WO2009029005A2 - Procédé et système pour assurer la sécurité d'un aéronef - Google Patents

Procédé et système pour assurer la sécurité d'un aéronef Download PDF

Info

Publication number
WO2009029005A2
WO2009029005A2 PCT/RU2008/000567 RU2008000567W WO2009029005A2 WO 2009029005 A2 WO2009029005 A2 WO 2009029005A2 RU 2008000567 W RU2008000567 W RU 2008000567W WO 2009029005 A2 WO2009029005 A2 WO 2009029005A2
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
vortex
protected
information
wake
Prior art date
Application number
PCT/RU2008/000567
Other languages
English (en)
Russian (ru)
Inventor
Nikolai Alekseevich Baranov
Andrei Sergeevich Belotserkovsky
Mikhail Igorevich Kanevsky
Igor Vladimirovich Pasekunov
Original Assignee
Gosudarstvennoie Uchrezhdenie 'federalnoe Agentstvo Po Pravovoi Zaschite Rezultatov Intellektualnoi Deyatelnosti Voennogo, Spetsialnog I Dvoinogo Naznachenia 'pri Ministerstve Yustitsii Rf'
Zakritoe Aktsionernoe Obschestvo 'rossiyskaya Aktsionernaya Assotsiatsiya 'spetstekhnika'
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Gosudarstvennoie Uchrezhdenie 'federalnoe Agentstvo Po Pravovoi Zaschite Rezultatov Intellektualnoi Deyatelnosti Voennogo, Spetsialnog I Dvoinogo Naznachenia 'pri Ministerstve Yustitsii Rf', Zakritoe Aktsionernoe Obschestvo 'rossiyskaya Aktsionernaya Assotsiatsiya 'spetstekhnika' filed Critical Gosudarstvennoie Uchrezhdenie 'federalnoe Agentstvo Po Pravovoi Zaschite Rezultatov Intellektualnoi Deyatelnosti Voennogo, Spetsialnog I Dvoinogo Naznachenia 'pri Ministerstve Yustitsii Rf'
Publication of WO2009029005A2 publication Critical patent/WO2009029005A2/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D25/00—Emergency apparatus or devices, not otherwise provided for

