HK1097914A - Integrated system for aircraft vortex safety - Google Patents

Description

Integrated system for aircraft vortex safety

Technical Field

The present invention relates to providing a method and a device for safe piloting operations of an aircraft, and in particular to observing the occurrence of pre-warning or preventing an accidental situation linked to the risk of the aircraft entering another flying object causing a danger zone of distributed air flow, this being the so-called "wake vortex" generated by this object or as a result of a steady air flow around the flying object.

Background

The problem of providing safe aircraft flight is a problem of great current interest and involves several technical and organizational problems. One such problem is to provide safe flight when the determining factor is the aerodynamic influence of high levels of turbulence in the vortex, for example, when another aircraft is flying in the vicinity and the wake vortex is created by other objects that are subjected to high levels of turbulence and turbulent air flow.

It is known that flying aircraft generate wake vortices. An aircraft encountering wake vortices generated by another aircraft produces significant changes to its angle of attack and glide. Aircraft are exposed to the effects of aerodynamic forces and moments that can cause the aircraft to fall off its tail, which can lead to dangerous situations when flying at low altitudes from ground, e.g., during take-off and landing, since the aircraft cannot compensate for the effects of such forces and moments by means of aircraft control.

The appearance of an aircraft with low aspect ratio wings and heavy wing loads may increase the wake vortex strength, thereby increasing the risk of the aircraft entering the wake vortex region.

A great deal of research work on transport and vortex attenuation has shown that environmental factors such as wind, wind direction transitions, stratification, and turbulence play an important role in these processes.

On the basis of reasonable forecasted wake dynamics, taking into account the effects of new forecasted weather conditions and atmospheric conditions, and the effects of ground on wake dynamics, a potential opportunity is to optimize the safe distance between aircraft during landing, takeoff and cruise flights.

One major trend in determining this problem is to study an on-board computer system operating in real time, determine the risk level of aerodynamic effects on the aircraft, and allow the option of further modifying the flight control of the aircraft with the aim of effectively compensating for such aerodynamic disturbances.

Another task may be referred to as an informational task that provides the pilot with information about the wake vortex location and the position of the aircraft relative to the wake vortex within a predetermined time period.

Methods and devices for observing wake vortices on a display are well known, based on mathematical models that take into account vortex generator aircraft and current weather data. According to the technical solution, the device makes use of a fast-response display in which it is possible to observe the simulated wake vortices (US, 5845874, a) generated by the aircraft and located in the vicinity of the aircraft to be protected. However, in the case of a protected aircraft with many aircraft in the vicinity, for example, an airport, the display may show a large number of simulated wake vortices, and it is therefore difficult to identify which wake vortices pose a real danger to the aircraft and which are negligible.

One of the most promising methods for improving flight safety is to provide the pilot with a forecasted position of the wake vortices in real time, the entry of the aircraft into this position possibly causing an accident.

Warning systems for wake turbulence are well known. The system is designed for onboard installation. Only if the system evaluates that such an entry is likely to occur after a certain period of time, it informs the aircraft crew that a wake vortex may be entered into another aircraft (US, 6177888, a). The system provides mutual coordinates of the two aircraft, exchanges warning signals and information about the current height, distance and orientation from the ground, and tracks the wake vortex path relative to the local wind speed. The system determines a distance or time before the aircraft enters a wake vortex of another aircraft and indicates that the aircraft is approaching the wake vortex when the distance or time is less than a preset threshold. The width and height of each wake vortex volume in the set of points on the wake vortex path is calculated as a function of the distance from the given point to the adjacent aircraft.

However, such a system does not solve the problem of providing the pilot with information about the level of danger when entering wake vortices, nor does it suggest to avoid entering wake vortices for aircraft operation.

Furthermore, various aircraft flight conditions require a reduction in the distance between aircraft, for example during successive take-off and landing of the stations, which is very important for increasing the capacity of the stations.

Reliable knowledge of wake vortex locations and structures and their effect on the aircraft at the forecasted time is beneficial to meet the conflicting requirements of increased flight efficiency and safety.

Wake vortex warning systems are well known. The system is designed for on-board installation and to alert pilots to the presence of another aircraft in the vicinity of the aircraft in anticipation of danger (US, 6211808, B1). The system consists of a spherical antenna of dielectric material with 8 receiver sectors for detecting microwave signals reflected from other aircraft. However, this system is quite expensive and does not provide the pilot with information about the occurrence of dangerous air disturbances.

There is another solution which provides a method of preventing the intersection of an aircraft with the wake vortex of another aircraft (WO 00/71985). The solution requires determining the position, geometry and structure of wake vortices generated by the other aircraft, the presence of which is determined by means of information received from the onboard system of the first aircraft, information received from the other aircraft, or information received from the airport. The solution also requires the determination of the altitude of the other aircraft, the forecasted position of the wake vortex of the other aircraft with respect to the environmental conditions, in particular the wind speed and direction, the air temperature, the received data with reference tables, or by making a model of the wake vortex by observing the position and the path with respect to the first aircraft, the intersection of the wake vortex path with the trajectory of the first aircraft, in the case of which an alarm signal is used. Generally, the method is used in an airport area to provide safe flight of two aircraft. Implementation of the method may result in an increase in the altitude of the first aircraft on the second aircraft. The method utilizes a Traffic collision avoidance System (Traffic collision avoidance System). However, the first aircraft pilot receives visual information of all vortex regions in the flight zone due to the presence of the second aircraft. Thus, this situation does not provide the pilot with a true wake vortex hazard picture.

It is well known that NASA, USA is largely concerned with improving terminal area efficiency, and in particular, during aircraft take-off and landing, one trend of research work is to implement AVOSS (aircraft vortex spacing system) which combines the outputs of different systems and elaborates dynamic criteria for safe wake vortex separation, which depend on weather stripsPiece (37)^th Aerospace SciencesMeeting &Exhibit, January 11-14, 1999, Reno, NY, NASA Langley research Center, Hampton, Va.). Such a system represents current and forecasted conditions, a model of wake vortex transmission, and wake vortex decay from ground to take-off and landing glide paths under these weather conditions, as well as real-time feedback of wake vortex behavior. Comparing wake vortex behavior with previously determined safe corridor dimensions and calculated data regarding wake vortex attenuation. The result is the required safe aircraft separation. If wake vortices are present for longer than expected, reducing the standard separation is prohibited. Wake vortex behavior is calculated for a number of 'windows' from the taxi path height to the runway threshold.

