RU2304293C1 - System for aviation ecological monitoring of atmospheric pollution in cruising flight - Google Patents

Abstract

FIELD: ecology, possible use for monitoring pollution of atmosphere in cruising flight.

SUBSTANCE: system contains, positioned onboard the probing plane, meters of gas composition of sprays, spectral composition of sprays, pressure and temperature of atmosphere, relative moisture and water content of atmosphere, transparence of clouds and condensation trail from the engine of generator plane, haze meter, central processor of onboard digital computing machine. Probing plane includes air intake, communication and control system, onboard equipment of consumer of satellite navigation system, navigation and guidance system, automatic control. Additionally system includes generator plane and ground-based control equipment. Generator plane contains onboard equipment of satellite navigation system consumer, navigation and guidance system, automatic control, communication and control systems. Ground-based control equipment contains infrared laser locator, electronic-optical transformer, computer. Generator plane and ground-based equipment are connected to probing plane through devices of communication and control system.

EFFECT: increased precision of evaluation of conditions of generation and chars of condensation traces.

2 cl, 3 dwg

Description

The invention relates to aeronautical engineering, in particular to systems for assessing anthropogenic environmental impacts, the role of atmospheric pollution, studying their effects on the Earth’s climate, and also to creating and testing equipment when conducting flight research in the interests of ecology.

A Special Report of Working Groups I u III of the Intergovernmental Panel of Climate Change, Cembridge University Press, 1999, report shows that aviation makes a significant contribution to pollution of the upper troposphere. The combustion products emitted by aircraft engines increase the concentration of carbon dioxide, water vapor, methane, carbon oxides, nitrogen, etc. and contain aerosols, which, in turn, initiate the formation and development of cirrus clouds, which have a noticeable effect on radiation exchange.

Cirrus clouds usually occupy large areas. Most often, the cirrus cloud is part of the frontal cloud system and is either connected to the underlying cloud layer or forms a separate layer. They have the form of continuous homogeneous fields and belong to cirrostratus clouds (Cs), sometimes they include sections of cirrocumulus (Cc). Intra-mass cirrus clouds are distinguished by a variety of species, which reflects the difference in the mechanisms of their formation (wave and convective movements, mixing of air masses, boundary disturbances in jet flows, etc.). According to the phase structure, the clouds of the upper tier are classified as purely ice, especially at temperatures below -40 ° C, where long-term existence of water in the liquid state is impossible. These clouds are composed of fairly large crystalline particles. The characteristic fibrous heterogeneity of their visual spatial structure is associated with the bands of incidence of large crystals.

One of the most significant factors in the influence of aviation on the formation and development of cirrus clouds is the condensation traces (CS) of aircraft, which are formed as a result of condensation and freezing of water vapor contained in the exhaust jet of aircraft engines. CSs are formed at the same heights as cirrus clouds, in structure they are close to them. By the beginning of the 1990s, the area covered by CS was estimated at an average of 0.1% of the earth's surface. By 2050, an increase in area of up to 0.5% can be expected. Under appropriate meteorological conditions (increased humidity at low temperatures, below -40 ° C) in the upper layers of the troposphere and lower layers of the stratosphere, CSs can serve as a triggering mechanism (“trigger” effect) for the formation and especially for intensive development of cirrus clouds that exist near the passage of airways .

There are known works aimed at developing models of climate change and weather, but it does not fully take into account the effect of air pollution by aircraft engine emissions on the formation of condensation traces and, ultimately, on the formation and development of cirrus clouds.

Famous IPA DLR Falcon flying laboratory (Germany) for the study of climate change in Europe, built in accordance with the Mesoscale Alpine Program (MAP), adopted in Zurich in 1994 (http://www.map2.ethz.ch/mip) . The LL equipment includes a lidar based on aerosol backscattering, a Doppler lidar (wind), discharged radiosondes used for complex work to determine weather conditions, hydrological conditions, and gravitational phenomena.

