RU2722888C1 - Method for integral display of flight situation parameters - Google Patents

Abstract

FIELD: physics.SUBSTANCE: invention relates to a method for integral display of flight situation parameters. To implement the method, data from an information and measurement system consisting of a set of systems for measuring motion and state of an aircraft, on-board aircraft, ground and satellite navigation systems, an on-board computer system and means of displaying information of aircraft, which enables displaying on the screen of a multifunctional digital indicator a set of flight situation parameters. Set of parameters of flight situation is displayed in a certain way, taking into account their mutual conditioning and interaction, which is manifested in various aspects - in location, connection, sizes of scales and indicators.EFFECT: higher flight safety due to continuous formation and presentation of an integral volume of information on the flight situation and reduced load on the pilot.1 cl, 16 dwg

Description

The invention relates to the field of information and display support for onboard control systems for manned aircraft (AC) and ground control systems for unmanned aerial vehicles (UAVs).

The level of technology.

During piloting, the aircraft pilot / UAV operator must:

- determine the correctness and effectiveness of the current pilot mode;

monitor compliance with flight safety requirements

Aircraft / UAV;

- perform simultaneous monitoring of the functioning parameters of the aircraft and the tactical situation (TO);

- carry out control taking into account limitations on the tactical and technical characteristics of the aircraft and the influence of external factors.

One of the ways to solve the aforementioned problems is to improve the information and control field (ICP) of the aircraft cockpit as the most important part of the ergatic system “aircraft + operator + environment”.

Of particular importance is the provision of the necessary and sufficient display of the complex of parameters of the flight situation at the current time and the forecast of its development in accordance with the ergonomic requirements of the components of the information display system (SDI).

There are two most constructive ways to accomplish this task:

Integration in traditional display systems on multifunctional digital indicators of the MFCI (frames of the flight pilot indicator KPI, TO), collimator aviation indicators (KAI), helmet-mounted target designation and indication system (NSCI) of the required and sufficient number of flight, tactical parameters and the most important parameters of engine operation, allowing the operator to control the current flight situation without resorting to different display objects;

- improvement of the coding and display system of aerobatic, tactical parameters and the most important parameters of the power plant operation to ensure simultaneous perception and the formation of a qualitative assessment of the situation, as well as the control of finding the quantitative values of the parameters within the permissible or specified limits of change.

In the often used KPI frame, the scale-parametric principle of displaying aerobatic parameters is used, which causes discreteness in obtaining information. This forces the operator to integrate separately perceived parameter values in the internal plan during the flight, which contributes not only to an increase in the time deficit for decision-making, but also prevents the possibility of the formation of a constantly necessary idea of aircraft in space stabilized relative to the Earth — the formation of a flight image. When improving the coding system in the KPI frame, it is necessary to use flight situation modeling methods that take into account the principle of anthropocentric features, that is, allow the operator to use the advantages of a person over technical devices in their activities, namely the ability to use visualization and integrity of perception in their activities.

To solve these problems, a number of devices are installed in the cockpit of the aircraft / at the automated workplace (AWP) of the UAV operator, which display the necessary information. It is assumed that priority is given to the most accurate of the available sensor systems and measurement systems that determine the current values of the flight situation parameters.

To ensure any flight regime of the aircraft / UAV, it is necessary to use both technical and human resources in the complex. In this case, a contradiction appears between the increasing power supply, technological complexity, ergonomic equipment of the equipment and the limited intellectual and psycho-physiological capabilities of the pilot / operator. Management errors are usually explained by errors or difficulties in perceiving and processing information due to the delay in the receipt of signal characteristics, omissions of necessary information, incompleteness and uncertainty of received messages (Ponomarenko V.A. Psychology of the human factor in a dangerous profession. Edited by M.I. Botov, - Krasnoyarsk, 2006). The results of studies of the psychophysiological characteristics of human activity and the state of flight, as well as the ergonomic features of avionics (Vorona A.A., Gander D.V., Ponomarenko V.A. Theory and practice of psychological support for flight labor. - M: Military Publishing House, 2003) show that in modern systems of indication and control there are significant shortcomings in terms of ensuring the most efficient and safe operation of aircraft. Constant improvement of the systems for ensuring the completeness and accuracy of the provision of flight information is required, improvement of the quality of the indication and ergonomic component of the information-control field (IC) of the cockpit of the aircraft / UAV of the UAV operator to ensure the timeliness and high degree of awareness of the pilot about the parameters of the flight situation and, thereby, increase safety piloting.

Known patent "Command-flight indicator", RU 2207514. The start date of the patent expiration date: 01/10/2002.

This patent proposes a variant of a flight-pilot indicator, which displays a set of flight situation parameters in the form of traditional scales and indicators and a horizon, in which the modified Leader display principle is used.

The proposed method for displaying flight situation parameters on the horizon is designed for aircraft in director or manual modes along a given path or along a path whose parameters can be calculated at the current time, for example, the landing path with measured / transferred aboard the aircraft deviation from the specific planning path airfield.

A scheme is proposed for processing the measured parameters of the flight situation and the parameters previously stored in the memory of the on-board computer system to perform calculations of the relative positions of the aircraft and Leader symbols.

Innovations in building a horizon include:

- movable tape scales of altitude and instrument speed with the location of the marks of set values at the level of the center of the frame, convenient for indicating small mismatches of the flight situation parameters in height and speed;

- the location of the roll angle scale in the upper part of the horizon with the reference to the current roll value from the vertical; interval of disclosure of the roll scale (-60 °; + 60 °);

- vertically and horizontally centered arrangement of all characters in the frame, as a sign of stable aircraft movement along a given or calculated path.

The relative location of the trajectory, the central symbol of the aircraft and the "Leader" gives the pilot instantly perceived discrepancies in heading, height and angle of heel. The indication of certain parts of the Leader symbol in flashing mode or in a changed color indicates the inaccuracy of the calculated values of the mismatch at the heading, pitch, roll angle, speed.