However, such systems have several limitations, such as: without considering the high wind direction transition, it may prevent the wake vortex from falling or the original wake vortex from rising; the lack of consideration of a particular turbulence scale, which is necessary to correct the wake vortex decay model, and other things may cause an abnormal situation to occur due to the inconsistency of the calculated wake vortex parameters with the actual wake vortex parameters provided to the flight controller.

Furthermore, the AVOSS implementation can result in increased loading of the flight controller, subjecting it to severe emotional burdens, as they are labor intensive and can create an unnecessary risk of taking incorrect decisions.

It should be kept in mind that foreign safety systems primarily utilize so-called 'instrument flight rules' when aircraft flight is performed on the basis of commands made by the flight controller and implemented in either commander or automatic mode.

However, the most critical in flight controller activity is to make the correct decision in an emergency. There are two stages in the process: identify the situation and determine activities intended to eliminate the emergency. At the beginning of each activity, the flight controller should consider additional steps. The perception of visual and audio signals in spoken form from long-term memory, display media or hearing takes a certain time in the case of insufficient time. The time to perceive the graphical symbol is much less and the recognition of the presence of separate image areas improves the accuracy of the determination.

Furthermore, physical factor effects such as acceleration can shift the brain cycle of the pilot and can even temporarily lose consciousness in the case of emotional and nervous stress. Therefore, a reasonable approach to solve this problem is to provide the pilot or flight controller with graphical symbol information in advance, which is required to make a decision.

Disclosure of Invention

The object of the present invention is to develop a safety system for aircraft flight under the risk of wake vortices being generated by the entering other aircraft, ground objects, and moving or immobile objects on the sea in the vicinity of the flying aircraft, including take-off and landing conditions.

The specific task of the present invention is to develop an integrated vortex safety system that informs the user of the presence of wake vortices generated by different objects in the vicinity of the aircraft, which can cause danger to the aircraft according to danger criteria chosen by the user. The system should also inform the user about the geometrical parameters of wake vortex danger areas, the entry of which could cause accidents. Another feature of the system is to prompt the pilot or other user that may affect the flight of the aircraft to generate control signals for ensuring safe evasive action by the aircraft.

This specified task can be accomplished by developing an integrated system for aircraft vortex safety, comprising the following subsystems:

an aircraft information subsystem capable of determining, storing, and providing information to a user regarding the location of the aircraft;

a wake vortex information subsystem capable of determining, storing, and providing information to a user regarding the proximity of the aircraft to wake vortex generators;

an environmental information subsystem capable of determining, storing and providing information to a user regarding environmental conditions in the vicinity of the aircraft at current and forecasted times;

a warning subsystem that warns the user that the aircraft is likely to encounter a wake vortex danger zone generated by the vortex generator within the user selected forecasted time;

a user subsystem capable of at least determining, storing and indicating to the user the information received from the other subsystems and forming a signal suggesting evasive action for the aircraft during a user selected time period following the user receiving a warning of the potential entry into the vortex generator wake vortex danger area at the forecasted time;

a communication subsystem that forms an integration of subsystems in a single complex.

Further, the integrated system according to the present invention includes:

an aircraft information subsystem providing information to the warning subsystem regarding at least aircraft configuration, coordinates and attitude in the inertial frame, aircraft velocity and angular velocity components in the aircraft frame;

a vortex generator subsystem that provides processing, storing and transmitting information to a user regarding at least vortex generator type, coordinates and attitude in an inertial frame, airspeed and angular velocity components;

an environmental information subsystem that provides processing, storing and transmitting information to a user regarding at least the components of wind velocity in an inertial coordinate system at different heights in the region of wake vortices and the ambient turbulence;

a warning subsystem that informs the user that the aircraft is likely to encounter the vortex generator danger zone, calculates at least a position and an intensity of the vortex generator wake vortex danger zone, forecasts the position zone of the aircraft at the forecasted time, and sends information to the user subsystem regarding the aircraft is likely to encounter the vortex generator wake vortex danger zone at the forecasted time;

a user subsystem which receives, processes, stores and indicates information from the warning subsystem at least as to the nulling of the distance from the area of the aircraft forecasted positions to the vortex generator wake vortex danger area at the forecasted time, and forms a signal indicating the variation of the aircraft position to increase said distance.

Furthermore, according to the present invention, the integrated system should be implemented in the following manner:

the aircraft information subsystem is realized on the basis of standard aircraft-mounted equipment of an aircraft and/or ground, sea and/or aerospace navigation complex equipment;

the vortex generator information subsystem is realized on the basis of standard airborne equipment of an aircraft and/or standard equipment of a vortex generator and/or air traffic control equipment used for the ground, the sea or an aerospace complex;

the environment information subsystem is realized on the basis of standard airborne equipment of an aircraft and/or standard meteorological equipment for an air traffic control system or ground, sea and/or aerospace navigation complex equipment;

the warning subsystem is implemented on the basis of user computer software and/or an onboard unified indicator system and/or an indicator system of air traffic control service or an aerospace navigation complex on the ground at sea and/or in the field of flight controllers, which informs the user that the aircraft may encounter a vortex generator wake vortex danger zone;

the user subsystem is realized on the basis of user computer software and/or standard equipment software on board the aircraft and/or ground or sea navigation complex software on the site of the flight controller;

the communication subsystem is realized on the basis of an airborne multipath channel of a data transmission communication system and/or information exchange.

According to the invention, the integrated system user may be an aircraft and the implementation of the advisory signal may be performed by an aircraft crew or an aircraft auto-flight system.

Further, in accordance with the present invention, the integrated system user may be an air traffic control service; when the advisory signal is transmitted to the aircraft crew member, the crew member or the aircraft automatic control system may implement the advisory signal.