A known method of remote environmental monitoring of urban areas (see RF patent No. 2003120018, G01C 11/04 of 2003.07.01), implemented in real time on board an aircraft, including the design of a system of heuristic features for various classes of homogeneous structures and their classification according to the decisive a rule based on the criteria for minimum weighted distances. The construction of a reference system of information features is carried out for heterogeneous structures that form along the flight path in the process of dividing the earth's surface into an analysis area of equal area determined by the technical characteristics of the equipment. For each area of analysis at the selected reference levels in three-dimensional space, a normalized reference vector is constructed, the difference between this vector and the normalized vector measured during monitoring is calculated. The calculated total difference of vectors for all reference levels, which is a characteristic measure of the changes that occurred in the areas of analysis, is compared with the detection threshold, which depends on the a priori probability of detecting changes, and if the threshold measure is exceeded, a decision is made on the presence of environmental changes.

However, this method is not intended to study the CS of aircraft associated with their influence on the formation of cirrus clouds.

Known (see US patent No. 5285256) equipment with a rear view and a method for detecting condensation traces (COP) of an airplane. Using a lidar mounted in the rear of the aircraft, a randomly modulated laser beam is directed toward detecting the volume of the CS. The bistatic type lidar has a laser and a receiving telescope with a forward beam scattering detection detector. The process of detecting beam scattering includes computer processing of the results and analysis of the detection of CS in the tail of the aircraft.

The lidar installed on board the aircraft allows us to distinguish between the CS and the clouds, which allows us to solve the problem of identifying the CS and cirrus clouds. The speed of flight, the type of engine, and various atmospheric parameters influence the onset of the formation of the COP. Cirrus clouds have a low degree of supersaturation, the time of their formation from 1 μs to 1 s.

The laser beam penetrates deeper into the structure of the cirrus cloud, but the CS more effectively reflects light in the detection volume. At this time, the lidar signal will have a larger peak from the CS than from cirrus clouds, which scatters back with increasing distance.

The lidar is installed at a certain angle to the axis of the engines. The returned signal from the CS is received by the detector (survey sensor) using the lidar telescope. The lidar signals are modulated according to a random distribution law, so the received signals from each engine differ individually. The occurrence of CS in the cloud is determined by computer processing of experiments and displayed on the display screen.

However, this method and apparatus for detecting CS does not allow a comprehensive assessment of the parameters of the CS, in particular to determine the geometric and optical parameters (length, diameter, density) and the duration of the existence of the already formed CS.

The famous flying laboratory (LL) of the Central Aerological Observatory (TsAO) "Cyclone" on the basis of the Il-18 aircraft, which was intended to study the physics of free atmosphere, cloud cover, weather conditions, the ozonosphere, aerosols, radar and radiosonde techniques, etc.

LL equipment included: inertial navigation system I-21, satellite navigation system (SNA) - GPS, radio altimeter RV-18, angle of attack and slip sensors, a system for measuring temperature and pulsations of outdoor air with infrared temperature sensors, static and dynamic pressure sensors connected with a data recording system - a computer. In addition, lidars for measuring the polarization and concentration of aerosol radiation, the vertical distribution of aerosols, equipment for determining the spectrum and concentration of aerosols and particles, a solar spectrometer, and an ultrasonic radiometer were installed on the LL.

However, this system is not intended to study the condensation traces of aircraft and their influence on the formation of cirrus clouds and does not physically exist at this time.

Significant difficulties in experimental studies of the microstructure and microphysical parameters (water content, transparency, etc.) of cirrus clouds, and especially CS behind airplanes, are associated with low values of the values to be measured, which in most cases lie below the sensitivity thresholds of common aircraft devices.

The purpose of the invention is to increase the accuracy of assessing the conditions of formation and characteristics of the COP and the influence on them of the physicochemical composition of the products of combustion of the exhaust gas stream during aviation monitoring of atmospheric pollution during cruise flight.

