RU39960U1 - INFORMATION TEAM LEADER SYSTEM - Google Patents

Abstract

An information command-and-lead system containing multifunctional indicators, a calculator of the aircraft navigation (helicopter) system, an integrated control system for the aircraft (AL), as well as a voice informant and signaling devices, functional subsystems of the on-board equipment complex, a radar system, and optical-electronic sighting devices, characterized in that its structure includes an on-board geographic information system and a system for preventing dangerous flight conditions, the functioning of which ensured There are a module for the base of geoinformation data, a module for compiling cartographic information files and navigation objects, a module for assessing dangerous states, a module for generating command and leader information for high-precision maneuvering and warning of dangerous states, and a module for generating navigational and cartographic information, and displaying aerobatic command and leader information the indicator is represented as a mnemonic frame of a new type of horizon, in which the principle of pseudo-volume image is used ia the symbol of your aircraft observed from another object located at an unchanged distance from the rear at the same height and ground speed with the controlled object, as well as a pseudo-volume image of a “leader” that changes position relative to the symbol of the controlled object, configuration and size depending from the generated command signal and deviations from the given trajectory and angular movements of the aircraft and from the given restrictions, which allows the pilot to form actions for controlling the aircraft

Description

The utility model relates to the field of aeronautical engineering (avionics) and can find application in the creation of flight and navigation equipment for airplanes and helicopters for flights under high-precision maneuvering conditions in difficult conditions.

When flying in difficult weather conditions at extremely low altitudes above a difficult terrain, a large number of flight accidents occur due to the pilots losing their perception of their spatial position and, as a result, the illogical control of the aircraft. To ensure flight safety under these conditions, the creation of an information-control field is required, which enables the pilot to simultaneously see the main flight parameters and dangerous conditions and form control actions appropriate to the situation.

The well-known principles for constructing an information-control field based on electro-mechanical indicators or on the basis of screen multifunction indicators (IFIs) are not without drawbacks in providing pilots with a reliable idea of the spatial position and condition of the control process in difficult conditions. Integration of two MFIs, an airborne geographic information system (GIS), a flight hazard warning system (AEC), a flight control system (helicopter), an integrated control system (KSU) for an aircraft, functional subsystems of a complex of airborne equipment (BWC), as well as the formation of flight mnemonics information and navigational conditions using the new principles for the presentation of flight information and geo-information about the flight area can eliminate the above e weaknesses.

The purpose of this proposal was to create a system of information command and leader support for the aircraft crew on high-precision maneuvering modes, which makes it possible to concentrate on the on-screen indicators the main flight and control information in the form of information command and leader ideas about the status of the control process and pseudo-volumetric image of dangerous states of approaching the terrain and to objects of threat in flight in the interests of:

- creating conditions for the pilot to simplify the determination of the spatial position of the controlled object and the ease of the simultaneous formation of control actions by the controls through the main channels;

- facilitating the formation of the pilot’s image of the control goal by the observed image of the leader;

- providing the pilot with visual command and leader information about the given motion parameters on the basis of the "do as I do" principle;

- improving flight safety conditions and the accuracy of trajectory maneuvering by concentrating information about critical conditions in the leader image and the presence of command information about control actions in it to correct the control process parameters and the direction of parrying dangerous deviations;

- improving flight safety conditions when approaching terrain, ground obstacles and objects of “threat” of a collision in flight in conditions of limited visibility of the off-cab situation due to the pseudo-volume presentation of cartographic information with a majorant of the preferred elevations of the terrain in the flight horizon window on the indicator and the pseudo-volume symbol of the collision threat object , as well as the creation of an active flight safety module over a complex terrain using cartographic information Mats.

The essence of the proposed utility model is illustrated by the figures, where:

- figure 1 presents a block diagram of an information command-leader system;

- figure 2 shows the mnemonic of the flight indicator for safe and high-precision maneuvering of the aircraft;

- figure 3 presents the mnemonic of the flight indicator for safe and high-precision maneuvering of the helicopter;

- figure 4 presents the mnemonic image of an electronic aeronautical chart and navigational and tactical situation.

