RU2324203C2 - Method and system of warning for airvehicles about potential vortex wakes danger condition - Google Patents

Abstract

FIELD: aircraft operations.

SUBSTANCE: method implies warning at the moment air vehicle potentially gets into danger area of generators vortex wakes. The system provides analysis of the air vehicle environment, determines path and intensity of generators vortex wakes in the vicinity of air vehicle, intersections coordinates of vortex wakes with reference plane and geometrics of their danger areas on basis of danger criteria defined by user. Virtual reference plane is arranged at anticipatory distance towards air vehicle route, evaluated on basis of selected anticipatory period long enough for air vehicle to make an escape maneuver. Within reference plane the system forms high attention area, expected air vehicle position area and danger areas of vortex wakes for predictable point of time. Then it tracks intersections of high attention area and/or expected air vehicle position area with danger areas of vortex wakes and by means of display device and visualizer attracts user's attention to this event.

EFFECT: flight safety improving.

18 cl, 4 dwg

Description

Technical field

The invention relates to methods and devices for ensuring the safe operation of aircraft, in particular to methods for preventing and / or preventing emergency situations associated with the possible entry of an aircraft into the danger zone of a disturbed air stream from another object, the so-called vortex wake generated by the object, including number when the object flows around the air stream.

State of the art

The problem of ensuring the flight safety of aircraft is very relevant and includes a number of scientific, technical and organizational-methodological problems. One of these problems is to ensure flight safety in conditions where the factor determining the level of flight safety is the impact on the aircraft of aerodynamic jets of a high degree of turbulence, which are formed both when an object generating jets moves in the vicinity of the aircraft, and when there is an aircraft in the vicinity apparatus of objects streamlined by air currents having a high degree of turbulence and vorticity.

It is known that when the aircraft moves in airspace, the so-called “vortex wake” is formed, which is formed by the air flow surrounding it.

If an aircraft enters the vortex trace of another object, for example, another aircraft, it leads to a significant change in the angles of attack and glide. In this case, the aerodynamic forces and moments influence the aircraft, which, for example, can throw it away from the track and at low altitudes, for example, during landing or take-off of the aircraft, lead to emergency situations due to the impossibility of compensating for such an impact by the aircraft controls .

The appearance in aircraft of aircraft having wings of small elongations with a high specific load leads to an increase in the intensity of the vortex wake, which accordingly increases the risk of the aircraft entering it.

Numerous studies of the movement and decay of vortices have shown that atmospheric factors such as wind, wind shear, stratification and turbulence play an important role in these processes.

There is a potential possibility of optimizing safe distances between aircraft during landing, take-off and flight based on reliable forecasting of the dynamics of the vortex wake, taking into account the current and short-term forecast of the relevant meteorological conditions, the influence of atmospheric conditions and the proximity of the earth to the dynamics of the vortex wake.

One of the main directions for solving the problem of ensuring the flight safety of an aircraft in conditions when the vortex aerodynamic trail is the determining factor is the choice of flight modes that provide a given level of safety.

The creation of on-board computer systems operating in real time, determining the degree of danger of aerodynamic disturbances acting on the aircraft, and allowing choosing the method of subsequent correction of the aircraft control in order to most effectively compensate for these disturbances, can contribute to solving this problem.

Another task that can be attributed to information tasks is the task of providing the pilot with information about the position of the vortex wake and the position of the aircraft relative to it at the predicted point in time.

A known method and device for creating visual displays of vortex traces by mathematical modeling them based on the characteristics of the aircraft generating a vortex wake, taking into account the influence of atmospheric conditions on the state of the vortex wake. Moreover, according to the technical solution, the device uses a quick-response display, on which the simulated vortex traces from each aircraft located near the aircraft are visualized (US 5845874, A). However, if there are a large number of other aircraft surrounded by the aircraft, for example, near an aerodrome, the display will show a large number of simulated vortex traces, which will make it difficult to determine which vortex traces present a real danger to the aircraft and which of them can be ignored.

One of the most promising ways to improve flight safety is to provide the pilot in real time with information about the predicted position of the vortex traces, hit in which can lead to a flight accident.

There is a known warning system for turbulence of a wake designed to be placed on board aircraft, which provides for informing the crew of the aircraft about the potential entrance into the vortex wake of another aircraft only when the system determines that the entry of the specified aircraft into the vortex wake of another aircraft will occur through a certain predetermined period of time (US 6177888, A). The system provides for the interaction of these aircraft with each other, the exchange of warning signals and information on the flight altitude, distance and bearing, tracking the flight path of the vortex wake volume taking into account local wind speed and has the ability to determine the distance or time before the aircraft enters the vortex wake volume another aircraft. The system provides an indication of proximity to the volume of the vortex wake when the distance or time to such an input becomes less than a predetermined threshold. In this case, the width and height of the vortex wake volume are calculated at each point from a plurality of points along the vortex wake path as a function of the distance from the specified point to the adjacent aircraft.

However, such a system does not solve the problem of informing the pilot about the degree of danger of getting into the identified vortex tracks and about the rational maneuver of the aircraft to prevent it from falling into the vortex track.

In addition, the variety of operating conditions for aircraft requires reducing distances between aircraft, for example, during successive take-off or landing of aircraft at aerodromes, which is important for increasing the capacity of aerodromes.

Reliable knowledge of the position and structure of the vortex wake and the features of its impact on the aircraft at the predicted point in time will help to meet conflicting requirements to improve the performance of flight tasks and improve flight safety.

A known collision avoidance system with a vortex wake, installed on each aircraft to warn the pilot of the aircraft about the predicted danger of the presence in the surrounding aircraft space of another aircraft (US 6211808, B1), which is a spherical antenna made of dielectric material having eight sectors with receiving devices installed in them for receiving microwave signals reflected from other aircraft located I'm in his neighborhood. However, such a system is expensive and does not provide the pilot with information about the presence of dangerous air disturbances.

A technical solution is known regarding the scheme and method for preventing the intersection of an airplane path with a vortex wake of another aircraft (WO 00/71985), which consists in determining the position, configuration and type of vortex disturbances caused by another aircraft, the presence of which is detected using information from the on-board systems of the first aircraft , information from another plane or information from the airfield, in determining its height, the predicted position of the vortex wake generated by it, taking into account atmospheric conditions, in particular speed and wind direction, air temperature, in reconciling the obtained data with a look-up table or modeling a vortex wake with visualization of the position and its trajectory relative to the first aircraft, predicting the point of intersection of the vortex wake trajectory and the path of the first aircraft with the generation of a danger signal in case of such an intersection. Basically, the method is used to ensure the safety of the movement of two aircraft in the airport area and its implementation can lead to an increase in the flight height of the first aircraft over the second aircraft. At the same time, Traffic Alert and Collision Avoidance systems are used. However, at the same time, the pilot of the first aircraft is visualized with information about all areas of vorticity assumed in the region of movement of the first aircraft due to the presence of the second aircraft, which does not give the pilot a picture of the true danger of these vortices for his flight.

