CN117644978A - Aircraft icing early warning method, system, electronic equipment and storage medium - Google Patents
Aircraft icing early warning method, system, electronic equipment and storage medium Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
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Abstract
The invention discloses an aircraft icing early warning method, an aircraft icing early warning system, electronic equipment and a storage medium, wherein the method comprises the following steps: acquiring current flight parameters of an aircraft; acquiring the total temperature of the surface of the machine body corresponding to the current flight parameter from a mapping relation between the pre-stored flight parameter and the total temperature; and responding to the total temperature of the surface of the machine body to be less than or equal to the critical total temperature, and carrying out aircraft icing early warning. The invention can reduce the possibility of false alarm of the icing detector and reduce the starting frequency of the anti-icing system. And no additional sensor is required to be installed or the aircraft is redesigned, so that the early warning of the icing of the surface of the aircraft is simply and efficiently finished.
Description
Technical Field
The invention relates to the technical field of aircraft anti-icing protection, in particular to an aircraft icing early warning method, an aircraft icing early warning system, electronic equipment and a storage medium.
Background
The aeroplane icing can greatly reduce the aerodynamic performance and the maneuvering performance of the aeroplane, and even cause serious accidents of the aeroplane destruction and the human death. The icing detector is used as an important component of the aircraft environment control system and is used for detecting an aircraft icing signal in real time and sending out alarm information. However, in practical applications, the icing detector may have a false alarm, that is, since the icing detector is usually installed on a windward location (such as a wing, a tail surface) or a nose surface, the installation position of the icing detector may cause the detected temperature to be lower than the total temperature of the incoming flow, so that the icing detector is frozen earlier than the machine body, and a false alarm is generated. Therefore, there is a need for an aircraft icing warning method with higher accuracy.
Disclosure of Invention
The invention provides an aircraft icing early warning method, an aircraft icing early warning system, electronic equipment and a storage medium, and aims to effectively solve the icing false alarm problem.
According to a first aspect of the present invention, the present invention provides an aircraft icing warning method, comprising:
acquiring current flight parameters of an aircraft;
acquiring the total temperature of the surface of the machine body corresponding to the current flight parameter from a mapping relation between the pre-stored flight parameter and the total temperature;
and responding to the total temperature of the surface of the machine body to be less than or equal to the critical total temperature, and carrying out aircraft icing early warning.
Further, before the step of obtaining the current flight parameters of the aircraft, the method further comprises:
acquiring an icing early warning signal generated by an icing detector;
and responding to the total temperature of the surface of the machine body is less than or equal to the critical total temperature, and performing aircraft icing early warning, wherein the method comprises the following steps of:
responding to the total temperature of the surface of the machine body being less than or equal to the critical total temperature, and carrying out aircraft icing early warning according to the icing early warning signal;
the icing early-warning signal is restrained in response to the total temperature of the surface of the machine body being greater than the critical total temperature;
the icing detector detects local icing or icing conditions to generate the icing early-warning signal.
Further, the current flight parameters include a trim configuration of the aircraft, a current flight altitude, a current flight speed, a current flight angle of attack, a current sideslip angle, and a current ambient static temperature.
Further, the mapping relation between the pre-stored flight parameter and the total temperature is obtained at least through one analysis of the following big data analysis methods: polynomial response surface, kriging model, radial basis function, support vector machine, multivariate interpolation and regression, and polynomial chaotic expansion.
Further, the mapping relation between the pre-stored flight parameters and the total temperature is obtained based on a polynomial response surface model, and the polynomial response surface model is constructed based on a flow field sample;
the step of obtaining the total temperature of the surface of the machine body corresponding to the current flight parameter from the mapping relation between the pre-stored flight parameter and the total temperature comprises the following steps:
determining a current flow field from the polynomial response surface model according to the current flight parameters, wherein the current flow field comprises surface total temperature information of each part of the aircraft;
acquiring the total temperature of the engine body surface corresponding to the part position from the current flow field according to the position information of a plurality of parts of the aircraft, and determining the minimum total temperature of the engine body surface from the total temperature of the engine body surface; the component position information is the position information of the component in the polynomial response surface model.