Definitions

  • 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, in including when the object flows around the air stream.
  • 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.
  • 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.
  • 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.
  • the device uses a quick-response display, on which the simulated vortex traces from each aircraft located near the specified aircraft are visualized (US, 5,845,874, A).
  • US, 5,845,874, A the quick-response display
  • 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, 6,177,888, 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, the volume of the vortex wake taking into account the local wind speed, and has the ability to determine the distance or time before the aircraft enters the volume swirl track of 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.
  • 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.
  • 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, Bl), which is a spherical antenna made of dielectric material having eight sectors with receivers installed in them for receiving microwave signals reflected from other aircraft that find I was in his neighborhood.
  • US, 6211808, Bl is a spherical antenna made of dielectric material having eight sectors with receivers installed in them for receiving microwave signals reflected from other aircraft that find I was in his neighborhood.
  • a technical solution is known regarding the scheme and method for preventing the intersection of the path of the first aircraft with the vortex wake of the second aircraft (WO 00/71985, Al), which consists in determining the position, configuration and type of vortex disturbances caused by the second aircraft, the presence of which is detected using information from the airborne system of the first aircraft, information from the second aircraft or information from the airfield, determination of the height of the second aircraft, the predicted position of the vortex wake generated by it, taking into account atmospheric conditions in particular, wind speed and direction, air temperature, reconciliation of the obtained data with a look-up table or simulation of a vortex wake with visualization of the position and its trajectory relative to the first aircraft, prediction of 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.
  • 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.
  • the systems Traffiered Alert and ⁇ llisiop Avoidaps are used.
  • the pilot of the first aircraft is visualized with information about all areas of vorticity assumed in the area 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.
  • a known system for measuring zones of turbulence in the direction of the tail wind of an airplane (WO 2006/016075, Al), installed on board, containing lidar, emitting an optical beam in the direction in front of the aircraft and receiving a reflected optical beam, directional detectors connected to the control means, a first operating device using an internal correction algorithm and a second operating device using an external correction algorithm that provides potential control signals to activate at least , one control surface of the aircraft.
  • this system provides only a change in the position of the aircraft to reduce the impact on it of turbulence zones that are ahead in the course.
  • AVOSS Vortex Interval Detection System
  • 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 vortex traces 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 “windows” of approach from the height of the glide path to the end of the runway.
  • 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;
  • 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;
  • the position, geometric and mass characteristics and motion parameters of the vortex generator it is preferable to use information about the type of vortex generator, its speed, angular velocity and the coordinates of its path points, and information from the user’s databases geometric and mass characteristics of the aircraft.
  • the intensity and trajectory of the vortex wake in space and the determination of its hazardous zones are determined on the basis of these data, by mathematical modeling of the vortex wake of the vortex generator taking into account the influence of environmental conditions.
  • the simulation is based on the representation of the initially ideally symmetric formation of the vortex bundles of the vortex wake of the aircraft, followed by the imposition of environmental parameters on the model, for example, wind shear, wind speed and other parameters.
  • environmental parameters for example, wind shear, wind speed and other parameters.
  • the aim of the present invention is to provide a method for ensuring the vortex safety of an aircraft in flight, take-off and landing, providing the pilot with information about the predicted flight a situation modeled on the basis of actual measurements, and an analytical assessment of the situation in terms of the possibility of a flight accident, and an indication of the way out of it.
  • the task was to develop a method for ensuring the vortex safety of an aircraft, in which, under the conditions of providing the pilot with a protected aircraft or the traffic control service, information about the presence of vortex traces in the field of flight, take-off and landing of the aircraft, predicted based on actual measurements of their parameters, posing a danger to the protected aircraft, tracking their movement in airspace, as well as the formation of control signals to prevent the protected aircraft from entering the hazardous vortex wake zones based on the determination of the predicted relative position of the protected aircraft and the dangerous vortex wake vortex wake zone for it in a certain control section ahead of the aircraft, at a distance over which in case of danger, the aircraft can maneuver the evasion of the danger zone of the vortex wake, also to the pilot or flight control service dispatcher m to develop a decision on the choice of evasive maneuver, they provide current information on the time remaining until the entrance of the aircraft controlled by him into the danger zone.
  • the task was to determine in the current mode the time of the initial circulation of vortex towers of vortex wakes vortex generators for the most reliable prediction of the formation and behavior of the vortex wake of each aircraft.
  • Changing the configuration of an aircraft means, for example, changing the operating mode of engines, including the failure of one or several 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 air flow and, consequently, to a change in aerodynamic forces and moments due to the influence of aerodynamic disturbances, including the vortex wake, as well as to a change in the aircraft’s ability to compensate for such effects.