Disadvantages:

- inconsistency of the content of the principle of control of the aircraft according to the position of the "Leader" in the director mode and in the manual control mode; in the director mode, the position of the “Leader” is determined by the specified parameters of the aircraft trajectory and the mismatch of these values with the current aircraft motion parameters; control of the aircraft by heading, roll and pitch is expressed in the elimination of discrepancies in the values of these parameters and the coincidence of characters; in manual piloting mode, the pilot actually changes the flight parameters of the real aircraft, but the control result is displayed in a change in the position of the "Leader";

- the distribution of indications in case of false data on the mismatch of the flight parameters between the individual parts of the same symbol "Leader" can lead to a delay and errors in the perception of information;

- the rotation of the symbol "Leader" relative to its center corresponds to the difference between the current and set values of the roll of the aircraft; while the rotation of the symbols of the horizon relative to the center of the frame corresponds to a roll, visible from the Earth; such a situation cannot provide an instantaneous correct perception of roll mismatch and the implementation of the correct control action.

Known patent "Flight indicator", RU 2474862. Date of the beginning of the countdown of the patent: 12/28/2011

The basis of the indication on the KPI RU 2474862 is a system for processing the current flight situation parameters during aircraft flight along a predetermined path and the parameters stored in the onboard computer system of the aircraft determined by flight regimes, many trajectories, aerodynamic characteristics of the aircraft, inertial-mass, weight and other parameters that depend on flight safety and the performance of a flight mission, and the calculation of the current values of the mismatch and correction values for: roll angle, pitch angle, glide angle, instrument speed, lateral deviation from the trajectory, range deviation, height deviation.

Constructive and visual display of the totality of the above characteristics, an indication system on an analog of the horizon is selected, consisting of:

- the central symbol of the aircraft of variable shape, having the ability to only rotate in accordance with the current value of the angle of heel relative to the center of the frame; the shape of the central symbol displays the current values of the parameters of the roll angle, pitch angle, glide angle and instrument speed;

- a moving Leader symbol, the position of which in the frame and the shape reflect the calculated values of the mismatch and corrections of the values of the aircraft flight parameters along a given path;

- a symbol of radio altitude, stationary at altitudes of greater than 300 meters and moving to the center of the frame in accordance with an uneven height scale in the range (0 m; 300 m); 0 scale division is at the center of the frame.

The disadvantages of the KPI RU 2474862 include:

- the implementation of control actions to combine the symbol of the aircraft and the "Leader" in a sufficiently large number of parameters may require the pilot to pay extreme attention to the indication on the horizon and, accordingly, lack of time and attention to identify the situation by other parameters of the state of the aircraft and the outside environment;

- for small mismatches in roll, pitch, glide angle, and especially in magnitude of speed, the execution of symbols of the aircraft and the "Leader" with lines can lead to errors and difficulties in perceiving these mismatches; permissible errors are not specified when combining symbols and color characteristics of symbols and states;

- the conditions for changing the piloting mode and / or the possibility of urgent calculation of the maneuvering trajectory, which is more complicated than when driving along a given route, and the corresponding correction values of the flight parameters in conditions of time and attention deficit, are not specified.

Known patent "Method and device for processing and displaying information of piloting an airplane", US 7616130. The start date of the patent expiration date: 02/26/2007.

US 7616130 proposes a method and apparatus for processing flight situation parameters and displaying data, allowing calculating and displaying a mismatch according to the main parameters of aircraft piloting when following a path predefined in a three-dimensional coordinate system.

The proposed method for calculating and displaying deviations from the given values of the flight situation parameters — horizontal speed, vertical speed, and deviation from the given trajectory — and methods for displaying the result of actions allows eliminating the discrepancies by sequential compensation methods using the controls.

US 7616130 proposes a pilot signal view on an information display device presenting the necessary information in an easy-to-interpret form that allows the aircraft pilot to perform flight operations that are intuitive to him. The relative position of the symbols on the indicator is calculated in accordance with the device and control laws for a particular type of aircraft in such a way that the control strategy is reduced to the imposition of the centers of indicators and symbols.

The device proposed in US 7616130 can be used both on helicopters and on airplanes in indicators of any type, in particular, on indicators on the aircraft windshield.

The disadvantages of the method of US 7616130 include the need to take into account in calculations the features of the device and control a specific type of aircraft in which this display method will be applied, which is not specifically discussed.

Known patent "Aviation orientation system", US 8421649. The start date of the patent expiration date: 02/22/2010.

According to the method of supporting the spatial orientation of the pilot, US8421649 is rather close to the claimed invention. The authors of US8421649 use the indication of the symbols of significant aerobatic parameters that are stationary relative to the plane of the screen — the angle of heel and the pitch angle, and refuse to indicate the moving symbols of the artificial horizon and aircraft in the frame.

The display of the roll and pitch angles is supplemented by digital counters of the current instrument speed and altitude values that are in the pilot's field of view near the main display frame.

US 8421649 describes a mechanism for setting the aircraft parameters and flight situation in various flight modes in the on-board computer, based on which the pilot can be helped in case of loss of situational awareness and spatial disorientation. There are various ways of issuing information - visual messages, voice messages, the possibility of rejecting one of the types of messages at the choice of the pilot. Messages are provided that relate not only to the warning about the need to start corrective actions to prevent the loss of spatial orientation and the essence of the action, but also to its end.

In the indication of scales and indicators of the angle of heel and pitch angle, a standard color coding is used.

A non-standard solution for displaying the roll scale and two versions of the roll indicators should attract the attention of the pilot when performing flight modes that do not involve large deviations from situationally justified parameter values.

The disadvantages of US 8421649 include:

- reducing the totality of the aerobatic parameters displayed in the standard aerobatic display and which must be taken into account when performing the flight, to indicate the pitch angle and roll angle;

- a combination of scales and pointers in the frame, not causing natural associations with the space of flight.