Further, the polynomial response surface model is obtained by the following method:
determining m static temperature sample working conditions according to an icing temperature altitude envelope of the aircraft;
coupling a flight envelope of the aircraft with the icing temperature altitude envelope according to the static temperature sample working conditions to obtain m x n sample working conditions;
acquiring m x n flow field samples based on the sample working condition;
and establishing a polynomial response surface model according to the flow field sample and by using a polynomial response surface method.
Further, the icing detector is at least one of a magnetostrictive icing detector, a capacitive icing detector, an optical fiber icing detector or a microwave icing detector.
According to a second aspect of the present invention, there is also provided an aircraft icing warning system comprising:
the flight parameter acquisition module is used for acquiring the current flight parameters of the aircraft;
the central processing module is used for acquiring the total temperature of the surface of the machine body corresponding to the current flight parameter from the mapping relation between the pre-stored flight parameter and the total temperature; and responding to the total temperature of the surface of the machine body to be less than or equal to the critical total temperature, and carrying out aircraft icing early warning.
Further, the flight parameter acquisition module comprises a total pressure sensor, a static pressure sensor, an attack angle sensor, a sideslip angle sensor and a total temperature sensor which are all connected with the central processing module;
the total pressure sensor is used for acquiring total pressure, the static pressure sensor is used for acquiring static pressure, the attack angle sensor is used for acquiring attack angle, the total temperature sensor is used for acquiring ambient static temperature, and the sideslip angle sensor is used for acquiring sideslip angle.
Further, the system also comprises a display module connected with the central processing module, and the display module performs early warning display when receiving the icing early warning signal.
According to a third aspect of the present invention, there is also provided an electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing the steps of the aircraft icing warning method as described above when executing the program.
According to a fourth aspect of the present invention there is also provided a storage medium having stored therein a plurality of instructions adapted to be loaded by a processor to perform the steps of an aircraft icing warning method as described above.
Through one or more of the above embodiments of the present invention, at least the following technical effects can be achieved: and inversion is carried out to obtain the total temperature of the surface of the aircraft body by using the detected current flight parameter and the mapping relation between the flight parameter and the total temperature obtained by the previous statistical analysis, the total temperature of the surface of the aircraft body is compared with the critical total temperature, and the icing early warning is carried out under the condition that the total temperature of the surface of the aircraft body is less than or equal to the critical total temperature instead of the icing detector early warning, so that the possibility of false alarm of the icing detector is reduced, and the starting frequency of an icing prevention system is reduced. And no additional sensor is required to be installed or the aircraft is redesigned, so that the early warning of the icing of the surface of the aircraft is simply and efficiently finished.
Drawings
The technical solution and other advantageous effects of the present invention will be made apparent by the following detailed description of the specific embodiments of the present invention with reference to the accompanying drawings.
FIG. 1 is a flowchart of an aircraft icing warning method according to an embodiment of the present invention;
FIG. 2 is a second flowchart of an aircraft icing warning method according to an embodiment of the present invention;
FIG. 3 is a schematic flow chart of a process for obtaining a polynomial response surface model according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of an aircraft icing early warning system according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to fall within the scope of the invention.
In the description of the present invention, it should be noted that, unless explicitly specified and defined otherwise, the term "and/or" herein is merely an association relationship describing associated objects, and means that three relationships may exist, for example, a and/or B may mean: a exists alone, A and B exist together, and B exists alone. The character "/" herein generally indicates that the associated object is an "or" relationship unless otherwise specified.
In the actual operation process of the aircraft, the icing detector is found to generate icing when the total temperature of the surface of the aircraft is above 13 ℃ in the course of the descent of the aircraft, and a ICEDETECTED alarm is given out, which is not consistent with the original icing early-warning condition, wherein the preset icing early-warning condition is that the total temperature (TAT) of the surface of the aircraft is equal to or lower than 10 ℃ (50 DEG F) when the aircraft is in flight, and the icing early-warning is given out when any form of visible water and gas (such as cloud, fog, rain, snow and ice with visibility equal to or lower than 1600m (1 mile) exists. That is, false alarms occur in the icing detector.
Through root cause analysis and problem reproduction, it is found that since the icing detector is installed at a position lower than the total incoming flow temperature, the icing detector is easier to freeze than the aircraft body (taking the above example as an example, when the icing detector reaches the pre-warning total temperature of 10 ℃ earlier than the aircraft body, the total surface temperature of the aircraft body is more than 13 ℃ actually, and the icing pre-warning condition is not satisfied), the icing detector icing can trigger the icing alarm, and after triggering the icing alarm, the anti-icing system can be started. However, in actual situations, the aircraft body is not frozen, and the anti-icing system is not necessarily started.