According to the invention, the integrated system should comprise as warning subsystem a subsystem informing that the aircraft is likely to encounter the vortex generator wake vortex danger area at the forecasted time, the system comprising:

an aircraft tracker capable of receiving information about the configuration of the aircraft, the position, coordinates, and attitude in the inertial frame at the current time;

a vortex generator tracker capable of receiving information about vortex generator position, geometric and weight characteristics, and motion parameters in the inertial frame at the current time;

a memory unit capable of storing information about the vortex generator position and motion parameters in an inertial frame;

an environmental parameter detector capable of receiving information about environmental parameters of the aircraft and the vortex generators in a current time-combined space;

a wake vortex tracker capable of determining vortex generator wake vortices in the form of a set of vortex central paths in an inertial frame;

means for selecting a delay time capable of calculating a time period during which the aircraft is at least likely to take flight evasive action, so that the aircraft avoids the vortex generator wake vortex danger zone after receiving a warning signal that wake vortices are likely to be encountered;

means for simulating a control plane capable of calculating a delay distance equal to the distance covered by the aircraft during the delay time, modeling a control plane located in front of the aircraft, perpendicular to its direction of flight over the delay distance, and determining the forecasted time required by the aircraft to acquire the control plane in an inertial frame;

means for determining the parameters of the danger zone, capable of determining the geometrical characteristics of the vortex generator wake vortex danger zone in the form of a set of danger zones in the vortex generator vortex zone at the forecasted time;

forecasting means capable of determining the wake vortex path of a vortex generator in the form of the centre of the generator vortex region in the inertial frame and the set of generator wake vortex intensities at the forecasted time;

means for calculating the points of intersection, capable of determining the coordinates of the points of intersection of the generator wake vortex trajectory with the aircraft flying through the control plane at the forecasted time;

a zone forming device capable of forming an intersection of a wake vortex path with a wake vortex hazard zone control plane in the form of a set of generator wake vortex hazards, wherein an incoming aircraft may have flight parameters exceeding allowable limits; forming an intersection point with a prescribed control plane relative to the flight in an aircraft forecasted position area control plane within an aircraft forecasted time; forming a warning area of the forecast position of the aircraft; providing information to a user regarding entry of the wake vortex danger zone into the warning zone;

a transformation unit capable of calculating the coordinates of the aircraft forecasted position area, the warning area and the wake vortex danger area in the aircraft coordinate system;

a first intersection condition test unit capable of calculating a distance from the warning area to the wake vortex danger area and marking a distance at which it becomes zero;

a second intersection condition test unit capable of calculating the distance from the aircraft forecasted position area to the wake vortex danger area and marking the distance at which it becomes zero;

a first indicating unit capable of forming and transmitting a signal of the distance from the area of the aircraft forecasted position to the vortex generator wake vortex danger area becoming zero;

a second indicating unit capable of indicating a distance from the warning zone to the vortex generator wake vortex danger zone becoming zero.

The system according to the invention has the following features:

the aircraft parameter tracker is capable of receiving at least information regarding aircraft configuration, coordinates, flight speed, pitch, yaw and roll;

said vortex generator tracker being capable of receiving at least information about vortex generator type, flight speed, angular velocity and generator waypoint coordinates;

the environmental parameter detector is at least capable of receiving information regarding local wind speed magnitude and direction, high altitude wind patterns, environmental turbulence intensity, and underlying terrain type;

the wake vortex tracker is capable of determining a vortex generator wake vortex path in the form of a set of generator vortex region center and wake vortex intensity on the basis of stored information about vortex generator type, velocity, angular velocity, and coordinates of points on the generator path;

the device for simulating the control plane can model the control plane on the basis of information about the position, flight attitude, speed and delay time of the aircraft;

the device for determining the parameters of the danger zone can determine the geometrical characteristics of the generator wake vortex danger zone on the basis of the stored track point coordinates and the generator wake vortex intensity information as well as the information of configuration, position, speed and angular speed of the aircraft in an inertial coordinate system;

the forecasting device is capable of determining the wake vortex path and the intensity of the vortex generator on the basis of the information about the wake vortex path, in the form of a set of the trajectory of the generator vortex region center and the wake vortex intensity in an inertial coordinate system;

the means for calculating the intersection points are able to determine the coordinates of the intersection points of the generator wake vortex trajectory with the control plane on the basis of information about the coordinates of the control plane and the wake vortex trajectory in the inertial frame at the forecasted time;

the area forming means are able to form wake vortex danger areas, aircraft forecasted position areas and warning areas on the basis of coordinate information about the intersection of the generator wake vortex path with the control plane at the forecasted time, information on the geometrical characteristics of the danger areas in the form of a set of generator vortex danger areas, and aircraft position, attitude, velocity and angular velocity information relative to the flight rules in an inertial frame;

the transformation unit is capable of calculating the coordinates of the aircraft forecasted position area, the warning area and the wake vortex danger area in the aircraft coordinate system on the basis of information about the aircraft forecasted position area coordinates, the warning area coordinates and the wake vortex danger area coordinates and information about the aircraft coordinates and the flight attitude, preferably the pitch, yaw and roll angles in the current time inertial coordinate system.

Further in accordance with the present invention, the warning subsystem in the integrated system includes: vortex generator tracker, memory unit, wake vortex tracker, unit for evaluating parameters of a hazard zone, device for evaluating parameters of a hazard zone, forecasting device, device for calculating intersection points, area forming unit, transformation unit, first and second intersection condition testing unit, and signal unit capable of simultaneously signaling each vortex generator adjacent to an aircraft.

Furthermore, it is desirable that said means for selecting a delay time in an integrated system according to the invention can be implemented with a current corrected delay time.

Furthermore, it is desirable according to the invention that the area forming unit can be realized with the current correction of the possible location area of the aircraft.

Furthermore, it is desirable that the area forming unit can be realized with a current correction warning area according to the present invention.

Furthermore, it is desirable that the current correction delay time, the current correction aircraft possible location area, and the current correction warning area may be implemented manually according to the present invention.

Furthermore, it is desirable that the above-described correction can be implemented in a semi-automatic or fully automatic manner according to the present invention.

Further, it is desirable that, according to the present invention, the integrated security system includes: the user observes a unit of information about the aircraft position and the vortex generator wake vortex danger zone.

Further, it is desirable that the user subsystem includes: an indicating unit and a warning indicating unit selected from the group consisting of a visual, an audible and a tactile unit.