The information command and leader system contains an on-board geographic information system 1, a system for preventing dangerous flight conditions 2, multi-function indicators 3, a computer for navigation (helicopter) 4, an integrated control system for the aircraft 6 at the control object 7, interconnected via interface modules 5, and also a voice informant and signaling devices 8, functional subsystems of the complex of on-board equipment 9, radar system 10, optoelectronic sighting devices .

The on-board geographic information system 1 contains a module of the geographic information database 12, a module for aggregating cartographic information files and navigation objects 13, and is intended to provide modules of the command-leader information system and subsystems of the on-board equipment complex with digital real-time cartographic information.

Airborne Geographic Information System:

- generates an on-board database of digital cartographic information using databases of ground-based geographic information systems, radio-technical situation data, and information about navigation objects and flight conditions;

- carries out the reception and storage of a digital map of the flight area;

- provides the formation of an electronic moving map in 2D (2D +) format with the display of the aeronautical environment;

- provides the formation of a pseudo-volume image in front of the underlying relief of the underlying surface (in 3D format) for manual piloting in low-altitude flight mode with bypassing and flying around obstacles;

- provides the formation of information about the profile of the relief along the predicted trajectory in low-altitude flight mode. The database of digital cartographic information may contain information about the fields:

- terrain

- object composition of the area,

- ground-based radar and radio equipment,

- radio thermal radiation,

- optical (light) contrasts,

- infrared contrasts and other fields.

The system for warning dangerous states of flight 2 contains a module for assessing dangerous states 14, a module for generating command-and-leader information 15 for high-precision maneuvering, preventing collisions with the earth's surface using digital cartographic information, and removing aircraft from dangerous states of proximity to ground obstacles and objects of “threat” in flight, a module for generating navigational and cartographic information 16 for constructing an electronic aeronautical map from navigational and tactical situations oh and for route planning.

It is designed to provide information to increase the level of safety and flight efficiency, to indicate dangerous conditions of trajectory control and to signal about dangerous proximity to the ground and objects of “threat” in flight. The system generates aerobatic, trajectory information for use in trajectory maneuvering modes based on current and predicted information, as well as signals for outputting from dangerous flight conditions.

The formation of information support for automated control of removal from the earth's surface, light and sound signaling about a dangerous approach to the terrain and dangerous conditions is carried out in the following sequence:

- determination of the zone of the current location of the aircraft in three-dimensional space, taking into account the accuracy of navigation systems and a database of digital terrain maps;

- prediction of the spatial flight path of the aircraft;

- determination of zones of dangerous state of trajectory movement and decision-making about the possibility of collision with the ground (determination of the degree of danger) using a digital map of the terrain, flight situation and the predicted flight path;

- the formation of information to indicate to the crew a digital map

terrain with the relief and elements of the object environment showing hazardous areas;

- the formation of a given trajectory (a given velocity vector) for flying around and avoiding obstacles;

- the formation and issuance of control information for display and in the automatic control system for outputting the aircraft from dangerous conditions associated with trajectory control;

- the formation and issuance of commands for warning visual and audible alarms about dangerous conditions and dangerous proximity to the terrain.

One of the most important functions of the system for preventing dangerous flight conditions is the function of early warning of the approach of obstacles to the earth, which ensures flight throughout all stages, including the evolution of the aircraft. It provides an overview of the front of the aircraft within a given working space and timely signaling if elements of the underlying surface fall into this space. The workspace is the space in the vicinity of the current and predicted trajectory of the aircraft to a given range. When determining the workspace, the aircraft’s maneuvering capabilities for exiting hazardous conditions and equipment used to verify the presence of a dangerous condition of trajectory control, as well as the accuracy of navigation sources, are taken into account. The working space is determined by the estimated range in the direction of the flight of the aircraft, the distance and the corridor of safe movement on both sides of the horizontal projection of the flight path and a predetermined downward distance, depending on the vertical predicted flight path. The working space varies depending on the stage of the flight, the distance to the runway and the required height above the underlying surface to perform its functions. The size of the working space in the horizontal plane will increase if necessary, rotation in accordance with the predicted trajectory.