It is known that the US National Aeronautics and Cosmonautics Administration (NASA) pays great attention to improving the efficiency of the aerodrome zone, in particular, during take-off and landing of aircraft and one of the development areas is the creation of the Vortex Interval Detection System (AVOSS), which will combine outputs of various systems; and develop dynamic weather-dependent dynamic criteria for swirl trace intervals (37 ^th Aerospace Sciences Meeting & Exhibit, January 11-14, 1999, Reno, NV, NASA Langly Research Center, Hampton, VA). These systems represent current and predicted weather conditions, models of the movement of the vortex wake and its attenuation in these weather conditions from the surface of the earth to the height of the landing or take-off glide path, and also provide feedback on the behavior of the vortex wakes in real time. The behavior of the track is compared with predetermined dimensions of the safety corridor and the determination of the dying of the track, as a result of which the desired separation intervals for aircraft are found. If traces continue to exist longer than expected, then a reduction in the interval between take-off or landing of aircraft is prohibited. In this case, the behavior of the trace is calculated on the set of "approach" windows from the height of the glide path to the end of the runway. However, there are a number of limitations in this system, such as the lack of taking into account the vertical wind shear, which can impede the lowering of the track or lead to its rise, the lack of taking into account the specific scale of turbulence necessary to model the decay of the track, and others that can lead to an emergency due to non-compliance pre-provided manager with calculated trace parameters and actual trace parameters. In addition, the use of the AVOSS system will increase the load on flight controllers, who in the present conditions experience significant emotional stress, as well as to intensify their work, which is undesirable, as it increases the possibility of dispatchers making inadequate decisions.

It should be borne in mind that foreign security systems are mainly focused on the application of the so-called instrumental flight rules, when the aircraft is controlled based on the commands of the flight dispatcher, implemented in director or automatic mode on board the aircraft.

However, it is known that in operator activity the most difficult is the decision-making in an extreme situation. It consists of two stages: identification of the situation and determination of the procedure for its elimination. Before each next step, the operator must anticipate his next steps. The perception of visual or speech signals in verbal form from a long-term memory, from a display device or by ear requires a certain amount of time in conditions of time pressure. The time of perception of graphic symbols is much shorter and the recognition of the situation when indicating the highlighted areas of the image can also improve the adequacy of decision-making.

In addition, the impact of such a physical factor as acceleration causes a decrease in the cerebral circulation in the pilot, which, under conditions of neuro-emotional overstrain, can cause even a short-term loss of consciousness. Therefore, providing the pilot or flight dispatcher with the information necessary for making a decision before the decision is made and in graphic symbols is preferable.

Disclosure of invention

The aim of the present invention is the creation of a warning system about the possibility of an aircraft entering a danger zone of a vortex wake generated by an object located in the vicinity of the aircraft and called a "vortex generator". Moreover, not only aircraft are considered as vortex generators, but also ground and surface objects, the vortex trace of which can be dangerous for the aircraft. The set of points in space, when hit by forces and moments acting on the aircraft, can lead to a dangerous situation, is described as a “dangerous vortex wake zone”.

When creating the invention, the task was to develop a method and device for warning about the possibility of an aircraft entering a dangerous, from the point of view of design and operating conditions of the aircraft, vortex wake zone, which would provide information about the presence of vortex wakes in the vicinity of the aircraft that are dangerous for the aircraft, their movement and possible directions of the exit of the aircraft from hazardous areas by determining the projected position Niya aircraft and the danger zone of the vortex generator wake vortices in a control section ahead of the rate of the aircraft, at a distance, during which overcome the aircraft in an emergency, can make a maneuver to evade the danger zone of the wake vortex. At the same time, it is advisable to determine the location of the vortex wake in space, taking into account the dynamics of changes in environmental parameters, and the position of the aircraft in space, taking into account changes in its configuration and established standards for flight production.

Changing the configuration of an aircraft means, for example, changing the operating mode of engines, including the failure of one or more engines, changing the geometry of the aircraft, for example, sweep the wing, icing the surface of the aircraft and other changes that lead to a change in the flow around it in an incident flow and, therefore, to a change in aerodynamic forces and moments due to the action of aerodynamic disturbances, including a vortex wake, as well as to a change in the aircraft to compensate for such effects.

The task was also to create a device for implementing the warning method according to the invention.

The problem was solved by creating a warning method about the possibility of an aircraft entering the danger zone of the vortex wake of the vortex generator, in which:

- receive information about the configuration, location and orientation of the aircraft relative to the inertial coordinate system at the current time;

- receive information about the position, geometric and mass characteristics and about the motion parameters of the vortex generator relative to the inertial coordinate system at the current time;

- save information about the position and motion parameters of the vortex generator in an inertial coordinate system;

- receive information on environmental parameters in the field of joint placement of the aircraft and the vortex generator at the current time;

- determine the trajectory of the vortex wake of the vortex generator as a set of trajectories of the centers of the vorticity regions generated by the specified vortex generator, and the intensity of the vortex wake in the inertial coordinate system at the current time;

- save information about the coordinates of the points of the trajectory and the intensity of the vortex wake as a set of trajectories of the centers of the regions of vorticity of the vortex generator in an inertial coordinate system;

- choose the lead time, during which it is possible, at least, to perform a maneuver of changing the flight path of the aircraft, ensuring the aircraft to evade the danger zone of the vortex wake of the vortex generator after warning about the possibility of getting into it;

- calculate the anticipatory distance equal to the distance covered by the aircraft during the lead, simulate a control plane located in space in front of the aircraft perpendicular to the direction of its movement at a proactive distance from the aircraft, and determine the predicted time of flight of the aircraft through the specified control plane in the inertial coordinate system;

- determine the geometric characteristics of the danger zone of the vortex wake of the vortex generator as a set of dangerous zones of the vorticity regions generated by the specified vortex generator at the predicted point in time;

- determine the trajectory and intensity of the vortex wake of the vortex generator as a set of trajectories of the centers of the vorticity regions generated by the vortex generator, relative to the inertial coordinate system at the predicted point in time;

- determine the coordinates of the intersection of the trajectory of the vortex wake of the vortex generator with the specified reference plane at the predicted time of flight of the aircraft through it;

- form around the indicated point of intersection the dangerous zone of the vortex wake as a set of dangerous zones of the vorticity regions generated by the indicated generator, when it enters into the aircraft motion parameters can exceed the permissible limits; form in the indicated control plane the region of the positions of the aircraft predicted, taking into account the established standards of flight production, at the forecast moment of time the aircraft intersects the specified control plane, an area of increased attention is formed around the region of the predicted positions, information about the danger zone of the vortex wake in which will be provided to the user;

- determine the coordinates of the points of the area of the predicted positions of the aircraft, points of the area of increased attention and points of the danger zone of the vortex wake in the coordinate system associated with the aircraft;

- calculate the distance from the area of increased attention to the danger zone of the vortex wake;

- calculate the distance from the area of the predicted positions of the aircraft to the danger zone of the vortex wake;

- carry out for the user an indication of the event that the distance from the area of increased attention to the danger zone of the vortex wake of the indicated vortex generator is zero;

- carry out for the user an emergency indication of the event that the distance from the area of increased attention to the danger zone of the vortex wake of the specified vortex generator is zero.