  • the task was also to inform the pilot of the protected aircraft and / or air traffic control service about the flight situation, which may develop after some predicted time if there are various vortex generators in the flight, take-off or landing area, with an indication of the time remaining before a possible entrance the aircraft into the danger zone for it of the vortex traces of these generators.
  • each protected aircraft in the field of its flight or take-off or landing, including data on the type of aircraft, its configuration, its mass, its linear and angular speeds, its location, its trajectory and its orientation, including, preferably, the angles of pitch, yaw and roll of the aircraft, relative to the inertial coordinate system at the current time;
  • each aircraft from the group of aircraft that are vortex generators in the field of flight or take-off or landing of the indicated protected aircraft, including data on the type of each vortex generator, its configuration, its mass, its linear and angular speeds , its location, its trajectory, its orientation, preferably the pitch, yaw and roll angles, relative to the inertial coordinate system at the current time;
  • - users receive information on environmental parameters in the field of flight, take-off or landing of the protected aircraft at the current time, including information on the magnitude and direction of the local speed wind, wind profile in height, degree of turbulence, type of underlying surface;
  • the flight situation is visualized at the predicted point in time with the relative position of the specified dangerous zone and the area of the predicted positions of the protected aircraft in the control plane displayed;
  • the relative position of the predicted position area of the protected aircraft and the hazard zones of the vortex generators determines the smallest value of the lead-time control time, which corresponds to the zero distance between the danger zone of the vortex wake vortex trace and the region of the predicted positions of the protected aircraft apparatus, and displays it for the user at the current time;
  • - generates a prescriptive signal for a protected aircraft and / or aircraft from a group of vortex generators to maneuver to ensure that the protected aircraft evades the danger zone of the vortex traces of the vortex generator for a user-selected lead time after receiving a warning about the possibility of the aircraft entering the danger zone vortex trace of a vortex generator at a predicted point in time; and the users are protected aircraft and / or air traffic control service.
  • the initial circulation of the vortex trails of the vortex wake of aircraft from the group of protected aircraft and from the group of vortex generators was determined using mathematical modeling.
  • the initial circulation of the vortex vortex bundles of the aircraft from the group of protected aircraft and from the group of these vortex generators is determined by measuring it.
  • the initial circulation of the vortex vortex bundles of the aircraft is measured by determining the frequency difference of the probe beam supplied at the selected frequency to the space behind the aircraft in the region of origin of the vortex vortex bundles and the reflected signal.
  • the initial circulation of the vortex wake vortex bundles be determined using a lidar mounted on the protected aircraft and on each of the vortex generators, with the probe beam directed into the space behind the aircraft into the region of the generation of the vortex wake vortex bundles .
  • each aircraft which is the generator of vortices in the field of flight, take-off or landing of the protected aircraft, and visualization of the flight situation, showing the relative position of the danger zone and the area of the predicted positions the aircraft and the indication of the smallest control lead-time was carried out in relation to the danger zones of the vortex tracks located in the control olny plane in the field of increased attention.
  • the user can carry out the current correction of the coordinates of the area of the predicted positions of the protected aircraft.
  • the user can perform the specified current correction in the manual control mode or in the semi-automatic or automatic mode ..
  • the protected aircraft it is desirable for the protected aircraft to indicate zero distance from the area of special attention to the danger zone of the vortex wake of the vortex generator in the control plane and / or emergency indication of zero distance from the region of the predicted positions of the protected aircraft to dangerous the vortex trace zones of the vortex generator should be carried out using an indication selected from the group including visual, audio, and tactile indication.
  • the apparatus it is advisable to automatically record in a protected on-board drive of a protected aircraft the apparatus, at least during the emergency indication of the event that the distance from the region of the predicted positions of the protected aircraft to the vortex trace zone of the vortex generator dangerous to it, the current information about the value of the selected lead time, the coordinates of the control plane, the region of the predicted positions of the protected aircraft and zones of vortex traces of other aircraft that are dangerous for it from the group of vortex generators at the predicted time and of the pilot of the smallest in size of control time value of pre-emption.
  • the task was also solved by creating a system for ensuring the vortex safety of an aircraft in the field of its flight, takeoff and landing, including:
  • subsystem (1) of information about the protected aircraft capable of at least receiving, processing, generating, storing and providing users with information about the type of each of these protected aircraft, its configuration, mass, speed, location, its trajectory and position in space relative to the inertial coordinate system at the current time, including pitch, yaw and roll angles, and about the initial circulation of the vortex bundles of its vortex wake relative to the inertial nnaya coordinate system at the current time;
  • a subsystem (2) of information about vortex generators which are aircraft from the group of vortex generators in the field of finding a protected aircraft, capable of at least receiving, processing, generating, storing and providing users with information about the type of aircraft, its configuration, mass , its linear and angular velocities, its location, trajectory and orientation, including pitch, yaw and roll angles, and about the initial circulation of the vortex bundles of the vortex wake of the vortex generator finally inertial coordinate system at the current time;
  • - subsystem (3) of environmental information that is capable of capturing, saving and providing users with information on the state of the environment in the field of joint location of the protected aircraft and the vortex generator at the current time and at a predicted time