To solve this problem, an aerosol gas composition meter, an aerosol spectral composition meter, a nephelometer, atmospheric pressure and temperature meters, atmospheric relative humidity and water meters, and an onboard digital computer central processor connected to their outputs are included in the system of aviation ecological monitoring of atmospheric pollution in cruise flight; (BCVM), placed on board a sounding airplane containing an air intake, a communication and control system, They are closely connected to the onboard consumer equipment of the SNA, a navigation and guidance system, an automatic control system, separately connected through the outputs of the communication and control systems, navigation and guidance systems to the sixth and seventh inputs of the central computer CPU.

According to the invention, an aircraft generator is introduced into the system with a series-connected consumer equipment of the SNA, navigation and guidance systems, automatic control, a separately controlled communication and control system connected to the second input of the navigation and guidance system.

In addition, the control system on the aircraft-generator includes a device for injecting water into the exhaust nozzle of an aircraft engine, which allows varying the moisture content of the jet for experimental purposes, to simulate the gas exhaust jet of engines that will run on alternative fuels. In addition, a ground-based measuring system, equipped with a lidar and an electron-optical converter connected to the inputs of a computer, was introduced to photoregistrate the crystalline and droplet phases of the clouds.

The structure of the probe aircraft includes equipment for measuring the parameters of the oncoming air flow and exhaust jet of the investigated engine of the aircraft generator, equipment for measuring the physicochemical composition of the CS, moisture meters, water content and transparency of the clouds and the CS connected to the inputs of the digital computer, a computer for the formation of the CS associated with the release of digital computers, forming an analytical information system for predicting the formation of a condensation trail and a comprehensive assessment of the impact of its parameters on the environment at. At the same time, the aircraft generator and ground equipment are connected with the sounding aircraft through communication and control systems.

Thus, the aviation environmental monitoring system, including an aircraft generator, a sounding aircraft and ground equipment, will allow to identify the quantitative and physico-chemical composition of the CS of the engines under study and their effect on atmospheric pollution in cruise flight.

To clarify the invention, Fig. 1 is a structural diagram of an aeronautical environmental monitoring system for aircraft engines; figure 2 - the flight path of the aircraft generator and probe; figure 3 - temperature dependence of the partial pressure of steam in a mixed stream and saturated steam above water and ice.

Figure 1 shows:

1 - satellite navigation system (SNA), the space part

2 - equipment and apparatus of a sounding airplane

3 - on-board equipment of the consumer SNS

4 - navigation and guidance system (SNN)

5 - automatic control system (ACS)

6 - communication and control system (SSU)

7 - meters of pressure (P) and temperature (T) of the atmosphere

8 - measuring instruments of relative humidity (hygrometer) and atmospheric water content

9 - analytical information-measuring system (AIIS)

10 - the central processor of the on-board digital computer (BCM)

11 - aerosol gas composition meter - gas analyzer (GA)

12 - transparency meter KS

13 - meter spectral composition of aerosols

14 - nephelometer

15 - intake counter-atmospheric flow or gas stream of the investigated engine

16 - equipment and apparatus of the aircraft generator with the engine under study

17 - on-board equipment of the consumer SNA

18 - navigation and guidance system (SNN)

19 - water injection system into the exhaust stream

20 - communication and control system

21 - automatic control system

22 - ground monitoring control equipment

23 - communication and control system

24 - electron-optical Converter (EOC)

25 - computers

26 - lidar

27 - calculator conditions of formation of the COP

28 - a complex of measuring equipment of the flying laboratory of a sounding airplane.

Figure 2 shows:

1 - satellite navigation system (SNA), the space part

35 - probe

36 - aircraft generator with the investigated engine

23 - communication and control system

24 - electron-optical Converter (EOC)

25 - electronic computer (computer)

26 - lidar.

Figure 3 shows:

29 - dependence of the partial pressure of steam saturated above water

30 - dependence of the partial pressure of steam saturated over ice

31 - mixing line of the exhaust stream when saturated above water

32 - mixing line when saturated over ice

33 - boundary case of the mixing line

34 - mixing line below saturation above ice.