Ideally, according to the invention, the integrated system comprises means for determining a parameter of the hazard zone, comprising:

a unit for aircraft planning capable of calculating a set of aircraft geometric features on the basis of aircraft configuration, coordinates, flight speed, pitch angle, yaw and roll, which are necessary for evaluating the generator wake vortex induction and the additional aerodynamic forces and moments acting on the aircraft;

a unit for evaluating the additional aerodynamic forces and moments acting on the aircraft at a given point and induced by the generator wake vortices, in the form of a set of the vortex centre trajectory and the generator wake vortex intensity in an inertial frame, on the basis of stored information about the path of the wake vortex point, and capable of calculating these aerodynamic forces and moments on the basis of information about the aircraft configuration, position in the inertial frame, flight speed, angular velocity, and aircraft geometry;

a unit for estimating a risk level of the aerodynamic disturbance at a given point, capable of estimating the risk level on the basis of a user-selected criterion;

a unit for determining that the aerodynamic forces and moments of the aircraft induced by the generator wake vortices are points of danger, capable of determining the coordinates of points on the danger area on the basis of a user-selected danger criterion;

a unit for evaluating the geometrical characteristics of the wake vortex danger area, which is able to calculate these geometrical characteristics on the basis of the coordinate information of the points of the danger area.

According to the invention, in the warning subsystem, the unit for evaluating the wake vortex danger zone geometry is able to approximately determine the danger zone boundary.

According to the invention, the permissible aircraft roll torque induced by the vortex generator wake vortices is preferably selected in the integrated system.

Furthermore, according to the invention, the aircraft roll torque induced by the vortex generator wake vortices can be selected as a risk criterion in the integrated system.

According to the invention, preferably, said wake vortex tracker and forecast unit in the integrated system comprises: a programmable element; and said unit for evaluating the geometrical characteristics of the wake vortex danger zone is implemented in software of a programmable element.

According to the invention, the devices of the integrated system and the units can be positioned differently.

Furthermore, according to the invention, the integrated system may comprise a system for storing information at least about the delay time, the control plane coordinates, the aircraft forecasted position area, and the vortex generator danger area at least during an emergency indication time period in which the distance from the aircraft forecasted position area to the vortex generator wake vortex danger area becomes zero.

Drawings

The invention is described by way of example and with reference to the accompanying drawings, in which:

FIG. 1 is an information flow diagram of an integrated eddy current safety system according to the present invention;

FIG. 2 is a user subsystem for implementing a warning subsystem and incorporating features that inform the user that the aircraft may encounter vortex generator wake vortex danger zones in accordance with the present invention;

FIG. 3 is a unit for implementing the evaluation of geometrical features according to the invention;

FIG. 4 is information that may be observed in a user subsystem in accordance with the present invention;

fig. 5 is a representation of the form of information that may be observed in a user subsystem in accordance with the present invention.

Detailed Description

The invention can be illustrated by means of embodiments which do not limit its application. Fig. 1 represents a scenario in which the user is an aircraft flying in the vicinity of the airport (hereinafter denoted a/C), while the flight of another aircraft in the vicinity generates wake vortices (hereinafter referred to as vortex generators or VGs). The aircraft is equipped with a navigation system that can measure navigation and flight parameters of itself and other aircraft.

The airport navigation device comprises the following devices: for example, the International radio System Complex (VOR Radar Range) containing nearby navigational VOR/DMEs, which is a standard device operating on foreign airlines, is used to automatically and continuously determine aircraft position (ranging up to 370km and covering 0-40 °), the automatic direction finder is used to indicate aircraft bearing, e.g., ARP-7S type bearing, and the APR-8 type navigation station provides flight operations for aircraft equipped with the automatic direction finder.

Fig. 1 shows an information flow diagram of an aircraft vortex safety system according to the invention, in which an aircraft subsystem 1 holds information about the aircraft, and a vortex generator subsystem 2 (hereinafter denoted VG) and an environmental subsystem 3 are implemented in the above-described flight and navigation complex, partly on the basis of an aircraft station installation. In accordance with the present invention, these systems determine, store and transmit information about aircraft attack and sideslip angle, angular velocity, aircraft control yaw, machine mode, overload in the aircraft coordinate system, indicated airspeed, acceleration, flight attitude angle, and velocity vectors in the inertial coordinate system, position coordinates, radar weather data, following ground type, vortex generator position, and information about other wake vortex generator positions, their shape, size, velocity and altitude, high altitude wind mode, wake vortex generator type, their waypoint coordinates, and their geometry and weight data to other subsystems of the integrated vortex safety system.

A warning subsystem (4) informs the user that the aircraft will eventually enter the vortex generator hazard zone, which is implemented on the basis of an aircraft flight navigation system and an aircraft computer system. The user subsystem (5) is implemented on the basis of an aircraft computer system and a pointing and vision system, for example a head mounted display system. The communication subsystem (6) is realized on the basis of a plurality of onboard information channels.

According to the invention, the warning subsystem (4) and the part of the user subsystem (5) comprising the vision system are implemented according to the scheme shown in fig. 2. On the basis of the information received from the subsystems (1), (2) and (3), the warning subsystem (4) calculates the wake vortex path in the vicinity of the aircraft as a set of vorticity wake vortex central path points, determines the geometrical data of the VG wake vortex area, meets the requirements of the risk criteria specified by the user, when the a/C intersects some simulated control plane located before the a/C, which is perpendicular to the flight trajectory at a predetermined distance from the a/C, for example, the roll angle of the a/C under the wake vortex effect is forecasted within the forecast time; information about the possible forecasted positions of the aircraft and the wake vortex danger area on the control plane is formed, the danger level of the aircraft is evaluated, and the distance between the danger area and the A/C is tracked in real time.

By means of an acoustic, tactile or visual indication, the user subsystem (5) informs the pilot about the entry of the forecasted event into the hazard zone and provides the user with visual information, forming a desired signal such as an acoustic signal. If the subsystem (5) is also on-site at the flight controller, this information can be replicated, allowing the flight controller to focus on making the correct decisions.

According to the scheme shown in fig. 2, in the warning subsystem (4), the a/C parameter tracker (7) receives information about the aircraft from the subsystem (1) through the communication subsystem (6), and in particular, according to the invention, the information relates to the a/C configuration, the coordinates in the inertial frame at the current time, the flight speed, the angular velocity, the tilt angle, the yaw and the roll angle.

The wake vortex generator tracker (8) receives information about the wake vortex generators from the subsystem (2) via the communication subsystem (6) and stores information about the type of VGs, the flight speed, the angular velocity and the trajectory point in the inertial frame in a memory device (9).