  • subsystem (5) of the user capable of receiving, processing, storing and displaying information for the user from other subsystems and generating a prescriptive signal for the maneuvers to protect the aircraft from the danger zone of the vortex traces of the generators by the protected aircraft and / or generator vortices during the user pre-emptive time after the user receives a warning about the possibility of the aircraft entering the danger zone of the vortices o trace vortex generator at the predicted point in time;
  • control subsystem (6) capable of receiving, processing, storing and displaying information, including at least information from the user warning subsystem (4) about the predicted situation of the protected aircraft entering the vortex wake generator’s vortex wake zone, which may cause a flight accident, and information from the subsystem (5) of the user about the prescriptive signal transmitted to the user to perform maneuvers of the vortices by the protected aircraft and / or generator ayuschego evading aircraft from the danger zone of wake vortices vortex generators;
  • vortex wake generators information subsystem (2) was implemented on the basis of standard onboard equipment of the aircraft and / or equipment of the air traffic control system and / or equipment of ground, sea and / or aerospace navigation systems;
  • subsystem (3) of environmental information was implemented on the basis of the standard on-board equipment of the aircraft and / or on the basis of the standard equipment of the meteorological support of the air traffic control system or as part of ground, sea and / or aerospace navigation systems; subsystem (4) of warning the user about the possibility of the aircraft entering the danger zones of the vortex traces of the vortex generators was implemented on the basis of the software of the user's computer systems and / or on-board unified indication systems and / or indication systems of air traffic control dispatch services or is part of the ground, marine and / or aerospace navigation systems at the location of the flight dispatcher;
  • the communication subsystem (7) was implemented on the basis of telecode communication systems and / or airborne multiplex communication channels.
  • the subsystem (1) of information about the protected aircraft and the subsystem (2) of information about the vortex generators contain devices that determine the initial circulation of vortex bundles of vortex traces generated by aircraft, relative to the inertial coordinate system using mathematical modeling.
  • the subsystem (1) of information about the protected aircraft and the subsystem (2) of information about the vortex generators contain devices that determine the initial circulation of vortex bundles of vortex traces generated by aircraft, relative to the inertial coordinate system by measuring it .
  • the subsystem (1) of information about the protected aircraft and the subsystem (2) of information about the vortex generators contain devices that determine the initial circulation of vortex bundles of vortex traces generated by aircraft devices by determining the frequency difference of the probe signal supplied at a selected frequency to the space behind the aircraft in the region of origin of the vortex wiring harnesses of the specified aircraft, and the reflected signal.
  • the subsystem (1) of information about the protected aircraft and the subsystem (2) of information about the vortex generators contain devices that determine the initial circulation of the vortex bundles of the vortex wake using lidars mounted on the aircraft, in the direction of the probing beam into the space behind this aircraft to the region of origin of the vortex bundles of its vortex wake.
  • the subsystems (1,2,3,4,5,6,7) work simultaneously with respect to each aircraft, which is a protected aircraft or a vortex generator in the field of flight, take-off or landing of a protected aircraft apparatus.
  • the subsystems (1,2,3,4,5,6) are made with the possibility of current correction of the calculated parameters in manual control mode or in semi-automatic or automatic mode ..
  • control subsystem (6) contain a device that provides information provided to the protected aircraft about the predicted situation of the protected aircraft entering the vortex wake of the vortex generator, which could lead to a flight accident, information about induced by the user the smallest value of the control lead time remaining before the aircraft enters the specified danger zone and information about the prescriptive signal transmitted to the user to perform a vortex of a vortex maneuver by the protected aircraft and / or generator, providing the aircraft to evade the danger zone of the vortex traces of the vortex generators.
  • the monitoring subsystem (6) comprises a device that automatically records in a protected on-board drive of a protected aircraft for at least the time of emergency indication of the event that the distance from the region of the predicted positions of the protected aircraft is zero the apparatus to the zone of the vortex wake of the vortex generator, which is dangerous for it, at least the current information about the value of the selected lead-in time and the smallest control lead-time value induced for the pilot.
  • Fig.l is a diagram of the operational interaction of aircraft and services that are users in a method for ensuring the vortex safety of an aircraft, according to the invention, an embodiment
  • Figure 2 is a diagram of the information flows of the vortex safety system of an aircraft, according to the invention, an option.
  • the invention can be illustrated by a non-limiting embodiment of the method for ensuring the vortex safety of an aircraft (hereinafter JTA), the scheme of which is presented in FIG. 1 for the case when the user is the protected aircraft 1 (hereinafter - JlA I) in flight mode along the route in the vicinity of the aerodrome, and in its vicinity in flight are two other aircraft 2 and 3, which are vortex generators (hereinafter - GW 2 and HS 3).
  • JTA non-limiting embodiment of the method for ensuring the vortex safety of an aircraft
  • JTA the scheme of which is presented in FIG. 1 for the case when the user is the protected aircraft 1 (hereinafter - JlA I) in flight mode along the route in the vicinity of the aerodrome, and in its vicinity in flight are two other aircraft 2 and 3, which are vortex generators (hereinafter - GW 2 and HS 3).
  • aircraft 1, aircraft 2 and aircraft 3 are equipped with on-board flight and navigation systems that provide measurement of the navigation and flight parameters of their own aircraft and combine subsystems that complement and correct each other: short-range and long-range navigation systems, a beacon system, a satellite navigation system, Doppler system for measuring ground speed and drift angle, inertial system, radar system, optoelectronic system and laser range finder, radio altimeter, air signal system, sensors angles of attack and slip, overloads, angular velocities, gyro vertical, inter-aircraft navigation system, airborne integrated display system for aircraft and contains a computer complex, devices for indicating, signaling and visualizing information, for example, an indicator on the windshield and / or display.