Moreover, in the method according to the invention:

- as information about the position, geometric and mass characteristics and motion parameters of the vortex generator, preferably use information about the type of vortex generator, its speed, angular velocity and the coordinates of the points of its trajectory;

- save information about the coordinates of the trajectory points, the displacement velocity and the angular velocity of the vortex generator in the inertial co-ordinate system;

- information on the magnitude and direction of the local wind speed, on the wind profile in height, degree of turbulence, type of underlying surface is preferably used as information on environmental parameters;

- the trajectory and intensity of the vortex trace of the vortex generator at the current time as a set of trajectories of the centers of the vorticity regions generated by the indicated vortex generator, is determined by calculation based on the stored information about the type of vortex generator, the coordinates of its trajectory points, the speed of movement and angular velocity, or based on instrumental measurements;

- modeling of the control plane is carried out on the basis of information about the location, orientation, speed of the aircraft and the selected lead time at the current time in an inertial coordinate system;

- determination of the geometric characteristics of the danger zone of the vortex wake of the vortex generator as a set of dangerous zones of the vortex areas generated by the specified generator is carried out on the basis of the stored information about the coordinates of the points of the trajectory and the intensity of the track of the vortex generator as a set of trajectories of the centers of the vortex areas in the inertial coordinate system, position information, the speed of movement and the angular velocity of the aircraft in an inertial coordinate system;

- the trajectory and intensity of the vortex wake of the specified vortex generator at the predicted point in time is determined based on information about the trajectory and intensity of the vortex wake of the specified vortex generator as a set of trajectories of the centers of the vorticity regions generated by the indicated generator in the inertial coordinate system;

- determination of the coordinates of the points of intersection of the trajectory of the vortex wake of the specified vortex generator with the control plane at the predicted point in time is carried out on the basis of information about the coordinates of the control plane in the inertial coordinate system and the trajectory of the vortex wake of the specified vortex generator in the inertial coordinate system at the predicted point in time;

- the formation in the control plane of the danger zone of the vortex wake of the vortex generator, the area of the predicted positions of the aircraft and the area of increased attention is carried out on the basis of information about the coordinates of the points of intersection of the vortex wake of the specified vortex generator with the control plane at the predicted time, information about the geometric characteristics of the danger zone of the vortex wake the specified generator as a set of dangerous zones of the swirl regions generated by the specified generator, information and on the position, orientation, speed of movement and angular speed of the aircraft, taking into account the established standards for flight production;

- determination of the coordinates of the area of the predicted positions of the aircraft, the coordinates of the area of increased attention and the coordinates of the danger zone of the vortex wake in the coordinate system associated with the aircraft is carried out on the basis of information about the coordinates of the area of increased attention, the area of the positions of the aircraft predicted taking into account established standards for the production of the danger zone of the vortex wake at the predicted point in time and information about the coordinates of the aircraft and its position, etc. dpochtitelno pitch angles, aircraft yaw and roll, in an inertial coordinate system at the current time.

When implementing the warning method of the possibility of a vortex wake entering the danger zone according to the invention, the user is provided with only the vortex wake information necessary for him to be able to carry out an effective maneuver to prevent the aircraft from entering the vortex wake. By pre-processing the vortex wake information implemented in the present invention, it is possible to reduce the amount of induced information, leaving only a useful part of it. The result is an adequate perception by the user, for example, by the pilot, of the spatial position of the aircraft relative to the vortex wake at the predicted point in time, which makes it possible to take timely measures to prevent the aircraft from entering the danger zone of the vortex wake. In addition, the advantage of this method of prevention is the ability to account for changes in aerodynamic forces acting on the aircraft and moments caused by a change in its configuration, since it is possible to adapt the operations of the method to environmental conditions, flight characteristics, and operating modes of the aircraft systems.

According to the invention, it is advisable to carry out the operation of the warning method simultaneously with respect to each of the vortex generators located in the vicinity of the aircraft.

In addition, in the warning method according to the invention, it is advisable to carry out the current correction of the selected lead time, which allows you to take into account the specifics of the flight mode and the flight task to be solved.

In addition, in the warning method according to the invention, it is advisable to carry out the current correction of the coordinates of the region of the predicted positions of the aircraft, which allows to resolve situations of uncertainty of the incoming information by correspondingly resizing the region of the predicted positions of the aircraft.

In addition, in the warning method according to the invention, it is advisable to carry out the current correction of the coordinates of the area of increased attention, which allows you to adjust the time for deciding whether to perform the appropriate maneuver to avoid the vortex wake.

Moreover, according to the invention, it is advisable to carry out the specified correction in manual mode, semi-automatic or automatic mode.

In addition, according to the invention, it is advisable to provide the user with information about the coordinates of the control plane, the area of increased attention, the area of the predicted positions of the aircraft and the danger zones of the vortex traces of the vortex generators located in the vicinity of the aircraft.

Moreover, according to the invention, it is advisable to visualize for the user information about the location in the control plane of the area of the predicted positions of the aircraft and information about the location of the dangerous zones of the vortex wake of the vortex generators.

In addition, according to the invention, it is desirable to indicate that the distance from the area of increased attention to the danger zone of the vortex wake of the vortex generator in the control plane is zero and / or that the distance from the region of the predicted positions of the aircraft to the danger zone of the vortex wake of the vortex generator is zero using the indication selected from the group including visual indication, audio indication and tactile indication.

In addition, according to the invention, it is advisable to save information about the value of the lead time, the coordinates of the control plane, the area of the predicted positions of the aircraft and the danger zones of the vortex traces of the vortex generators during the time of the emergency indication of the event that the distance from the region of the predicted positions of the aircraft to the danger zone of the vortex trace vanishes vortex generator.

The task was also solved by creating a warning system about the possibility of an aircraft entering the danger zone of the vortex wake of the vortex generator, including:

- a device for tracking the parameters of the aircraft, capable of receiving information about the configuration, location and orientation of the aircraft relative to the inertial coordinate system at the current time;

- a tracking device for the vortex generator, capable of receiving information about the position, geometric and mass characteristics and about the motion parameters of the vortex generator relative to the same coordinate system at the current time;

- a storage device capable of storing information about the position and motion parameters of the vortex generator in an inertial coordinate system;

- a medium parameter detector capable of receiving information on environmental parameters in the field of joint placement of the aircraft and the vortex generator at the current time;

- a vortex wake tracking device capable of determining the trajectory and intensity of a vortex wake of a vortex generator as a set of trajectories of the centers of vorticity regions in an inertial coordinate system;

- a storage device capable of storing information about the coordinates of the trajectory points and the intensity of the vortex wake as a set of trajectories of the centers of the vorticity regions in an inertial coordinate system;

- a lead time selection device capable of calculating a time during which, at least, it is possible to perform a maneuver of changing the flight path of the aircraft, providing the aircraft to evade the vortex wake of the vortex generator after warning about the possibility of getting into it;

- a control plane simulation device capable of calculating a pre-emptive distance equal to the distance covered by the aircraft in the selected lead time, form a control plane located in space in front of the aircraft perpendicular to the direction of its movement at a pro-active distance from the aircraft, and determine the predicted time of flight of the aircraft apparatus through the control plane in an inertial coordinate system;

- a device for determining the parameters of the danger zone, capable of determining the geometric characteristics of the danger zone of the vortex wake of the vortex generator as a set of dangerous zones of the vortex regions generated by the vortex generator, at the predicted point in time;

- a prediction device capable of determining the trajectory and intensity of the vortex wake of the vortex generator as a set of trajectories of the centers of the vorticity regions generated by the vortex generator, the vortex wake relative to the inertial coordinate system at the predicted point in time;

- a device for calculating intersection points, capable of determining the coordinates of the points of intersection of the trajectory of the vortex wake of the vortex generator with the control plane at the predicted time point when the aircraft intersects the specified control plane;

- a device for the formation of zones and regions, providing the formation around the intersection of the trajectory of the vortex wake with the control plane of the danger zone of the vortex wake as a set of dangerous zones of the vortex areas generated by the vortex generator, if it enters the aircraft the movement parameters can exceed the permissible limits, the formation in the specified the control plane of the area predicted, taking into account the established standards for the production of flight, the positions of the aircraft in the forecast emy time intersection aircraft reference plane; the formation around the area of predicted positions of the area of increased attention, information about getting into the danger zone of the vortex wake should be provided to the user;

- a transition unit capable of calculating the coordinates of the area of the predicted positions of the aircraft, the area of increased attention and the danger zone of the vortex wake in the coordinate system associated with the aircraft;

- the first block of checking the intersection condition, capable of determining the distance from the area of increased attention to the danger zone of the vortex wake and recording the moment of its equality to zero;

- the second block checking the condition of the intersection, able to determine the distance from the area of the predicted positions of the aircraft to the danger zone of the vortex wake and fix the moment of its equality to zero;

- an indication device providing an indication of the event that the distance from the area of increased attention to the danger zone of the vortex wake of the vortex generator is zero;

- an emergency indication device providing an indication of the event that the distance from the region of the predicted positions of the aircraft to the danger zone of the vortex wake of the vortex generator is zero.