The environmental parameter detector (10) receives environmental information from the subsystem (3) through the communication subsystem (6), for example from the aircraft air data system or from flight officers, regarding local wind speed and direction, high altitude wind patterns, turbulence, the following ground type in the combined a/C and VG region of the inertial frame at the current time t.

On receiving information from the memory unit 9, the wake Vortex tracker 11 calculates VG wake Vortex paths and intensities as the geometry of Vortex centers in the inertial frame, e.g. by means of the author's ' knock-how ' Algorithm, or by means of well-known algorithms for calculating wake Vortex paths and intensities (Northwest Research Association, inc., the Aircraft Vortex spacing system (AVOSS), Algorithm Version 3.1.1), which can calculate the center of Vortex area paths on the basis of differential equations integrating describing spatially and temporally evolving vortices, or by means of other algorithms providing said calculations. The memory unit 12 holds these data. The vortex region coordinates can also be determined by instrumental measurements, e.g. by means of lidar, by means of measuring and estimating the tangential velocity of the air flow, further calculating the wake vortex path and intensity. The device 13 selects a delay time required for the a/C avoidance action. According to the invention, the delay time can be corrected in the current mode by means of manual, semi-automatic or fully automatic control, taking into account the characteristics of the pilot technique or the flight mission. On the basis of receiving information from the device 7 about the a/C coordinates, the flying speed, the tilt, the yaw and the roll angle, and on the basis of receiving information about the selected delay time Δ t from the device 13, the control plane (hereinafter denoted CP) simulation unit 14 simulates a CP located before the a/C, which is perpendicular to the trajectory at the delay distance from the a/C, for example in the form of the coefficients of the CP in the IF and determines the forecasted time t + Δ t at which the a/C flies through the CP. Any computing device capable of performing such calculations, such as an a/C on-board computer, may be used as unit 14. On the basis of the VG wake vortex paths and intensities saved in the relevant device 12 and the forecast time information from the simulation device 14, the forecasting device 15 calculates VG wake vortex path coordinates and intensities in the form of a set of vortex centre paths at the forecast time in IF. On the basis of receiving information from the device 7 about the a/C coordinates, the flight speed, and the angular velocity and information from the memory unit 12 about the VG wake vortex path coordinates and intensity in the form of a VG vortex region central path, the hazard zone parameter evaluation device 16 determines VG wake vortex hazard zone geometry data in the form of a set of VG vortex hazard zones over the forecast time t + Δ t according to the selected hazard criterion. According to the invention, the allowable roll of the A/C or the allowable value of the roll torque of the A/C induced by the VG wake vortex can be selected as a risk criterion.

According to the invention, the wake vortex tracker 11 and the predictor device 15 may comprise programmable elements, for example, capable of calculating the VG wake vortex paths and intensities, while the device 16 may be implemented in the software of such elements, i.e. in a database of calculation geometries for calculating the wake vortex danger zones of different types VG, depending on different environmental conditions and VG movements, the aerodynamic forces and moments induced on the a/C by the different intensity wake vortices, for example, the a/C roll moments.

On the basis of the information on the CP coordinates, for example, the device 17 (fig. 2) implemented in the a/C flight instrument system calculates the intersection of the VG wake vortex path with the CP at the forecasted time t + Δ t, based on the CP coordinate information received from the device 14 and the wake vortex path information from the device 15, for example, by choosing two wake vortex path points on both sides of the CP, with the distance between them being interpolated.

A zone forming device 18, for example, as part of a computer in an A/C inertial navigation system, which forms a wake vortex hazard zone around the intersection of the VG wake vortex path with the CP; the aircraft forecasted position area (hereafter AAFP) and the warning area (hereafter AA) are the set of points on the control plane with respect to the flight rules at the forecasted time t + Δ t. In accordance with the present invention, the device 12 can currently modify the coordinates of the AAFP and AA, which is important for the pilot to coordinate evasive maneuvers in flight situations.

The transformation unit 19 calculates the coordinates of AAFP, VG wake vortex danger area and AA in the A/C coordinate system.

Then, the first unit 20 testing the intersection condition calculates the distance from the AA to the wake vortex danger zone so that its event of nulling can be tracked, and the second unit 21 testing the intersection condition calculates the distance from the AAFP to the wake vortex danger zone so that its event of nulling can be tracked.

Information about the zeroing of these two events at the forecasted time is provided to the user subsystem 5 and is directed to the means 22 and 23, for example to the means 22 in case of a zeroing of the distance between AA and wake vortex danger (audible indication) and to the means 23 of pilot warning tactile indication in case of a zeroing of the distance between AAFP and wake vortex danger. The tactile indication should motivate the pilot to take emergency measures for the a/C evasive action. The pilot has time to handle, relative to the a/C speed and the delay distance, the flight evasive maneuver computed by the CP simulator 14. Depending on the current situation after receiving the first indicator signal from the device 22, the pilot may modify the delay time, for example by setting a discrete value by means of manual control, switching to another value by semi-automatic control, or automatically adjusting, i.e. increasing or decreasing, the condition of the delay time value in case of a criterion setting. Such indication terminates with increasing distance.

According to the invention, the user can view information about the mutual position of the AAFP and the danger zone in the CP within the forecast time in the vision device 24, for example on a display, a windshield indicator, or an a/C navigation chart, and an information volume limit that is not relevant to the pilot; and view the hazard zone only after they intersect with the AA.

According to the invention, the means 16 for evaluating the parameters of the hazard zone can be implemented according to the scheme shown in fig. 3 and can comprise: an a/C planning unit 25 which can receive information from the means 7 in the warning subsystem 4, by means of any known method, and calculate a set of a/C geometrical parameters with respect to the a/C configuration; a unit 26 receiving information from the unit 25 and from the means in the warning subsystem 4 and evaluating the additional aerodynamic forces and moments induced by the VG wake vortices at the appropriate points. Then, on the basis of the given risk criterion, unit 27 determines the risk level of the aerodynamic disturbance at the given point; unit 28 determines the points belonging to the wake vortex danger zone; and unit 29 determines the geometric features of the hazard zone as a set of points and approximately delineates the hazard zone boundary for simplifying viewing of the hazard zone in the display. Information about the VG wake vortex hazard zone is then sent to the device 18 of the warning system and can be viewed when there is a risk of AC entering the hazard zone.