Known patent "Integral indicator of flight control", US 6028536. The start date of the patent expiration date: 16.11.1995.

US 6,028,536 proposes an integrated flight control indicator for providing visual information displayed in symbolic and digital form. The symbolic display of the flight situation parameters provides simultaneous pilot recognition of the position of the aircraft (aircraft) in the Earth's space, corresponding to the view from the aircraft to the Earth. The display of the main parameters of the flight situation using naturally recognizable symbols provides simultaneous recognition of the flight situation and makes it possible to vary the display scale in the direction of decreasing size, which allows the proposed method of indication not only on the displays of the aircraft cockpit, but also in the helmet-mounted indicators and indicators on the windshield Aircraft, minimize additional images in the pilot's field of vision in flight modes, requiring visual control of the situation in the outside space.

The method for displaying the parameters necessary for flight control, proposed here, is supplemented by leader symbols to ensure flight along a given trajectory and to complete an approach approach using ILS instrumental landing system data. This method of displaying the parameters necessary for flight control allows the indication necessary to perform a flight with enveloping the terrain.

The method of displaying US parameters 6028536 necessary for flight control is supplemented by display elements for visualizing and displaying flight situation parameters in the case of using weapons for air targets.

The configuration of the main symbols of the proposed integrated flight control indicator - the central fixed symbol of the aircraft, the arc of the sky, the arc of the earth, the ratio of the angular dimensions of the arc of the sky and the arc of the earth, the position of the horizon line, understood as a line corresponding to 0 ° pitch, the symbols of the direction of inclination of the trajectory, the roll of the earth, the position of the vertical speed symbol corresponding to the flight of the aircraft at a height greater than the specified one, the symbol for achieving the minimum permissible altitude ensures their instant recognition and position within the integral indicator, which provides a qualitative assessment of the parameters of the flight situation that correspond to them.

The location and configuration of the aircraft heading symbols and the speed scale provides a simultaneous perception of the direction of aircraft movement and the value of the current aircraft speed relative to the basic speed values set and calculated by the on-board computer for a particular aircraft - the minimum allowable and maximum allowable speeds, stall speed, and the speed of maintaining the integrity of the aircraft structure.

The use of digital tape scales and indicators provides an error-free reading of the current values of pitch and angle of attack.

The mnemonic scale of the parameters for using weapons for air targets and its location within the integrated indicator are convenient for instant high-quality perception by the pilot.

The use of color coding of the symbols of the integrated flight control indicator improves the conditions for recognition and assessment of the flight situation.

The disadvantages of the integrated flight control indicator US 6028536 should include:

- reading the quantitative values of the roll, altitude, speed, course of the aircraft and the mismatch of the latter with a given direction angle is difficult due to the variable display location;

- the display of figures of symbols of the artificial horizon of the earth, central symbols of the aircraft, symbols of trajectory markers, a symbol of vertical speed, a line to indicate the height of the aircraft above the surface of the earth with arcs and lines of small thickness can make it difficult to identify them, especially in the monochrome version required by the helmet-mounted indicator and indicator on the windshield of the aircraft;

- the success of the use of the integrated flight control indicator for roll values greater than the absolute value of 90 ° is not obvious; there are no restrictions on the amount of roll; flight situations are not described and are not shown in the figures when the roll is larger in absolute value 90 °, and with different values and sign values of pitch.

The closest in technical essence to the claimed invention in terms of essential features is the patent “Flight-control device for logical indication of the position and control of an aircraft in space (options)”, RU 2331848. Date of the patent validity starting date: 06.10.2008.

In patent RU 2331848, there are two options for implementing an aerobatic display system in the flight cockpit instrumentation system of the aircraft cockpit - a mechanical version of the display device and a display option in the KPI frame on the MFCI screen adopted in the modern aircraft ICP.

For comparison with the method of indicating flight parameters of the claimed invention, the second option is selected based on the implementation method in the IUP.

The system for displaying flight parameters of a flight situation of patent RU 2331848 in a flight control device for logical indication of the position and control of an aircraft in space contains:

- the display area in the form of a circle on the screen MFCI;

a concave pitch scale with an average vertical screen oriented in the vertical direction;

- an arched non-uniform roll scale located lower along the border of the display area, designed to count the roll angle according to the position of the wing of the aircraft symbol;

- pointer to the velocity vector,

- indicator of the conditional horizon (0 ° pitch) in the form of a fixed horizontal line plotted on the screen perpendicular to the average vertical of the screen;

- three-dimensional image of the rear view of the aircraft above the pitch scale, the bow of which is oriented from the screen towards the middle vertical of the screen;

light background of the screen field above the line of the indicator of the conditional horizon, showing the sky;

- the dark background of the screen field under the line of the indicator of the conditional horizon, showing the Earth.

The MFCI is associated with a processor unit configured to generate a graphical display of a concave pitch scale with an average screen vertical, an arched roll scale under a conditional horizon indicator, an image of a volumetric model of an aircraft in front of a pitch scale oriented with the nose towards the middle vertical of the screen and with a function for changing the image the aircraft’s volume mockup by programmatically changing the position of its bow according to the current pitch to the left and right of the middle vertical of the screen parallel to the line of the conventional horizon and the rotation of the housing of the specified mock along the roll relative to the center of the frame, as a function of digital signals corresponding to the precession of individual gyroscopes.

The pointer of the velocity vector is made in the form of two lines spaced relative to the middle vertical of the screen beyond the pitch scale, relative to which the pointer of the power-to-weight ratio of the aircraft moves, made in the form of two arrows facing each other, which can move relative to the pointer of the velocity vector in the vertical direction to demonstrate the energy engine power reserve at this stage of the flight.

The symbol of the artificial horizon is made in the form of a line corresponding to the position of the natural horizon of the Earth’s surface at the current value of the height of the aircraft and located under the indicator of the conditional horizon. The artificial horizon symbol rotates relative to the center of the frame by an angle inverse to the current roll of the aircraft.