The early warning function of approaching land and “threat” objects in flight is carried out by evaluating the parameters of the exit from the safe flight spatial zone in front of the aircraft according to the predicted flight path and providing the necessary signaling in the event of a potential hazard based on processing information from navigation systems, a low altitude radio altimeter, and a digital map terrain, radar system, optoelectronic sighting devices.

The calculator of the aircraft navigation system (helicopter) 4 is designed to solve the problems of navigation, control of high-precision maneuvering and the formation of command-leader information. In the formation of the aircraft navigation (helicopter) system, in the formation of command-leader information, the concept of controlling the velocity vector with the help of a single system is used

controlling a speed vector containing longitudinal, lateral, and directional control loops, a powertrain traction control loop, and normal overload and angle of attack limits for all flight modes, operating in accordance with the reference flight models of the aircraft, the target and the “threat” object, generated by the computer.

The calculator of the control system of the aircraft 4 is connected to the on-board geographic information system 1, the hazard warning system for flight 2, multi-function indicators 3, the integrated control system of the aircraft 6 through interface modules 5, which provide input-output control and operating modes.

Multi-functional indicators 3 include:

- GPUs 17,

- color liquid crystal monitors 19.

The display of aerobatic information on the indicator provides:

software module for the formation of a horizon horizon frame and flight parameters indication fragments 20, a pseudo-volume (3D) image generation module for dangerous trajectory maneuvering conditions and dangerous state output signals 21, and a flight indicator mnemonic for safe high-precision maneuvering 18P. Displaying the navigation environment on the indicator is provided by: a software module for generating an electronic aeronautical chart and displaying a navigation situation 22, a module for generating pseudo-volume (2D +) images of dangerous states near the earth's surface 23, as well as mnemonics of an air navigation map with a 18HT navigational-tactical situation.

For safe and high-precision maneuvering at extremely low altitudes, the mnemonic frame of the on-screen aerobatic indicator has been formed, providing the pilot with an instant visual representation of the spatial position and the required control actions. In the formation of the information frame of the flight indicator for safe and high-precision maneuvering, the goal was to create the possibility of concentrating on one screen display the basic flight information and a pseudo-volume image of dangerous states of approaching the topography of the earth.

A small frame of flight information is designed to provide the crew with the necessary information about flight and navigation parameters, as well as about the necessary control actions during flight and high-precision maneuvering at extremely low altitudes.

The snapshot is based on the introduction of a new type of horizon, which uses the principle of a pseudo-volumetric image of the symbols of its aircraft and the “leader” observed from another aircraft in a geocentric coordinate system located at an unchanged rear distance at the same height and ground speed with a controlled object ( images of the pseudo-volumetric character of the aircraft and

“Leaders” are projected onto a plane perpendicular to the ground speed vector). The image of the “leader” moves relative to the symbol of the controlled aircraft, changes its configuration and size depending on the generated command signal of the deviation from the given trajectory and angular movements of the aircraft and the given restrictions, which allows the pilot to form actions for controlling the aircraft and eliminating critical states in accordance with the principle "do as I do"

The mnemonic encoder flight indication of the aircraft (shown in figure 2) contains static and dynamic display fragments:

- information frame of the horizon (24);

- Fragments of the display of aerobatic parameters (34-40).

The information horizon horizon has:

- The horizon horizon in the form of two (vertical) lines, closed (above and below) by two arcs of light gray color. Fill of the horizon above the moving horizon is light blue, below the horizon is light gray. During the operation of the module of early warning of approaching the earth, within the boundaries of the symbol of the horizon, a pseudo-volume image of the forward-lying terrain appears with a majorant of preferred heights (25) in the predicted flight zone in accordance with the angle of inclination of the trajectory and the track angle.