Fig. 4 shows the simulated control plane and VG wake vortex positions in the user alert subsystem 4, e.g. subsystem 4 is located in the a/C nacelle. However, the subsystem 4 may also be located on-site in the flight controller, for example at an airport or in a ship's hold, and merely provide the pilot with visual information by means of on-board visual means.

Fig. 5 shows visual information on the navigation chart display, which is normally used on a/C head-mounted indicated a/C cabins, and displays symbols generated by an onboard navigation system, for example, with an onboard inertial navigation system (AINS), which displays the a/C forecasted position (AAFP) and VG wake vortex danger zones 31 and 32 at the forecasted time. The area 30 of the AAFP has a rectangular shape with a size proportional to the size of the possible location area of the a/C body. According to the present invention, no boundaries of the warning area 36 are shown on the display, and it is appropriate to project the wake vortex danger area on the display only when the danger areas 31 and 32 intersect the AA 33 simultaneously, e.g. an audible indication of an event. The wake vortex hazard zones 31 and 32 may have a circular shape or any shape that facilitates visual viewing of the geometry. Furthermore, the picture may be accompanied by visual indications, e.g. with light or colour extended over the area, or borders 33, 34 and 35 on the AAFP area 30 and wake vortex danger areas 31 and 32, respectively.

According to the invention, it is suitable to store current information about the chosen delay time, the coordinates of the control plane, the area of the aircraft forecasted positions, the vortex generator wake vortex danger area in the emergency cycle, which indicates the event of the distance nulling of the vortex generator from the area of the aircraft forecasted positions to the wake vortex danger area. Such representation can be by means of separate information storage means (not shown in the drawings) placed in the aircraft cabin, for example in flight recorder (so-called "black box") systems, as well as ground, sea or air control equipment. Obtaining this information allows measures to be taken to eliminate the cause of an air accident, estimating the pilot technique in the case of wake vortices in the vicinity of the aircraft, when the entry into the danger zone may cause a change in the configuration of the aircraft or its path.

Of course, the given example contains only one wake vortex generator and indicates only one VG wake vortex danger zone, but these calculations and tracking VG wake vortices are performed with respect to the aircraft adjacent to all VGs, and only the area of the dangerous VG wake vortex is observed on the display. Based on the assessment of the location of the potential danger area made by the pilot on the display, a correct decision can be made as to the proper evasive action of the aircraft.

According to the invention, the subsystem 4 for warning of the possibility of the A/C encountering a VG wake vortex danger zone can be implemented by means of standard air and ground equipment, such as, for example, an A/C in-air navigation System (AINS), an air data computer System (ADC), a Doppler System (DS), a Forward looking Radar (FVR), and by means of information from an Air Traffic Control (ATC) system, a Joint indicator System (UIS), an Information Exchange Multiplex (IEMC), and information from information systems compatible with the above-mentioned systems, which are used on board aircraft in other countries, such as, for example, the traffic warning Collision avoidance System (TCAS).

Furthermore, according to the invention, devices in the integrated system can be positioned discretely on different targets or different a/cs of the air traffic control system or VGs which provide the user with information about the results of the calculation of the operation by means of indication and vision. The users of such information may be the a/C crew, as well as the air traffic control services of the airport and the ships that consult the a/C crew during flight, which involve suggested routes or operations to avoid dangerous flight situations, which are extremely important in low visibility and severe weather conditions.

It should be clear to the aeronautics sciences and avionics technologists that the integrated wake vortex safety system according to the invention employs a comprehensive approach to aircraft flight safety issues, applicable to cruise flight as well as during take-off and landing.

User subsystems located on the a/C cabin and in the field of the flight controller can provide current information corrections under the control of the flight controller and can currently correct information about the vortex conditions in the landing or takeoff area, which can provide safe takeoff and landing operations and reduce the time intervals during takeoff and landing of the aircraft.

Furthermore, with the integrated safety system according to the invention, the burden on the flight controller can be reduced, which provides instructions to the pilot, since the decision-making responsibility regarding avoiding operations is on the pilot who receives additional information, thereby simplifying the decision-making. In any case, we should keep in mind that without the integrated vortex safety system according to the invention, there is no information about the location of the wake vortex danger zone, and the pilot may risk making a false decision.

It should be clear to the experts in the field of aeronautics and sciences and avionics that the integrated wake vortex safety system according to the invention may contain improvements and refinements within the scope of the claims of the invention, linked to different system operating conditions and to improvements in navigation and information systems. For example, we can use different computational algorithms that most closely approximate the operation of the system, applying different methods to point out and view user information, which can improve the user's perceived appropriateness, including the use of different information streams.

Experts in air traffic control will understand that the integrated vortex control system according to the invention can also be used to perform the function of air traffic control, since some vortex situations on the ground and in the vicinity of the flight VGs can be resolved by means of warning systems placed separately on the aircraft, on the hold and on the stations, which, combined into a combined information system, can prevent the occurrence of dangerous situations related to the encounter of a/C with wake vortex danger zones of different VGs. Possible VG classes include different types of aircraft, e.g., airplanes, helicopters, unmanned aircraft, marine vessels including aircraft carriers, and ground structures and other objects.

Industrial applications

According to the invention, an integrated system for aircraft vortex safety can be realized in the form of a program adapted to certain types of a/C, a/C operating conditions, and equipment types, which is compatible with the information system of air traffic control.

The integrated vortex safety system according to the invention can be easily implemented with the aid of well-known devices, which can be installed on different aircraft, as well as various simulators for training pilots and flight controls for various activities in the wake vortex hazard.

Claims (22)

1. An integrated system for aircraft vortex safety, the system comprising:

an aircraft parameter information subsystem (1) capable of receiving, storing and providing information to a user regarding aircraft configuration, position, airspeed, and attitude;

a vortex generator information subsystem (2) capable of receiving, storing and providing to a user information regarding vortex generator configuration, location, flight speed, and attitude of all vortex generators located adjacent to the aircraft;

an environmental parameter information subsystem (3) able to receive, store and provide to the user information about the environmental conditions in the vicinity of the aircraft at the forecasted time;

a warning subsystem (4) which warns the user of the risk of the aircraft encountering vortex generator wake vortices within the forecasted time;

a user subsystem (5) able to receive, store and provide to the user information about other subsystems and to form command signals for the aircraft evasion actions, so as to ensure that the aircraft evades the vortex generator danger zone within a delay time chosen by the user after the user receives a warning signal that the aircraft is at risk of encountering vortex generator wake vortices within the forecasted time;

a communication subsystem (6) for ensuring integration of these subsystems into a federated complex.