To increase the information content in the device, the pitch scale can be made with the possibility of changing the bit depth of the scale in the direction from the line of the conventional horizon to the periphery of the screen, which is especially important for visual indication of pitch angles approaching 90 degrees in absolute value.

The displayed signs of the flight situation are essential and are interconnected with the formation of a stable set of essential features sufficient to obtain the required technical result.

As conceived by the inventors, the symbol of the artificial horizon unambiguously shows not only the position of the aircraft during maneuvering, but also its position relative to the natural horizon. Together with the information of the additional altitude indicator (the location of which relative to the KPI frame is not indicated), the symbol of the artificial horizon allows you to unambiguously interpret the position of the aircraft in space directly. Thus, the symbol of the artificial horizon can serve as an indication element, contributing to the preservation of the spatial orientation of the pilot during maneuvering.

The display on the KPI of the invention RU 2331848 has progressive trends in displaying flight situation parameters, but their real content due to the conventionality of displaying values important for piloting requires experimental confirmation. These include:

- the sufficiency of the symbol of the artificial horizon for timely and error-free perception, taking into account the prescribed function of the indication element, which helps to maintain the spatial orientation of the pilot during maneuvering;

- simultaneous roll indication according to the rule "view from the Earth on the Sun" on the BC symbol and the back roll on the symbol of the natural horizon, leading to the intersection of the line of the wings of the aircraft and the line of the natural horizon (figure with the type of indication at heel angles greater than 90 ° in absolute value in the description patent not submitted);

- the indication of the change in the course of the aircraft is limited to the indication of the sliding angle;

- indication of the angle of attack combined with a pointer to the velocity vector; it is assumed that the calculation rules specified in the on-board computer system make it possible to quantitatively and qualitatively display the absolute value and sign of both quantities.

Researched Prototypes

1. Patent RU 2207514 C1, 07.26.2003.

2. Patent RU 2331848 C2, 04/20/2008.

3. Patent RU 2474862 C1, 12/28/2011.

4. Patent US 7616130 B2, 10/11/2009.

5. Patent US 8421649 B2, 02.21.2011.

6. Patent US 6028536 A, 11.16.1995.

The essence of the claimed invention.

The problem to which the claimed invention is directed is to achieve the necessary and sufficient display of the parameters of the state of the flight situation at the moment and the forecast of its development, which ensures the prevention of spatial orientation and / or the preservation of the flight image in a stabilized space of the Earth in conditions of combat maneuvering, especially low altitudes, and in difficult meteorological conditions (SMU).

The method of integrated display of flight parameters of the claimed invention is implemented on the basis of the aerobatic parameters presentation system set forth in "A new concept of an integrated flight instrument and justification of information issued to a pilot in special flight situations." Skibin G.G., Ayvazyan S.A., Bogdanov Yu.V., Radchenko M.I., Belousova V.S., Moscow, 2013.

The invention is confirmed by drawings.

The type of indication of the flight situation parameters of the claimed invention is presented in Figure 1, illustrating a set of main indicator objects of the presented display method on the KPI.

Figure 2 shows the type of indication when flying at low altitude.

Figure 3 shows the type of indication of the angle of attack with a positive value within the range of acceptable values of the angle of attack.

Figure 4 shows the type of indication of the angle of attack with a negative value within the range of acceptable values of the angle of attack.

Figure 5 shows the type of indication of the angle of attack with a positive value within the range of acceptable values of the angle of attack with an aircraft roll greater than 90 ° (possibly less than -90 °).

Figure 6 shows the type of indication of the angle of attack with a positive value greater than the maximum allowable angle of attack.

Figure 7 shows a view of the central symbol of the aircraft; the central symbol of the aircraft is depicted with mechanization elements displayed in the respective aircraft flight modes.

Figure 8 shows the type of indication on the central symbol of the aircraft of the position of the pointers of the current value of vertical overload n _y and the recommended value of vertical overload, greater than the maximum allowable value n by _urek ≥ n _maxim , a pointer to the current value of the angle of attack, less than the maximum allowable value.

Figure 9 shows the type of indication on the central symbol of the aircraft of the position of the pointers at the current value of vertical overload n _y = 1 and the recommended value of vertical overload n by _urek ≤ n _maxim , a pointer to the current value of the angle of attack equal to the maximum allowable value.

Figure 10 is a view indicating the central position of the sun symbol pointer vertical acceleration, the smaller the minimum acceptable value n _y ≤ n _Umino and pointer angle of attack, the smaller the minimum acceptable value.

Figure 11 shows the type of indication when the aircraft is performing an upward maneuver.

Figure 12 shows the type of indication when performing the aircraft downward maneuver.

Figure 13 shows a view of the display of aerobatic flight parameters in a horizontal flight in a situation where a turn is necessary when there is a significant discrepancy between the current aircraft course and the given course.

Figure 14 shows the type of indication of the resolution of the situation in Figure 8 when realizing the possibility of a quick change in the course of the aircraft by a sufficient increase in the speed of the aircraft and an allowable increase in vertical overload.

Figure 15 shows a view of the instrument speed scale.

Figure 16 presents a flowchart of a data processing procedure characterizing the current flight situation for image formation on a flight indicator according to the claimed invention. It consists of: information-measuring system (IMS), on-board computer system (BVS) and information display system (SDI).

The information-measuring system includes systems for measuring the parameters of motion and state of the aircraft located on board the aircraft, for example,

- Inertial navigation system ANN,

- Doppler speed and drift meter DISS,

- SHS air signal system,

- automatic control system of self-propelled guns,

- bodies and control drives of the aircraft OS,

- aircraft power plant,

- fuel system sensors,

and terrestrial and satellite navigation systems, for example,

- satellite navigation system SNA,

- ground-based radio navigation system, in particular, the system of short-range navigation beacons RSBN / VOR,

- KGS heading system.

The data processing procedure for image formation on the flight indicator characterizing the current flight situation is performed as follows.

