RU2496121C1 - Method for provision of aircraft flight vortex safety - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: proposed method comprises transmission of "board-to-board" and "board-to-flight control center (FCC)" data in radio mode and/or telegraph mode with transmission by every aircraft (aircraft-generator) of data on parameters of vortex trace created thereby obtained by measurements and/or computation in aircraft system of coordinates. It comprises also reception of said data by another aircraft of FCC (further on referred to as subscribers) in transmitter reach of appropriate aircraft-generator. It includes also the computation of effects of vortex trace and analysis of said data by subscribers in their system of coordinates. Note here that aircraft-generator transmitted data comprises that on its location (in its system of coordinates), its transmitter category, aircraft-generator speed and bearing, its weight and data transmission time, data atmosphere turbulence, wind speed and direction, temperature and barometric data. Subscribers receiving said data estimate the chances of flying through vortex trace zone and, if necessary, measure the atmosphere characteristics and/or allow for FCC data required for said computation, and/or allow for said characteristics with allowance for changes in gusts or turbulence. Note here that vortex trace parameters are defined with allowance for vortex trace drift, stochastic atmospheric phenomena, for example, gusts of turbulence.

EFFECT: perfected methods.

5 cl

Description

The present invention can be used to warn of the possibility of an aircraft (LA) getting into the vortex wake zone.

A known method of monitoring the surrounding space (see, for example, “Vortex Safety System of Airports”, http://www.lsystems.ru/catalog/spec_systems/safety_aeroport/ of 02/07/2011), including sensing an arbitrarily selected viewing sector using a Doppler lidar .

The known method provides the possibility of obtaining information about the intensity and dynamics of the vortex wake behind the aircraft, as well as the intensity of turbulence in the vortex wake, the turbulence profile and the spatial distribution of the components of the wind speed, however, for its use in flight conditions, it is necessary to install the appropriate equipment on board.

The closest analogue prototype is a warning method about the possibility of an aircraft entering the danger zone of a vortex wake (see, for example, RF patent No. 23234203 with priority dated July 25, 2003, IPC: G01S 13/95), including obtaining information about the configuration, location and aircraft orientation relative to the inertial coordinate system at the current time, obtaining and saving information about the parameters of the vortex generator (GV) motion and its position, geometric and mass characteristics relative to the same coordinate system at the current time change, obtaining information on environmental parameters in the field of joint placement of aircraft and airfoil, determining the trajectory and intensity of the vortex wake of the water heater as a set of trajectories of the centers of the vorticity regions generated by the specified water heater in the inertial coordinate system at the current time, storing information about the coordinates of the trajectory and the intensity of the GV vortex wake as a set of trajectories of the centers of the vorticity regions in an inertial coordinate system, the choice of lead time, during which the aircraft can at the very least, perform a maneuver of the flight path, ensuring the aircraft is avoiding the vortex wake of the hot air after warning about the possibility of falling into it, calculating the anticipatory distance equal to the distance traveled by the aircraft during the lead, simulate a control plane located in the space in front of the aircraft, and determine the predicted time of flight of the aircraft through the specified reference plane in the inertial coordinate system, and also perform for the user an indication of the event of zero standing to the danger zone of the vortex wake of the indicated HS.

The known method allows you to organize an air traffic control system with the provision of informing the user about the possibility of a dangerous flight situation, however, its implementation will require the creation of warning systems integrated in a single information system located on aircraft, ships, airfields, etc., which is associated with the need for significant financial costs and in some cases impractical.

The objective of the invention is to develop a method of information support for the vortex safety of an aircraft flight, which allows to warn pilots about the danger of falling into a vortex track ahead of an aircraft.