2. The system of claim 1, wherein:

the aircraft parameter information subsystem (1) ensures reception, processing, saving, and transmission of information at least about the aircraft configuration, coordinates and flight attitude in the inertial frame, aircraft velocity and angular velocity components in the aircraft frame to the warning subsystem;

said vortex generator information subsystem (2) ensures receiving, processing, storing, and transmitting to the user information regarding at least vortex generator type, coordinates and attitude in inertial frame, velocity and angular velocity components;

said ambient parameter information subsystem (3) ensures the reception, processing, storage, and transmission of information to the user regarding at least the components of the wind speed in the inertial frame at different heights in the region of the presence of the wake turbulence, and the ambient turbulence;

the warning subsystem (4) informs the user that the aircraft is likely to encounter the vortex generator danger zone, at least calculates the position and the intensity of the vortex generator wake vortex danger zone, forecasts the position zone of the aircraft within the forecasting time, and transmits the information that the aircraft is likely to encounter the vortex generator wake vortex danger zone within the forecasting time to the user subsystem;

the user subsystem (5) receives, processes, stores and indicates information from the warning subsystem at least as to the nulling of the distance from the area of the aircraft forecasted position to the vortex generator wake vortex hazard at the forecasted time, and forms a signal indicating the change in the aircraft position to increase said distance.

3. A system according to claim 1 or 2, wherein:

the aircraft information subsystem (1) is realized on the basis of standard aircraft-mounted equipment of an aircraft and/or ground, sea and/or aerospace navigation complex equipment;

the vortex generator information subsystem (2) is realized on the basis of standard aircraft-mounted equipment and/or standard vortex generator equipment and/or air traffic control equipment for ground, sea or aerospace complex;

the environmental information subsystem (3) is realized on the basis of standard onboard equipment of an aircraft and/or standard meteorological equipment for an air traffic control system or ground, sea and/or aerospace navigation complex equipment;

the warning subsystem (4) is implemented on the basis of user computer software and/or an onboard unified indicator system and/or an indicator system of air traffic control service or an aerospace navigation complex on the ground at sea and/or on the site of a flight controller, which informs the user that the aircraft may encounter vortex generator wake vortex danger zones;

the user subsystem (5) is realized on the basis of a user computer and a navigation system, and belongs to standard equipment on board an aircraft and/or a ground or sea navigation complex on the site of a flight controller;

the communication subsystem (6) is realized on the basis of an airborne multiplex of data transmission communication systems and/or information exchange.

4. A system according to any one of claims 1 to 3, wherein: the user is an aircraft and the command signals are implemented in an aircraft flight control system.

5. A system according to any one of claims 1 to 3, wherein: the user is an air traffic control service and the command signals are implemented in an aircraft flight control system.

6. The system according to any of the claims from 1 to 5, wherein said warning subsystem (4) informing the user that the aircraft may encounter the vortex generator wake vortex danger area at the forecasted time comprises a system comprising:

an aircraft tracker (7) capable of receiving information about the configuration, position, coordinates, and attitude of the aircraft in the inertial frame at the current time;

a vortex generator tracker (8) capable of receiving information about vortex generator position, geometric and weight characteristics, and motion parameters in the inertial frame at the current time;

a memory unit (9) capable of storing information about the vortex generator position and motion parameters in an inertial frame;

an environmental parameter detector (10) capable of receiving information about environmental parameters of the aircraft and the vortex generators in a current time-combined space;

a wake vortex tracker (11) capable of determining vortex generator wake vortices in the form of a set of vortex centre paths in an inertial frame;

a memory device (12) capable of storing information about vortex generator wake vortex path point coordinates in the form of a set of vortex region centers and wake vortex intensity in an inertial frame;

means (13) for selecting a delay time capable of calculating a time period during which the aircraft is at least likely to take flight evasive action, so that the aircraft avoids the vortex generator wake vortex danger zone after receiving a warning signal that it is likely to encounter wake vortices;

means (14) for simulating a control plane capable of calculating a delay distance equal to the distance covered by the aircraft during the delay time, modelling the control plane located in front of the aircraft, perpendicular to its flight direction over the delay distance, and determining the forecasted time required by the aircraft to acquire the control plane in an inertial frame;

means (15) for determining the parameters of the danger zone, able to determine the geometrical characteristics of the vortex generator wake vortex danger zone in the form of a set of danger zones in the vortex generator vortex zone at the forecasted time;

a predictor device (16) able to determine a vortex generator wake vortex path in the form of the centre of the generator vortex region in the inertial frame and the set of generator wake vortex intensities at the predicted time;

means (17) for calculating the points of intersection, able to determine the coordinates of the points of intersection of the generator wake vortex trajectory with the aircraft flying through the control plane at the forecasted time;

a zone forming device (18) capable of forming an intersection of a wake vortex path with a wake vortex hazard zone control plane in the form of a set of generator wake vortex hazards, wherein an incoming aircraft may have flight parameters exceeding allowable limits; forming an intersection point with a prescribed control plane relative to the flight in an aircraft forecasted position area control plane within an aircraft forecasted time; forming a warning area of the forecast position of the aircraft; providing information to a user regarding entry of the wake vortex danger zone into the warning zone;

a transformation unit (19) capable of calculating the coordinates of the aircraft forecasted position area, warning area and wake vortex danger area in the aircraft coordinate system;

a first intersection condition test unit (20) capable of calculating the distance from the warning zone to the wake vortex danger zone and marking the distance at which it becomes zero;

a second intersection condition test unit (21) capable of calculating the distance from the area of the aircraft forecasted positions to the wake vortex danger area and marking the distance at which it becomes zero;

a first indicator unit (22) capable of generating and transmitting a signal indicating the distance from the area of the aircraft forecasted positions to the vortex generator wake vortex danger area becoming zero;

a second indicating unit (23) capable of indicating the distance from the warning zone to the vortex generator wake vortex danger zone becoming zero.