- A pseudo-volume symbol of an object (26) with a chassis, a keel of variable length, made by double bypass, and with a rectangular bracket (27) - an indicator of the limit value of the angle of attack and the angle of glide (lateral risks of the bracket) or overload (when reaching n _for ^additional _max or α ^additional _max bracket starts flashing). The symbol of the controlled object changes its configuration depending on the change in the sliding angle and rotates relative to the center of the horizon horizon depending on the actual angle of heel, while together with the symbol of the object the symbols of the vector-director control principle are rotated (variable length keel 31 and bracket 27)

- The symbol of the current speed vector (28) in the form of a circle with two lateral risks and one risk at the top with a double contour, located at the gap of the central part of the aircraft symbol when the current speed vector coincides with the vector of the given speed.

- The symbol of the “leader” (29), which carries information about the given parameters of the spatial position and movement, according to which actions are formed in accordance with the “do as I” principle, and information about critical states by changing the configuration and blinking of the corresponding elements of the leader image that prescribe actions to eliminate critical conditions. "Leader" has the form of an aircraft - a triangle projected onto the horizon horizon screen. The base of the triangle is similar to the symbol of a controlled object with a chassis (without a keel) made by double bypass. The position of the "leader" on the screen provides the formation of a given control action along the longitudinal channel and roll. The center of the “leader” symbol moves within the circle of the horizon horizon field relative to the center point

symbol of the object is proportional to the command signal of spatial control of the aircraft. The size of the base of the triangle of the leader symbol changes depending on the deviation of the ground speed from the given ground speed. If the current ground speed is less than the specified one, then the wings of the leader symbol are smaller in comparison with the wingspan of the symbol of the object. When an object exceeds a predetermined speed, the “leader” symbol becomes larger than the symbol of the object, which requires a decrease in flight speed. The height of the top of the triangle, symbolizing the bow of the symbol of the object, is proportional to the specified angle of inclination of the trajectory. The top of the triangle indicates the qualitative state of the given flight parameters by moving the top up and down, respectively, to the right and left. At the apex of the “leader” triangle, a two-digit counter for the specified angle of inclination of the yellow trajectory is displayed. The angle of inclination of the base of the triangle (the symbol of the wings of the “leader” with the chassis) is equal to the specified angle of heel. When controlling through the roll and pitch channels, the pilot achieves the coincidence of the airplane symbol with the “leader” symbol. The specified dynamics of the control process for congestion (angle of attack) is ensured when the keel symbol of variable length (31) coincides with the directory label (30) of the specified control action (in the form of a corner) and is held in the vicinity of the mark. When controlling a power plant, the pilot ensures that the symbols of the object and the “leader” coincide in magnitude. Thus, the “leader” symbol is a vector-director pseudo-volume symbol with a high-quality indication of the set flight parameters along the roll, pitch, slip, speed, altitude and lateral deviation channels, providing control of the spatial position of the object and the airspeed vector.

- The roll scale (32) is fixed in the window of the horizon, with zero risks performed by double bypass and the aircraft symbol moving along the roll. If the roll readings are unreliable, the airplane silhouette is removed from the display, the center point remains.

- Symbol (33) deviations from the given height of the span over the topography (mountain).

A pseudo-volume image of the forward-lying terrain in the predicted flight zone is displayed in accordance with the angle of inclination of the trajectory. Relief portions in the forecasted flight zone falling into the region lying above the ground speed vector are painted red, terrain sections falling into the altitude zone between the predicted velocity vector and the “ski” are separated from the velocity vector by the allowable span height of preferred heights, painted over yellow. The rest of the image of the overlying terrain, which fell into the horizon, is painted in light gray-brown colors in accordance with the cartographic image of the terrain.