Aiming at the situation that the icing detector has false alarm, the aircraft icing early warning method, the system, the electronic equipment and the storage medium provided by the invention are used for solving the problems of false alarm of the icing detector and false start of the anti-icing system.
The invention provides an aircraft icing early warning method, an aircraft icing early warning system, electronic equipment and a storage medium.
Fig. 1 is a flowchart of an aircraft icing early-warning method according to an embodiment of the present invention, fig. 2 is a flowchart of a second aircraft icing early-warning method according to an embodiment of the present invention, and as shown in fig. 1 and fig. 2, an aircraft icing early-warning method includes the following steps:
s101, acquiring current flight parameters of the aircraft.
In this step, the current flight parameters of the aircraft are acquired by various sensors originally installed on the aircraft, for example, the current flight altitude of the aircraft is acquired by using an atmospheric pressure sensor, a radar altitude sensor, a GPS, etc.; acquiring the current flight speed of the aircraft through an airspeed sensor, a ground speed sensor, an inertial navigation system, a GPS (global positioning system) and the like; the angle of attack of the flight is obtained by an angle of attack sensor, etc.
S102, acquiring the total temperature of the surface of the machine body corresponding to the current flight parameter from a mapping relation between the pre-stored flight parameter and the total temperature.
In this step, the mapping relationship between the pre-stored flight parameter and the total temperature may be obtained by performing statistical analysis on the collected or simulated flight parameter and the corresponding body surface total temperature data in advance, and may be one of polynomial response surfaces, kriging models, radial basis functions, support vector machines, multivariate interpolation and regression, polynomial chaotic expansion and other approximate models.
After the current flight parameter is obtained, the total temperature of the engine body surface under the current flight parameter is obtained from the mapping relation between the pre-stored flight parameter and the total temperature, namely the total temperature of the engine body surface is obtained through inversion of the mapping relation between the current flight parameter and the total temperature.
It should be noted that the total temperature refers to the temperature of the air around the aircraft plus the additional heat generated by the movement of the aircraft and the emission of the engine. It is a parameter comprehensively considering air temperature and dynamic heat, and is important for the performance and safety of the aircraft.
S103, responding to the total temperature of the surface of the machine body to be less than or equal to the critical total temperature, and carrying out aircraft icing early warning.
In this step, if the total temperature of the body surface obtained by the inversion in S102 is also less than or equal to the critical total temperature, the aircraft is directly subjected to the early warning of icing, and the anti-icing system is started according to the early warning of icing of the aircraft.
Wherein, critical total temperature TAT Cri Based on aircraft design characteristics and safety level, TAT is typically determined Cri ≥0℃。
According to the aircraft icing early warning method provided by the embodiment of the invention, the total temperature of the aircraft body surface is obtained through inversion by using the detected current flight parameter and the mapping relation between the flight parameter and the total temperature obtained through the previous statistical analysis, and the total temperature of the aircraft body surface is compared with the critical total temperature, and the icing early warning is carried out under the condition that the total temperature of the aircraft body surface is less than or equal to the critical total temperature instead of the icing detector early warning, so that the possibility of false alarm of the icing detector is reduced, and the starting frequency of an icing prevention system is reduced. And no additional sensor is required to be installed or the aircraft is redesigned, so that the early warning of the icing of the surface of the aircraft is simply and efficiently finished.
In some embodiments of the invention, after S102, the method further comprises:
determining whether the aircraft is in an icing pre-warning scene according to the acquired current flight parameters of the aircraft, for example, determining that the aircraft is in the icing pre-warning scene when the ambient static temperature is less than 10 ℃ and visible moisture (such as cloud, fog, rain, snow, freezing rain or ice crystals with visibility less than or equal to 1 mile) exists in any mode. When the aircraft is in an icing early warning scene, acquiring the total temperature of the surface of the aircraft body corresponding to the current flight parameter from a mapping relation between the pre-stored flight parameter and the total temperature, and judging the icing early warning of the aircraft.