  • each of these complexes contains devices for determining the initial circulation of vortex bundles of its own trace protected by JlA 1 and JIA 2, including at least one lidar, providing a probe beam into the space behind the JIA in the region of origin of the vortex bundles of its vortex wake , and receiving a reflected signal with a measurement of the difference in their frequencies.
  • the complex for example, in JIA 1 determines the initial circulation of the vortex bundles of this JIA 1 and transfers it in the current mode to other users, for example, other aircraft and / or the aerodrome complex
  • Aerodrome navigation equipment can be, for example, a complex containing an international radio navigation system such as VOR / DME (VOR is a radio beacon for measuring azimuth, DME is a beacon for measuring range), which is standard for ensuring flights on international international routes and is designed for continuous automatic detection JIA locations (established system standards: range of the system up to 370 km, range 0-40 °), automatic direction finder for azimuth indication JIA, e.g., type ARP- 7C, and the drive station, for example, APP-8 type intended for flight JIA, equipped with automatic radio.
  • VOR is a radio beacon for measuring azimuth
  • DME is a beacon for measuring range
  • JIA locations established system standards: range of the system up to 370 km, range 0-40 °
  • automatic direction finder for azimuth indication JIA e.g., type ARP- 7C
  • the drive station for example, APP-8 type intended for flight JIA, equipped with automatic radio.
  • FIG. 2 shows a diagram of the information flows of the vortex safety system of an aircraft according to the invention, an option when the JIA information subsystem 1, the HS information subsystem 2 and the environmental information subsystem 3 are implemented in the indicated navigation and navigation system and, partially, based on aerodrome equipment, and record, store and provide other subsystems of the vortex safety system according to the invention with information on angles of attack and slip, angular rotational speeds JIAl and B2, GVZ around the connected coordinate axes, deviations of the governing bodies, engine operating mode, overloads along the connected coordinate axes, orientation angles JIAl and GB2, GVZ in the associated coordinate system, configuration information JIAl and GB2, GVZ, instrument speed, acceleration, orientation angles the velocity vector in the inertial coordinate system at the current moment of time, about the initial circulation of the vortex bundles of the vortex tracks JIA 1, GV 2, GV 3, the position coordinates of JIAl and GB2, GVZ in space, radar information about the meteorological situation
  • Subsystem 4 for warning the user about the possibility of an aircraft entering the danger zone of the GW vortex wake can be implemented on the basis of the flight-navigation complex and the aircraft computing system
  • user subsystem 5 can be implemented on the basis of the JlAl computer system
  • information display and visualization devices for example, an indicator on the windshield and / or display
  • the switching subsystem 6 is implemented on the basis of airborne multiplexed information exchange channels.
  • subsystem 4 can also be located at the location of the flight dispatcher, for example, at an aerodrome or ship, and the pilot can only be provided with information visualized on-board visualization devices.
  • the user warning subsystem 4 and a part of the user subsystem 5, including the visualization system can be implemented in a known manner (WO 2005/010554, Al).
  • the warning subsystem 4 calculates the trajectories of the vortex tracks GB2 and the GVZ located in the vicinity of JlAl, for example, in a known manner (WO 2005/010554, Al), determines the geometric characteristics of the vortex zones trace of hot water satisfying a hazard criterion set by the user, for example, the angle of heel JlA under the predicted impact of the vortex wake on JlA at the predicted time of crossing JlA of some simulated control -plane, in the space situated ahead JlA perpendicular to its direction of movement at a distance from the proactive JlA, generates in the control plane information on the mutual arrangement of the projected JlA and wake vortex danger areas, determines the degree of their danger to the JIA and, in the current mode, monitors the distance between the danger zone and the area of the predicted positions of the JIA.
  • mathematical modeling of the vortex traces JIAl, GB2, GBZ can be carried out, for example, using well-known algorithms, such as the algorithm that is the object of the “know-how” of the inventors (WO 2005/010554, Al), or, for example, using the well-known algorithm for calculating the trajectory and intensity of the vortex wake (Northwest Resecss Associats, Ips, Airfax Vortex Spacing System (AVOSS), Algorithm Versiop 3.1.1), which provides the calculation of the coordinates of the centers of the vorticity regions based on the integration of the differential equation Tei vorticity in space and time, or other algorithms that provide said calculation.
  • well-known algorithms such as the algorithm that is the object of the “know-how” of the inventors (WO 2005/010554, Al)
  • the well-known algorithm for calculating the trajectory and intensity of the vortex wake Northwest Resecss Associats, Ips, Airfax Vortex Spacing System (AVOSS), Algorithm Vers
  • Subsystem 4 warning stores this data.
  • the parameters of the initial coordinates of the vorticity regions are determined using instrumental measurements, according to the invention, using laser radar devices of the lidar type with measuring and estimating the magnitude of the initial circulation of the vortex bundles or using mathematical modeling of the tangential velocities of the vortex wake air flow followed by calculation of the trajectory and intensity of the vortex wake .
  • the warning subsystem 4 determines the relative position of the area of the predicted positions of the protected JlAl and hazardous zones GB2 and GVZ, determines the smallest value of the lead-forward control time, which corresponds to the equal to zero distance between the danger zone of the vortex trace GB2 and GVZ and the area of the predicted positions of the protected JlAl, and displays it for the user at the current time.
  • information for the JIAl pilot visualized on the display of the navigation chart, which is usually used in the JIA to indicate the JIA course and to display symbols generated by the inertial navigation system, for example, the Airborne Navigation System (AINS)
  • the airborne Navigation System can be presented, for example, in the area of increased attention shown on the map and the image in it of the area of the predicted JIAl positions and dangerous' zones vortex traces of GV 2 and GVZ in space at a predicted point in time, as previously described by the authors of the present invention (WO 2005/010554, Al).