The on-board computer system receives the current values of the flight situation parameters from sensors and measuring systems located on board the aircraft and outside the aircraft.

Here, each of the parameters determining the state of the aircraft and the parameters used in the display is analyzed for reliability, either on the basis of a priori information about its possible values, or by processing several data from various sources of information, depending on the nature of the parameter.

Further, the checked current values of the flight situation parameters and with the reliability attributes assigned to them (0 or 1) are sent to the secondary signal generation unit.

Here, according to the algorithms of the present invention, taking into account the data calculated in the BVS or contained in its memory, for example, permissible and recommended values of aerobatic parameters depending on the flight mode, descriptions of routes and navigation points, internal variables and functional dependencies are formed that are used directly to build indication.

These data go to the information display system - to the image symbol generator, where the characteristics (sizes, shapes, position coordinates on the MFCI or KAI screen, colors and display modes) of the display symbols corresponding to the current state of the flight situation and signs of reliability are formed. Further, on their basis, an image of the KPI frame on the MFCI screen is built.

When displaying the flight situation parameters in the claimed invention, flight situation modeling methods are used that take into account the anthropocentric principle, that is, allowing the operator to use the advantages of a person over technical devices in their activities, namely the ability to use the clarity and integrity of perception in their activities.

The method of integral display of the flight situation parameters of the claimed invention allows to display a set of parameters, taking into account their interdependence and mutual influence, which is manifested in various aspects - in the location, connectedness, size of scales and pointers, indicators, grouping and duplication.

The method of integral display of the flight situation parameters of the claimed invention in the frame of the CRPD at the MFCI meets the basic requirements for display systems of the information-control field (ICP) of the aircraft cockpit:

- Presentation of the synthesized modeling image, allowing you to simultaneously control a large number of parameters;

- use of the angle of heel indication according to the principle “view from the ground on the aircraft”;

- ensuring the display of information common to all phases of flight in a single form;

- combination of additional information necessary for individual phases of flight, with general information.

The type of display of aerobatic parameters is a system of parametric units interconnected in accordance with the laws of aerodynamics and the rules of operation of aircraft on-board equipment systems, the main of which are shown in Figure 1.

This type of indication allows you to constantly, at a qualitative level, monitor the status of the flight situation, and also contains a sufficient number of indicators for the numerical values of the parameters to control the necessary control actions and failure indicators to monitor the performance of the SDI:

1, 1a - pointers to the current values of vertical overload n _y and angle of attack; a duplicate symbol (1a), visually not associated with the vertical overload scale (36), allows you to qualitatively determine the relationship between the current vertical overload value and the recommended vertical overload value by the position of the duplicate symbol relative to the opening angle of the exchange rate scale (2);

2 - the course scale in the form of an arc of variable size, oriented at the current aircraft course, revealing symmetrically with respect to the current aircraft course;

3 - scale of angle of attack;

4 - indicator of the current value of the aircraft;

5 - pointer roll aircraft, counted from the vertical; if there is no reliable roll value, the pointer is fixed at 0 ° and is displayed in yellow in flashing mode with a frequency of 2.5 Hz;

6 - a symbol of the position of the Sun relative to the current course of the sun;

7 - barometric altitude indicator for heights of large 100 meters; barometric height scale is not uniform; digitization of the scale is indicated on the elements of the reference scale (22); digitization of the scale from the symbol “0” (0 m) to the symbol “3.” (3000 m) is displayed constantly; digitization symbols corresponding to values greater than 3000 m are displayed according to the following rule: when exceeding a barometric height of 3000 m, the symbol "6." is displayed, when exceeding 6000 m - the symbol "18."; on the scale, the specified flight altitude or the specified height interval in the form of a segment can be displayed as an index;

8 - a scale of small heights (Figure 2); displayed at barometric altitude and radio altitude values less than 100 meters;

9, (9a) —the instrument speed indicator (km / h) in combination with the instrument speed scale (33) and the Mach number indication (31); the instrument speed indicator is duplicated (9a) at the end of the course scale on the right in combination with the true speed indicator (11);

10 - group display current values of vertical speed (m / s) and barometric altitude NB (m);

11- indicator of true speed (km / h);

12 - the symbol of the recommended overload value when the pointer of the current value of the angle of attack deviates from the angle of attack indicator (13) by an angle proportional to the difference between the current value of the vertical overload n _y and the recommended value n _urek ;

13 is a pointer to the angle of attack with a pointer to the slope of the trajectory (14); the angle of deviation from the trajectory symbol corresponds to the value of the angle of attack within the interval of permissible positive values (38 figure 3) or negative values (39 figure 4); if the roll of the aircraft is greater than ± 90 °, the indicator of the angle of attack is displayed in an inverted position relative to the lower side of the symbol (40 Figure 5); outside the range of acceptable values, the center of rotation of the angle of attack indicator is fixed at a point corresponding to the nearest boundary of the acceptable interval, is indicated in the accepted warning color, for example, red (41 Figure 6).

14 - pointer to the angle of inclination of the trajectory;

15, 15a - “beams” representing the position of the plane of the artificial horizon corresponding to the zero value of the pitch angle;

16 - scale and radio altitude indicator for heights of large 100 meters; if the radio altitude is less than 100 meters, the scale (8) shown in Figure 2 is displayed;

17 - overload scale n _z ; a change in the current value of n _{z is} displayed by shifting the scale symbols relative to the central pointer in accordance with the sign and magnitude of the current value; the indicated range of values n _z - (-0.6; +0.6);

18 - a symbol of the Earth’s surface at small (lower than a sufficiently accurately determined radio altitude value) radio altitude values;

19 - the main symbol of the Earth;

20 - indicator of the current time of the time zone of the aircraft;

21 - the central symbol of the sun;

22 - reference scale;

23 - indicator of the current value of radio altitude; in case of doubt, displays as HP XXX; when the safety height is reached in the aircraft flight zone, indicator (23) is displayed in orange in flashing mode with a frequency of 2.56 Hz;

