engine intake flow returns to normal, and then the engine thrust returns to normal. De-icing will increase the engine load, increase fuel consumption, and reduce the maximum available load of the engine. Since there is a total temperature probe in the engine inlet duct, in order to save oil and reduce carbon emissions, the engine pod anti-icing valve is controlled to be closed, so that the de-icing rate gradually decreases to 0.

[0091] When simulating the engine anti-icing model, the simulation environment is as follows: 1) Aircraft cruising stage (10000ft+ / -1000ft); 2) The aircraft is in automatic flight state, and the throttle is disconnected after the engine inlet duct is 100% iced, the flight freeze is set, and the engine throttle lever is slowly moved to disengage to avoid ice throwing; 3) After the engine high-pressure rotor N2 vibration value tends to be stable (oscillating between the maximum and minimum values) or the engine inlet duct ice amount reaches the maximum value, turn on the engine de-ice button, wait for the engine N2 vibration value to gradually decrease and stabilize or check the engine inlet duct ice amount indicator value (becomes 0); 4) The time from turning on the engine de-ice button to the engine inlet duct ice amount becoming 0 is recorded as 30-60s (depending on the icing rate).

[0092] 3) When simulating the sensor anti-icing model, under the premise of power supply and normal operation of the engine, the heating wire is controlled by simulating the heating switch (active or passive) to produce a deicing rate greater than or much greater than the icing rate, and dynamically simulate heating deicing. The sensor anti-icing model is simulated in two cases by judging whether the aircraft is on the ground: a) On the ground, the total temperature probe anti-icing is not simulated, only the half-power pitot tube anti-icing and the full-power static pressure tube and angle of attack sensor anti-icing are simulated; b) In the air, the full-power total temperature probe, pitot tube, static pressure tube and angle of attack sensor anti-icing are simulated.

[0093] In practical applications, the general anti-icing model also includes the fuselage anti-icing model, which mainly includes whether the fuselage is coated with anti-icing paint to suppress the increase of ice volume and prevent the continuous increase of resistance. In the triggered icing environment, the fuselage anti-icing model can effectively suppress the continuous increase of icing rate.

[0094] 4) When simulating the ice shedding model, under the premise of normal engine operation, control the engine throttle lever to reduce the speed of the engine blades from the low-pressure rotor speed N1 to the minimum allowable low-pressure rotor speed IDLE, and keep it for a period of time. The ice on the engine blades will be partially thrown off due to centrifugal force. Control the engine throttle lever again to quickly increase the speed of the engine blades to (70%~90%) N1. The ice on the engine blades will be partially thrown off due to the influence of rotational inertia. Repeat the above steps to throw off all the ice on the engine blades. The engine blades throw off ice, the amount of ice on the blades decreases, and the vibration value of the engine low-pressure rotor N1 decreases. After multiple ice shedding, the engine vibration value tends to be normal, and the vibration value of the motion system returns to normal.

[0095] In the embodiment of the present invention, the simulation of the anti-icing model corresponding to the deicing part is realized.

[0096] A second embodiment of the present invention provides an ice scene simulation method, which is applied to an ice scene simulation system. The ice scene simulation system includes: a control device and an aircraft simulator, the aircraft simulator includes a control module, and the method includes: determining a simulation type through the control device, the simulation type including an icing model and an anti-icing model; determining an icing rate and an icing location through the control device; determining that the icing location is a wing, a fuselage, an engine, or a sensor, and simulating a general icing amount on the wing, fuselage, engine, or sensor based on the icing rate to simulate the wing icing model, the fuselage icing model, the engine icing model, or the sensor icing model; determining that the icing location is a wing, a fuselage, an engine, and a sensor, and when the icing amount is greater than a preset icing amount, simulating a deep icing amount based on the icing rate to simulate the deep icing model; determining a deicing rate and a deicing location according to a trigger operation received by the control module, and simulating the anti-icing model based on the deicing location and the deicing rate. In the above technical solution, the on-site staff can trigger the control device to determine whether the simulation type is an icing model or an anti-icing model; when the simulation type is an icing model, the on-site staff can continue to trigger the control device to determine the icing rate and icing location, and simulate the icing model according to the icing location and icing rate, so as to simulate the icing amount determined according to the icing rate at the icing location; when the simulation type is an anti-icing model, the pilot or researcher on the aircraft simulator can trigger the control module, and then the aircraft simulator can determine the deicing rate and deicing location according to the trigger operation sent by the control module, and simulate the anti-icing simulation according to the deicing location and deicing rate, so as to simulate deicing according to the deicing rate at the icing location, and simulate the icing scene and anti-icing scene through the icing model and anti-icing model, so as to provide a simulated icing scene for flight training, so that pilots can train in a more realistic environment and improve aviation flight safety as much as possible. At the same time, it provides a data basis for studying the operation of aircraft in icing scenes and anti-icing scenes.