The system of aviation environmental monitoring of atmospheric pollution in cruise flight includes a meter of aerosol gas composition 11, an aerosol spectral composition meter 13, a nephelometer 14, atmospheric pressure and temperature meters 7, atmospheric relative humidity and water meters 8, and a central processor 10 connected to their outputs; in the complex of measuring equipment of a flying laboratory 28 on board a sounding airplane 35 containing a counter-air intake 15, a communication and control system I 6, serial connected consumer equipment 3 of the satellite navigation system (SNA) 1, navigation and guidance system 4, automatic control system 5, separately connected through the outputs of the communication and control system 6 and navigation and guidance system 4 to the sixth and seventh inputs of the central processor BTsVM 10. Aircraft generator 36 with a water injection system 19 into the exhaust nozzle of the engine under study, serially connected by the on-board equipment of the consumer 17 SNA, navigation and guidance systems was introduced into its composition 18, automatic control 21, a separately controlled communication and control system 20 connected to the input of the water injection system, the second input of the navigation and guidance system 18. Ground control equipment 22, made with lidar 26, an electron-optical converter 24, connected to computer inputs 25. In addition, the measuring instrument complex of the flying laboratory 28 of the sounding aircraft 35 includes a transparency meter KS 12 connected to the inputs of the computer 10, a computer for the formation conditions of the computer 27 connected to the output of the computer 10 forming the analytical information and automated measuring system 9. In this plane generator 36 in the surface equipment 22 associated with the aircraft-sounder 35 through the communication control system apparatus and 6, 20, 23.

The system operates as follows (figure 1 and figure 2).

Environmental monitoring of atmospheric pollution is carried out in a cruising wake flight of a generator plane 36 and a sounding airplane 35 with flight and navigation equipment 3, 4, 5, 6 and 17, 18, 20, 21 when controlled in additional control by ground means that are independent of changes weather conditions. Preliminarily determine the temperature behind the turbine of the test engine mounted on the generator plane 36, the relative humidity, temperature, water content of the atmosphere, the spectral composition of the aerosols of the oncoming air and the gas stream of the test engine is measured. And the water injection system in the exhaust nozzle of the engine 19 is used to simulate the increased moisture content in the case of the use (in the future) of alternative fuels, for example liquid hydrogen.

Quantitative characteristics of the formation of CS.

CSs behind airplanes form at the same heights as cirrus clouds, and are close in structure to them, therefore they are even called artificial cirrus clouds. CS are formed with a certain combination of atmospheric parameters: temperature, pressure, humidity and parameters of the exhaust jet of an aircraft engine. Physically, the formation of CS begins in the process of cooling the exhaust stream, which mixes with the surrounding air, when its temperature drops to the dew point, and with further cooling, steam supersaturation occurs, as a result of which condensate is released. This process continues to the point where, due to further mixing (dilution) of the jet, the humidity decreases to a value at which the condensation stops despite a decrease in temperature. In the future, CS can stably exist for a long time only if the humidity of the ambient air remains above saturation above the ice. When the vapor pressure drops below this value, the CS evaporates.

With an increased concentration of crystallization nuclei in the atmosphere and in a mixed stream, the formation of CS can also occur at a vapor pressure below saturation above water, but with supersaturation it is necessary with ice. Such CSs are very unstable, quickly dissipate, and have a low optical density.

For a quantitative assessment of the conditions of formation and existence of CS, the following should be known: temperature t _nv , pressure p and relative humidity of the ambient air at the considered height φ%, exhaust gas temperature behind the turbine t _t , coefficient of excess of air in the combustion chamber of the gas generator circuit of the engine α _ks ; for a dual-circuit engine, t _cm at the exit section of the exhaust nozzle of the mixing chamber and air excess coefficient α _cm (in the absence of a mixing chamber, the values of t _cm and α _cm obtained by mixing the jets from the fan and the gas generator in the atmosphere at the level of the gas generator exhaust nozzle).