The essence of the invention lies in the fact that the method of information support for the vortex safety of flight of aircraft is characterized by the implementation of data transfer "board-to-board" and "board-to-air traffic control system (ATC)" in broadcast mode and / or in point-to-point mode with the transmission of information by each aircraft (aircraft generator) about the parameters of the vortex wake created by it, obtained by measuring and / or calculating in the aircraft coordinate system of the aircraft generator, the reception of this information by each other aircraft and / or air traffic control system (d subscribers) located in the access area of the transmitter of the corresponding aircraft generator, then calculating the effects of the vortex wake in the coordinate system of the aircraft subscribers and analyzing this information by the aircraft subscribers, and such data in the aircraft coordinates of the aircraft are included in the transmitted information of the aircraft generator, such as the location of the LA generator and the category of its transmitter, the speed and course of the LA generator, its weight and time of transmission of information to them, atmospheric turbulence data, wind speed and direction, temperature barometric pressure, and the receiving LA subscribers assess the possibility of passing the zone created by the LA generator of the vortex wake, and, if necessary, measure atmospheric characteristics, and / or take into account the data received from the air traffic control system, necessary for the corresponding calculation of the vortex wake, and / or take into account atmospheric characteristics taking into account the variability of gusts of wind and / or turbulence, while the parameters of the vortex wake are determined taking into account the drift of the vortex wake, including taking into account the influence of stoch -terrorist atmospheric influences such as gusts and / or turbulence, and the magnitude of the circulation produced by the aircraft wake vortex generator is determined from the relationship:

G (t) = 4Ge ^-tσ _T ^{/ L} / πρVL.

where ρ is the air density, V is the flight speed, L is the wing span of the aircraft, G is the weight of the aircraft, σ _T is the standard deviation of the wind speed.

In this case, the drift of the vortex wake due to the influence of wind in free space is determined by the relations:

z _1,2 (t) = ± 1/2 + W _z t; y _1,2 (t) = W _y t, where z _1,2 (t) and y _1,2 (t) are the corresponding coordinates (the mathematical expectation of the position of the corresponding coordinates) of the center of the vortices, W _z and W _{y are the} average wind speeds according to the corresponding coordinate, and the drift of the vortex wake due to the influence of wind in the area of influence of the underlying surface is determined by the relations:

z _1,2 (t) = ± Δz (t) / 2 + W _z t, where Δz (t) is the distance (the mathematical expectation of the distance) between the diverging vortices, and the remaining notations correspond to the ones written earlier.

In addition, the standard deviation (RMS) of the drift of the vortex wake is determined from the expression:

. $${\sigma }_r=1.22{\sigma }_T\sqrt{{\tau }_{T}t}$$

.

, где i=x, y, z, а остальные обозначения соответствуют записанным ранее.Here, τ _T = L _T / W is the time scale of turbulence, L _T is the spatial scale of turbulence, W is the average wind speed, and $$W=\sqrt{\Sigma W{i}^2}$$

, where i = x, y, z, and the remaining notation corresponds to the ones written earlier.

The technical result of the proposed invention is to increase the flight safety of the aircraft by obtaining information about the possibility of getting the corresponding aircraft into the vortex zone.

When flying in the atmosphere of an aircraft, it creates a vortex wake, which can be dangerous for other aircraft. This problem is also relevant for airports in organizing take-off and landing of aircraft.

The proposed method of information support for the flight of an aircraft involves solving this problem by informing interested users of the airspace about the place and time of occurrence of the vortex situation and identifying the approach of danger by analyzing the information received on the parameters of this vortex situation, the coordinates of its formation and movement, as well as by appropriate measuring atmospheric characteristics in the area of the intended location of the corresponding user.

At the same time, measurements of the atmospheric characteristics in the corresponding zone of the airport can be made by using, for example, a complex of autonomous lidar modules, including a long-range Doppler lidar, a laser-Doppler scanner of vortex traces, and also a Doppler laser meter with a vertical wind profile, which allows obtaining information about such parameters, such as: the vertical profile of the wind speed and the spatial distribution of the vertical component of the wind speed, the profile of turbulence and intensity l turbulence in the vortex traces, the intensity and dynamics of the vortex traces behind the aircraft, etc. (see, for example, "Vortex Safety Systems of Airports", http://www.lsystems.ru/catalog/spec_systems/safety_aeroport/).

Measurement of atmospheric characteristics (temperature, pressure, etc.) can be performed directly on the aircraft using appropriate sensors and an airborne weather radar (see, for example, http://ru.wikipedia.org/wiki/).

