CN111874234B - Ice accumulation prediction method based on Ic index and relative vorticity and airborne equipment - Google Patents
Ice accumulation prediction method based on Ic index and relative vorticity and airborne equipment Download PDFInfo
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- CN111874234B CN111874234B CN202010709408.1A CN202010709408A CN111874234B CN 111874234 B CN111874234 B CN 111874234B CN 202010709408 A CN202010709408 A CN 202010709408A CN 111874234 B CN111874234 B CN 111874234B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/20—Means for detecting icing or initiating de-icing
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- G—PHYSICS
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- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
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- G08G5/0091—Surveillance aids for monitoring atmospheric conditions
Abstract
The invention discloses an ice accumulation prediction method based on an Ic index and relative vorticity and airborne equipment. The working principle of the airborne equipment is that an airborne receiver is used for receiving a predicted data product, the temperature and the relative vorticity are introduced as judgment standards on the basis of forecasting ice accumulation by an Ic index algorithm, whether ice accumulation occurs in a flight area and the degree of the ice accumulation possibly occur are predicted through numerical simulation, and the predicted ice accumulation is displayed on a display. The method overcomes the defect that the existing Ic ice accumulation index only considers two influence factors of temperature and relative humidity and has poor rationality for predicting the ice accumulation degree, so that a pilot can make a more effective coping strategy before flying, and the method has important significance for optimizing the flight safety and airspace resources of an airplane.
Description
Technical Field
The invention belongs to the technical field of aircraft icing prediction, and particularly relates to a method for forecasting aircraft icing and an icing degree based on an Ic index algorithm and airborne equipment.
Background
When an airplane flies in a cloud layer containing supercooled water drops, certain parts on the surface of the airplane body are quickly condensed into ice, the shape and the surface characteristics of the ice are changed, the aerodynamic characteristics of the airplane are seriously influenced, the resistance is increased, the lift force is reduced, the control of horizontal tails and vertical tails is reduced, and the airplane can be out of control in serious conditions to cause flight accidents. According to data survey statistics, flight accidents caused by ice accumulation in the United states during the period from 1983 to 2003 account for 13% of total accidents. Among the accidents caused by ice accretion between 1990 and 2000, 92% of the accidents caused by ice accretion in the air were accidents.
At present, a numerical prediction method is a commonly used prediction method for aircraft ice accretion, and methods combining numerical prediction or numerical prediction with aircraft ice accretion experience formulas, such as an Ic ice accretion index, a RAOB ice accretion algorithm, a NAWAU ice accretion algorithm, a scem (vv) ice accretion index and the like, are mostly used.
It should be noted that the main weather factors influencing the aircraft icing include water vapor flux divergence, vertical speed, relative vorticity and the like, but the Ic index algorithm mostly used in the domestic aircraft icing forecasting method only considers atmospheric temperature and relative humidity threshold values, does not consider other weather factors, has an empty report in time and space, is low in accuracy, and is low in the degree of rationality of the icing degree forecast, so that the improvement of the accuracy degree of the aircraft icing prediction by people is restricted, and when the empty report icing airspace is avoided in flight, the waste of airspace resources can be caused.
Disclosure of Invention
In order to solve the technical problems, the invention provides a method for forecasting the ice accretion and the ice accretion degree of an aircraft based on an Ic index algorithm, so as to improve the accuracy of forecasting the ice accretion of the aircraft, overcome the defect that the existing Ic ice accretion index only considers two influence factors, namely temperature and relative humidity, and has poor rationality in forecasting the ice accretion degree, provide a more effective coping strategy for a pilot before the flight, and have important significance for optimizing the flight safety and airspace resources of the aircraft.
The invention adopts the following technical scheme for solving the technical problems:
an ice accretion prediction method based on an Ic index and relative vorticity comprises the following specific steps:
step 1, establishing an Ic icing index prediction equation, and calculating an Ic icing index:
Ic＝[(Rh-50)×2]×[t×(t+14)/(-49)]
wherein: rhRelative humidity, t is atmospheric temperature;
step 2, predicting the ice accretion of the airplane according to the following judgment basis:
if t is greater than 0, the aircraft has no ice accumulation, if t is less than or equal to 0 and the relative vorticity vo is less than or equal to 0, if t is less than or equal to 0 and vo is greater than or equal to 0 and less than or equal to Ic <50, the aircraft has slight ice accumulation, if t is less than or equal to 0 and vo is greater than 0 and less than or equal to 50 and Ic <80, the aircraft has moderate ice accumulation, and if t is less than or equal to 0 and vo is greater than 0 and Ic is greater than or equal to 80, the aircraft has severe ice accumulation.