24 - flight time;

25 - available time (hours and minutes) at the current fuel consumption rate;

26 - current amount of fuel; if the fuel quantity is not reliable, indicators (26) and (25) are displayed in yellow in flashing mode with a frequency of 2.5 Hz;

27 - recommended overload value by purek;

28 - interval of recommended values on the engine speed scale;

29 - pointer and the value of the left / first engine speed in percent;

30 - pointer and the value of the rpm of the right / second engine in percent;

31 - indicator of the Mach number (M);

32 - the limit position of the engine speed scale corresponding to a value of 100%;

33 - instrument speed scale; the scale (Figure 15) is interfaced with the heading scale in such a way that the current value of the instrument speed is located at the heading of the heading scale (58); the arc of the scale (61) displays the allowable speed range from the evolutive speed (pointer 60) to the maximum allowable speed in the current flight mode (pointer 57); green recommended speed indicator (59); if the maximum permissible speed is exceeded, part of the arc (61) of the speed scale behind the maximum permissible speed indicator is indicated in red;

34 - pointer to a given course; in modes that require the flight of the aircraft to a given navigation point, symbols of the drift angle and the given track angle can be additionally displayed;

35 - scale vertical overload n _y ;

36 - current value of vertical overload;

37 is a symbol of the sky.

Figure 16 shows a diagram of the processing of flight information for presentation in the form of display elements in the KPI frame.

In the model for displaying the aerobatic parameters of the KPI, it is accepted to display the position of the aircraft — a view from the Earth to the aircraft. To build an indication of the aircraft above the Earth's surface, the data of meters located on the aircraft and outside it, coming to the symbol generator from the on-board computer system (Figure 16), are used.

The basic symbol of the Earth (19) is used to determine the true position of the aircraft in space and serves as the basis for restoring the spatial orientation of the operator, which was impaired during flight on the KAI during difficult maneuvering, flight in the SMU and in other similar circumstances. The Earth symbol is stationary until the aircraft reaches a height corresponding to a sufficiently accurately determined value of the radio height; then the symbol rises and reaches the center of the frame at zero height; the law of movement of the symbol is chosen so that at low altitudes, less than 100 meters, correspond to the scale of heights (8) of Figure 2. In the case of aircraft moving along a descending path and approaching a dangerous height, the Earth symbol is displayed with a color change in a flashing mode.

The symbol of the position of the plane of the artificial horizon, formed by "rays" (15, 15a), allows you to instantly determine the direction of the aircraft relative to the Earth:

- decrease if the symbol is above the sun and the "rays" are directed from top to bottom;

- increase in height if the symbol is below the sun and the "rays" are directed from bottom to top;

the horizontal arrangement of the "rays" corresponds to the horizontal flight of the aircraft.

The slope of the "rays" is determined by the value of the angle of inclination of the trajectory; the slope of the “rays” exactly corresponds to the slope of the trajectory in a given range of values, which may vary depending on the flight mode. Since the symbol of the virtual horizon should give a qualitative assessment of the flight situation outside this interval, the slope of the "rays" is fixed. Similarly, the position of the symbol (15, 15a) relative to the central symbol of the aircraft is precisely determined by the value of the pitch in a given range of values, which may vary depending on the flight mode; outside this interval, the position of the symbol relative to the BC symbol is fixed. "Rays" are formed by a sequence of strokes, the values of which are constructed according to the law of perspective to create an image of a plane; their movement within the “beam” corresponds to the sign and magnitude of the overload n _{x in} an intuitive way.

Symbols of the Earth (19) and the artificial horizon (15, 15 a) provide a visual representation of the position and movement of the aircraft in the vertical component of space stabilized relative to the Earth. Figure 11 shows a variant of the upward movement of the aircraft at a pitch value of + 40 °, in which the Earth symbol is not visible with the commonly used method of displaying the artificial horizon symbol - a line separating the sky symbol and the Earth symbol (for example, patent RU 2207514 C1, 07.26.2003; patent RU 2331848 C2, 04/20/2008), - the display field of the aerobatic parameters is entirely painted in the colors of the sky symbol. Similarly, Figure 12 shows a variant of the aircraft downward maneuver at a pitch value of -60 °, in which the sky symbol is not visible with the commonly used method of indicating the artificial horizon symbol (for example, patent RU 2207514 C1, 07.26.2003; patent RU 2331848 C2, 20.04. 2008) - the display field of the aerobatic parameters is entirely painted in the colors of the sky symbol. In both situations, as practice shows, when using this method of indicating the symbol of the artificial horizon, aircraft pilots experience increased psychophysiological stress when maneuvering in the vertical component of space with a long absence of the indication of the Earth symbol or sky symbol.

Display character group:

- course scale (2),

- scale (35) and indicators of the current value (36) and recommended value (27) of vertical overload,

- scales (33) and indicators (9, 9a) of the current instrument speed,

- the aircraft roll index, measured from the vertical (5), allows one to instantly determine the possibility of safe maneuvering in the plane of the horizon of space stabilized relative to the Earth, and to control the finding of the instrument speed, roll and overload n _y in safe, permissible intervals, regardless of the specific values of the latter , and determine the necessary control actions to keep the speed, roll and overload n _y within acceptable limits, to correct the situation, for example, for an urgent transition to horizontal flight, increase in instrument speed, etc.

To ensure the named aspect of the indication, the angle of the heading scale (2) is determined by the heel value, which excludes the downward movement of the aircraft with permissible vertical overload n by the _urek . The value of n _is determined by the ratio of the minimum permissible instrument speed for the current flight mode of a particular aircraft and the current value of instrument speed.

The vertical overload scale n _y (35) is interfaced to the heading scale (2) so that the heading line limiter coincides with the corresponding recommended overload n _{value urek} . With proper / safe piloting, the current overload value (36) should not exceed the recommended value (27) - the pointer (1, 1a) should be within the symbol of the heading scale (2).