Moreover, according to the invention in the warning system:

- the tracking device for the parameters of the aircraft is able to receive information, at least about the configuration, coordinates, speed, angles of pitch, yaw and roll of the aircraft;

- the tracking device for the vortex generator is capable of receiving information at least about the type of vortex generator, its speed, angular velocity and the coordinates of the points of its trajectory;

- a medium parameter detector is capable of receiving information, at least, about the magnitude and direction of the local wind speed, wind profile in height, degree of turbulence, type of underlying surface;

- the vortex wake tracking device is capable of determining the trajectory and intensity of the vortex wake of the vortex generator as a set of trajectories of the centers of the vortex regions based on the stored information about the type of vortex generator, the coordinates of its trajectory points, the speed of movement and angular velocity;

- a control plane simulation device is capable of simulating a control plane based on information about the location, orientation, speed of the aircraft and the lead time;

- the device for determining the parameters of the danger zone is able to determine the geometric characteristics of the danger zone of the vortex wake of the vortex generator based on the stored information about the coordinates of the trajectory points and the intensity of the vortex generator trace, information about the configuration, position, speed of movement and angular velocity of the aircraft in an inertial coordinate system;

- the prediction device is capable of determining the trajectory and intensity of the vortex wake of the vortex generator based on information about the trajectory and intensity of the vortex wake as a set of trajectories of the centers of the vorticity regions generated by the vortex generator in an inertial coordinate system;

- the device for calculating the intersection points is able to determine the coordinates of the intersection points of the trajectory of the vortex wake of the vortex generator with the control plane based on information about the coordinates of the control plane and the vortex wake trajectory in the inertial coordinate system at the predicted point in time;

- a device for the formation of zones and regions capable of forming a danger zone of a vortex wake, an area of predicted positions of an aircraft and an area of increased attention based on information about the coordinates of the points of intersection of a vortex wake of a vortex generator with a control plane at a predicted point in time, information about the geometric characteristics of the danger zone as a set of dangerous zones of vorticity regions generated by the vortex generator, information about the position, orientation, displacement velocity and angular orosti aircraft flight against established production norms in the inertial coordinate system;

- the transition unit is able to calculate the coordinates of the area of the predicted positions of the aircraft, the area of increased attention and the danger zone of the vortex wake in the coordinate system associated with the aircraft, based on the coordinates of the area of the attention, the area of the predicted positions and the danger zone of the vortex wake at the predicted time in the inertial coordinate system and information about the coordinates of the aircraft and its position, preferably the pitch, yaw and roll angles, to the inertial nthe coordinate system at the current time.

Moreover, according to the invention, it is advisable that the warning system contains a tracking device for a vortex generator, storage devices, a tracking device for a vortex wake, a device for determining hazardous area parameters, a prediction device, a device for calculating intersection points, a device for forming zones and areas, the first and second verification units crossing conditions, an indication device and an emergency indication device capable of simultaneously ensuring the performance of its functions in relation to each from vortex generators located in the vicinity of the aircraft.

In addition, according to the invention, it is desirable that the lead-time selection device is configured to perform current lead-time correction.

In addition, according to the invention, it is desirable that the device for forming zones and regions be configured to perform current correction of the coordinates of the region of the predicted positions of the aircraft.

In addition, according to the invention, it is desirable that the device for forming zones and regions is configured to perform current correction of coordinates of the area of increased attention.

Moreover, according to the invention, it is advisable to correct the lead time, the coordinates of the area of the predicted positions of the aircraft and the coordinates of the area of increased attention to carry out in the mode of manual or semi-automatic regulation.

In addition, according to the invention, it is possible to carry out the specified correction in automatic mode.

This embodiment of the warning system devices provides the flexibility of its application both in the conditions of manual control of the aircraft, and when using the automatic control system (hereinafter - ACS) of the aircraft.

In addition, according to the invention, it is advisable that the warning system contains a visualization device for the user of information about the location in the control plane of the area of the predicted positions of the aircraft and the danger zones of the vortex traces of the vortex generators.

Moreover, according to the invention, the indicating device and the emergency indicating device can be selected from the group including visual, audio, and tactile indicating devices.

In addition, according to the invention, the warning system as a device for determining the parameters of the danger zone of the vortex wake of the vortex generator may include a device including:

- an aircraft schematization unit capable of calculating, based on information about the configuration, coordinates, movement speed, pitch, yaw and roll angles, the set of geometric characteristics of the aircraft necessary to calculate the additional aerodynamic forces acting on it and the moments induced by the vortex wake of the vortex generator ;

- a unit for determining the aerodynamic forces and moments acting on the aircraft at a given point in space, induced by the vortex wake of the vortex generator, capable of calculating them based on the stored information about the coordinates of the points of the vortex wake trajectory as a set of trajectories of the centers of the vorticity regions and the vortex generator wake intensity in the inertial coordinate system , information about the configuration, position, movement speed and angular velocity of the aircraft in the inertial coordinate system t and about the geometric characteristics of the aircraft;

- a unit for determining the danger of aerodynamic disturbances at a given point in space, capable of assessing the danger of disturbances according to a hazard criterion set by the user;

- a unit for determining the set of points in space at which the aerodynamic forces and moments induced by the vortex trace of the vortex generator are dangerous, capable of determining the coordinates of the points of space belonging to the danger zone, based on their selection according to the hazard criteria set by the user;

- a unit for determining the geometric characteristics of the danger zone of the vortex wake, capable of calculating them based on information about the coordinates of points belonging to the danger zone.

This embodiment of the warning system using the device for determining the parameters of the danger zone of the vortex wake according to the invention allows, when choosing a hazard criterion, to take into account the configuration and flight mode of the aircraft and the pilot's qualifications.

Moreover, according to the invention, a permissible roll angle of the aircraft can be selected as a hazard criterion.

In addition, according to the invention, a permissible roll moment induced by the vortex wake can be selected as a hazard criterion.

Moreover, according to the invention, it is advisable that the unit for determining the geometric characteristics of the danger zone of the vortex wake was able to approximate the boundary of the danger zone, which simplifies the visualization of the danger zone of the vortex wake in the visualization device.

Moreover, according to the invention, the vortex wake tracking device and the prediction device comprise a programmable component, and the danger zone parameter determination device is implemented in the programmable component software.

In addition, according to the invention, the device for determining the parameters of the danger zone may contain a database containing the characteristics of the danger zones of the vortex traces of various types of generators in different flight conditions.

In addition, according to the invention, the warning system may include a device for storing information about the lead time, the coordinates of the control plane, the area of the predicted positions of the aircraft and the danger zones of the vortex traces of the vortex generators during the emergency indication of the event that the distance from the area of the predicted positions of the aircraft to dangerous is zero zone of the vortex wake of the vortex generator.