An onboard ice accretion prediction device comprises a receiver, a computer processing system and an ice accretion prediction result display system;
the receiver is used for receiving the atmospheric temperature, the relative humidity and the relative vorticity and sending the atmospheric temperature, the relative humidity and the relative vorticity to the computer processing system;
the computer processing system calculates the Ic ice accumulation index according to the atmospheric temperature and the relative humidity received by the receiver; and obtaining the prediction result of the ice accretion of the airplane according to the following judgment basis: if t is greater than 0, the aircraft has no ice accumulation, if t is less than or equal to 0 and the relative vorticity vo is less than or equal to 0, the aircraft has no ice accumulation, if t is less than or equal to 0 and vo is greater than 0 and less than or equal to 0 and Ic <50, the aircraft has slight ice accumulation, if t is less than or equal to 0 and vo is greater than 0 and less than or equal to 50 and Ic <80, the aircraft has moderate ice accumulation, and if t is less than or equal to 0 and vo is greater than 0 and Ic is greater than or equal to 80, the aircraft has severe ice accumulation;
the ice accretion prediction result display system is used for displaying the prediction result of the aircraft ice accretion.
Further, the receiver comprises a receiving antenna, an input circuit, a high-frequency amplifier, a mixer, an intermediate-frequency amplifier, a demodulator and a low-frequency amplifier; the receiving antenna receives a numerical prediction product sent by ground equipment, the input circuit extracts the atmospheric temperature, the relative humidity and the relative vorticity sent by the ground equipment from the numerical prediction product received by the receiving antenna, the high-frequency amplifier amplifies the output of the input circuit, the mixer converts the output of the high-frequency amplifier into an intermediate-frequency signal, the intermediate-frequency amplifier amplifies the output of the mixer, the demodulator demodulates the output of the intermediate-frequency amplifier, and the low-frequency amplifier amplifies the output of the demodulator.
Compared with the prior art, the invention adopting the technical scheme has the following technical effects: according to the method, the temperature and the relative vorticity are introduced as judgment standards on the basis of the forecast of the ice accumulation by the Ic index algorithm, so that the accuracy of the forecast of the ice accumulation of the airplane is improved, the defect that the forecast rationality of the ice accumulation degree is poor due to the fact that the existing Ic ice accumulation index only considers two influence factors, namely the temperature and the relative humidity is overcome, a pilot can make a more effective coping strategy before flying, and the method has important significance for the optimization of airplane flying safety and airspace resources.
Drawings
FIG. 1 is a flow chart of the method for forecasting aircraft icing and icing degree based on the Ic index algorithm according to the present invention;
fig. 2 is a display information diagram of the 550 hectopascal ice-accretion predicting device in a certain area at a certain time according to the invention.
Detailed Description
The method for forecasting the ice accretion and the ice accretion degree of the airplane based on the Ic index algorithm and the airborne equipment adopted by the invention are described in detail with reference to the attached drawings and specific examples.
The established prediction equation of the ice accumulation index for the Ic is shown in (1), and is used for calculating the ice accumulation index for the Ic and preliminarily judging the ice accumulation condition of the airplane.
Ic＝[(Rh-50)×2]×[t×(t+14)/(-49)] (1)
Wherein R ishRelative humidity (%) and temperature (deg.C) were obtained from the numerically predicted product. The relative humidity part in the formula represents the change process of the water vapor condition in the atmosphere and the size of the water drop, and the maximum and minimum values are taken when the relative humidity is 100% and 50%, respectively. The temperature part shows the law of the size and quantity of water drops as a function of temperature, taking the minimum value 0 when the temperature T is-14 ℃ and 0 ℃, and [ T x (T +14)/(-49) when the temperature T is-7 ℃]The maximum value of 1 is taken in part, i.e. the variation in size and number of water droplets varies over the range of t-14 ℃ to 0 ℃. The international civil aviation organization recommends the Ic icing index to be divided as follows: when Ic is more than 0 and less than or equal to 50, judging that slight ice accretion exists; ic is more than 50 and less than or equal to 80, and moderate ice accumulation is judged; ic > 80, judging that there is serious ice accumulation, but because only the temperature and relative humidity threshold values are considered, other atmospheric factors are not considered, the false alarm rate is higher. Supercooled water is a factor for directly judging whether ice accretion is possible, the temperature of less than 0 ℃ is a necessary condition for the existence of the supercooled water, and a large number of literature researches show that the ice accretion temperature is generally between 0 and-15 ℃, so t is introduced<0 is used as a direct condition for judging whether or not the ice accretion occurs.