At the same time, interested airspace users perform on-board and on-board air traffic control (ATC) communications and each aircraft transmits information about the vortex situation created by it through a broadcasting channel of multiple access and / or via point-to-point radio communication (BO) with inclusion in this information of data on BO parameters in the plane or in the ground coordinates of the transmitting aircraft (hereinafter referred to as the aircraft generator) obtained by appropriate calculations and / or measurements, and also report the location of the aircraft generator ora, its weight and category of its transmitter, time of information transmission to it, its course and flight speed, atmospheric turbulence data, wind speed and direction, temperature and barometric pressure (see, for example, Transmission of meteorological data received on board aircraft (aircraft) via ADS-B transmission lines for vortex wake, air traffic and meteorological applications (Aircraft Derived Meteorological Data via ADS-B Data Link for Wake Vortex, Air Traffic Management, and Weather Application), project "Definition of operational services and environmental conditions (OSED ) ”(Operational Servic es and Environmental Definition), RTCA SC-206, SG-1, Vortex Trace Subgroup, ATS and MET, edition 0.1, p.12, 09.21.2011) as a result, it is possible to receive this information by every other aircraft and / or ground air traffic control services of aerodrome services (hereinafter referred to as LA-generator subscribers) located in the zone of accessibility of the corresponding transmitter, as well as subsequent processing and analysis of the information received by subscribers, while the information-receiving subscribers assess the possibility of passing the vortex wake created by the LA-generator, a reference point keeping at the time of diffusion of the vortex wake, as well as its drift by the wind (see, for example, V. Yaroshevsky et al. “The influence of the vortex wake on the dynamics of the flight of a passenger aircraft”, Flight. Vol. TsAGI-90, 2009), respectively, when following these aircraft in the direction of occurrence of the indicated aircraft and when passing the aircraft generator in the safety zone of the corresponding aerodrome, and the receiving aircraft and air traffic control services, if necessary, measure atmospheric characteristics and / or take into account the characteristics the atmosphere according to a probabilistic model taking into account the variability of gusts of wind and / or turbulence, while the parameters of the vortex wake are determined taking into account its drift due to the influence of stochastic atmospheric influences, for example, gusts of wind and / or turbulence.

It is known (see, for example, Burkin BC “Development of a stochastic model of vortex traces of a real-time aircraft and determination of exchange information between an aircraft and ground-based air traffic control services in the interests of creating an on-board vortex warning system” report of FSUE “GosNIIAS” No. 34 (16044) 2011, Moscow, 2011 city, p. 40) that during the propagation of the formed vortices, a change in the values of circulation Г (t) can be represented in the form:

Г (t) = Г ₀ е ^-γt , where γ = 0.82q / b.

Here Г ₀ = G / ρVb is the vortex circulation at the moment of formation, q is atmospheric turbulence, b = πL / 4 is the distance between the vortices of the wake (assuming that the elliptical distribution of the circulation over the span is true immediately after the plane), G [kg · m · Sec ^-2 ] - aircraft weight, ρ [kg · m ^-3 ] - air density, V [m · sec ^-1 ] - flight speed, L [m] - wing span (see, for example, G.G. Sudakov “Mathematical models and numerical methods for calculating the characteristics of satellite traces of their effects on the aircraft”, Abstract of dissertation for the degree of Doctor of Technology science, Moscow, 2005, pp. 14-15, see also VV Vyshinsky, GG Sudakov “Vortex trace of an airplane and flight safety issues” Proceedings of MIPT, 2009, volume 1, No. 3, p. .78).

After substitutions, carrying out the transformations, we obtain:

G (t) = 4Ge ^{-qt / L} / πρVL.

Taking into account that, by definition, q≡σ _T , where in the stochastic formulation σ _T is the standard deviation of the wind speed (see, for example, Burkin BC “Development of a stochastic model of the vortex traces of real-time aircraft and determining exchange information between the aircraft and ground-based ATC services in the interests of creating an on-board whirlwind warning system ”report of FSUE“ GosNIIAS ”No. 34 (16044) 2011, Moscow, 2011 p. 51), we have:

G (t) = 4Ge ^-tσ _T ^{/ L} / πρVL.