In other embodiments of the present invention, ice warning may also be implemented in combination with the ice detector, and in particular, before S101, the method further includes:
acquiring an icing early warning signal generated by an icing detector;
correspondingly, S103 includes:
responding to the total temperature of the surface of the machine body being less than or equal to the critical total temperature, and carrying out aircraft icing early warning according to the icing early warning signal;
the icing early-warning signal is restrained in response to the total temperature of the surface of the machine body being greater than the critical total temperature;
the icing detector detects local icing or icing conditions to generate the icing early-warning signal.
In this embodiment, according to the working principle of the icing detector, it is known that whether the icing detector detects local icing at the installation position of the icing detector or whether icing conditions (specifically, temperature, liquid water content, droplet size, etc.) are met, and if the icing detector detects local icing at the installation position of the icing detector or the icing conditions are met, an icing early warning signal is generated. However, due to the limitation of the installation position of the icing detector, the situation of false alarm may exist, and when the icing early-warning signal is acquired, the current flight parameter of the aircraft is utilized to determine whether the icing early-warning signal is false alarm or not.
The icing detector is at least one of a magnetostrictive icing detector, a capacitive icing detector, an optical fiber icing detector, or a microwave icing detector, which is not limited.
If the total temperature of the body surface obtained by the inversion in S102 is greater than the critical total temperature, it is determined that the icing detector reaches the critical total temperature first, but the body surface does not reach the critical total temperature yet, and the icing early-warning signal generated by the icing detector is misinformation and needs to be suppressed to prevent the unnecessary anti-icing system from being started. The method specifically can intercept the icing pre-warning signal of the time, and can display a prompt that the icing pre-warning signal is possibly misreported while displaying the icing pre-warning signal, or other inhibition measures which do not pre-warn the icing pre-warning signal of the time.
According to the aircraft icing early warning method provided by the embodiment of the invention, the icing early warning signal originally output by the icing detector is further analyzed, and whether the possibility of false alarm exists is judged. The method comprises the steps of inversion to obtain the total temperature of the surface of an aircraft body by using the detected current flight parameters and the mapping relation between the flight parameters and the total temperature obtained by the previous statistical analysis, comparing the total temperature of the surface of the aircraft with the critical total temperature of an icing early warning signal generated by an icing detector, and determining that the icing detector does not misreport under the condition that the total temperature of the surface of the aircraft is less than or equal to the critical total temperature, and carrying out early warning according to the icing early warning signal. And under the condition that the total temperature of the surface of the machine body is larger than the critical total temperature, determining that the situation that the icing detector reaches the critical total temperature before the machine body to generate false alarm occurs, and inhibiting the icing early-warning signal. Therefore, the invention can accurately screen the scene that the icing detector is frozen and the aircraft body is not frozen, thereby filtering the icing alarm signal, reducing the starting frequency of the anti-icing system, and improving the operation economy and market competitiveness of the aircraft on the premise of not reducing the safety level. And the position structure of the ice detector, the generation of an ice early warning signal and the like do not need to be redesigned, so that the method is simple and effective.
In some embodiments of the invention, the current flight parameters include a trim configuration Config of the aircraft, a current flight altitude H, a current flight speed Ma, a current angle of flight attack AOA, a current sideslip angle AOS, and a current ambient static temperature SAT.
The configuration Config (specifically, the information of the configuration of the wing slat) of the airplane refers to the position and the morphological configuration of the wing and the flap of the airplane, and can be obtained through a high-lift system in the airplane.
The flight attack angle AOA is obtained through an attack angle sensor, the current sideslip angle AOS is obtained through a sideslip angle sensor, and the current ambient static temperature SAT is obtained through a total temperature sensor.
The flying height H and the flying speed Ma are calculated according to the obtained atmospheric data, for example, the flying speed Ma is calculated according to the standard sea level pressure value, the sound speed on the standard sea level, the corrected static pressure value, the corrected full pressure value, the dynamic pressure value and other data.
Based on the flight parameters, the mapping relation between the pre-stored flight parameters and the total temperature specifically refers to the mapping relation between the flight configuration, the altitude, the speed, the attack angle, the sideslip angle, the ambient static temperature and the total temperature of the surface of the aircraft body.
The mapping relation among the flight configuration, the altitude, the speed, the attack angle, the sideslip angle, the ambient static temperature and the total surface temperature of the aircraft body can be obtained by a response surface method in a nonlinear regression analysis method.