Brief Description of the Drawings

The invention is further illustrated by the description of an example implementation of the warning method according to the invention using a warning system according to the invention, not limiting the application of the invention and not beyond the scope of the invention, and the accompanying drawings, in which:

Figure 1 is a schematic representation in space of an aircraft, a vortex generator, a vortex wake generated by it and displayed in the control plane information according to the warning method in accordance with the described embodiment of the invention;

Figure 2 - diagram of the method of warning about the possibility of an aircraft entering the danger zone of the vortex wake of the vortex generator according to the invention using the warning system according to the invention;

Figure 3 - embodiment of a device for determining the parameters of the danger zone of a vortex wake of a vortex generator according to the invention;

4 is a diagram of the image information on the display of the navigation map provided by the warning system according to the invention.

An embodiment of the invention

As an example, the embodiment of the invention described in the diagram of FIG. 1 is described, when the warning system is implemented as part of standard equipment aboard one aircraft (hereinafter referred to as “Aircraft”), the vortex generator is another aircraft (hereinafter referred to as HS) and the user of the information is the crew of the aircraft. The description uses specific terminology, but it must be borne in mind that each term covers all equivalent terms used in solving similar problems.

When implementing the warning method of the possibility of an aircraft entering the hazardous area of the HV vortex wake according to the invention, a volume of information is generated in some control plane about the location of the aircraft in space at the predicted time at the calculated anticipated distance in front of the aircraft and the possible location of the vortex tracks of the HV around it, which will be for aircraft dangerous. Moreover, according to the invention, the information is adjusted taking into account environmental conditions at the location of the control plane.

According to the scheme of FIG. 2, in the described warning system about the possibility of an aircraft entering the hazardous area of the GW vortex wake according to the invention, the aircraft parameters tracking device 1 implemented, for example, in a computer of an automatic flight control system of an aircraft (hereinafter, ACS of an aircraft) receives, for example, flight and navigation system of the aircraft information on the configuration, coordinates, speed, angular velocity of the aircraft, the pitch, yaw and roll angles at the current time t in the inertial coordinate system (hereinafter referred to as the ISK).

A GV tracking device 2, implemented, for example, in an ACS computer of an aircraft, receives, for example, from an airborne radar station of an aircraft, from a front-view radar or from a ground dispatcher, or via a multiplex information exchange channel, and a storage device 3 stores information about the type of GV , the speed of its movement, the angular velocity and the coordinates of the points of its trajectory in the ISK.

The detector 4 of the environmental parameters, implemented, for example, in the flight-navigation system computer, receives, for example, information from the airborne warning system or from the flight controller about the magnitude and direction of the local wind speed, wind profile in height, degree of turbulence, type of underlying surface in areas of joint placement of aircraft and GV relative to ISK at the current time t.

A vortex wake tracking device 5, implemented, for example, in an ACS computer, based on information from a storage device 3, calculates the trajectory and intensity of the GW vortex wake as a set of trajectories of the centers of the vorticity regions in the ICS, for example, using algorithms such as a well-known calculation algorithm trajectories and intensities of the vortex wake (Northwest Research Associates, Inc., Aircraft Vortex Spacing System (AVOSS), Algorithm Version 3.1.1), which provides the calculation of the coordinates of the centers of the vortex regions based on the integration of the differential equation describing the evolution of vorticity regions in space and time. A storage device 6 stores this data.

The coordinate parameters of the vorticity regions can also be determined using instrumental measurements, for example, using laser radar devices such as lidar, measurements and estimation of the tangential velocity of the air flow, followed by calculation of the trajectory and intensity of the vortex wake.

The lead time selection device 7, for example, implemented in an ACS computer, calculates the lead time necessary to perform a maneuver to change the aircraft trajectory. This selected lead time according to the invention can be adjusted in the current mode using manual control, semi-automatic or automatic control, taking into account, for example, pilot qualifications or the characteristics of the assigned flight task.

The control plane modeling device 8 (hereinafter - KP), based on information from the device 1 about the coordinates, speed, angles, yaw and roll of the aircraft and information from the device 7 about the selected lead time, calculates the anticipatory distance equal to the distance covered by the aircraft in the selected lead time, simulates the CP located in the space in front of the aircraft perpendicular to the direction of its movement at a proactive distance from the aircraft, for example, in the form of coefficients of the equation of the plane K in CSI and determines the forecasted time t + Δt after the aircraft flight manual in KIU. As the device 8, any computing device can be used that allows such calculations, for example, a computer on board an aircraft.

The forecasting device 9, based on the information about the trajectory and intensity of the vortex wake of the HS stored in device 6, and the predicted time from the device 7, calculates the coordinates of the trajectory and the intensity of the vortex wake of the HS as a set of trajectories of the centers of the vorticity regions at the predicted time t + Δt in the CSI.

The device 10 for determining the parameters of the danger zone on the basis of information from the device 1 on the coordinates, speed and angular velocity of the aircraft and from the storage device 6 on the coordinates of the points of the trajectory and intensity of the vortex wake as a combination of the trajectories of the centers of the vorticity regions generated by the hot air, determines in accordance with the selected criterion geometrical characteristics of the danger zone of the GW vortex wake trace as a set of hazard zones of the vorticity regions generated by GW at the predicted time t + Δt. In this case, as a hazard criterion according to the invention, an allowable roll angle of the aircraft or, for example, a permissible roll moment induced by the vortex wake of the hot water can be selected.

Moreover, according to the invention, the vortex wake tracking device 5 and the prediction device 9 may comprise a programmable component, in this case, the trajectory and intensity of the GW vortex wake, and the device 10 is implemented in the software of this component - a database of calculated geometric characteristics of the vortex wake hazard zones different types of GW depending on various environmental conditions and the parameters of the GW motion, aerodynamic forces and moments induced on the aircraft by vortex traces of personal intensity, for example, roll moments.

The device 11 (Figure 2), implemented, for example, in the computer of the flight control and navigation system, on the basis of information about the coordinates of the CP calculates the coordinates of the points of intersection of the trajectory of the vortex wake from the CS at the predicted time t + Δt based on information about the coordinates of the CP from device 8 and information from the device 9 about the vortex wake trajectory, for example, by selecting the vortex wake trajectory points located on different sides of the CP, with the interpolation of the distance between them.

The device 12 for forming zones and regions, placed, for example, as part of the computer of the onboard inertial navigation system of the aircraft, forms around the point of intersection of the trajectory of the HS vortex wake with the KP a dangerous zone of the vortex wake, the area of the aircraft’s predicted flight conditions (hereinafter referred to as OPP LA) ) at the predicted point in time t + Δt and the area of increased attention (hereinafter OPV) as a set of many points on the control plane. According to the invention, the device 12 allows the current correction of the coordinates of the airborne landing gear of the aircraft and airborne vehicles, which is important for the pilot in coordinating the evasion maneuver with the situation of the flight mission.

Transition block 13 calculates the coordinates of the airborne clearance of the aircraft, the danger zone of the vortex wake of the HV and the HW in the coordinate system associated with the aircraft.

Then, the first intersection condition verification unit 14 calculates the distance from the OPV to the danger zone of the vortex wake, tracking the event of its equality to zero, and the second intersection condition verification unit 14 calculates the distance from the OPP to the danger zone of the vortex wake of the HS, tracking the event of its zero equality.

Information about equality to zero at the predicted time point of the indicated distances is sent to the user’s installed devices, for example, in the pilot's cockpit, display devices 16 and 17, for example, to the audio display device 16, if the distance between the OPV region and the vortex wake danger zone is equal to zero, and then, for example, to the emergency tactile indication device 17 in the event that the distance between the airborne landing gear and the danger zone of the vortex wake is equal to zero. Tactile indication is designed to encourage the pilot to take urgent measures to perform a maneuver to evade the aircraft from the danger zone. At the same time, the pilot has the time for maneuver set by the user, taking into account the speed of movement of the aircraft. Depending on the situation, after receiving the first indication, the lead time can be corrected by the pilot, for example, by manual adjustment, by setting a digital parameter for the lead time, or by automatic regulation with the establishment of the conditions for increasing or decreasing this time.