Fragments of the display of aerobatic parameters contain:

- course scale (34);

- barometric height scale (35);

- radio height scale (36);

- scale instrument flight speed (37);

- scale of the variometer (38);

- scale of angle of attack (39);

- overload scale (40);

- digital flight parameter counters

In the lower part of the mnemo frame, the predicted trajectory (41), the profile of the terrain (42) under the predicted trajectory with coloring of the hazardous areas of low-altitude flight and the scale of deviations (43) from the given flight altitude over the dangerous elevation of the relief in the forecasted flight section in the deviation range = 600 m are displayed , the predicted predetermined path of passage of obstacles of the terrain (44).

The aerodrome display for a helicopter (shown in figure 3) contains static and dynamic pieces of indication:

- information horizon horizon (45),

- the pseudo-volume symbol of the helicopter (46),

- symbol of thrust-to-weight ratio (47),

- overload symbol (48),

- director's mark (49),

- pitch angle counter (50),

- symbol of a leader (51),

- rotor speed symbol (52),

- variometer (53),

- pointer bar height and geometric height (54),

- an indicator of the operation of the SAU steering drives (55),

- a symbol of the geometric height of the underlying surface (56),

- speed indicator (57),

- hover indicator with para-visual display of the “treadmill” type of small values and ground speed trends in hover mode (58),

- navigation indicator (59),

- counters of outdoor temperature, true flight speed, ground speed (60).

During the operation of the module of early warning of approaching the earth, within the boundaries of the symbol of the horizon, a pseudo-volume image of the forward-lying terrain appears with a majorant of preferred heights in the forecasted flight zone in accordance with the angle of inclination of the trajectory and the track angle.

If necessary, instead of the navigation indicator (59), the mnemonic of the aeronautical chart with information about the navigational and tactical situation can be called up.

In automated control mode, the “leader” symbol changes

the shape, depending on the value of the set pitch and slip angles, rotates depending on the value of the set roll, moves around the screen depending on the amount of deviation in height and lateral deviation from the given path, and the magnitude of the symbol changes depending on the deviation of the flight speed from the set. If the flight speed is less than the specified one, then the “leader” goes forward and its visible dimensions become smaller.

The information command-leader system in the “free” flight mode (in the manual control mode) has one image of a managed object. The symbol of the leader’s object is, as it were, under the symbol of the managed object until the “free” flight is carried out within the limits established for the aircraft. When an aircraft exits during the piloting process beyond the limits, the leader object symbol appears on the information field, indicating what actions should be taken to enter a controlled object within the limits, and attract the pilot's attention by blinking.

The mnemonic of the aeronautical chart and information on the navigational and tactical situation shown in Figure 4

consists of four graphic layers, called using the frame buttons:

- “Goals” - an indication of the position of ground and air objects (targets), information about which was obtained via command lines of radio communication, using decryption of radar signals and / or from other sources;

- "Plan" - flight plan;

- "radar" - indication of the image obtained using the radar;

- "Map" - 2D + image of a topographic aviation map. All the above image layers are displayed in the reverse order of enumeration, in the agreed scale and coordinate system, with a single reference point. Scale control is performed from the frame buttons “≪” and “≫” and is displayed accordingly to the scales.

Information about the route is presented in the form of a combination of symbols of the navigation points and the symbol of the object, the location of which on the screen relative to each other is determined by the current geographical coordinates of the object and navigation points.

The mnemonic frame displays:

- intermediate points of the route (MRP) that make up the current route (previous and subsequent), the symbol of the MRP is presented in the form of a circle with an indication of the number of the MRP; - PPM-ts (targets) is distinguished by a double bypass;

- beacons (RM), shown in the form of a triangle with an arrow in the presence of communication with the RM or with underlining if there is no communication with the RM;

- airfields;

- landmarks.