In a flight situation that requires a quick change in the current aircraft heading for a flight to a given navigation point, a given heading may be outside the disclosure of the heading scale (Figure 13). Aircraft pilot can provide a safe and rapid change in the current course by increasing the instrument speed with a coordinated increase in the interval of permissible heel values and the magnitude of the permissible vertical overload, controlled by the indication on the group of symbols (2, 5, 9, 27, 35, 36, 27), as shown in figure 14.

If the limiting values of the angle of heel for a particular aircraft are specified in the current flight mode, the disclosure of the heading scale (2) is determined by the smaller of these values and the magnitude of the heel with permissible vertical overload n by _urek .

With engine speed indicators (29, 30), engine performance characteristics, such as starting mode, shutdown, emergency shutdown, afterburner mode, maximum permissible speed, exceeding the maximum permissible gas temperature, vibration, etc., can be displayed in symbolic form.

The location of the indicators (28, 29, 30) directly in the KPI frame allows you to control the operation of the engines without additional attention, since it does not require shifting the pilot's gaze to other indicators on the MFCI or aircraft cabin instruments.

The central symbol of the aircraft (21) is a stylized image of the aircraft when viewed from the rear and consists of two groups symmetrical with respect to the center of the figure (Figure 7). Each group contains a horizontal straight line segment identified with the aircraft wing (42, 42a), an inclined straight line segment identified with the aircraft keel, (43, 43a) a circle identified with the engine (48, 48a). The main figure of the aircraft symbol will be supplemented by symbols for the takeoff position of the flaps (44, 44a), the landing position of the flaps (45, 45a), the landing gear (46, 46a) and other mechanization elements in the corresponding flight modes of the BC. The engine operation characteristics are displayed against the background of the symbols (43, 43a) with the same symbols as with engine speed indicators (29, 30).

The position of the aircraft symbol in the frame of the KPI is fixed, it displays the angle of heel of the aircraft by rotation relative to the center of the symbol. The position of the center of the aircraft symbol coincides with the position of the symbols of the artificial horizon (15, 15a) at a pitch value of zero.

Figures 8, 9, 10 show options for displaying symbols of the current value of the angle of attack, the recommended value of vertical overload, and the indicator of the current value of vertical overload for various values of the named parameters. In Figure 8, figure (62) displays the current value of the angle of attack. Figure (62) opens upward from the wing symbol with a positive angle of attack. The disclosure of the figure symbolizing the angle of attack, down from the wing symbol corresponds to negative values of the angle of attack (54 of Figure 10). The symbol of the current value of the angle of attack reaches the keel position at the maximum permissible value, as shown in Figure 9 - (52). When the angle of attack is within acceptable limits, figure (62) has a light blue color associated with the air flow. Further disclosure of the symbol to an opening angle of 90 ° corresponds to an increase in the angle of attack also to 90 °. The angle of attack symbol (52) is framed in red, and part of the symbol behind the keel is fully displayed in the accepted warning color. Upon reaching the minimum acceptable value of the angle of attack, the disclosure angle of the figure (54, 54a) is 25 °; figure (54) is displayed in the accepted warning color.

Similarly, turning symbol (50) in Figure 8 up from the wing corresponds to an increase in vertical overload from 1 to the maximum allowable value in the position on the keel symbol. With a further increase in vertical overload, the symbol (50) is indicated in the accepted warning color. The decrease in vertical overload from a value of 1 is indicated by turning the symbol (55 figure 10) down from the wing. The symbol position of the current vertical overload with a value of 1 is shown in Figure 9 - (51). The symbol of the recommended vertical overload is displayed only in the space between the wing and keel symbols, since if the calculated recommended value of the maximum permissible overload is exceeded, the calculated value is taken to be the maximum permissible value. So in Figure 8, the symbol of the recommended vertical (49) overload coincides with the position of the keel corresponding to the maximum permissible value. In Figure 9, the recommended vertical overload symbol (53) is located between the wing and keel symbols.

The current values of the instrument speed (9) and true speed (10) in units of km / h are constantly displayed under the course scale limiters (2), which corresponds to the accepted rule for determining the angle of opening of the course scale depending on the magnitude of the current aircraft speed. The value of the instrument speed relative to the limiting values can be estimated by the position of the instrument speed scale (33) on the heading scale (2). The dynamics of changes in aircraft instrumental speed are displayed intuitively, perceptibly by the movement of the elements making up the "rays" of the artificial horizon plane, determined by the sign and magnitude of the overload n _x .

. В заданном интервале значений числа Маха

; индикация счетчика числа М (31) с точностью 0,01.Mach number (31) is displayed when a certain set value is reached

. In a given range of Mach numbers

; indication of the counter of the number M (31) with an accuracy of 0.01.

The values of the coefficients k ₀ , k ₁ and k ₂ are selected in accordance with the characteristics of a particular type of aircraft.

The scale of the angle of attack (3) and the scale of vertical overload n _y (35) are combined in such a way that the pointer (1, 1a) marks the current values of both the angle of attack and the vertical overload n _y . The scale of the angle of attack is revealed in a given interval relative to the current value; scale digitizing symbols belonging to the interval of acceptable values of the angle of attack are displayed in green; scale digitization symbols outside the range of acceptable values of the angle of attack are displayed in red. With a dangerous approximation of the current value of the angle of attack to the border of the interval of acceptable values, part of the pointer (1, 1a) above the scale of the angle of attack is displayed in a flashing mode with a frequency of 2.5 Hz.

The group of indication of vertical speed and barometric height (10) moves vertically in connection with the symbol of the angle of inclination of the path (14) in the range of values (-30 °; + 30 °), outside this interval of values of the angle of inclination of the path, the position of the group of indicators (10) is fixed. In horizontal flight with cruising speed, the position of the group of symbols (10) coincides with the position of the right symbol of the “ray” (15a).