AIIS calculator (block 9) calculates:

- temperature gradient of the partial vapor pressure in the mixed stream (mixing line) according to the formula:

- индекс паровыделения, т.е. масса водяного пара, образующегося при сгорании 1 кг топлива (для применяющегося в настоящее время авиационного керосина

); α - коэффициент избытка воздуха - для одноконтурного двигателя это относится к камере сгорания, т.е. α_кс, для двухконтурного - к камере смешивания, т.е. α_см;Where

- steam release index, i.e. mass of water vapor generated during combustion of 1 kg of fuel (for currently used aviation kerosene

); α - coefficient of excess air - for a single-circuit engine, this applies to the combustion chamber, i.e. α _ks , for double-circuit - to the mixing chamber, i.e. α _cm ;

- the dependence of the partial pressure of saturated steam on temperature according to the formula:

in which for vapor pressure above water a = 7.63; c = 241.9; over ice a = 9.5, b = 265.5; E _{0 ° C} = 610.7 Pa.

- partial vapor pressure in the atmosphere:

_HB e = Eφ / 100 Pa.

As a result of processing the obtained data at the output of the calculator, a graph of the partial vapor pressure in the mixed jet versus temperature at the considered flight altitude (ambient air pressure) and known parameters of the engine exhaust jet is obtained. Depending on the combination of these factors, the following cases are possible (Fig. 3): if the mixing line passes above the saturation curve above water (line 31), i.e. if there is supersaturation above water, then a stable CS is formed; if the mixing line passes below saturation above water, but there is a supersaturation with ice (line 32), then a CS can form with an increased concentration of crystallization nuclei in atmospheric air and in the exhaust stream; if the mixing line passes below the saturation curve above the ice (line 34), then the CS cannot form.

CSs are visible due to the reflection of light by the constituent particles of the wake in the direction of the observer. The luminescence of the wake depends on the reflective properties of the particles and the intensity and direction of the incident light. A CS becomes visible if its glow (relative to the background, i.e., contrast) exceeds a certain threshold value. To do this, the optical thickness τ, the product of the volume coefficient of attenuation (extinction) of light by the medium and the path length of the light beam in this medium, should be at least 0.02. The optical thickness τ = D · d ² (π / 4) · n · Q _cxi depends on the density of the number of particles, n, their diameter, d, the geometric diameter of the trace D (which depends on the angle of view) and the absorption intensity Q _cxi . The latter nonlinearly increases depending on the particle diameter d, but to a lesser extent than the wavelength of light λ (about 0.55 μm): varies from 0 to 1 in the range of values 0≤d / λ≤1 and reaches a value of 2 at d / λ> 1.

For a known particle size, the numerical density is determined by the ratio:

where m _L is the specific water content of water (or ice), kg / kg, ρ and ρ _L are the densities of air and water.

In this way:

where D is the diameter of the trace,

d is the particle diameter,

τ is the optical thickness.

Due to the fact that light is reflected by small particles forward (relative to the incident light), the CS is better seen if it is observed at a small angle relative to the Sun.

CS with a diameter of 50 m with drops of water with a diameter of 2 μm can be visible at a water content of 0.1 g / m ³ . For the formation of a faint trace, water content of 0.004 g / m ^{3 is} required and for a clear trace, 0.01 g / m ³ . But under adverse observation conditions, a greater water content is required, about 0.1 g / m ³ . For a more accurate determination of the boundaries of the CS, it is necessary to know the spectrum of particle sizes and certain information about the observation conditions.

КС может быть невидимым также в случае, когда содержит очень много мелких частиц; при d<0,5 мкм наблюдается голубой туман с малой контрастностью относительно фона.The optical thickness can be expressed in terms of the particle allocation index EI _parz — the mass of particles (droplets or crystals) per unit mass of fuel (kg / kg), which is associated with the number density of particles n, dispersion factor F, and the dependence

CS can also be invisible in the case when it contains a lot of small particles; at d <0.5 μm, blue fog is observed with low contrast relative to the background.