  • the region of the predicted positions JlAl may have the form, for example, of a rectangle whose dimensions are proportional to the dimensions of the region of the possible position of the JIAl case in space.
  • 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, sound, this event.
  • Danger zones of vortex traces can take the form, for example, of a circle or other geometrical figure convenient for visual perception.
  • the image may be accompanied by a visual indication, for example, light or color, of the areas of the predicted JlA positions themselves! and danger zones of vortex traces or their boundaries.
  • Subsystem 4 warnings selects the lead time required to perform a maneuver to change the trajectory of JlA.
  • This lead time 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 user subsystem 5 through the communication subsystem 7, informs the JIAl pilot about the predicted event of entry into the danger zone using sound, tactile or visual indications and provides visualization of this information for him and the flight dispatcher, as well as generates a prescriptive signal, for example, sound, about the need to execute recommended maneuver. Based on the presented indication of the smallest value of the control lead time, the pilot evaluates the possibility of performing the recommended maneuver and makes a decision on its implementation.
  • the monitoring subsystem 6 stores current information about the value of the selected lead time, the coordinates of the control plane, the area of the predicted positions JlA! and the danger zones of the vortex traces of GB2 and GVZ, as well as the corresponding minimum control lead time induced for the pilot during the emergency indication of the event that the distance from the area of the predicted positions JIAl to the danger zones of the vortex trace GB2 and GVZ is zero, as well as information about the prescribed JlA! A maneuver to evade JIAl from entering the danger zone.
  • This storage can be achieved using, for example, a separate information storage device located both on board, for example, in the so-called “black box” information recording system, and as part of ground, surface, and space air traffic control devices.
  • a separate information storage device located both on board, for example, in the so-called “black box” information recording system, and as part of ground, surface, and space air traffic control devices.
  • the availability of such information will allow for the implementation of measures to determine the causes of air crashes in order to assess the actions of the JIA pilot in the situation of the presence of vortex traces in the space surrounding it, falling into the danger zones of which could lead, for example, to a change in the JlA configuration or to change its trajectory.
  • the warning subsystem 4 for the possibility of JlA getting into the danger zone of the GW vortex wake can be implemented using standard on-board and ground-based equipment, for example, the JlA airborne inertial navigation system ( ⁇ irb Replacerpe ⁇ adjust ⁇ attribute ⁇ l Navi-ani Introduceti Introducet Sust Canalm (AINS), the airborne signal system ( ⁇ ir D Canalm Stamming speed meter (Dorler System (DS), the front-view radar JIA (Fogward Wi-Radag (FVR) and the use of information from air traffic control (Air Traffic Control (AT) ), unified display systems (IPadisystem Sustem (UIS), multiplexed information exchange channel (Ipormatiop Exhapl Multilex Channel (IEMC), as well as information systems compatible with the indicated systems used on the JIA of other countries, for example, collision
  • the subsystems of the vortex safety system of an aircraft according to the invention can be localized separately at various objects of the motion control system or various JlA and GV, providing the user with information about the results of operational calculations by indicating and visualizing them.
  • users of such information can be both JlA crews and dispatch services of aerodromes, ships advising JIA crews on flights on the recommended flight path or on the need for JlA maneuvers to eliminate a dangerous flight situation, which is especially important in conditions of poor visibility and difficult weather conditions .
  • the vortex safety system is the embodiment of an integrated approach to the problem of ensuring the safety of aircraft, and is applicable both in flight conditions along the route and in conditions of landing or take-off of aircraft.
  • subsystem 5 of the user located both on board the JlA and in the location of the flight dispatcher, can provide current correction of the information available to the dispatcher on the vortex situation in the area of landing or landing, which will not only increase the safety of takeoff and landing, but also reduce the time interval between the JIA during take-off or landing.
  • the application of the vortex safety method according to the invention will reduce the load of the flight dispatcher to generate prescriptive instructions to the pilot, since the responsibility of deciding on the maneuver to evade the danger zone of the vortex wake lies with the pilot, and he is provided with additional information to facilitate decision making. It should be borne in mind that, one way or another, the pilot makes a decision now, without using this method of ensuring vortex safety according to the invention, but in the absence of information about the location of the dangerous zones of the vortex traces.
  • the integrated vortex safety system according to the invention can also be implemented to perform flight control functions, since the vortex situation can be monitored in the vicinity of ground HVs and flying HVs using warning systems installed autonomously on the JIA, on ships, at aerodromes, combined into a single information system, which helps to prevent the creation of contingencies related to JIA getting into dangerous situations Ones of vortex traces of various HS.
  • JV can be JIA various types, for example, airplanes, helicopters, unmanned aerial vehicles, as well as sea vessels, including aircraft carriers.
  • the method and system for ensuring the vortex safety of an aircraft according to the invention can be implemented based on the use of equipment available on the JIA and in air traffic control complexes, with additional installation of devices that ensure the performance of the method operations described above.
  • the operating conditions of the JlA in the form of programs adapted to the JlA type, the operating conditions of the JlA, the type of equipment used on it, and compatible with air traffic control information systems.
  • the simulators for training pilots and controllers in vortex hazard conditions can also be used for installation on various aircraft, as well as in various simulators for training pilots and controllers in vortex hazard conditions