[0097] Embodiment 3

[0098] Embodiment 3 of the present invention provides an ice scene simulation system, such as Figure 1 As shown, the system includes: a control device 110 and an aircraft simulator 120, the aircraft simulator 120 includes a control module 1210, the control device 110 is used to: determine the simulation type of the ice scene, the simulation type includes an icing model and an anti-icing model; determine the icing rate and the icing location, and simulate the icing model based on the icing location and the icing rate; the control module 1210 is used to: determine the deicing rate and the deicing location according to the received trigger operation, and simulate the anti-icing model based on the deicing location and the deicing rate.

[0099] Among them, the icing model includes a general icing model and a deep icing model. The general icing model includes a wing icing model, a fuselage icing model, an engine icing model and a sensor icing model. The icing part of the wing icing model is the wing, the icing part of the fuselage icing model is the fuselage, the icing part of the engine icing model is the engine, the icing part of the sensor icing model is the sensor, and the icing parts of the deep icing model are the wing, fuselage, engine and sensor.

[0100] Accordingly, the control device 110 is specifically used to: determine that the icing parts are wings, fuselage, engines or sensors, and simulate general icing amounts on the wings, fuselage, engines or sensors based on the icing rate to simulate the wing icing model, fuselage icing model, engine icing model or sensor icing model; determine that the icing parts are wings, fuselage, engines and sensors, and when the icing amount is greater than a preset icing amount, simulate deep icing amounts based on the icing rate to simulate the deep icing model.

[0101] In addition, the anti-icing model includes a general anti-icing model, and the general anti-icing model includes a wing anti-icing model, an engine anti-icing model and a sensor anti-icing model. The deicing part of the wing anti-icing model is the wing, the deicing part of the engine anti-icing model is the engine air intake, and the deicing part of the sensor anti-icing model is the sensor.

[0102] Accordingly, the control module 1210 is specifically used for: when the trigger operation includes turning on the wing de-icing button, determining that the de-icing part is the wing, determining the de-icing rate according to the trigger operation, and controlling the opening of the wing de-icing valve to simulate the wing anti-icing model based on the de-icing rate; when the trigger operation includes turning on the engine de-icing button, determining that the de-icing part is the engine air inlet, determining the de-icing rate according to the trigger operation, and controlling the engine nacelle de-icing valve to simulate the engine anti-icing model based on the de-icing rate; when the trigger operation includes turning on the sensor de-icing button, determining that the de-icing part is the sensor, determining the de-icing rate according to the trigger operation, and controlling the opening of the heating wire to simulate the sensor anti-icing model based on the de-icing rate.

[0103] Further, controlling the wing de-icing valve to open to simulate the wing anti-icing model based on the de-icing rate includes: controlling the wing de-icing valve to open within a preset time period, and simulating the wing anti-icing model when the aircraft is on the ground based on the de-icing rate.

[0104] Furthermore, the anti-icing model includes an ice-shedding model, and the deicing part of the ice-shedding model is the engine blades.

[0105] Accordingly, the control module 1210 is specifically used for: when the trigger operation includes adjusting the engine speed, determining that the deicing part is the engine blade, and controlling the engine blade to rotate according to the engine speed included in the trigger operation, so as to simulate the ice shedding model based on the deicing rate.

[0106] Further, controlling the engine blades to rotate according to the engine speed included in the trigger operation includes: controlling the engine blades to alternately accelerate and decelerate according to the engine speed included in the trigger operation.

[0107] The ice scene simulation system provided by the embodiment of the present invention can execute the ice scene simulation method provided by any embodiment of the present invention, and has the corresponding functional modules and beneficial effects of executing the ice scene simulation method.

[0108] It is worth noting that in the embodiment of the above-mentioned ice scene simulation system, the various modules included are only divided according to functional logic, but are not limited to the above-mentioned division, as long as the corresponding functions can be achieved; in addition, the specific names of the functional units are only for the convenience of distinguishing each other, and are not used to limit the scope of protection of the present invention.

[0109] It should be understood by those skilled in the art that the modules or steps of the present invention described above can be implemented by a general-purpose computing device, they can be concentrated on a single computing device, or distributed on a network composed of multiple computing devices, optionally, they can be implemented by a program code executable by a computer device, so that they can be stored in a storage device and executed by the computing device, or they can be made into individual integrated circuit modules, or multiple modules or steps therein can be made into a single integrated circuit module for implementation. Thus, the present invention is not limited to any specific combination of hardware and software.

[0110] In addition, the acquisition, storage, use, and processing of data in the technical solution of the present invention are in compliance with the relevant provisions of national laws and regulations.