The size of droplets and ice crystals in the CS can increase or decrease due to condensation or evaporation. Changes in particle size and the nature of their size distribution can have a strong effect on the property of the aerosol. Vapors are able to condense with the formation of droplets in the absence of condensation centers, if the degree of supersaturation is large enough. In this case, the rate of formation (nucleation) becomes significant only when the amount of supersaturation reaches 200 ... 400%.

The effectiveness of optical methods for studying the microstructure of atmospheric aerosol is determined by the resolution of the optical equipment and the features of the functional relationships between the optical characteristics of scattering media and their microstructure.

The measurement of cloudiness and CS parameters is divided into:

- microphysical properties of clouds;

- aerosol properties in an inter-cloud and non-cloud atmosphere,

- the internal content in the crystals of particles remaining after evaporation of crystallized water;

- the concentration of gases in the atmosphere in the area of airways.

Aerosol particles and crystals larger than 0.1 μm are measured using optical instruments, these include:

- an optical dispersion meter - a particle size determinant, a numerical meter of fine particles and a differential analyzer with a counter in block 13;

- nephelometer - a polarizing device for measuring optical density in block 14.

On-board equipment has the following ranges of measurements of atmospheric (background) characteristics: temperature (0 ...- 70 ° С) and pressure (200 ... 1100 GPa) meters, block 7; relative humidity above water (0 ... 100%) and need ice (0 ... 120%), block 8; meters of total water content (0 ... 0.1 g / m ³ ); numerical particle density (0 ... 10 1 / cm ³ ), block 12.

Measuring instruments of characteristics of KS have the following ranges: temperature measuring instruments (-20 ° С ...- 65 ° С), block 7; relative humidity above water (10 ... 100%), above the ice (10 ... 130%), block 8; water content of the liquid phase (0.001 ... 1 g / m ³ ), the crystalline phase (0.001 ... 2 g / m ³ ) with a measurement repetition rate of at least 1 Hz, block 8; droplet size meter (1 ... 95 μm), block 13; particle size and shape (25 ... 800 μm) of the aerosol particle size spectrum (0.1 ... 3 μm), block 13; extinction coefficient meter (0 ... 5 1 / km), block 12; particle optical density meter (0 ... 20 1 / cm ³ ), block 12.

In the meter of aerosol gas composition, block 11 is in the gas analyzer, the principle of operation is to use the dependence of one of the optical properties of the analyzing mixture on the concentration of the component to be determined. To solve the gas analysis problem, it is necessary to determine a unique dependence of the optical parameter of the component being determined on its concentration. Optical GAs are based on measuring the refractive index of the gaseous medium of a gas nitroferometer or the parameters of absorption of radiant energy in the UV or IR spectral regions.

The absorption of radiant energy by a gas in block 11 leads to changes in the energy state of atoms, molecules and their groups, the nature and extent of these changes depending on the energy of the absorbed radiation. Energy absorption in the infrared region of the spectrum is associated with intramolecular transitions due to rotational motions within molecules and their groups. Gases whose molecules consist of two or more atoms, except oxygen, nitrogen and hydrogen, have the ability to absorb infrared radiation. The differences in the absorption spectra, as well as the dependence of the absorption on the gas concentration, make it possible to conduct a selective analysis of the determined component (absorbing radiation) in complex gas mixtures.

The functional diagram of the HA infrared absorption consists of: a radiation source - a nichrome spiral heated by a passing current up to 700 ... 900 ° C, an emission spectrum in the range of 1800 ... 4500 nm, a radiant energy modulator that feeds it to the measuring chamber (with gas ) with a frequency of ƒ _m = 5 ... 20 Hz and an electronic circuit using an AC amplifier. In the chamber of the receiver, filled with gas and sealed, the gas inside it, absorbing radiation, is heated, a change in temperature ΔТ leads to an increase in pressure in the receiver by ΔР. The transducer element of the beam detector is a condenser microphone, the membrane of which, representing the wall of the beam detector, is connected to the amplifier input together with a fixed electrode - an optical-acoustic effect. The sensitivity of the beam detector is 10 ^-4 W / cm ² .