7. The system of claim 6, wherein:

the aircraft parameter tracker (7) is at least capable of receiving information about aircraft configuration, coordinates, flight speed, pitch, yaw and roll angle;

said vortex generator tracker (8) being capable of receiving at least information on vortex generator type, flight speed, angular velocity and generator waypoint coordinates;

the environmental parameter detector (10) is at least capable of receiving information regarding local wind speed magnitude and direction, high altitude wind patterns, environmental turbulence intensity, and underlying terrain type;

said wake vortex tracker (11) being able to determine the wake vortex path of the vortex generator on the basis of the saved information in the form of the centre of the vortex area of the generator and the intensity of the wake vortex, which information is related to the type of vortex generator, the speed, the angular velocity, and the coordinates of the points on the generator path;

said means (14) for simulating a control plane are capable of modeling the control plane on the basis of information relating to aircraft position, attitude, speed, and delay time;

the device (15) for determining the danger zone parameters can determine the geometrical characteristics of the generator wake vortex danger zone on the basis of the stored track point coordinates and generator wake vortex intensity information and the information of configuration, position, speed and angular speed of the aircraft in the inertial coordinate system;

the forecasting device (16) is able to determine, on the basis of the information about the wake vortex path, the wake vortex path and the intensity of the vortex generator in the form of a set of trajectories of the generator vortex region center and wake vortex intensity in an inertial coordinate system;

said means (17) for calculating the intersection points are able to determine the coordinates of the intersection points of the generator wake vortex trajectory with the control plane on the basis of the information about the coordinates of the control plane and the wake vortex trajectory in the inertial frame at the forecasted time;

the area forming device (18) is capable of forming a wake vortex danger area, an aircraft forecasted position area and a warning area on the basis of coordinate information about the intersection of the generator wake vortex path with the control plane at the forecasted time, information on the geometrical characteristics of the danger area in the form of a set of generator vortex danger areas, and aircraft position, flight attitude, velocity and angular velocity information relative to the flight rules in an inertial frame;

the transformation unit (19) is capable of calculating the coordinates of the aircraft forecasted position area, the warning area and the wake vortex danger area in the aircraft coordinate system on the basis of information about the aircraft forecasted position area coordinates, the warning area coordinates and the wake vortex danger area coordinates and information about the aircraft coordinates and the flight attitude, preferably the pitch, yaw and roll angles in the current time inertial coordinate system.

8. System according to claim 6 or 7, wherein said warning subsystem (4) comprises: vortex generator tracker (8), memory units (9 and 12), wake vortex tracker (11), means (15) for determining parameters of the hazard zone, forecasting means (16), means (17) for calculating the intersection point, area forming means (18), a first unit (19) and a second unit (20) for testing the intersection conditions, signalling means capable of simultaneously signalling each vortex generator in the vicinity of the aircraft.

9. A system according to any of claims 6-8, wherein said means (14) for selecting the delay time in the warning subsystem (4) is implemented using the current corrected delay time.

10. A system according to any one of claims 6 to 9, wherein the area forming means (18) in said warning subsystem (4) is implemented using current corrective aircraft forecasted position area coordinates.

11. System according to any of claims 6-10, wherein the area forming means (18) in said warning subsystem (4) can be implemented using current corrected warning area coordinates.

12. A system according to any of claims 9-11, wherein the correction is effected manually.

13. A system according to any of claims 9-11, wherein the correction is effected in a semi-automatic or fully automatic manner.

14. The system according to any one of claims 6-13, wherein said user system (5) comprises: means (24) for the user to observe information concerning the location of the aircraft forecasted location areas and vortex generator wake vortex danger areas on the control plane.

15. A system according to any one of claims 6 to 14, wherein said user system (5) comprises: an indicating means (22) and an alarm indicating means (23) selected from the group comprising visual, audible and tactile means.

16. System according to any of claims 6 to 15, wherein said means (15) for determining vortex generator danger zone parameters in said warning subsystem (4) comprises:

a unit (25) for aircraft planning capable of calculating a set of aircraft geometric features on the basis of aircraft configuration, coordinates, flight speed, pitch angle, yaw and roll, which are necessary for evaluating the generator wake vortex inducements and the additional aerodynamic forces and moments acting on the aircraft;

a unit (26) for evaluating the additional aerodynamic forces and moments acting on the aircraft at a given point and induced by the generator wake vortices, in the form of a set of the vortex centre trajectory and the generator wake vortex intensity in an inertial frame, on the basis of stored information about the path of the wake vortex point, and capable of calculating these aerodynamic forces and moments on the basis of the position, flight speed, angular velocity, and aircraft geometry in relation to the aircraft configuration, inertial frame;

a unit (27) for estimating the risk level of the aerodynamic disturbance at a given point, capable of estimating the risk level on the basis of a user-selected criterion;

a unit (28) for determining that the aerodynamic forces and moments of the aircraft induced by the generator wake vortices are points of danger, capable of determining the coordinates of points on the danger area on the basis of a user-selected danger criterion;

a unit (29) for evaluating the geometrical characteristics of the wake vortex danger zone, which is able to calculate these geometrical characteristics on the basis of the coordinate information of the points of the danger zone.

17. The system according to claim 16, wherein said unit (29) for determining wake vortex hazard geometry and said unit (15) for determining hazard parameters in said warning subsystem (4) are capable of approximately determining hazard boundaries.

18. The system according to any of claims 1-17, wherein the roll allowed by the aircraft is selected as a risk criterion for wake vortices of the vortex generator.

19. The system according to any of claims 1-17, wherein the aircraft roll torque induced by the vortex generator wake vortices is selected as a risk criterion for the vortex generator wake vortices.

20. The system according to any one of claims 6-19, wherein said wake vortex tracker (11) and said predictor device (16) in said warning subsystem (4) comprise: the programmable element, and said means (15) for determining the parameters of the hazard zone are implemented in software of the programmable element.

21. The system according to any of claims 6-20, wherein the devices and units of said warning subsystem (4) and said user subsystem (5) are positioned differently.

22. The system according to any of the claims 1 to 21, wherein said user subsystem (5) comprises: a system for storing information relating to the delay time, the coordinates of the control plane, the area of the aircraft forecasted position, and the vortex generator danger zone at least during an alarm indication time when the distance from the area of the aircraft forecasted position to the vortex generator wake vortex danger zone becomes zero.