The next MRP along the route and subsequent route points are connected by segments in the order of their location along the route. For MRP

to which the flight is carried out, the logic of displaying the line of a given path depends on the control method:

- with the route control method and lateral deviation of the object less than 5 km, the previous and next route points are connected by a segment. If the deviation of the object is more than 5 km, the broken line is made of two segments: the perpendicular from the object to the orthodromy and the segment from the intersection of the orthodromy with the perpendicular to the next MRP;

- with the track method for controlling the segment, the center of the symbol of the object and the next MRP are connected;

- with a combined control method, the line of the given path is displayed as a broken line: the center of the symbol of the object is connected by a segment with a point of start of a turn, which is connected with the exit point to a given course and then with the symbol of the next route point. In a repeated approach, a broken line can have up to 4 break points for displaying flight along two circles.

If you change the route from the current flight point using the multifunction control panel, or if you manually changed the control mode to route, then the point at which the object was at the time of the change of the flight control mode or mode is displayed as the previous MRP.

Information about the goals is presented in the form of a combination of target symbols and an object symbol, the location of which on the screen relative to each other is determined by the current geographical coordinates of the targets received from external sources or calculated in the forecast mode. The definition of targets or their selection from the radar background is done by pointing at them a crosshair (from the joystick) and pressing the "Capture" button.

Cartographic information (“Map”) is represented by the bottom (background) layer of the frame on the indicator in the form of an image of an aeronautical map in 2D + format in the selected coordinate system and scale.

Information from the radar (“radar”) is superimposed on the image of the map (if available) or on a black screen (background) in the form of a scan of the locator in the selected coordinate system and scale. At the same time, the multifunctional indicator framing buttons are updated, allowing you to set the optimal contrast of the radar information in relation to the background (map).

The joint use of digital map data, accurate information about the current coordinates of the aircraft’s location according to the integrated control system, radio navigation and landing systems, taking into account aerobatic flight restrictions and weather information, allows you to pre-warn and display the approach of hazardous spatial zones and hazardous states during trajectory control, as well as signal the need to withdraw the aircraft from the danger zone.

The functional diagram of the information team-leader system allows you to solve the following tasks:

1) indicative support of high-precision trajectory maneuvering modes in the spatial zone of safe flight and near the surface of the earth in difficult flight conditions with the display on the screen of MFIs of information command-leader indication, electronic flight map, radar information about obstacles and weather conditions;

2) providing the crew with indication of the parameters of the dangerous state of the trajectory control in the zone of complicating flight conditions and in the zone of complex (emergency) flight situations;

3) early warning of the approach of land obstacles;

4) warning of premature reduction in altitude during the approach;

5) determination of dangerous states of trajectory maneuvering and ensuring their display on MFIs in pseudo-volume (in 2D + and 3D formats) images;

6) the formation of a given velocity vector and control information for low-altitude flight regimes with overflight and obstacle avoidance based on information about the terrain, as well as the withdrawal of the aircraft from dangerous conditions;

7) the formation of signals and commands for warning light and sound alarms, as well as voice messages about a dangerous approach to the terrain and dangerous conditions of the control process.

8) prediction of the spatial trajectory and the formation of information about a given velocity vector (about the given ones: the magnitude of the velocity, the slope of the trajectory and the track angle) to derive the aircraft from dangerous states of the trajectory control.

The system provides for determining the parameters of aircraft navigation in the spatial zone of a given flight and predicting the flight path in the time interval from 3 to 60 seconds.

Such a technical solution for providing information to the crew of an aircraft in difficult flight conditions can improve flight safety conditions and the accuracy of trajectory maneuvering and increase the efficiency of using aircraft for various purposes.

Using the materials of this proposal, modeling was carried out on an interactive modeling stand and positive results were obtained [2, 4], confirming the feasibility of the proposed model.

Thus, the proposed utility model will allow, in the authors' opinion, the creation of an informational command and leader system for providing the aircraft crew with the indication necessary for flying in high-precision maneuvering modes in difficult weather conditions at extremely low altitudes over difficult terrain and meeting the requirements of modern aviation technology and ergonomics, as well as for the formation of control information in the interests of ensuring active flight safety using an integrated aircraft control system.