The main quantitative characteristic in blocks 12 and 13 of the absorption of optical energy by atmospheric gases is the monochromatic absorption coefficient K (V), which is included in the expression of Bouguer’s law, which describes the attenuation of a plane monochromatic wave. Knowing the dependence of this coefficient on the wavelength, the gas absorption spectrum can be determined by the energy losses of laser radiation caused by this gas and any radiation with a predetermined intensity distribution over the wavelengths. For a gas mixture, it is necessary to know the allowed absorption spectra of each of the components making up the mixture. Laser spectroscopy combines high monochromaticity with the ability to control the wavelength, provides spectra with ultra-high resolution.

Optical waves, meeting on their way various atmospheric aerosols, lose energy due to its scattering by particles. The magnitude of the loss depends on the size of the particles, their concentration, chemical composition and shape. All four of these parameters vary within a very wide range.

Obtaining the absorption spectrum of a substance in the gas phase is carried out in block 13 in the study of environmental pollution by laser sensing. Satisfactory resolution and sensitivity is provided by the method of high-speed laser spectroscopy. Spectroscopic measurements using this method are reduced to precision measurements of the wavelength of the laser generation (with its simultaneous change during generation) and the display of the intensities of the probing and studied signals. The investigated substance is filled with a multi-pass optical cuvette. The radiation source is a ruby laser with a regular generation mode and a controlled emission spectrum. The radiation wavelength is measured using a stabilized helium-neon laser, a Fabry-Perot interferometer, and a photocell (selective loss method). This increases the time of interaction of radiation with matter. Most environmental monitoring devices are capable of measuring only one value, so for a comprehensive assessment of environmental parameters, you have to use a large number of devices and deal with a huge stream of information coming from them, which is represented by these devices in the form of heterogeneous and rapidly changing values. Collectively measured quantities become known as a result of mathematical processing. Therefore, for a comprehensive assessment of environmental parameters, a system is used that receives information directly from measuring sensors; it quantizes by level and time, digitally encodes the measured value, performs mathematical or logical operations with the measured values, and which stores the received information and provides it in the required form. These functions are performed by the AIIS analytical measuring and information system (block 9), which includes the central processor BTsVM 10 and the calculator of the conditions for the formation of KS 27. The structure of AIIS is parallel. AIIS performs automatic monitoring of environmental parameters and maintaining them within certain limits, and can also work in forecast mode. Means of presentation in the form of graphs, tables on screens. AIIS performs mathematical processing of measurement information, analysis of impurities, aerosols in the air; methods of pattern recognition, methods of factor analysis, etc. are used.

When studying meteorological formation by sounding the atmosphere with a polarizing lidar 26, the amount of information obtained can be substantially expanded. Radiation reflected from a spherical homogeneous particle preserves the state of polarization of the incident wave, and partial depolarization occurs when reflected from nonspherical and inhomogeneous particles. When real meteorological objects are located, additional depolarization of the reflected signal is observed, due to multiple reflection on the ensemble of particles. The magnitude of the depolarization of radiation reflected from water clouds does not depend significantly on the radiation wavelength in the visible and near-IR spectral regions and on scattering to the cloud, but is determined to a greater extent by the size spectrum, cloud particle concentration, and solid reception angle. Lidar 26 allows the study of depolarizing properties of various states of the atmosphere and clouds of crystalline and droplet phases. The monostatic system has a laser source and a receiving telescope located in one place. The principle of operation of the system based on the use of scattering as the main means of studying the atmosphere. This can be scattering either directly on the studied components, or on other components; when the components of interest have a measurable effect on the transmission of the laser beam.