It is also known (see, for example, Burkin BC “Development of a stochastic model of vortex tracks of a real-time aircraft and determination of exchange information between an aircraft and ground-based air traffic control services in the interests of creating an on-board vortex warning system” report of FSUE “GosNIIAS” No. 34 (16044) 2011, Moscow , 2011, p.41) that the drift of a vortex wake by the wind in free space is determined by the relations:

Z _1,2 (t) = ± 1/2 + W _z t; y _1,2 (t) = W _y t, where z _1,2 (t) and y _1,2 (t) are the corresponding coordinates (the mathematical expectation of the position of the corresponding coordinates) of the center of the vortices, W _z and W _{y are the} average wind speeds according to the corresponding coordinate, and the drift of the vortex wake due to the influence of wind in the area of influence of the underlying surface is determined by the relations:

z _1,2 (t) = ± Δz (t) / 2 + W _z t, where Δz (t) is the distance (the mathematical expectation of the distance) between the diverging vortices, and the remaining notations correspond to the ones written earlier.

In the general case, the variance of the vortex position for random gusts of wind with speeds W (t) can be written in the form:

, $$D_r={\displaystyle \int {\displaystyle {\int }_0^t\overline{w(t_{\mathrm{one}})w(t_2)}d{t}_{\mathrm{one}}d{t}_2={\sigma }_t^2{\displaystyle \int {\displaystyle {\int }_0^t{\rho }_t(t_{\mathrm{one}},t_2)d{t}_{\mathrm{one}}d{t}_2}}}}$$

,

- дисперсия скорости турбулентных порывов ветра, ρ_t(t₁,t₂) - нормированная временная корреляционная функция скорости порывов и r={z, у} - компоненты координат вихря.Where $${\sigma }_t^2$$

is the dispersion of the velocity of turbulent gusts of wind, ρ _t (t ₁ , t ₂ ) is the normalized time correlation function of the speed of gusts, and r = {z, y} are the components of the coordinates of the vortex.

The calculation of the drift of the vortex wake for the Karman correlation function for t >> τ _T leads to the result:

и $${\sigma }_r=1.22{\sigma }_{Т}\sqrt{{\tau }_{Т}t}$$

. $$D_r=1.49{\sigma }_t^{2}t{\tau }_T$$

and $${\sigma }_r=1.22{\sigma }_T\sqrt{{\tau }_{T}t}$$

.

Here τ _t = L _t / W is the time scale of turbulence [sec], where

, где i=x, y, z.L _t is the spatial scale of turbulence [m], a W is the average wind speed [m / s], and $$W=\sqrt{\Sigma W_i{}^2}$$

where i = x, y, z.

In this case, the most probable value is L _t ≈300 m, and σ _T <0.5 m / s for a calm atmosphere and σ _T > 2.5 m / s for a strongly perturbed atmosphere, (see, for example, Burkin BC “Development of stochastic models of vortex traces of a real-time aircraft and determination of information exchange between an aircraft and ground-based air traffic control services in the interests of creating an on-board vortex warning system ”report of FSUE“ GosNIIAS ”No. 34 (16044) 2011, Moscow, 2011, p. 50-53).

Thus, for each aircraft, the magnitude of its vortex wake and the coordinates of its wind drift can, in principle, be calculated and relayed during radio communications for the appropriate orientation of interested users of airspace.

The implementation of the method of information support flight of the aircraft is as follows:

Airborne aircraft communicate “board-to-board” and “board-to-air traffic control system (ATC)” via a multi-station access broadcasting channel and / or via point-to-point radio communications and transmit information about the vortex (VO) situation created by it with including in this information data on the VO parameters and the maximum value of the vortex wake generated by the transmitting LA (LA generator) and its wind drift in aircraft or in the ground coordinates of the LA generator, obtained by appropriate calculations and / or measurements , and also report the transmission time, speed and direction of flight of the LA generator and other above data.

After receiving this information by each other aircraft and / or ground control centers of the aerodrome services of air traffic control (air traffic control) (hereinafter referred to as subscribers) located in the access area of the respective transmitter, the subscribers perform subsequent processing and analysis of the received information, assess the possibility of passage of the area of the created aircraft by the corresponding aircraft the vortex wake generator, determined, for example, by the distance between the aircraft generator and the subscriber following in the direction of this vortex wake, as well as when passing A generator in the aerodrome safety zone is conducted measuring characteristics of the atmosphere.