Landscapes

  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Traffic Control Systems (AREA)
  • Navigation (AREA)

Abstract

La présente invention concerne des procédés et systèmes pour assurer la sécurité des aéronefs et comprend un procédé et un système d'avertissement de l'utilisateur, notamment de l'équipage d'un aéronef ou du dispatcher des vols, sur la probabilité de se retrouver dans des zones dangereuses des turbulences générées par des générateurs de tourbillons se trouvant à proximité de l'aéronef, qui est modélisée sur la base des données obtenues en temps réel sur les paramètres géométriques et massiques de l'aéronef et des générateurs de tourbillons, et sur la circulation initiale de flux tourbillonnaires et de leurs traces, à un moment prévisible de l'intersection de l'appareil avec un plan de référence modélisé, situé à une distance d'anticipation dans le sens du mouvement de l'aéronef, le calcul s'effectuant sur le temps d'anticipation suffisant pour réaliser une manoeuvre d'évitement. Le système d'avertissement de l'utilisateur détermine les trajectoires et l'intensité des traces des générateurs de tourbillons, les coordonnées d'intersection des traces de tourbillons avec un plan de référence, les paramètres géométriques des zones dangereuses sur la base du critère de danger introduit par l'utilisateur, et forme dans le plan de référence une zone d'attention particulière, une zone de positions prévisibles de l'aéronef et des traces dangereuses de tourbillons à un moment prévu; il effectue le suivi des événements de traversée de la zone d'attention particulière et/ou du de la zone des positions prévisibles de l'aéronef avec les zones dangereuses de traces de tourbillon, assure la mobilisation de l'attention de l'utilisateur par rapport à cet événement et informe l'utilisateur sur la durée de temps d'anticipation minimal avant l'entrée de l'appareil dans la zone dangereuse correspondante.
PCT/RU2008/000567 2007-08-23 2008-08-21 Procédé et système pour assurer la sécurité d'un aéronef WO2009029005A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU2007131794/11A RU2007131794A (ru) 2007-08-23 2007-08-23 Способ и система обеспечения вихревой безопасности летательного аппарата
RU2007131794 2007-08-23

Publications (1)

Publication Number Publication Date
WO2009029005A2 true WO2009029005A2 (fr) 2009-03-05

Family

ID=40388067

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU2008/000567 WO2009029005A2 (fr) 2007-08-23 2008-08-21 Procédé et système pour assurer la sécurité d'un aéronef

Country Status (2)

Country Link
RU (1) RU2007131794A (fr)
WO (1) WO2009029005A2 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10055998B1 (en) 2017-08-25 2018-08-21 Airbus Operations (S.A.S.) Ground-based identification of wake turbulence encounters
US10276050B2 (en) 2016-05-19 2019-04-30 Airbus Operations (S.A.S.) Method making it possible to identify the proximity of a wake turbulence and to generate a report relative to that proximity
US11030907B1 (en) 2020-06-19 2021-06-08 Honeywell International Inc. Methods, systems, and apparatuses for identifying and indicating the secondary runway aiming point (SRAP) approach procedures