After obtaining the mapping relation among the flight configuration, the altitude, the speed, the attack angle, the sideslip angle, the ambient static temperature and the total body surface temperature of the aircraft, the total body surface temperature is obtained by the following steps:
and determining a current flow field from the response surface model according to the current flight parameters, wherein the current flow field comprises surface total temperature information of each part of the aircraft. Specifically, a current flow field P 'corresponding to the current flight parameter is determined from the response surface model p=f (Config, H, ma, AOA, AOS, SAT) +epsilon according to the detected current flight parameter, and the current flow field P' includes the total body surface temperature of each position.
And acquiring the total body surface temperature corresponding to the part position from the current flow field according to the information of the part positions of the aircraft, and determining the minimum total body surface temperature from the total body surface temperatures. Wherein the component position information is the position information of the component in the response surface model.
That is, after determining the current flow field information, determining the total body surface temperature corresponding to the components from the current flow field information according to the position information of the components of the aircraft, specifically determining the total body surface temperatures of different components in the response surface model according to the position information of the components, i.e., TAT (X, Y, X) =p TAT (X,Y,X)。
Then determining the minimum total body surface temperature, TAT, from the total body surface temperatures corresponding to the components min ～[Config,H,Ma,AOA,AOS,SAT]。
The plurality of component position information refers to position information of all components exposed to air, and the components include, but are not limited to, wings, horizontal tails, vertical tails, nacelle, fuselage, and the like.
Or, the total temperature of the machine body surface at all positions in the current flow field can be directly searched to determine the minimum total temperature of the machine body surface.
After the total temperature of the minimum body surface is determined in the global or local searching mode, comparing the total temperature of the minimum body surface with the critical total temperature, and if the total temperature of the minimum body surface is less than or equal to the critical total temperature, carrying out early warning according to the icing early warning signal. And if the minimum total temperature of the surface of the machine body is greater than the critical total temperature, inhibiting the icing early-warning signal.
In some embodiments of the invention, the response surface model is obtained by the steps shown in fig. 3:
and determining m static temperature sample working conditions according to the icing temperature altitude envelope of the aircraft.
Coupling a flight envelope of the aircraft with the icing temperature altitude envelope according to the static temperature sample working conditions to obtain m x n sample working conditions x min ＝[Config,H,Ma,AOA,AOS,SAT]。
And obtaining m x n flow field samples based on the sample working condition. The sample working conditions can be simulated and calculated to form m x n flow field samples through CFD simulation, and the flow field samples can be obtained through numerical simulation methods of other modes such as a finite element method and a boundary element method, and the flow field samples are not limited.
And establishing a response surface model according to the flow field sample by using a response surface method. In particular a higher order response surface model.
Based on any one of the above embodiments, another embodiment of the present invention further provides an aircraft icing pre-warning system, and fig. 4 is a schematic structural diagram of the aircraft icing pre-warning system provided by the present invention, as shown in fig. 4, where the aircraft icing pre-warning system includes a flight parameter acquisition module 401 and a central processing module 402.
The flight parameter obtaining module 401 is configured to obtain a current flight parameter of the aircraft.
In this module, specifically include total pressure sensor, static pressure sensor, angle of attack sensor and total temperature sensor, wherein, total pressure sensor is used for acquireing total pressure, static pressure sensor is used for acquireing static pressure, angle of attack sensor is used for acquireing the angle of attack, total temperature sensor is used for acquireing the ambient static temperature, the angle of sideslip sensor is used for acquireing the angle of sideslip.
And calculating the flying speed and the flying height based on the obtained total pressure, static pressure and other atmospheric data, thereby obtaining the flying speed and the flying height.
The central processing module 402 is configured to obtain a total body surface temperature corresponding to the current flight parameter from a mapping relationship between a pre-stored flight parameter and the total temperature; and responding to the total temperature of the surface of the machine body to be less than or equal to the critical total temperature, and carrying out aircraft icing early warning.
The total pressure sensor, the static pressure sensor, the attack angle sensor, the total temperature sensor and the icing detector are all in communication connection with the central processing module, and are arranged near the aircraft nose, and the measured flight parameters represent the real incoming flow condition of the far field of the aircraft.