In lidar 26, the photorecorder is tuned to the wavelength of the laser radiation. When propagating in the atmosphere, laser radiation interacts with aerosols and molecules. Part of the scattered radiation is collected by a telescope and recorded by a sensitive photomultiplier. The detected signal is recorded as a function of time to allow spatial resolution measurements of atmospheric scattering. Then an analysis of the recorded data is carried out to find the distribution of aerosols.

For scattering studies, the most important aerosol characteristic is the distribution function.

Particle size distribution is obtained by sampling and measuring the particles or indirectly by attenuation measurements in block 14, which determines the concentration, size and shape of the dispersing particles.

The methods used for counting and measuring particles make it possible to obtain the number of particles in a certain size range (size classes). The data are presented in the form of histograms showing how many particles n _i in the size class r _i . Concentration - the total number in units of volume is

This value is proportional to the total area of the histogram.

The relationship between the particle size distribution and the scattering characteristic is important. The attenuation coefficient for scattering is calculated from the measured particle size distribution. Particle content and attenuation coefficient cannot really be measured in the same gas volume. Using an integrating nephelometer, attenuation coefficients are measured by passing an aerosol stream through an illuminated instrument chamber and measuring the resulting scattering. The volume and mass of particles in micrograms per 1 m ^{2 of} aerosol measured by samples in the place where the nephelometer is located.

To determine the composition of the particles and their vertical distribution, optical sounding is carried out from the surface of the earth. In addition to the sampling method, optical methods allow continuous monitoring of the vertical structure of the aerosol for several hours — a method based on measuring scattering in block 26. The searchlight is mounted vertically or at a known zenith angle. The brightness of a certain portion of the searchlight beam is measured by the electron-optical method (block 24), and the receiver is located far enough from the searchlight to provide a measurement angle favorable from the point of view of the geometry of the problem. To obtain a given power from a source, the brightness of the observed ray section depends on the scattering indicatrix at a given height and on the vertical distribution of the total coefficient. According to these data, the concentration of particles is determined.

For a comprehensive assessment of studies of atmospheric conditions and clouds of crystalline and droplet phases, a computer 25 is used, as well as for control and monitoring of ground facilities 22 regardless of changes in weather conditions.

A positive effect in the operation of the aviation environmental monitoring system during flight research is achieved by studying the complex effects of the physicochemical composition of the emissions of the engine under study installed on a generator aircraft. The aviation environmental monitoring system also makes it possible to make predictions about the effect of aviation on the formation of spacecraft and their influence on the development of cirrus clouds, which have a significant impact on the radiation exchange of the atmosphere and the earth's surface.

Claims (2)

1. A system of aviation environmental monitoring of atmospheric pollution during a cruise flight, including a gas composition meter of aerosols, a spectral composition of aerosols, a nephelometer, atmospheric pressure and temperature meters, atmospheric relative humidity and water meters, and a central processor of an on-board digital computer connected to their outputs ) placed on board a sounding airplane containing an air intake, a communication and control system, serially connected boards the consumer equipment of the satellite navigation system (SNA), navigation and guidance system, automatic control system, separately connected through the outputs of the communication and control systems, navigation and guidance systems to the sixth and seventh inputs of the central processor of the computer, characterized in that the aircraft is introduced into it -generator with series-connected on-board equipment of the SNA consumer, navigation and guidance systems, automatic control, separately controlled communication and control system, connected to the second input of the navigation and guidance system, ground-based control equipment made with lidar, an electron-optical converter connected to the inputs of an electronic computer that provides photoregistration of crystalline and droplet phase clouds, and cloud transparency and engine condensation track gauges are introduced into the probe generator aircraft connected to the inputs of the computer, the calculator of the conditions for the formation of a condensation trail associated with the output of the computer, forming an analytical and formational system, wherein the generator and a plane-ground equipment associated with the plane-sounder system via the communication device and control. 2. The system of aviation environmental monitoring of atmospheric pollution in a cruise flight according to claim 1, characterized in that in addition to the control system on the generator aircraft, a device for injecting water into the exhaust nozzle of an aircraft engine for modeling a gas exhaust jet of engines that will run on alternative fuels is included.

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