With an increase in the indicated distances, the indication stops, which indicates that the aircraft leaves the situation that is dangerous for the aircraft and helps to relieve the voltage from the user.

According to the invention, it is advisable to visualize for the user information on the relative position of the aircraft airspace and the hazardous area in the control room at the predicted time in the visualization device 18, for example, on the display or the navigation map of the aircraft, as well as to limit the amount of information that is not relevant for the pilot, to visualize the dangerous position zones only after their intersection with OPV.

According to the invention, the hazardous area parameter determination device 10 can be made according to the invention and comprise, as shown in the diagram of FIG. 3, an aircraft schematization block 19 receiving information from the warning system device 1 (FIG. 2), made in any known manner and calculating a set of geometric aircraft characteristics, taking into account its configuration, block 20, receiving information from block 19 and information from the warning system device 6 (Figure 2) and determining additional aerodynamic forces and moments, induction Bathrooms wake vortex at the point GV space. Then, block 21 determines, based on a specified hazard criterion, the degree of danger of aerodynamic disturbances at a given point in space, block 22 determines points of space belonging to the danger zone of the vortex wake, and block 23 determines the geometric characteristics of the danger zone as a set of points and approximates the boundaries of the danger zone to simplify visualization danger zone on display. Information about the parameters of the danger zone of the GW vortex wake then goes to the warning device 8 and is visualized in case of danger of an aircraft entering it.

Figure 4 shows the display 24 of the navigation chart, which is usually used in aircraft to indicate the course of the aircraft and to display the characters generated by the onboard inertial navigation system, for example, the Airborne Inertial Navigation System (AINS), with the image of the area 25 of the predicted positions of the aircraft and hazardous areas 26, 27 vortex traces of HS in space at the predicted point in time. Region 25 OPP LA can take the form of, for example, a rectangle whose dimensions are proportional to the dimensions of the region of the possible position of the aircraft in space. The boundaries of the area of increased attention are not shown on the display, since according to the invention it is advisable that the image of the danger zones of the vortex traces is projected on the display only if the danger zones intersect with the area of increased attention at the same time as indicating, for example, an audible event. Therefore, we can assume that the area 28 of increased attention is shown on the display. The danger zone 26, 27 of the vortex traces may take the form, for example, of a circle or other geometrical figure convenient for visual perception. In this case, the image may be accompanied by a visual indication, for example, light or color, of the regions 25, 26, 27 or their boundaries 29, 30, 31, and in the event of the event of crossing the border 29 of the region 25 of the airborne landing gear with the border of the region, for example danger zone 26, - accompanied by emergency audio indication or tactile indication.

Of course, although in the described example only one of the vortex generators is presented and the behavior of only one dangerous zone of the vortex wake of one HS is visualized and induced, the calculations for tracking the vortex wake of the HS are carried out for all the HSs located in the vicinity of the aircraft, and only the zones are displayed vortex traces of HS, which must be avoided due to their danger to the aircraft. At the same time, based on the pilot’s assessment of the location scheme of potentially dangerous zones on the display, an adequate decision can be made about the nature of the maneuver of the aircraft, which will lead to the aircraft leaving the area of dangerous vortex traces.

According to the invention, it is advisable to store, for example, in the so-called “black box” information recording system, current information about the value of the selected lead time, the coordinates of the control plane, the area of the predicted positions of the aircraft and the danger zones of the vortex traces of the vortex generators during the emergency indication of the event of zero distance from the area of the predicted positions of the aircraft to the danger zone of the vortex wake of the vortex generator, which will allow I to establish the cause of the crash to the aircraft pilot action evaluation purposes in the situation of the presence in the surrounding space of the vortex trails from entering the dangerous zone which could lead, for example, to aircraft configuration change or a change in its trajectory.

The method and system for warning about the possibility of an aircraft entering the hazardous area of a GW vortex wake according to the invention can be implemented using standard on-board and ground equipment, for example, the Airborne Inertial Navigation System (AINS) onboard inertial navigation system, and the Air Data Computer System (ADC) ), Doppler drift speed meter Doppler System (DS), Forward View Radar (FVR) front-view radar and information from Air Traffic Control (ATC), a single indie system United Indication System (UIS), the multiplex channel for the exchange of information Exchange Multiplex Channel (IEMC), as well as information systems compatible with these systems used on aircraft of other countries, for example, Collision Avoidance System (TCAS), warning systems traffic hazards Traffic Alert, USA.

In addition, the warning system devices according to the invention can be localized separately at various objects of the motion control system or various aircraft and airborne vehicles, providing the user with information about the results of operational calculations by indicating and visualizing them at the user's location.

At the same time, users of such information can be both aircraft crews and dispatch services of aerodromes, ships advising aircraft crews when flying about the recommended flight path or about the need for aircraft maneuver to eliminate a dangerous flight situation.

For air traffic control specialists, it is clear that the warning system according to the invention can also be implemented to perform flight control functions, since tracking the vortex situation in the vicinity of ground-based HVs and flying HVs can be carried out using warning systems located autonomously on aircraft, on ships, on aerodromes, combined into a single information system, which helps to prevent the creation of emergency situations associated with the entry of aircraft into the danger zones of the vortex traces of various HS. Moreover, various types of aircraft can be used as warheads, for example, airplanes, helicopters, unmanned aerial vehicles, sea vessels, including aircraft carriers, ground structures, and other objects.

Specialists in the field of aviation and avionics should understand that in the method and system of warning about the possibility of an aircraft entering the danger zone of the GW vortex wake according to the present invention, improvements and improvements can be made that do not go beyond the claims and claims of the present invention, for example, related to the difference in the conditions of application of the system, as well as the improvement of navigation and information systems. For example, various computational algorithms that most accurately implement the operations of the warning method according to the invention can be applied, various methods of indicating and visualizing the information provided to the user, improving the adequacy of the perception of the information received by the user, are applied, and various information flows are used in the operations of the method.

Industrial applicability

A warning system about the possibility of an aircraft entering the hazardous area of a GV vortex wake is advisable to implement in the form of programs adapted to the type of aircraft, the operating conditions of the aircraft, the type of equipment used on it, and compatible with air traffic control information systems.

The warning system according to the invention can be easily implemented using well-known computing devices, can be used for installation on various aircraft, as well as in various simulators for training pilots and controllers in vortex hazard conditions.

Claims (18)