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2469411C1 (ru) * 2011-06-02 2012-12-10 Федеральное государственное унитарное предприятие "Государственный научно-исследовательский институт авиационных систем" Способ информационного обеспечения вихревой безопасности полета летательных аппаратов
RU2477893C1 (ru) * 2011-09-30 2013-03-20 Федеральное государственное унитарное предприятие "Государственный научно-исследовательский институт авиационных систем" Способ обеспечения вихревой безопасности полета летательного аппарата
RU2496121C1 (ru) * 2012-03-11 2013-10-20 Федеральное государственное унитарное предприятие "Государственный научно-исследовательский институт авиационных систем" Способ информационного обеспечения вихревой безопасности полета летательных аппаратов

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10276050B2 (en) 2016-05-19 2019-04-30 Airbus Operations (S.A.S.) Method making it possible to identify the proximity of a wake turbulence and to generate a report relative to that proximity
US10055998B1 (en) 2017-08-25 2018-08-21 Airbus Operations (S.A.S.) Ground-based identification of wake turbulence encounters
US11030907B1 (en) 2020-06-19 2021-06-08 Honeywell International Inc. Methods, systems, and apparatuses for identifying and indicating the secondary runway aiming point (SRAP) approach procedures

Also Published As

Publication number Publication date
RU2007131794A (ru) 2009-02-27

Similar Documents

Publication Publication Date Title
US7333030B2 (en) Method and system for preventing an aircraft from penetrating into a dangerous trailing vortex area of a vortex generator
CA2536671C (fr) Systeme integre de securite en matiere de tourbillons pour aeronef
RU2550887C2 (ru) Бортовая интегрированная система информационной поддержки экипажа и когнитивный формат представления полетной информации на этапе "взлет" многодвигательного воздушного судна
RU2634502C2 (ru) Способ и устройство для управления движением на аэродроме
EP2837914B1 (fr) Systèmes d'affichage et procédés permettant des affichages indiquant une heure d'arrivée requise
US8362925B2 (en) Avionics display system and method for generating flight information pertaining to neighboring aircraft
EP2830032B1 (fr) Systèmes, procédés et affichage de poste de pilotage d'aéronef pour afficher des informations intégrées d'altitude minimale de sécurité et d'altitude de vectorisation minimale sur un dispositif d'affichage dans un aéronef
US11482115B2 (en) Systems and methods for providing optimal sequencing and spacing in an environment of potential wake vortices
EP3309519A1 (fr) Système pour aéronef et procédé associé permettant d'afficher le cisaillement du vent
WO2009029005A2 (fr) Procédé et système pour assurer la sécurité d'un aéronef
US11574549B2 (en) Composite vertical profile display systems and methods
Mahapatra Aviation Weather Surveillance Systems: Advanced Radar and Surface Sensors for Flight Safety and Air Traffic Management
EP3401892A1 (fr) Système d'affichage et procédé pour indiquer une exigence temporelle
RU2324203C2 (ru) Способ и система предупреждения о возможности попадания летательного аппарата в опасную зону вихревого следа генератора вихрей
US9047770B2 (en) Method for determining an instantaneous or anticipated probable zone of occupancy of an aircraft in an airport navigation zone
RU2324953C2 (ru) Интегрированная система вихревой безопасности летательного аппарата
WO2007115359A1 (fr) Système d'affichage pour la régulation du trafic aéronautique et procédé
RU2695019C1 (ru) Способ предупреждения попадания летательного аппарата в опасную зону вихревого следа генератора вихрей
RU2695249C1 (ru) Способ предупреждения попадания летательного аппарата в вихревой след самолета-генератора вихрей
RU2397549C1 (ru) Способ предупреждения угрозы столкновения вертолета с наземными препятствиями
RU2758526C1 (ru) Способ предупреждения попадания летательного аппарата в вихревой след самолета-генератора вихрей
Holforty et al. Flight deck display of airborne traffic wake vortices
Menon et al. Metrics for Air Transportation System Safety Analysis
EP3985646A1 (fr) Systèmes et procédés d'affichage de profils verticaux composites
Baburov et al. Methods for Improving Flight Efficiency and Safety Based on Technologies Applicable in Collision Avoidance Systems

Legal Events

Date Code Title Description
NENP Non-entry into the national phase in:

Ref country code: DE