Sources of information

1. Information and command system. Copyright certificate No. 1381895 dated February 12, 1985

2. M.M.Silvestrov, I.A. Ehrlich, V.Yu. Lukanichev, N.P. Bezdetnov, etc. Engineering and psychological evaluation of the effectiveness of the pilot's interaction with the information-command display system during semi-natural modeling. Report. M. Research Institute of AO. 1988 50 p.

3. Qualification requirements of CT-xx-01. Underlying collision early warning system. Interstate Aviation Committee, 2000

4. M.M.Silvestrov, V.Yu. Lukanichev Yu.I. Begichev, L.M. Koziorov, L.O. Kotitsyn, and others. Development of the concept of creating a geographic information system for early warning of proximity to the ground. Report of the Research Institute of JSC and VVIA them. prof. N.E. Zhukovsky. 2002 142 p.

5. V.N. Bukov, Yu.I. Begichev, B. S. Kulabukhov, L. M. Koziorov, V. I. Konstantinov, V. Yu. Lukanichev, A. I. Naumov, M. M. Silvestrov. Development of a concept for the construction of a warning system for dangerous flight conditions. Collection. Integrated airborne systems. M. Publ. VVIA them. N.E. Zhukovsky, 2003.11s.

6. V.N. Bukov, Yu.I. Begichev, L. M. Koziorov, V. Yu. Lukanichev, A. I. Naumov, M. M. Silvestrov. Development of algorithmic support for a system for preventing dangerous flight conditions. Collection. Integrated airborne systems. M. Publ. VVIA them. N.E. Zhukovsky, 2003 11 p.

Claims (1)

An information command-and-lead system containing multifunctional indicators, a calculator of the aircraft navigation (helicopter) system, an integrated control system for the aircraft (AL), as well as a voice informant and signaling devices, functional subsystems of the on-board equipment complex, a radar system, and optical-electronic sighting devices, characterized in that its structure includes an on-board geographic information system and a system for preventing dangerous flight conditions, the functioning of which ensured There are a module for the base of geoinformation data, a module for compiling cartographic information files and navigation objects, a module for assessing dangerous states, a module for generating command and leader information for high-precision maneuvering and warning of dangerous states, and a module for generating navigational and cartographic information, and displaying aerobatic command and leader information the indicator is represented as a mnemonic frame of a new type of horizon, in which the principle of pseudo-volume image is used ia the symbol of your aircraft observed from another object located at an unchanged distance from the rear at the same height and ground speed with the controlled object, as well as a pseudo-volume image of a “leader” that changes position relative to the symbol of the controlled object, configuration and size depending on from the generated command signal and deviations from the given trajectory and angular movements of the aircraft and from the given restrictions, which allows the pilot to form actions for controlling the aircraft act and elimination of critical conditions in accordance with the “do as I” principle, and in which the improvement of flight safety conditions when approaching terrain and ground obstructions in conditions of limited visibility of the extra-cab environment is achieved through the pseudo-volume representation of cartographic information with a majorant of the preferred terrain heights in the horizon window, in addition, the display of the navigational and tactical situation on the indicator is provided by the representation of the air navigation mnemonic map with a navigational and tactical environment, on which the cartographic information in the form of an air navigation map in the selected coordinate system and at the selected scale has color coding depending on the zones of dangerous states near the terrain and objects of the “threat” in flight, as well as the fact that the calculator of the aircraft navigation (helicopter) system is connected to the airborne geographic information system, an early warning system for approaching the earth, multi-functional indicators and integrated systems th control through interface modules that provide input-output information and system operation modes for generating command-leader information using the concept of controlling the velocity vector using a single velocity vector control system containing longitudinal, lateral, directional control loops, a power traction control loop installations, contours of limitation of normal overload and angle of attack at all flight modes and reference flight models of a controlled object, target and object ″ Threats ″ generated by the computer, as well as for the formation of control information in the interests of ensuring active flight safety using an integrated control system.