In some embodiments of the invention, the system further comprises a scenario triggering module that determines whether the aircraft is in an icing warning scenario based on obtaining current flight parameters of the aircraft, for example, when the ambient static temperature is less than 10 ℃, and there is visible moisture (e.g., cloud, fog with visibility less than or equal to 1 mile, rain, snow, freezing rain, or ice crystals) in any manner. When the aircraft is in the icing pre-warning scene, the central processing module 402 acquires the total temperature of the surface of the aircraft corresponding to the current flight parameter from the mapping relation between the pre-stored flight parameter and the total temperature, and judges the icing pre-warning of the aircraft.
In some embodiments of the invention, the system further comprises an icing detector for generating the icing warning signal when the detected total temperature reaches a critical total temperature.
The central processing module 402 is configured to perform early warning according to the icing early warning signal in response to the total temperature of the body surface being less than or equal to the critical total temperature, and suppress the icing early warning signal in response to the total temperature of the body surface being greater than the critical total temperature.
By combining the detection result of the icing detector and the data inversion result, whether icing early warning is carried out or not is finally determined, so that the early warning accuracy is improved, and the false alarm rate of the icing detector is reduced.
In some embodiments of the present invention, the system further includes a display module connected to the central processing module, where the display module performs early warning display when receiving the icing early warning signal, and the display module is disposed in the cockpit, where it should be noted that the display may be displaying the icing early warning signal on a display screen, or may remind the pilot by performing voice broadcasting through a related playing device, which is not limited thereto.
In addition, the aircraft icing early warning system corresponds to the aircraft icing early warning method, and is not described herein.
Based on any of the foregoing embodiments, another embodiment of the present application further provides an electronic device, which may include: a Processor (Processor), a communication interface (Communications Interface), a Memory (Memory) and a communication bus, wherein the Processor, the communication interface, and the Memory communicate with each other via the communication bus. The processor may invoke logic instructions in the memory to perform the battery charge control method described above.
Further, the logic instructions in the memory described above may be implemented in the form of software functional units and stored in a computer-readable storage medium when sold or used as a stand-alone product. Based on such understanding, the technical solution of the present application may be embodied essentially or in a part contributing to the prior art or in a part of the technical solution, in the form of a software product stored in a storage medium, including several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the methods described in the embodiments of the present application. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), a magnetic disk, or an optical disk, or other various media capable of storing program codes.
Further, the logic instructions in the memory described above may be implemented in the form of software functional units and stored in a computer-readable storage medium when sold or used as a stand-alone product. Based on such understanding, the technical solution of the present application may be embodied essentially or in a part contributing to the prior art or in a part of the technical solution, in the form of a software product stored in a storage medium, including several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the methods described in the embodiments of the present application. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), a magnetic disk, or an optical disk, or other various media capable of storing program codes.
In another aspect, an embodiment of the present invention further provides a storage medium having a plurality of instructions stored thereon, where the instructions are adapted to be loaded by a processor to perform the aircraft icing early warning method provided in the foregoing embodiments, for example, including: acquiring current flight parameters of an aircraft; acquiring the total temperature of the surface of the machine body corresponding to the current flight parameter from a mapping relation between the pre-stored flight parameter and the total temperature; and responding to the total temperature of the surface of the machine body to be less than or equal to the critical total temperature, and carrying out aircraft icing early warning.
The apparatus embodiments described above are merely illustrative, wherein the elements illustrated as separate elements may or may not be physically separate, and the elements shown as elements may or may not be physical elements, may be located in one place, or may be distributed over a plurality of network elements. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art will understand and implement the present invention without undue burden.
From the above description of the embodiments, it will be apparent to those skilled in the art that the embodiments may be implemented by means of software plus necessary general hardware platforms, or of course may be implemented by means of hardware. Based on this understanding, the foregoing technical solution may be embodied essentially or in a part contributing to the prior art in the form of a software product, which may be stored in a computer readable storage medium, such as ROM/RAM, a magnetic disk, an optical disk, etc., including several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the method described in the respective embodiments or some parts of the embodiments.
In summary, although the present invention has been described in terms of the preferred embodiments, the preferred embodiments are not limited to the above embodiments, and various modifications and changes can be made by one skilled in the art without departing from the spirit and scope of the invention, and the scope of the invention is defined by the appended claims.