The reference scale (22) has divisions-strokes at 10 ° and divisions at 30 ° in the form of two points. The reference scale serves for the qualitative determination of the barometric height on the scale (7), the angle of heel (5), the angle of inclination of the trajectory (14) and the pitch angle according to the position of the pointer (13) relative to the horizontal - relative to the division of the reference scale, coinciding with the mark “3” barometric height scales (7).

The indicator of the current value of the set course with the pointer (34) is displayed if the pointer is outside the course scale (56 of figure 13).

It is assumed that the information-measuring system may include other or additional modern systems for measuring motion parameters and the state of the aircraft and navigation.

Proposed in the claimed invention, a method of integrated display of flight situation parameters, taking into account their interdependence and mutual influence, corresponds to the concept of safe flight.

The combination of indices and symbols used corresponds to the attention distribution technique and piloting techniques, which facilitates and retains the piloting skill for the pilot / UAV operator.

The method of integral display of flight situation parameters proposed in the claimed invention suggests possible additions and refinement of indications corresponding to the current flight mode and / or type of control of a particular aircraft. These modifications include:

- replacement or exclusion of appropriate flight parameters; for example, the exclusion of the indication of the angle of attack (symbols 12, 13, 38) and the replacement of the indication parameter on the scale (3) by the pitch angle;

- the choice of the type of symbols of the current operating modes of the engines with speed indicators (29, 30) and on the central symbol of the aircraft (21) in accordance with the ones implemented for a particular type of aircraft;

- display of visual instructions for the pilot in the TAKEOFF and LANDING modes, determined on the basis of current and preliminary assessments of TAKEOUT safety during take-off / take-off in the event of a failure of one of the engines or LAND safety during braking during run.

Safety assessments are generated in the BVS based on algorithms that use the well-known laws of physics and aerodynamics, current values of flight situation parameters and limitations contained in the operational documentation for a particular type of aircraft.

Similarly, it is possible to formulate safety performance estimates and add appropriate visual instructions when performing complex maneuvers.

The above options for a possible addition to the integral representation of the parameters of the state of the flight situation do not violate the concept of the claimed invention and can be made within the framework of the described embodiment without deviating from the essence and scope of the invention.

The method of integral display of the flight situation parameters of the claimed invention provides the aircraft pilot with simultaneous recognition of the aircraft's true position in the space stabilized relative to the Earth, and serves as the basis for the restoration of spatial orientation in difficult flight situations, for example, if emergency route change is required (fly over the danger zone, enter the coordinates of the navigation points, etc.) or during combat interaction with aircraft. This is the basis for recommending the use of system-forming display elements of the claimed invention in the frame in the flight control indicator (KPI), tactical situation indicator (TO), indication on the KAI, as well as the helmet-mounted target designation and indication system (NSCI).

The technical result consists in the continuity of the formation and provision of an integral amount of information about the flight situation, in ensuring a reduction in psychophysiological tension when controlling the parameters of the flight situation in various flight modes, in ensuring the simplicity of the actions of the pilot / UAV operator in a complicated situation and in long flights.

Claims (11)

A method for the integral display of flight situation parameters, for the implementation of which data from an information-measuring system consisting of a complex of systems for measuring the parameters of motion and state of aircraft on board the aircraft, ground and satellite navigation systems, on-board computer system, and means of the aircraft information display system are used , allowing you to display on the screen of a multifunctional digital indicator a set of flight situation parameters: - indicators of a given course and current course of the aircraft, - indicators of engine operating modes, - indicators of the current amount of fuel and the estimated time of its use at the current fuel consumption rate, - combined digital indicator of the current vertical speed and the current value of the barometric height, moving vertically of the frame with an indicator of the current angle of inclination of the trajectory, - digital radio altitude indicator, - scales and barometric altitude and radio height indicators, - a scale of vertical overload n _y with an indicator of the current value, recommended value and indicators of the boundaries of the interval of permissible values of n _y when approaching the current value of n _y , - digital indicators of instrument speed, true speed and Mach number, - a scale of the angle of attack with a pointer to the current value and pointers to the boundaries of the interval of acceptable values when approaching the current value of the angle of attack, - an indicator of the angle of heel, measured from the upper point of the reference scale with divisions of 10 ° and 30 °; characterized in that the indicators of such parameters of the flight situation as the angle of attack, vertical overload n _y , barometric altitude, radio height, and roll angle are duplicated by mnemonic symbols and scales, allowing you to instantly determine whether these parameters are in the acceptable ranges of values or their violation; adds an indication of the symbol of the current angle of inclination of the aircraft trajectory, the value of which is calculated by the values of the flight parameters measured on board the aircraft, and the transition formulas from the aircraft’s own coordinate system to the earth coordinate system; allows you to display a set of parameters of the flight situation, taking into account their interdependence and mutual influence, which is manifested in various aspects - in the location, connectedness, size of scales and pointers; provides an indication of the angle of the scale of the course corresponding to the values of the angle of heel, safe to maintain the maneuvering trajectory, excluding the downward movement of the aircraft; represents the symbol of the artificial horizon corresponding to 0 ° pitch, in the form of a symbol of the plane of the artificial horizon moving along the vertical of the frame in accordance with the current value of the pitch; represents the plane of the artificial horizon, in the future limited by "rays" formed by segments of straight lines with an angle of inclination of "rays", determined by the angle of inclination of the trajectory, with the direction of movement and the speed of movement of the segments of straight lines making up "rays" corresponding to the sign and magnitude of the longitudinal overload n _x , intuitively perceived as a perspective of the depth of space; uses flight simulation methods that take into account the anthropocentric principle, allowing the operator to use the advantages of a person over technical devices in their activities, namely the ability to use the clarity and integrity of perception in their activities; provides the aircraft pilot with instant recognition of the true position of the aircraft in the Earth’s space and serves as the basis for the restoration of spatial orientation in difficult flight situations; allows the use of system-forming elements of the indication of the claimed invention in the frame of the flight-pilot indicator, indicator of tactical situation, indication on the KAI, as well as the helmet-mounted target designation and indication system (NSCI).

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