Taking into account the diffusion time of the vortex wake and the coordinates of its wind drift increases the flight safety of the aircraft following in the direction of this vortex wake.

The use of airspace for radio communications via a broadcasting channel of multiple access and / or point-to-point radio communications is performed with time division of channels (see, for example, “Developing Recommendations for Creating a System for Automatic Dependent Observation of Aircraft Takeoff and Landing”, Report on Scientific research work of FSUE “GosNIIAS”, 2010) in the form of an integrated communication and data transmission system by providing several, for example, four, separate radio channels on one carrier wave with a frequency 25 kHz grid and modulation (nominally three voice channels and one data channel). In the first case, the group of subscribers has free access to the channel on the basis of the principle of “listen before turning on the microphone”, and in the second case, the channel is accessed with the permission of the ground station at the request of the board.

Claims (5)

1. A method for providing information on the vortex safety of flight of aircraft, characterized by the implementation of data transfer "board-to-board" and "board-to-air traffic control system (ATC)" in broadcast mode and / or in point-to-point mode with the transmission of information by each aircraft (By the LA-generator) about the parameters of the vortex wake created by him, obtained by measuring and / or calculating in the aircraft coordinate system of the LA-generator, by receiving this information by each other LA and / or air traffic control system (hereinafter referred to as subscribers) located in the the speed of the transmitter of the corresponding LA generator, then calculating in the coordinate system of the LA subscribers the effects of the vortex wake and analyzing this information with the LA subscribers, and such information in the aircraft coordinates of the aircraft as the location of the LA generator and the category are included in the transmitted information of the LA generator its transmitter, the speed and course of the LA generator, its weight and time of transmission of information to it, atmospheric turbulence data, wind speed and direction, temperature and barometric pressure, and Information subscribers LA assess the possibility of passing through the vortex wake created by the LA generator, and, if necessary, measure the atmospheric characteristics and / or take into account the data received from the air traffic control system for the proper calculation of the vortex wake and / or take into account the atmospheric characteristics taking into account the variability of gusts of wind and / or turbulence, while the parameters of the vortex wake are determined taking into account the drift of the vortex wake, including taking into account the influence of stochastic atmospheric influences, for example, gusts of wind and / or turbulence. 2. The method of information support for the vortex safety of an aircraft flight according to claim 1, characterized in that the amount of circulation created by the LA generator of the vortex wake is determined from the relation
$$G(t)=\mathrm{four}G{e}^{-t{\sigma }_T/L}/\pi \rho VL,$$

where ρ is the air density, V is the flight speed, L is the wing span of the aircraft, G is the weight of the aircraft, σ _T is the standard deviation of the wind speed. 3. The method of information support for the vortex safety of an aircraft flight according to claim 1, characterized in that the drift of the vortex wake due to the influence of wind in free space is determined by the ratios
z _1,2 (t) = ± 1/2 + W _z t; y _1,2 (t) = W _y t, where z _1,2 (t) and y _1,2 (t) are the corresponding coordinates (the mathematical expectation of the position of the corresponding coordinates), W _z and W _y are the average wind speed. 4. The method of information support for the vortex safety of an aircraft flight according to claim 1, characterized in that the demolition of the vortex wake due to the influence of wind in the influence area of the underlying surface is determined by the ratios
z _1,2 (t) = ± Δz (t) / 2 + W _z t, where Δz (t) is the distance (the mathematical expectation of the distance) between the diverging vortices, and the remaining notations correspond to the ones written earlier. 5. The method of information support for the vortex safety of an aircraft flight according to claim 1, characterized in that the standard deviation (RMS) of the drift of the vortex wake is determined from the expression
$${\sigma }_r=1.22{\sigma }_T\sqrt{{\tau }_{t}t}$$

,
here τ _t = L _t / W is the time scale of turbulence, L _t is the spatial scale of turbulence, W is the average wind speed, and $$W=\sqrt{\Sigma W{i}^2}$$

, where i = x, y, z, and the remaining notation corresponds to the ones written earlier.