Relative vorticity is an important weather element affecting ice accretion formation and may represent a condition of airflow movement. When the relative vorticity of the atmosphere is a positive value, the positive vorticity exists in the area, the advection of the positive vorticity in the air is favorable for causing the ascending motion, and the water vapor carried by the ascending motion is favorable for forming the accumulated ice of the airplane, so that the accuracy of the accumulated ice prediction is further improved by introducing the relative vorticity.
The flowchart for forecasting the ice accretion and the ice accretion degree of the airplane based on the Ic index algorithm is shown in fig. 1, the judgment basis of the ice accretion of the airplane is that the airplane does not have ice accretion if t is greater than 0, the airplane does not have ice accretion if t is less than or equal to 0 and the relative vorticity vo is less than or equal to 0, the airplane has light ice accretion if t is less than or equal to 0 and vo is greater than or equal to 0 and less than or equal to 0 and Ic is less than or equal to 50, the airplane has moderate ice accretion if t is less than or equal to 0 and vo is greater than or equal to 0 and is greater than or equal to Ic 80, and the airplane has severe ice accretion if t is less than or equal to 0 and vo is greater than or equal to 80.
The invention provides an airborne ice accretion prediction device, which comprises a receiver, a computer processing system and an ice accretion prediction result display system, wherein the receiver is used for receiving a signal from the computer processing system; the receiver is used for receiving the atmospheric temperature, the relative humidity and the relative vorticity and sending the atmospheric temperature, the relative humidity and the relative vorticity to the computer processing system; the computer processing system calculates the Ic ice accumulation index according to the atmospheric temperature and the relative humidity received by the receiver; and obtaining the prediction result of the ice accretion of the airplane according to the following judgment basis: if t is greater than 0, the aircraft has no ice accumulation, if t is less than or equal to 0 and the relative vorticity vo is less than or equal to 0, the aircraft has no ice accumulation, if t is less than or equal to 0 and vo is greater than 0 and less than or equal to 0 and Ic <50, the aircraft has slight ice accumulation, if t is less than or equal to 0 and vo is greater than 0 and less than or equal to 50 and Ic <80, the aircraft has moderate ice accumulation, and if t is less than or equal to 0 and vo is greater than 0 and Ic is greater than or equal to 80, the aircraft has severe ice accumulation; the ice accretion prediction result display system is used for displaying the prediction result of the airplane ice accretion.
Further, the receiver comprises a receiving antenna, an input circuit, a high-frequency amplifier, a mixer, an intermediate-frequency amplifier, a demodulator and a low-frequency amplifier; the receiving antenna receives a numerical prediction product sent by ground equipment, the input circuit extracts the atmospheric temperature, the relative humidity and the relative vorticity sent by the ground equipment from the numerical prediction product received by the receiving antenna, the high-frequency amplifier amplifies the output of the input circuit, the mixer converts the output of the high-frequency amplifier into an intermediate-frequency signal, the intermediate-frequency amplifier amplifies the output of the mixer, the demodulator demodulates the output of the intermediate-frequency amplifier, and the low-frequency amplifier amplifies the output of the demodulator. Because the received signal is often very weak and the noise generated in the mixer is often very large, the demodulator cannot work normally, and the receiving efficiency of the receiver is directly influenced, a high-frequency amplifier is arranged at the front stage of the mixer and has an amplification effect on the weak high-frequency signal, so that the signal-to-noise ratio is improved. The function of the if amplifier is to amplify the if signal output from the mixer, and its gain directly affects the sensitivity of the handset. The demodulator is used for demodulating the signal, stripping the original signal from the intermediate frequency signal and recovering the original low frequency signal. The low-frequency amplifier is used for amplifying low-frequency signals so as to meet the requirements of terminal devices.
The input end of the ice accumulation prediction result display system is used for being connected with a computer system, receiving ice accumulation prediction data and displaying the predicted ice accumulation degree by using different symbols.