[0111] Note that the above are only preferred embodiments of the present invention and the technical principles used. Those skilled in the art will understand that the present invention is not limited to the specific embodiments herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present invention. Therefore, although the present invention has been described in more detail through the above embodiments, the present invention is not limited to the above embodiments, and may include more other equivalent embodiments without departing from the concept of the present invention, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. A method for simulating an ice scene, characterized in that: Applied to an ice scene simulation system, the ice scene simulation system comprises: a control device and an aircraft simulator, the aircraft simulator comprises a control module, and the method comprises: Determining a simulation type by the control device, the simulation type including an icing model and an anti-icing model; Determine the icing rate and icing location by the control device, simulate the icing amount of the icing location based on the icing location and the icing rate, and obtain the icing model, wherein the icing location includes the wing, fuselage, engine and sensor; A deicing rate and a deicing location are determined according to a trigger operation received by the control module, and the anti-icing model is simulated based on the deicing location and the deicing rate, wherein the deicing locations include wings, engine air inlets, sensors and engine blades, and the anti-icing model includes a general anti-icing model and an ice-swinging model, the general anti-icing model includes a wing anti-icing model in which the deicing location is the wing, an engine anti-icing model in which the deicing location is the engine air inlet, and a sensor anti-icing model in which the deicing location is the sensor, and the deicing location of the ice-swinging model is the engine blades.

2. The ice scene simulation method according to claim 1, characterized in that: The icing model includes a general icing model and a deep icing model. The general icing model includes a wing icing model, a fuselage icing model, an engine icing model and a sensor icing model. The icing parts of the wing icing model are the wings, the icing parts of the fuselage icing model are the fuselage, the icing parts of the engine icing model are the engines, the icing parts of the sensor icing model are the sensors, and the icing parts of the deep icing model are the wings, the fuselage, the engines and the sensors.

3. The ice scene simulation method according to claim 2, characterized in that: The icing model is simulated based on the icing location and the icing rate, including: Determining that the icing location is a wing, a fuselage, an engine, or a sensor, and simulating a general icing amount on the wing, the fuselage, the engine, or the sensor based on the icing rate to simulate the wing icing model, the fuselage icing model, the engine icing model, or the sensor icing model; The icing parts are determined to be wings, fuselage, engines and sensors. When the icing amount is greater than a preset icing amount, the deep icing amount is simulated based on the icing rate to simulate the deep icing model.

4. The ice scene simulation method according to claim 1, characterized in that: Determining a deicing rate and a deicing location according to a trigger operation received by the control module, and simulating the anti-icing model based on the deicing location and the deicing rate, including: The trigger operation includes turning on a wing de-icing button, determining that the de-icing part is a wing, determining the de-icing rate according to the trigger operation, and controlling the opening of a wing de-icing valve to simulate the wing anti-icing model based on the de-icing rate; The trigger operation includes turning on the engine de-icing button, determining that the de-icing location is the engine air intake, determining the de-icing rate according to the trigger operation, and controlling the engine nacelle de-icing valve to simulate the engine anti-icing model based on the de-icing rate; The trigger operation includes turning on a sensor de-icing button, determining the de-icing part as a sensor, determining the de-icing rate according to the trigger operation, and controlling the turning on of a heating wire to simulate the sensor anti-icing model based on the de-icing rate.

5. The ice scene simulation method according to claim 4, characterized in that: Controlling the opening of the wing de-icing valve to simulate the wing anti-icing model based on the de-icing rate includes: The wing de-icing valve is controlled to be opened within a preset time period, and the wing anti-icing model when the aircraft is on the ground is simulated based on the de-icing rate.

6. The ice scene simulation method according to claim 1, characterized in that: Determining a deicing rate and a deicing location according to a trigger operation received by the control module, and simulating the anti-icing model based on the deicing location and the deicing rate, including: The trigger operation includes adjusting the engine speed, determining that the deicing part is the engine blade, and controlling the engine blade to rotate according to the engine speed included in the trigger operation to simulate the ice-shedding model based on the deicing rate.

7. The ice scene simulation method according to claim 6, characterized in that: Controlling the engine blades to rotate according to the engine speed included in the triggering operation includes: The engine blades are controlled to alternately rotate at an accelerated speed and a decelerated speed according to the engine speed included in the trigger operation.

8. An ice scene simulation system, characterized in that: include: A control device and an aircraft simulator, the aircraft simulator comprising a control module, the control device being used to: determine a simulation type of an ice scene, the simulation type comprising an icing model and an anti-icing model; determine an icing rate and an icing location, simulate an icing amount of the icing location based on the icing location and the icing rate, and obtain the icing model, wherein the icing location comprises a wing, a fuselage, an engine, and a sensor; the control module being used to: determine a deicing rate and a deicing location according to a received trigger operation, simulate an anti-icing model based on the deicing location and the deicing rate, wherein the deicing location comprises a wing, an engine air inlet, a sensor, and an engine blade, the anti-icing model comprising a general anti-icing model and an ice-swinging model, the general anti-icing model comprising a wing anti-icing model in which the deicing location is a wing, an engine anti-icing model in which the deicing location is an engine air inlet, and a sensor anti-icing model in which the deicing location is a sensor, and the deicing location of the ice-swinging model is an engine blade.

Images