1. A warning method about the possibility of an aircraft entering the danger zone of the vortex wake of the vortex generator, in which receive information about the configuration, location and orientation of the aircraft relative to the inertial coordinate system at the current time; get information about the position, geometric and mass characteristics of the vortex generator relative to the same coordinate system at the current time and about the parameters of its movement; save information about the position and motion parameters of the vortex generator in an inertial coordinate system; receive information on environmental parameters in the field of joint placement of the aircraft and the vortex generator at the current time; determine the trajectory and intensity of the vortex wake of the vortex generator as a set of trajectories of the centers of the vorticity regions generated by the specified vortex generator in the inertial coordinate system at the current time; save information about the coordinates of the trajectory points and the intensity of the vortex wake of the vortex generator as a set of trajectories of the centers of the vorticity regions in the inertial coordinate system; choose a lead time during which the aircraft can at least perform a maneuver of changing the flight path of the aircraft, ensuring the aircraft is evaded from the vortex wake of the vortex generator after warning about the possibility of getting into it; calculate the anticipatory distance equal to the distance covered by the aircraft during the lead, simulate the control plane located in space in front of the aircraft perpendicular to the direction of its movement at the anticipatory distance from the aircraft, and determine the predicted time of flight of the aircraft through the specified control plane in the inertial system coordinates; determine the geometric characteristics of the danger zone of the vortex trace of the vortex generator, as a set of dangerous zones of the vortex regions generated by the specified vortex generator, at the predicted point in time; determining the trajectory and intensity of the vortex wake of the vortex generator as a set of trajectories of the centers of the vorticity regions generated by the indicated vortex generator relative to the inertial coordinate system at the predicted point in time; determine the coordinates of the intersection of the trajectory of the vortex wake of the vortex generator with the specified reference plane at the predicted time of flight of the aircraft through it; form around the indicated point of intersection the dangerous zone of the vortex wake as a set of dangerous zones of the vorticity regions generated by the specified generator, when it enters into the aircraft motion parameters can exceed the permissible limits; form in the specified control plane the area of the predicted, taking into account the established standards for the production of flight positions of the aircraft at the predicted time point when the aircraft intersects the specified control plane; form an area of increased attention around the area of predicted positions, information about the vortex wake dangerous zone getting into it will be provided to the user; determine the coordinates of the points of the area of the predicted positions of the aircraft, points of the area of increased attention and points of the danger zone of the vortex wake in the coordinate system associated with the aircraft; calculate the distance from the area of increased attention to the danger zone of the vortex wake in the control plane; calculate the distance from the area of the predicted positions of the aircraft to the danger zone of the vortex wake; carry out for the user an indication of the event that the distance from the area of increased attention to the danger zone of the vortex wake of the specified generator is zero; carry out for the user an emergency indication of the event that the distance from the area of increased attention to the danger zone of the vortex wake of the specified vortex generator is zero. 2. The method according to claim 1, characterized in that as information on the position, geometric and mass characteristics and motion parameters of the vortex generator, preferably use information about the type of vortex generator, its speed, angular velocity and the coordinates of the points of its trajectory; save information about the coordinates of the trajectory points, the speed of movement and the angular velocity of the vortex generator in an inertial coordinate system; as information on environmental parameters, information is preferably used on the magnitude and direction of the local wind speed, wind profile in height, degree of turbulence, type of underlying surface; determine the trajectory and intensity of the vortex wake of the vortex generator at the current time, as a set of trajectories of the centers of the vorticity regions generated by the specified generator, based on the stored information about the type of vortex generator, the coordinates of its trajectory points, the velocity and angular velocity; modeling of the control plane is carried out on the basis of information about the location, orientation and speed of movement of the aircraft and the selected lead time at the current time in an inertial coordinate system; the geometric characteristics of the danger zone of the vortex wake of the vortex generator are determined, as the totality of the danger zones of the vortex areas generated by the indicated generator, based on the stored information about the coordinates of the trajectory points and the intensity of the vortex generator trail, as the totality of the trajectories of the centers of the vorticity regions in the inertial coordinate system, configuration information , position, speed of movement and angular velocity of the aircraft in an inertial coordinate system; the trajectory and intensity of the vortex wake of the indicated vortex generator at the predicted point in time is determined based on information about the trajectory and intensity of the vortex wake of the specified vortex generator, as a set of trajectories of the centers of the vorticity regions generated by the indicated generator in the inertial coordinate system; determining the coordinates of the points of intersection of the vortex wake trajectory of the specified vortex generator with the control plane at the predicted point in time is carried out on the basis of information about the coordinates of the control plane in the inertial coordinate system, the trajectory and intensity of the vortex wake of the specified vortex generator in the inertial coordinate system at the predicted point in time; the formation in the control plane of the danger zone of the vortex wake of the vortex generator, the formation of the area of the predicted positions of the aircraft and the area of increased attention is carried out on the basis of information about the coordinates of the points of intersection of the vortex wake of the specified vortex generator with the control plane at the predicted time, information about the geometric characteristics of the danger zone of the vortex wake the specified generator, as a set of hazardous areas of the swirl regions generated by the specified generator ohm, information about the position, orientation, movement speed and angular speed of the aircraft, taking into account the established standards for flight production; the coordinates of the area of the predicted positions of the aircraft, the coordinates of the area of increased attention and the coordinates of the danger zone of the vortex trace in the coordinate system associated with the aircraft are determined based on information about the coordinates of the area of increased attention, the area of the predicted positions of the aircraft, taking into account the established standards for flight performance and dangerous zones of the vortex wake at the predicted point in time and information about the coordinates of the aircraft and its position, pre respectfully, the pitch angles of the aircraft yaw and roll, in an inertial coordinate system at the current time. 3. The method according to claim 1, characterized in that the current correction of the lead time and / or the current correction of the coordinates of the area of the predicted positions of the aircraft and / or the current correction of the coordinates of the area of increased attention. 4. The method according to claim 1, characterized in that the operations of the method are carried out simultaneously for each of the vortex generators located in the vicinity of the aircraft, and the user is provided with information about the coordinates of the control plane, the area of increased attention, the area of the predicted positions of the aircraft and dangerous areas vortex traces of vortex generators located in the vicinity of an aircraft. 5. The method according to claim 1, characterized in that the user is visualized with information about the location in the control plane of the area of the predicted positions of the aircraft, the area of increased attention and the danger zones of the vortex wake of vortex generators. 6. The method according to claim 1, characterized in that the indication of the equality to zero of the distance from the area of increased attention to the danger zone of the vortex wake of the vortex generator in the control plane and / or the emergency indication of the equality of zero to the distance from the region of the predicted positions of the aircraft to the danger zone of the vortex wake of the generator vortices are carried out using an indication selected from the group including visual, audio and tactile indication. 7. The method according to claim 1, characterized in that they store information about the value of the selected lead time, the coordinates of the control plane, the area of the predicted positions of the aircraft and the danger zones of the vortex traces of the vortex generators during the emergency indication of the event that the distance from the region of the predicted positions of the aircraft is zero apparatus to the danger zone of the vortex wake of the vortex generator. 