The airborne icing prediction equipment of the invention utilizes an airborne receiver to receive a prediction data product, introduces temperature and mutual vorticity as judgment standards on the basis of forecasting icing by an Ic index algorithm, numerically simulates and predicts whether icing occurs in a flight area and the degree of possible icing, and displays the degree on a display.
The invention is described in further detail below with reference to the attached drawings and specific examples, which are provided for illustration only and are not intended to limit the scope of the invention.
Example (c): 26/10/2010, the ice accretion of a medium-heavy airplane appears in a certain airplane near 31.38 degrees N and 105.8 degrees E, and the flight record shows that the ice accretion time is 03: 33-03: 55(UTC), and the flying height is 4700 m. Airborne icing prediction equipment is set at 00: the forecast of ice accretion at 550 hectopamps at 00 is shown in figure 2.
The above description is only an embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can understand that the modifications or substitutions within the technical scope of the present invention are included in the scope of the present invention, and therefore, the scope of the present invention should be subject to the protection scope of the claims.
Claims (3)
1. An ice accretion prediction method based on an Ic index and relative vorticity is characterized by comprising the following specific steps:
step 1, establishing an Ic icing index prediction equation, and calculating an Ic icing index:
Ic＝[(Rh-50)×2]×[t×(t+14)/(-49)]
wherein: rhRelative humidity, t is atmospheric temperature;
step 2, predicting the ice accretion of the airplane according to the following judgment basis:
if t is greater than 0, the aircraft has no ice accumulation, if t is less than or equal to 0 and the relative vorticity vo is less than or equal to 0, if t is less than or equal to 0 and vo is greater than or equal to 0 and less than or equal to Ic <50, the aircraft has slight ice accumulation, if t is less than or equal to 0 and vo is greater than 0 and less than or equal to 50 and Ic <80, the aircraft has moderate ice accumulation, and if t is less than or equal to 0 and vo is greater than 0 and Ic is greater than or equal to 80, the aircraft has severe ice accumulation.
2. An airborne icing prediction device comprising a receiver, a computer processing system and an icing prediction result display system;
the receiver is used for receiving the atmospheric temperature, the relative humidity and the relative vorticity and sending the atmospheric temperature, the relative humidity and the relative vorticity to the computer processing system;
the computer processing system calculates the Ic ice accumulation index according to the atmospheric temperature and the relative humidity received by the receiver; and obtaining the prediction result of the ice accretion of the airplane according to the following judgment basis: if t>If t is less than or equal to 0 and the relative vorticity vo is less than or equal to 0, the aircraft has no ice accumulation, and if t is less than or equal to 0 and the relative vorticity vo is less than or equal to 0>0 and 0. ltoreq. Ic<If t is less than or equal to 0 and vo is less than or equal to 50, the plane is lightly iced>0 and 50. ltoreq. Ic<80, the airplane has moderate ice accumulation, if t is less than or equal to 0 and vo is>If the IC is more than or equal to 80 and 0, the airplane is seriously iced; wherein, the calculation formula of the Ic ice accumulation index is as follows: ic ═ R [ [ (R)h-50)×2]×[t×(t+14)/(-49)]，RhRelative humidity, t is atmospheric temperature;
the ice accretion prediction result display system is used for displaying the prediction result of the airplane ice accretion.
3. The on-board icing prediction device of claim 2, wherein said receiver comprises a receiving antenna, an input circuit, a high frequency amplifier, a mixer, an intermediate frequency amplifier, a demodulator, and a low frequency amplifier; the receiving antenna receives a numerical prediction product sent by ground equipment, the input circuit extracts the atmospheric temperature, the relative humidity and the relative vorticity sent by the ground equipment from the numerical prediction product received by the receiving antenna, the high-frequency amplifier amplifies the output of the input circuit, the mixer converts the output of the high-frequency amplifier into an intermediate-frequency signal, the intermediate-frequency amplifier amplifies the output of the mixer, the demodulator demodulates the output of the intermediate-frequency amplifier, and the low-frequency amplifier amplifies the output of the demodulator.
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| US5206806A (en) * | 1989-01-10 | 1993-04-27 | Gerardi Joseph J | Smart skin ice detection and de-icing system |
| EP1661100B1 (en) * | 2003-08-20 | 2009-10-07 | The Boeing Company | Methods and systems for detecting icing conditions |
| WO2013078628A1 (en) * | 2011-11-30 | 2013-06-06 | 天津空中代码工程应用软件开发有限公司 | Flight icing numerical simulation method of helicopter rotor wing |
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