Claims (12)
1. An aircraft icing early warning method is characterized by comprising the following steps:
acquiring current flight parameters of an aircraft;
acquiring the total temperature of the surface of the machine body corresponding to the current flight parameter from a mapping relation between the pre-stored flight parameter and the total temperature;
and responding to the total temperature of the surface of the machine body to be less than or equal to the critical total temperature, and carrying out aircraft icing early warning.
2. The aircraft icing warning method of claim 1, wherein prior to said step of obtaining current flight parameters of the aircraft, the method further comprises:
acquiring an icing early warning signal generated by an icing detector;
and responding to the total temperature of the surface of the machine body is less than or equal to the critical total temperature, and performing aircraft icing early warning, wherein the method comprises the following steps of:
responding to the total temperature of the surface of the machine body being less than or equal to the critical total temperature, and carrying out aircraft icing early warning according to the icing early warning signal;
the icing early-warning signal is restrained in response to the total temperature of the surface of the machine body being greater than the critical total temperature;
the icing detector detects local icing or icing conditions to generate the icing early-warning signal.
3. The aircraft icing warning method of claim 1 wherein said current flight parameters comprise a trim configuration of the aircraft, a current flight altitude, a current flight speed, a current flight angle of attack, a current sideslip angle and a current ambient static temperature.
4. The aircraft icing pre-warning method according to claim 1, wherein the pre-stored mapping relationship between flight parameters and total temperature is obtained at least by one of the following big data analysis methods: polynomial response surface, kriging model, radial basis function, support vector machine, multivariate interpolation and regression, and polynomial chaotic expansion.
5. The aircraft icing pre-warning method according to claim 4, wherein the mapping relationship between the pre-stored flight parameters and the total temperature is obtained based on a polynomial response surface model, which is constructed based on a flow field sample;
the step of obtaining the total temperature of the surface of the machine body corresponding to the current flight parameter from the mapping relation between the pre-stored flight parameter and the total temperature comprises the following steps:
determining a current flow field from the polynomial response surface model according to the current flight parameters, wherein the current flow field comprises surface total temperature information of each part of the aircraft;
acquiring the total temperature of the engine body surface corresponding to the part position from the current flow field according to the position information of a plurality of parts of the aircraft, and determining the minimum total temperature of the engine body surface from the total temperature of the engine body surface; the component position information is the position information of the component in the polynomial response surface model.
6. The aircraft icing warning method according to claim 5, wherein the polynomial response surface model is obtained by:
determining m static temperature sample working conditions according to an icing temperature altitude envelope of the aircraft;
coupling a flight envelope of the aircraft with the icing temperature altitude envelope according to the static temperature sample working conditions to obtain m x n sample working conditions;
acquiring m x n flow field samples based on the sample working condition;
and establishing a polynomial response surface model according to the flow field sample and by using a polynomial response surface method.
7. The aircraft icing warning method of any one of claims 2-6, wherein the icing detector is at least one of a magnetostrictive, capacitive, fiber optic or microwave icing detector.
8. An aircraft icing warning system, comprising:
the flight parameter acquisition module is used for acquiring the current flight parameters of the aircraft;
the central processing module is used for acquiring the total temperature of the surface of the machine body corresponding to the current flight parameter from the mapping relation between the pre-stored flight parameter and the total temperature; and responding to the total temperature of the surface of the machine body to be less than or equal to the critical total temperature, and carrying out aircraft icing early warning.
9. The aircraft icing pre-warning system of claim 8 wherein said flight parameter acquisition module comprises a total pressure sensor, a static pressure sensor, an angle of attack sensor, an sideslip angle sensor and a total temperature sensor all connected to said central processing module;
the total pressure sensor is used for acquiring total pressure, the static pressure sensor is used for acquiring static pressure, the attack angle sensor is used for acquiring attack angle, the total temperature sensor is used for acquiring ambient static temperature, and the sideslip angle sensor is used for acquiring sideslip angle.
10. The aircraft icing warning system of claim 8 further comprising a display module coupled to the central processing module, the display module providing a warning display upon receipt of an icing warning signal.
11. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the processor performs the steps of the aircraft icing warning method according to any of claims 1 to 7 when the program is executed.
12. A storage medium having stored therein a plurality of instructions adapted to be loaded by a processor to perform the steps of the aircraft icing warning method according to any of claims 1 to 7.
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| CN202311813071.9A CN117644978A (en) | 2023-12-26 | 2023-12-26 | Aircraft icing early warning method, system, electronic equipment and storage medium |
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