8. A warning system about the possibility of an aircraft entering the danger zone of the vortex wake of the vortex generator, including a device (1) for tracking aircraft parameters, capable of receiving information about the configuration, location and orientation of the aircraft relative to the inertial coordinate system at the current time; a device (2) for tracking the vortex generator, capable of receiving information about the position, geometric and mass characteristics of the vortex generator relative to the same coordinate system at the current time, and about the parameters of its movement; a storage device (3) capable of storing information about the position and motion parameters of the vortex generator in an inertial coordinate system; a detector (4) of environmental parameters, capable of receiving information about environmental parameters in the field of joint placement of the aircraft and the vortex generator at the current time; a vortex wake tracking device (5) capable of determining the trajectory and intensity of a vortex wake of a vortex generator as a set of trajectories of centers of vorticity regions in an inertial coordinate system; a storage device (6) capable of storing information about the coordinates of the points of the trajectory and the intensity of the trace of the vortex generator as a set of trajectories of the centers of the vorticity regions in an inertial coordinate system; a lead-time selection device (7) during which at least it is possible to perform a maneuver of changing the flight path of the aircraft, providing the aircraft to evade the vortex wake of the vortex generator after warning about the possibility of getting into it; a control plane modeling device (8) capable of calculating a pre-emptive distance equal to the distance covered by the aircraft during the lead, form a control plane located in space in front of the aircraft perpendicular to the direction of its movement at a proactive distance from the aircraft and determine the predicted time of flight the aircraft through the control plane in the inertial coordinate system; a device (10) for determining the parameters of the danger zone, capable of determining the geometric characteristics of the danger zone of the vortex wake of a vortex generator as a set of dangerous zones of vortex zones generated by a vortex generator at a predicted point in time; a prediction device (9) capable of determining the trajectory of the vortex wake of the vortex generator as a set of trajectories of the centers of the vorticity regions generated by the generator and the intensity of the vortex wake relative to the inertial coordinate system at the predicted point in time; a device (11) for calculating intersection points, capable of determining the coordinates of the points of intersection of the trajectory of the vortex wake of the vortex generator with the control plane at the predicted time point when the aircraft intersects the specified control plane; device (12) forming zones and regions, providing forming around the intersection of the trajectory of the vortex wake with the control plane of the danger zone of the vortex wake, as a set of dangerous zones of the vortex areas generated by the vortex generator, when it enters the aircraft motion parameters can exceed the permissible limits; the formation in the specified control plane of the region of the predicted positions of the aircraft, taking into account the established standards for the production of flight at the predicted time the aircraft intersects the control plane; the formation around the area of predicted positions of the area of increased attention, information about getting into the danger zone of the vortex wake should be provided to the user; a transition unit (13) capable of calculating the coordinates of the area of the predicted positions of the aircraft, the area of increased attention and the danger zone (vortex wake in the coordinate system associated with the aircraft); the first block (14) of checking the intersection condition, capable of determining the distance from the area of increased attention to the danger zone of the vortex wake and recording the moment of its equality to zero; the second block (15) of checking the crossing condition, capable of determining the distance from the area of the predicted positions of the aircraft to the danger zone of the vortex wake and recording the moment of its equality to zero; an indication device (16) providing an indication of the event that the distance from the area of increased attention to the danger zone of the vortex wake of the vortex generator is equal to zero; an emergency indication device (17) providing an indication of the event that the distance from the region of the predicted positions of the aircraft to the danger zone of the vortex wake of the vortex generator is equal to zero. 9. The system of claim 8, characterized in that: device (1) tracking the parameters of the aircraft is capable of receiving information, at least about the configuration, coordinates, speed, pitch, yaw and roll of the aircraft; the device (2) for tracking the vortex generator is capable of receiving information, at least, about the type of vortex generator, its speed, angular velocity and the coordinates of the points of its trajectory; the detector (4) of environmental parameters is capable of receiving information at least about the magnitude and direction of the local wind speed, wind profile in height, degree of turbulence, type of underlying surface; the vortex wake tracking device (5) is capable of determining the trajectory and intensity of the vortex wake of the vortex generator as a set of trajectories of the centers of the vorticity regions based on the stored information about the type of vortex generator, the coordinates of its trajectory points, the speed of movement and angular velocity; the control plane simulator (8) is capable of simulating a control plane based on information about the location, orientation and speed of the aircraft and the lead time; the device (10) for determining the parameters of the danger zone is able to determine the geometric characteristics of the danger zone of the vortex wake of the vortex generator based on the stored information about the coordinates of the trajectory points and the intensity of the vortex generator trace, information about the position, speed of movement and the angular velocity of the aircraft in an inertial coordinate system; the prediction device (9) is capable of determining the trajectory of the vortex wake of the vortex generator and the intensity of the vortex wake based on information about the trajectory and intensity of the vortex wake as a set of trajectories of the centers of the vorticity regions generated by the generator in an inertial coordinate system; the device (11) for calculating the intersection points is able to determine the coordinates of the intersection points of the trajectory of the vortex trace of the vortex generator with the control plane based on information about the coordinates of the control plane, the trajectory of the vortex trace in the inertial coordinate system at the predicted point in time; the device (12) for forming zones and regions is capable of forming a vortex wake danger zone, an area of predicted aircraft positions, an area of increased attention based on information about the coordinates of the points of intersection of the vortex wake of the vortex generator at the predicted time, information about the geometric characteristics of the danger zone, as a set of dangerous zones of vorticity regions generated by the vortex generator, information about the position, orientation, displacement velocity and angular velocity of the aircraft arata, taking into account the established standards of flight production, in an inertial coordinate system; the transition unit (13) is able to calculate the coordinates of the area of the predicted positions of the aircraft, the area of increased attention and the danger zone of the vortex wake in the coordinate system associated with the aircraft, based on the coordinates of the area of the attention, the area of the predicted positions and the danger zone of the vortex wake to the predicted point in time in an inertial coordinate system and information about the coordinates of the aircraft and its position, preferably the pitch, yaw and roll angles, inertia coordinate system at the current time. 10. The system of claim 8, characterized in that it contains a device (2) for tracking the vortex generator, storage devices (3, 6), a device (5) for tracking the vortex wake, a device (10) for determining the parameters of the danger zone, a device ( 9) forecasting, a device (11) for calculating intersection points, a device (12) for forming zones and areas, first and second blocks (13, 14) for checking the intersection conditions, an indication device and an emergency indication device capable of simultaneously performing their functions in relation to each from generators vortices located in the vicinity of the aircraft. 11. The system according to claim 8, characterized in that the lead-time selection device (7) is configured to carry out the current lead-time correction, the zones and regions formation device (12) is configured to carry out the current coordinate correction of the region of the aircraft's predicted positions and coordinates areas of increased attention. 12. The system of claim 8, characterized in that it contains a device (18) for visualizing information for the user about the location in the control plane of the area of the predicted positions of the aircraft and the danger zones of the vortex traces of the vortex generators. 13. The system of claim 8, characterized in that as the device (10) for determining the parameters of the danger zone of the vortex wake of the vortex generator contains a device including block (19) of the aircraft schematization, capable of calculating the set of geometric characteristics of the aircraft, necessary for calculating the additional aerodynamic forces and moments acting on it, induced by the vortex wake of the vortex generator; block (20) for determining the additional aerodynamic forces and moments acting on the aircraft at a given point in the space, induced by the vortex wake of the vortex generator, capable of calculating them based on the stored information about the coordinates of the points of the trajectories of the vorticity centers and the intensity of the vortex generator trail as a set of trajectories of the centers of the vortex regions in inertial coordinate system, information about the position, speed of movement and angular velocity of the aircraft in inertial systems coordinates and geometric characteristics of the aircraft; a unit (21) for determining the hazard of aerodynamic disturbances at a given point in space, capable of assessing the hazard of disturbances according to a hazard criterion set by the user; block (22) for determining the set of points in space at which additional aerodynamic forces and moments induced by the vortex trace of the vortex generator are dangerous, capable of determining the coordinates of the points of space belonging to the danger zone based on their selection according to the hazard criterion set by the user; block (23) for determining the geometric characteristics of the danger zone of the vortex wake, capable of calculating them based on information about the coordinates of points belonging to the danger zone. 14. The system of claim 8, characterized in that as the criterion of danger selected acceptable angle of heel of the aircraft. 15. The system of claim 8, characterized in that as the criterion of danger selected acceptable value of the moment of heel induced by the vortex wake. 16. The system of claim 8, characterized in that it contains a device for determining the geometric characteristics of the danger zone of the vortex wake, configured to approximate the boundary of the danger zone. 17. The system according to claim 8, characterized in that the vortex wake tracking device (5) and the prediction device (9) comprise a programmable component, and the hazardous area parameter determination device (10) is implemented in the programmable component software and contains a database of characteristics hazard zones of vortex traces of various types of vortex generators. 18. The system of claim 8, characterized in that it contains a device for storing and / or transmitting information to the user about the lead time, the coordinates of the control plane, the area of the predicted positions of the aircraft and the danger zones of the vortex traces of the vortex generators located in the vicinity of the aircraft, at least during the emergency indication of the event that the distance from the region of the predicted positions of the aircraft to the danger zone of the vortex wake of the vortex generator is zero.

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